# docs_fts_content

c1: EFTA00014014
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00014014.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
From:
To:
(USAFLS)"
Subject: Re: FW: Request for Written Staff Opinion ATTN Elizabeth Clark Tarbert
Date: Mon, 29 Sep 2008 17:32:47 +0000
Importance: Normal
Attachments: Florida_Bar_Ltr_re_Ethics_Opinion.pdf; Final_Victim_Notification__Sample.pdf:
Final_Victim_Notification_Represented_Sample.pdf
Inline-Images: graycol.gif
Dear Ms.
:
Thank you for re-sending the inquiry. Most inquiries receive a reply within 3-5 weeks.
Sincerely,
Elizabeth Clark Tarbert
Ethics Counsel
(USAFLS)"
on 09/29/2008 12:05:05 PM
To: "Ethics Opinions"
cc:
Subject: FW: Request for Written Staff Opinion ATTN Elizabeth Clark Tarbert
Staff:
Dear Ms. Tarbert - Here is my earlier e-mail.
Thank you.
Assistant U.S. Attorney
West Palm Beach, FL 33401
Phone
Fax
From:
(USAFLS)
Sent: Thursday, September 18, 2008 7:21 PM
To:
Cc:
(USAFLS);
(USAFLS)
Subject: Request for Written Staff Opinion
EFTA00014014

=== Page 2 ===
Dear Sir or Madam: Please see the attached correspondence. Thank you for your assistance.
<<Florida Bar Ltr re Ethics Opinion.pdf>>
<<Final Victim Notification -- Sample.pdf>>
<<Final Victim Notification Represented Sample.pdf>>
Assistant U.S. Attorney
West Palm Beach, FL 33401
Phone
Fax
(See attached file: Florida Bar Ltr re Ethics Opinion.pdf)(See attached file: Final Victim
Notification -- Sample.pdf)(See attached file: Final Victim Notification Represented Sample.pdf)
EFTA00014015


c1: EFTA00013521
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00013521.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
From:
To: "Jay Lefkowitz"
Bcc:
(USAFLS)"
Subject: RE: Epstein
Date: Wed, 31 Oct 2007 15:51:29 +0000
Importance: Normal
Jay,
Regarding your statement that "we are beginning to think about what discovery we may need to take to
verify any claims", I remind you that paragraph 8 of the agreement states that Epstein "waives his right to
contest liability and also waives his right to contest damages up to an amount as agreed to between the identified
individual and Epstein, so long as the identified individual elects to proceed exclusively under 18 USC S 2255
and agrees to waive any other claim for damages " That being said, you are correct in assuming that we do
not want to be copied on anything related to discovery. Monitoring the status of the negotiations/litigation by this
Office is limited to insuring that the terms and conditions of the Non-Prosecution Agreement are not breached.
From: Jay Lefkowitz [mailto:
Sent: Tuesday, October 30, 2007 4:54 PM
To:
Cc:
(USAFLS)
Subject: Re: Epstein
Thanks
I haven't heard anything from Judge Davis. I assume he is still willing to take on the role you asked him to take on, but can you please
let me know if that is not the case?
Also, we are beginning to think about what discovery we may need to take to verify any claims. I am assuming that your office does
not want to be copied on any subpoenas or anything related to discovery. But please let me know if that is an incorrect assumption.
Thanks Jay
Original Message
From:
Sent: 10/30/2007 02:42 PM AST
To: Jay Lefkowitz
Cc:
(USAFLS)"
Subject: Epstein
Jay,
Here is an executed version of the addendum. Please Fed Ex the original signature pages to me. Thanks,
EFTA00013521

=== Page 2 ===
<<epstein addendum 10 30.pdf>>
The information contained in this communication is
confidential, may be attorney-client privileged, may
constitute inside information, and is intended only for
the use of the addressee. It is the property of
Kirkland & Ellis LLP or Kirkland & Ellis International LLP.
Unauthorized use, disclosure or copying of this
communication or any part thereof is strictly prohibited
and may be unlawful. If you have received this
communication in error, please notify us immediately by
return e-mail or by e-mail to postmaster@kirkland.com, and
destroy this communication and all copies thereof,
including all attachments.
EFTA00013522


c1: EFTA00013286
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00013286.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
Subject: Re:
prosecution memo
Date: Wed, 06 Jan 2021 15:14:20 +0000
Embedded: Re:
prosecution_memo.msg
Message-Id: <2E83F9A6-4B7A-48B5-B678-49561CB46CE2@usa.doj.gov>
To:
Cc:
EFTA00013286


c1: EFTA00010342
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00010342.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
U.S. DEPARTMENT OF
U.S. Customs and Border Protection
U.S. Department of Homeland Security
HOMELAND ARCURITY
US Passport (P)
04/26/2019 12:40 EDT
Generated By:
Page 1 of 1
Passenger Information
Last Name
First Name
DOB
Gender
EPSTEIN
JEFFREY EDWARD
01/20/1953
M - Male
US Passport Information
Passport #
Passport Status
Document Type
I - - ISSUED
P - - PASSPORT
Issue Country
Issue Date
Expiration Date
USA UNITED STATES
05/31/2016
05/30/2020
Personal Information
Last Name
First Name
DOB
EPSTEIN
JEFFREY EDWARD
01/20/1953
Gender
Place of Birth
Nationality
M - Male
USA - UNITED STATES
For Official Use Only / Law Enforcement Sensitive
EFTA00010342


c1: EFTA00013191
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00013191.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
Event: Accepted: Meeting re MCC/Epstein
Start Date: 2019-08-13 15:45:00 +0000
End Date: 2019-08-13 16:15:00 +0000
Location: RC's office
Class: X-PERSONAL
Comment:
Date Created: 2019-08-13 12:16:43 +0000
Date Modified: 2019-08-13 12:16:43 +0000
Priority: 5
DTSTAMP: 2019-08-13 12:05:36 +0000
Attendee:
)
EFTA00013191


c1: EFTA00011163
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00011163.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
From:
To
Cc:
Subject: Defense MIL 4
Date: Tue, 19 Oct 2021 14:55:18 +0000
Attachments:4_Motion_to_Exclude_Accuser-3_Evidencepdf
Hey
Can we talk about defense MIL 4 sometime today or tomorrow? I think you briefed basically the same issue as a pretrial
motion, so it'd be great to talk through how to respond.
Thanks,
Assistant United States Attorney
Southern District of New York
New York, New York 10007
EFTA00011163


c1: EFTA00013479
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00013479.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
Event: Mw epstein defense team
Start Date: 2007-07-31 18:00:00 +0000
End Date: 2007-07-31 20:00:00 +0000
Organizer:
Class: X-PERSONAL
Date Created: 2015-04-04 00:21:49 +0000
Date Modified: 2015-07-22 20:34:55 +0000
Priority: 5
EFTA00013479


c1: EFTA00011669
c2: DataSet 8
c3: VOL00008
c4: DataSet 8/VOL00008/IMAGES/0001/EFTA00011669.pdf
c6: pdf
c7: images
c0:
=== Page 1 ===
OMB No. 2120-0020
Electronic Tracking Number
Exp: 5/31/2018
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 4701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
UNITED STATES / N188TS
RK-244
1. Aircraft
Make
Model
Series
RAYTHEON AIRCRAFT COMPANY
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Address
2. Owner
THORAIR LLC
City SANDUSKY
State OHIO
Zip
44871-2218
Country UNITED STATES
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
RAYTHEON AIRCRAFT COMPANY
AIRFRAME
(As described in Item 1 above)
RK-244
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Constant Aviation LLC
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City CLEVELAND
State OH
Certificated Repair Station
Zip
44143
Country USA
CRS#WC7R346J
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in Item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein Is true and d
Extended range fuel
per 14 CFR Part 43
App. B
10/04/2019
turn to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Approved
Rejected
FAA Flt. Standards
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individual
Designation No. CRS#
WC7R346J
10/04/2019
FAA Form 337 (10/06)
Page I
EFTA00011669

=== Page 2 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
UNITED /
10/04/2019
Nationality and Registration Mark
Date
Engine Inlet Rivet Repair
Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet
forebody assembly part number 541000-004, serial number R0010, in accordance with nextant
aerospace engineering order NT-EO-1118-31 rev IR dated 11/29/2018 with FAA form 8110-3
dated 11/30/2018.
Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the
aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft
maintenance manual or operators approved inspection program as appropriate.
Weight and Balance unaffected.
Reference Constant Aviation work order CCM-3160
END
Additional Sheets Are Attached
FAA Form 337 (10/06)
Page 2
EFTA00011670

=== Page 3 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
November 30, 2018
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Textron Aviation
N541000-004
Forebody Assy
Nextant Aerospace LLC
Cleveland, Ohio
LIST OF DATA
6, IDENTIFICATION
7. TITLE
NT-EO-1118-31
Engine Inlet Rivet Repair.
Rev. IR
November 29, 2018
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This
approval is only for the engineering data. It indicates the data listed above
demonstrates compliance only with the regulations specified by paragraph and
subparagraph listed below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire repair.
8. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody Assy P/N N541000-004,
S/N R0010 under Nextant Aerospace Work Order No. 10565.1.1.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-00],
25.619[25-23], and 25.625(a)(b)(c)(25-23].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
12347
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H18777-01
Page 1 of 1
EFTA00011671

=== Page 4 ===
EETA00011672

=== Page 5 ===
OMB No. 2120-0020
Electronic Tracking Number
Exp: 5/31/2018
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
UNITED STATES / N188TS
RK-244
1. Aircraft
Make
Model
Series
RAYTHEON AIRCRAFT COMPANY
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Address
2. Owner
THORAIR LLC
City SANDUSKY
State OHIO
Zip
44871-2218
Country UNITED STATES
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
RAYTHEON AIRCRAFT COMPANY
AIRFRAME
(As described in Item 1 above)
RK-244
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Constant Aviation LLC
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City CLEVELAND
State OH
Certificated Repair Station
Zip 44143
Country USA
Certificated Maintenance Organization
CRS#WC7R346J
D. I certify that the repair and/or alteration made to the unit(s) identified in Item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein Is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
App. B
10/04/2019
turn to Service
Pursuant to the authority given persons specified below, the amt identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Approved
Rejected
FAA Flt. Standards
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individual
Designation No. CRS#
WC7R346J
10/04/2019
FAA Form 337 (10/06)
Page I
EFTA00011673

=== Page 6 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
UNITED STATES/N188TS
10/04/2019
Nationality and Registration Mark
Date
Engine Inlet Rivet Repair
Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet
forebody assembly part number 541000-004, serial number R0010, in accordance with nextant
aerospace engineering order NT-EO-1118-31 rev IR dated 11/29/2018 with FAA form 8110-3
dated 11/30/2018.
Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the
aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft
maintenance manual or operators approved inspection program as appropriate.
Weight and Balance unaffected.
Reference Constant Aviation work order CCM-3160
END
Additional Sheets Are Attached
FAA Form 337 (10/06)
Page 2
EFTA00011674

=== Page 7 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
November 30, 2018
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Textron Aviation
N541000-004
Forebody Assy
Nextant Aerospace LLC
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
NT-EO-1118-31
Engine Inlet Rivet Repair.
Rev. IR
November 29, 2018
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This
approval is only for the engineering data. It indicates the data listed above
demonstrates compliance only with the regulations specified by paragraph and
subparagraph listed below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire repair.
8. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody Assy P/N N541000-004,
S/N R0010 under Nextant Aerospace Work Order No. 10565.1.1.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-00],
25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION - Under authority vested by direction of the Administrator and In accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H18777-01
Page 1 of 1
EFTA00011675

=== Page 8 ===

=== Page 9 ===
nextant aerospace
//REIMAGINED /REBUILT //REBORN
ENGINEERING ORDER
EO #: NT-EO-1118-31
Title: Engine Inlet Rivet Repair
ARTICLE DESCRIPTION
Effectivity (Aircraft Model)
Aircraft Serial Number(s)
Textron Aviation 400A
See Remarks
Description and/or Reason
The purpose of this EO is to allow for the installation of blind rivets (P/N: CR3212-5-XX) of appropriate length in place of the damaged solid rivet (P/N: MS20426AD5-XX) on the
engine inlet forebody assembly. The repair will be accomplished on the RH engine inlet forebody assembly (P/N: N541000-004, S/N: R0010).
REGULATORY
Any impect to the following Name will result in automatic classification of MAJOR FAA approval is required for of Items classified as MAJOR
AFM Change
RVSM
MEL
Inspection tasks/nterval
Previous Major Repair/Alterations
YES
X
NO
YES
X
NO
YES
X
NO
YES
X
NO
YES
X
NO
Does this EO significantly affect weight, balance, structural strength, aircraft performance, powerplant operation, flight characteristics, or other
MAJOR
MINOR
airworthiness qualities?
YES
X
NO
MINOR
MAJOR
Can this EO be accomplished by accepted practices or elementary operations?
YES
X
NO
MAJOR
MINOR
If improperly done, could this EO appreciably affect airworthiness?
X
YES
NO
Classification
Weight and/or Balance Change
FAA APPROVAL/ 8110-3
X
MAJOR
MINOR
X
STC (No. ST02371LA)
YES
X
NO
X
YES
NO
GENERAL
Drawing List/Attachments
Figure 1: Damaged Rivet Location on RH Engine Inlet Lip (Typical Shown)
Equipment List Update
Remarks/Refarences
YES
X
NO
Inlet:
P/N: N541000-004
S/N: R0010
WO: 10565.1.1 (Original WO, IR with approval). 13003 (IR.1 WO)
CherryMax Process Specification: CA-1015
REVISION
REVISION
DATE
DESCRIPTION
ECR #
REVISED BY
IR
11/29/2018
Initial Proposal
N/A
P. Avshalumov
IR.1
10/1/2019
Updated to remove specific number of rivets from description, change is minor and 8110-3 at IR stands
N/A
P. Avshalumov
ACTION
DATE
Prepared By
10/1/2019
Checked By
10/1/2019
ally signed by Pinkhas
Approved By
wsitjalumov
10/1/2019
2019.10.02 09:53:20-04:00
Page 1 of 3
Form No. NT-EO-01 / Rev A
This Document is Uncontrolled Once Printed
EFTA00011677

=== Page 10 ===

=== Page 11 ===
nextant aerospace
//REIMAGINED //REBUILT //REBORN
ENGINEERING ORDER
EO #: NT-EO-1118-31
Title: Engine Inlet Rivet Repair
PROCEDURES
ITEM
INSTRUCTIONS
Visually inspect the engine inlet lip and barrel for any other damaged, missing or loose fasteners.
1
If no additional discrepancies are detected, continue with repair as outlined below.
C.A.C. M/1
If additional descepancies are noted, contact Nextant Aerospace for disposition.
035
Visually inspect the engine rotor as defined in Sub Task 72-31-20-220-801 of the Williams International LINE MAINTENANCE
M/I
2
MANUAL FJ44-3AP 111000-202 (latest revision).
C.A.C.
If no additional discrepancies are detected, continue with repair as outlined below.
035
If additional discrepancies are noted, contact Nextant Aerospace for disposition.
3
Locate damaged rivets as shown in Figure 1 and carefully and completely drill out the remaining fastener material, making sure not to
damage, oblong, or oversize the fastener hole.
035
Prepare the holes of the missing fasteners for installation of CherryMax Rivets P/N CR3212-5-XX in lieu of nominal solid rivets
MS20426AD5-XX.
M/I
Prepare holes by drilling and reaming to the required rivet size, as required, per CherryMax document CA-1015
C.A.C.
4
Determine the correct grip length for the fasteners to be used, reference CherryMax document CA-1015
035
Using the manufacturer's recommended installation tool install the rivet fasteners per ChenyMax document CA-1015.
Inspect the completed rivet set to verify the locking collar has been inserted and the stem has fractured flush with the rivet head.
Refer to CherryMax document CA-1015 for inspection and verification.
END
LIMITATIONS
None
INSTRUCTIONS FOR CONTINUING AIRWORTHINESS (ICA's)
Follow the maintenance inspection practices in the aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft maintenance manual or operators
approved inspection program as appropriate.
COMPLIANCE
AIRCRAFT MODEL
AIRCRAFT REGISTRATION
AIRCRAFT SERIAL NUMBER
N188TS
RK244
sir Station # or individual's A&P number)
DATE
RS# WC7R346J
10/2/19
Page 2 of 3
Form No. NT-EO-01 / Rev A
This Document is Uncontrolled Once Printed
EFTA00011679

=== Page 12 ===

=== Page 13 ===
nextant aerospace
//REIMAGINED //REBUILT //REBORN
ENGINEERING ORDER
EO #: NT-EO-1118-31
Title: Engine Inlet Rivet Repair
Figure 1: Damaged Rivet Location on RH Engine Inlet Lip (Typical Shown)
Page 3 of 3
Form No. NT-EO-01 / Rev A
This Document is Uncontrolled Once Printed
EFTA00011681

=== Page 14 ===

=== Page 15 ===
OMB No. 2120-0020
Electronic Tracking Number
Exp: 5/31/2018
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
UNITED STATES/N188TS
RK-244
1. Aircraft
Make
Model
Series
RAYTHEON AIRCRAFT COMPANY
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Address
2. Owner
THORAIR LLC
City
SANDUSKY
State OH
Zip 44871
Country UNITED STATES
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
RAYTHEON AIRCRAFT COMPANY
AIRFRAME
(As described in Item 1 above)
RK-244
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name CONSTANT AVIATION
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
CLEVELAND
State OH
Certificated Repair Station
Zip 44143
Country UNITED STATES
Certificated Maintenance Organization
CRS# WC7R346J
D. I certify that the repair and/or alteration made to the unit(s) Identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signa
per 14 CFR Part 43
App. B
10/7/2019
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Approved
Rejected
FAA Flt. Standards
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS#
WC7R346J
Signature/Date Dr of Authorized Individual
10/7/2019
FAA Form 337 (10/06)
Page 1
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=== Page 16 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
UNITED STATES/N188TS
10/7/2019
Nationality and Registration Mark
Date
INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT
Complied with installation of BHE & Associates, LTD. STC# ST11216DS Installation of Automatic
Dependent Surveillance-Broadcast Out on Part 25 Aircraft IAW BHE & Associates, LTD. Master
Data List (MDL) number 584-00-0001 Rev.G. Dated 8/29/2019.
Reference BHE & Associates, LTD. Aircraft Flight Manual Supplement (AFMS) Installation of
ADS-B Out on Part 25 Aircraft. Report number 584-00-0046 Rev.C. Dated 5/4/2019.
Reference BHE & Associates, LTD. Electrical Load Analysis (ELA) Installation of ADS-B Out on
Part 25 Aircraft. Report number 584-00-0050 Rev.B. Dated 10/9/2018.
Reference BHE & Associates, LTD. Instructions for Continued Airworthiness (ICA) Installation of
ADS-B Out on Part 25 Aircraft. Report number 584-00-0047 Rev.D. Dated 3/19/2019.
Weight and Balance: Reference calculated weight and balance dated 10/7/2019.
Equipment List: Updated.
Reference Work Order: CCM-R3160.
END
Additional Sheets Are Attached
FAA Form 337 (10/06)
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=== Page 17 ===
United States of America
DEPARTMENT COMINISTRA
Department of Transportation
Federal Aviation Administration
Supplemental Type Certificate
Number: ST11216DS
This certificate issued to: BHE & Associates, Ltd.
San Antonio, TX 78216
certifies that the change in the type design for the following product with the limitations and conditions therefore as
specified hereon meets the airworthiness requirements of Part 25 of theFederal Aviation Regulations.
Original Product - Type Certificate Number:
Make: See attached AML
Model: See attached AML
See attached approved model list
(AML)
Description of Type Design Change:
Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft, in accordance with Master
Data List 584-00-0001, Revision IR, dated June 29, 2018 or later FAA approved revision. For Instructions for
Continued Airworthiness and Airplane Flight Manual Supplement reference the attached AML
Limitations and Conditions:
1. The installer must determine whether this design change is compatible with previously approved
modifications
2. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give
the other person written evidence of that permission.
3. See attached AML for additional limitations and conditions.
This certificate and the supporting data which is the basis for approval shall remain in effect until surrendered,
suspended, and revoked or a termination date is otherwise established by the Administrator of the Federal Aviation
Administration.
Date of Application: February 9. 2018
Date Reissued:
Date of Issuance: June 29. 2018
Date Amended:
By Direction ministrator
Signature
Title VT DRB Aviation Project ODA Administrator
ODA-831473-SW
Any alteration of this certificate is punishable by a fine of not exceeding $1,000. or imprisonment not exceeding 3 years, or both. This certificate may be
transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Type
Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to after an aircraft, aircraft engine, or
propeller. The STC's supporting documentation (drawings, instructions, specifications, flight manual supplements. etc.) is the property of the STC
holder. An STC holder who allows a person to use the STC to after an aircraft, aircraft engine, or propeller must provide that person with written
permission acceptable to the FAA. (Ref. 14 CFR 21.120).
FAA Form 8110-2 (5/14)
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FEDERAL
INVIATION
United States of America
Department of Transportation
ADMINISTRATION
Federal Aviation Administration
Supplemental Type Certificate
INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Aircraft Certification Office of the transfer of this
Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him.
Transfer Endorsement
Transfer the ownership of Supplemental Type Certificate Number: ST11216DS
To (Name and address of transferee)
From (Name and address of grantor)
Extent of Authority (if licensing agreement):
Date of transfer:
Signature of grantor:
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. This certificate may be
transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Type
Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or
propeller. The STC's supporting documentation (drawings, instructions, specifications, flight manual supplements, etc.) is the property of the STC
holder. An STC holder who allows a person to use the STC to alter an aircraft, aircraft engine, or propeller must provide that person with written
permission acceptable to the FAA. (Ref. 14 CFR 21.120).
FAA Form 8110-2 (5/14)
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DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
FOR THE
INSTALLATION OF ADS-B OUT
ON
PART 25 AIRCRAFT
REPORT No. 584-00-0047
Revision D
Date: 03/19/2019
NOTICE:
The contents of this document are proprietary to BHE & Associates, Ltd. and shall not be disclosed,
disseminated, copied, or used except for purposes expressly authorized in writing by BHE &
Associates, Ltd.
BHE & Associates, Ltd.
San Antonio, TX 78216 USA
CAGE: N/A
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DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
NOTICES AND SIGNATURES
Notices:
Note:
Paragraphs and/or figure numbers followed by | indicate a change by latest revision.
Approval Signatures:
NAME
SIGNATURE
Prepared by:
See rev IR
Checked by:
See rev IR
Approved by:
See rev IR
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Record of Revisions
Revision
Revision Number
Description of change
Approved
Date
By
IR
Initial Release
5/9/18
Page 8, Section 1.1 revised transponder and
A
GPS part numbers.
6/27/18
Page 10, Section 2 remove "Flight Hours" from
Table 4
Page 4, Revised list of aircraft models in
Introduction
B
Pages 9, 24-25, 28-29, Revised aircraft models
11/6/18
in Tables 3, 7, and 9.
Pages 8 and 28, clarified wording for installation.
Revised Table 3 on page 9
Revised Table 4 on page 10
Revised Table 5 on page 26
C
Revised Table 6 on pages 27 & 28
1/18/19
Revised section 6.1.9 on page 31
Revised figures on pages 13 & 20, Added figures
on pages 14, 17 & 18
Added STC number on page 4.
D
Added figure on page 24.
3/19/19
Revised form in Appendix C.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INTRODUCTION
These Instructions for Continued Airworthiness (ICA) document have been developed using the
guidelines in Appendix "H" of 14 CFR Part 25 as required by §FAR 21.50 and $25.1529.
This document is designed to provide avionics and aircraft technicians with sufficient information to
inspect, troubleshoot, adjust, repair, test, remove, and install ADS-B on the following Part 25 Aircraft.
Bombardier Inc. - CL-600-1A11, CL-600-2A12, CL-600-2B16 (Challengers)
Gulfstream Aerospace -1125 Westwind Astra, Astra SPX, Gulfstream 100, G150
Gulfstream - G-1159, G-1159A, G-1159B, G-IV, GV
Gulfstream - 200
Sabreliner - NA-265-65, NA-265-70, NA-265-80
Textron Aviation Inc. - 500. 550, S550, 560 (Citation)
Textron Aviation - 400, 400A (Beechjet)
Textron Aviation - 650
Textron Aviation - HS.125 Series 700A, HS.125 Series 700B, BAe. 125 Series 800A, BAe. Series
800B, Hawker 800XP, Hawker 750, Hawker 850XP, Hawker 900XP
Learjet - 60 (STC Aircraft)
Dassault Aviation - Falcon 10, Mystere-Falcon 50, Mystere-Falcon 20-C5/D5/E5/F5, Mystere-Falcon 200,
Mystere-Falcon 900
Table 1: Equipment
Type
Description
New CPN
Qty
DO-260B ADS-B Out
TDR-94
Transponder
622-9352-502
0, 1 or 2*
TDR-94D
Transponder
622-9210-502
0, 1 or 2*
GPS1203C
GPS Receiver
84327-50-XXXX
0 or 1
CI 429-200
GPS Antenna
CI 429-200
0 or 1
GPS-4000S
GPS Receiver
822-2189-
0, 1 or 2
004/005/006/007/010/011/100
*Either TDR-94 or TDR-94D will be installed.
The above equipment is installed in accordance with FAA Supplemental Type Certificate No.
ST11216DS See the List of Applicable Publications (LOAP) in Appendix A of this document.
The publications listed in the LOAP constitute the required information essential for continued
airworthiness for the aircraft.
The documents contained in the LOAP are a necessary part of this ICA and the latest revision
should be available to maintenance personnel when performing maintenance. The STC holder
will continue to monitor changes to the ICA that were the basis of the supplementary ICA and
provide revised supplemental ICA as necessary. The information in this document supplements
or supersedes the original manufacturer's maintenance manual only in those areas listed. For
limitations, procedures and other information not contained in this document, refer to the aircraft
manufacturer's maintenance manuals, illustrated parts manuals and wiring diagrams or the
vendor manuals as listed in the LOAP.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
RECORD OF REVISIONS
For continuous use of this document, this document must be maintained in current revision
status. Each time the STC holder finds it necessary to revise this document; a revision will be
distributed to all users of the STC. Revisions will be supplied to the customer by:
a)
E-mail with an attached PDF file, or
b) Compact Disc (CD) via mail
Changes to this document will be incorporated by an updated revision to the complete
document.
All pages will indicate the "new" revision level. Upon receipt of the new revision, the previous
revision should be discarded and replaced with the updated, current, revision. Changes to this
document will be listed in the revision block on page 3.
It is the responsibility of the person(s) performing maintenance on the installed system to ensure
that this document is current prior to performing this maintenance. The current revision number
may be verified by contacting the STC holder, BHE & Associates.
Report any discrepancies to the installation of this STC using the form in Appendix C of this
document. Once filled out the form must be sent to both the ODA and the STC holder. Their
addresses are as follows:
ODA
VT-DRB Aviation Consultants
San Antonio, Texas 78216
STC Holder
BHE & Associates Ltd.
San Antonio, Texas 78216
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
TABLE OF CONTENTS
INTRODUCTION
4
RECORD OF REVISIONS
5
1
SYSTEM DESCRIPTION
8
1.1
GENERAL
8
2 AIRWORTHINESS LIMITATIONS
10
2.1
Inspection Intervals
10
2.2
Inspection Program
22
2.3
Inspection Method
22
2.4
Eddy Current Inspection
28
3
MAINTENANCE PRACTICES
29
3.1
Removal/Installation
29
3.2
Access Location
29
4 POWER DISTRIBUTION
30
4.1
Circuit Breakers by Bus
30
5
SYSTEM TROUBLESHOOTING
31
6
INSPECTION REQUIREMENTS
31
6.1
Scheduled Inspections and Maintenance Checks
31
6.2
Wiring
34
Appendix A - List of Applicable Publications
A1
Appendix B - Special Tools and Equipment
B1
Appendix C - Discrepancy Reporting Form
C1
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
LIST OF FIGURES AND TABLES
Table 1: Equipment
4
Table 2 Equipment List
8
Table 3 Equipment by Aircraft
9
Table 4 Inspection Intervals
10
Table 5 Manual List
28
Table 6 Access Panel Location
29
Table 7 Equipment Installation Locations by Aircraft
29
Table 8 New and Upgraded Equipment
30
Table 9 Maintenance Manual by Aircraft
33
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1 SYSTEM DESCRIPTION
1.1 GENERAL
This STC will include installations and/or updates to equipment to allow for Automatic dependent
surveillance -broadcast Out (ADS-B Out). ADS-B periodically broadcasts information about each
aircraft, such as identification, current position, altitude, and velocity, through an onboard transmitter.
The equipment list in Table 2 below details the equipment required for this installation.
The TDR-94/94D Transponder(s) will be upgraded to part number 622-9352-502 (94) or 622-
9210-502 (94D), if not previously installed. The TDR-94/94D Transponder is an all solid-state,
crystal-controlled receiver/transmitter.
The transponder(s) will get the GPS information from either a newly installed Freeflight GPS1203C
GPS receiver and dedicated GPS antenna; or, a GPS-4000S GPS receiver. Depending on the
aircraft configuration, the GPS-4000/A/S may be previously installed. If the previously installed GPS-
4000/A/S is not a part number 822-2189-004/005/006/007/010/011/100 it will have to be upgraded
to one of these part numbers. (Reference Tables shown on drawing 584-00-0004 for applicable GPS
installation based on aircraft model)
Wiring is added dependent on the installed or replaced GPS receiver(s), Transponder(s), and
annunciator installed. (Reference Tables shown on drawing 584-00-0004 for applicable installations
based on aircraft model and subsequent Wire Routing drawing 584-00-0005).S section 6.1.9 for
details on inspection.
An optional ADS-B Out annunciator can be installed to alert the pilot that the ADS-B function of the
active transponder is not properly functioning. The ADS-B Out annunciator is required for all
standalone GPS installations. Standalone means the GPS only provides data to the transponders.
All 1203C installations and 4000S installations that only connect to the transponders are standalone.
It can be installed as an option for installations where the 4000S is used for both ADS-B and FMS
navigation. ((Reference Tables shown on drawing 584-00-0004 for applicable ADS-B Out
Annunciator installation based on aircraft model)
Table 2 Equipment List
Type
Description
New CPN
Qty
DO-260B ADS-B Out
TDR-94
Transponder
622-9352-502
0, 1 or 2*
TDR-94D
Transponder
622-9210-502
0, 1 or 2*
GPS1203C
GPS Receiver
84327-50-XXXX
0 or 1
CI 429-200
GPS Antenna
CI 429-200
0 or 1
GPS-4000S
GPS Receiver
822-2189-
0, 1 or 2
004/005/006/007/010/011/100
*Either TDR-94 or TDR-94D will be installed.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Table 3 below lists the equipment being installed by aircraft. The aircraft will leave with updated TDR-
94s or 94Ds depending on the what transponder was already existing.
Table 3 Equipment by Aircraft
Transponder
GPS
Aircraft
Antenna Installed
Installed/Retained/Replaced
Installed/Replaced
GPS-1203C or GPS-
Learjet 60
TDR-94s or 94Ds
CI 429-200
4000S
Gulfstream Aerospace
1125 Westwind Astra,
Astra SPX,
TDR-94s or 94Ds
GPS-4000S
N/A
Gulfstream 100,
G150
Gulfstream G-1159,
GPS-1203C or GPS-
TDR-94s or 94Ds
CI 429-200
G-1159B, G-IV, GV
4000S
Gulfstream G-1159A
TDR-94s or 94Ds
GPS-4000S
N/A
Gulfstream 200
TDR-94s or 94Ds
GPS-4000S
N/A
GPS-1203C or GPS-
Textron Aviation 500
TDR-94s or 94Ds
CI 429-200
4000S
Textron Aviation 550,
GPS-1203C or GPS-
TDR-94s or 94Ds
CI 429-200
S550, 560
4000S
GPS-1203C or GPS-
Textron Aviation 400
TDR-94s or 94Ds
CI 429-200
4000S
Textron Aviation
TDR-94s or 94Ds
GPS-4000S
N/A
400A
GPS-1203C or GPS-
Textron Aviation 650
TDR-94s or 94Ds
CI 429-200
4000S
Bombardier CL-600-
1A11
GPS-1203C or GPS-
TDR-94s or 94Ds
CI 429-200
CL-600-2A12, CL-
4000S
600-2B16
Sabreliner NA-265-
65,
TDR-94s or 94Ds
GPS-4000S
N/A
NA-265-70, NA-265-
80
Textron Aviation
HS.125 700A,
GPS-1203C or GPS-
TDR-94s or 94Ds
CI 429-200
BAe.125 800A/800B,
4000S
Hawker 800XP
Textron Aviation
HS.125 700B,
TDR-94s or 94Ds
GPS-4000S
Hawker
N/A
750/850XP/900XP
Dassault Aviation
Falcon 10, Mystere-
Falcon 50, Mystere-
Falcon 20-
TDR-94s or 94Ds
GPS-4000S
N/A
C5/D5/E5/F5,
Mystere-Falcon 200,
Mystere-Falcon 900
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2
AIRWORTHINESS LIMITATIONS
The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 CFR
$$43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.
2.1 Inspection Intervals
The following items require high Frequency Eddie Current inspections including 2.0 inch detailed visual inspection
around periphery of the installation. Inspections as listed in the table below.
Table 4 Inspection Intervals
Inspection requirements are for AML fuselage modification
Inspection Intervals (Flight
Cycles)
Detectable Crack
Threshold
Recurring
Length (in.)
Fwd bulkhead penetrations
4,000
4,000
0.200
GPS Antenna Installation
6,700
6,350
0.200
GPS Antenna Installation (See Note 1)
5,650
5,400
0.200
Note1: These intervals are applicable to the Textron Aviation Cessna 650 and all the Gulfstream Models
The following images specify antenna installation and bulkhead feedthrough installation locations.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
BOMBARDIER INC. CL-600-1A11 (CL-600),
-2A12 (CL-601), -2B16 (CL-601-3A VARIANT,
CL-601-3R VARIANT, CL-604 VARIANT)
ACCEPTABLE LOCATION
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
310.00
333.00
364.00
394.00
424.00
449.85
473.15
499.00
529.00
559.00
FS
FS
280.00
265.00
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
295.00
321.50
349.00
379.00
409.00
39.00
461.50
484.00
513.00
544.00
FS 250.00
FS 235.00
220.00
FS
H
210.00
FS
202.7
FS
193.00
FS
169.00
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
TEXTRON AVIATION 400
ACCEPTABLE LOCATION
FS
FS
172.24
196.46
FS
FS
FS
RS
FS
FS
FS
FS
124.61 141.14 159.25
184.30
203.35 221.46 240.75 260.04
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
116.34
132.87
150.20
166.14
190.35
212.40
231.42
250.39
269.69
71.65
FWD
PRESS
BLKHD
FS
20.28
FS
0.0
FS
FS
80.91
99.02
FS
FS
89.96 108.07
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
TEXTRON AVIATION INC.
550, S550, 560
ACCEPTABLE LOCATION
ACCEPTABLE LOCATION
FS
FS
FS
FS 225.23
151.00
179.02
205.23 (560)
FS
FS
AS
FS
FS
FS 134.00
165.00
193.00
223.40
94.00
117.00
FWD
PRESS
FS
BLKHD
59.00
000
#
FS
216.10
(560 ONLY)
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
TEXTRON AVIATION INC. 650
ACCEPTABLE LOCATION
FS
FS
FS
FS
FS
172.00
202.00
234.00
261.00
288.76
FS
FS
FS
FS
FS
FS
157.00
187.00
217.00
245.00
272.00
94.00
FWD
PRESS
FS
BLKHD
58.00
-
O
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
TEXTRON AVIATION
HS.125 SERIES 700A, BAe. 125 SERIES 800A & 800B,
HAWKER 800XP
ACCEPTABLE LOCATION
180.3 204.5 224.4
FB
F9A
F10
171
190.5
214.7
241.6
262.3
283.1
303.8
329.8
352.2
F7
F9
FOB
F10A
F11
F12
F13
F14
F15
000000
87.0
F1 F3 F4 F5 F6 F7
109.0
FWD
PRESS
BULKHEAD
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
LEARJET 60
ACCEPTABLE LOCATION
110.99
338.61
F7
124.39
151.19
176.59
201.79
222.18
F23
246.59
274.59
302.59
323.59
355.16
F8
F10
F12
F14A
F16
F18
F20B
137.79
F20
F21A
.
F25
164.59
184.99
210.19
234.19
260.59
288.59
316.59
346.63
99.57
F9
F11
F13
F15
F17
F19
F20A
F21
F22
F24
F6
197.59
F14
89.23
75.23
F5
61.23 F4
47.23
F3
33.23
F2
F1
0000
=
II
170.59
F11A
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
GULFSTREAM G- 1159,
G-1159B, G-IV
ACCEPTABLE LOCATION
FS
s
FS
145.0
69.0
193.0
FS
FS
FS
133.0
157.0
181.0
FS
63.0
FWD
PRESS
BLKHD
WL
100
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
GULFSTREAM GV
ACCEPTABLE LOCATION
FS
FS
FS
FS
157.0
181.0
205.0
229.0
FS
FS
FS
FS
FS
145.0
169.0
193.0
217.0
241.0
FS
63.0
FWD
PRESS
BLKHD
WL
100
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
AIRCRAFT
£
ALTERNATE LOCATION
[0]0]
(WL 0.0)
HoD
oto
010
God
000
LOOKING AFT AT FWD SIDE OF
FORWARD PRESSURE BULKHEAD
(TEXTRON AVIATION 400)
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
+
+
COD
LOOKING AFT AT FWD SIDE OF
FORWARD PRESSURE BULKHEAD
(TEXTRON AVIATION INC. 500, 550, S550, 560)
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
(ALTERNATE LOCATION)
(ALTERNATE LOCATION)
(ALTERNATE LOCATION)
LOOKING AFT AT FWD SIDE OF
FORWARD PRESSURE BULKHEAD
(LEARJET 60)
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2.2 Inspection Program
Perform additional fuselage modification inspections.
2.3 Inspection Method
Inspect fuselage skin in the modification area, doubler fastener holes area, using high frequency eddy current
inspection techniques, according to the intervals outlined in table 4. The detectable crack length for eddy current
inspection techniques is 0.200". For the fastener holes, the inspector should look for cracks on the surface of the
skin and doubler around the fastener holes.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSPECTION AREA & METHOD
FWD BULKHEAD PENETRATIONS
19
Typical Installation shown. Inspections are
applicable to all penetration installations
HFEC Inspection Area of the fuselage skin. HFEC
inspection includes 2.0 inch detailed visual inspection
around periphery of the installation
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSPECTION AREA & METHOD
FWD BULKHEAD PENETRATIONS
Typical penetration doubler Installation shown
Inspections are applicable to all penetration
installations containing a doubler.
HFEC Inspection Area of the fuselage bulkhead web
HFEC inspection includes 20 inch detailed visual
inspection around periphery of the installation
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSPECTION AREA & METHOD
GPS Antenna
+
+
+
+
+
+
+
+
+
+
+
Typical Installation shown. Inspections are
applicable to all antenna installations
HFEC Inspection Area of the fuselage skin HFEC
inspection includes 2.0 inch detailed visual inspection
around periphery of the installation
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSPECTION AREA & METHOD
GPS ANTENNA
+
+
+
Typical Installation shown. Inspections are
applicable to all antenna installations
HFEC Inspection Area of the fuselage skin. HFEC
inspection includes 2.0 mch detailed visual inspection
around periphery of the installation
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSPECTION AREA & METHOD
GPS ANTENNA
+
Typical Installation shown. Inspections are
applicable to all antenna installations
HFEC Inspection Area of the fuselage skin. HFEC
inspection includes 2.0 inch detailed visual inspection
around periphery of the installation
REPORT No. 584-00-0047, Rev: D
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2.4 Eddy Current Inspection
For eddy current inspection requirements and procedures, refer to the referenced documents in the
table below for the different aircraft types.
The following documents describe the various procedures and requirements for HF eddy current
inspection including personnel, instrumentation, equipment setup and standardization, probes, special
tools and equipment eddy current standards, and eddy current test procedures required by the Cessna
Aircraft Company.
The defects identified by this method are incipient fatigue or corrosion stress cracks in bores,
machining radii, shoulders and countersunk holes, and in the actual skin. The direction of propagation
defects are perpendicular to in-flight stresses in the case of fatigue stress cracks, or perpendicular to
internal stresses for stress corrosion cracks. This method also detects minor corrosion-induced surface
damage.
Table 5 Manual List
Document
Aircraft
Manual
Number
Learjet 60
Non-Destructive Inspection
NDI-2
Manual
(Chapter 3)
Textron (Citation)
Series 500 Non-Destructive
5056ND
500, 550, S550, 560
Testing Manual
(Part 6, Chapter 20)
Textron (Citation)
Model 650 Non-Destructive
65ND
650
Testing Manual
(Part 6, Chapter 20)
Textron (Beechjet)
Model 400/400A/400XP
128-590001-9C29
400, 400A
Maintenance Manual
(Chapter 20-80-03)
Textron (Beechcraft)
125 Series 1-800, Hawker
N/A
HS.125 700A, Bae. 125 800A,
750, 800, 800XP, 850XP, and
Bae. 125 800B,
900XP Non-Destructive
(General Techniques
Hawker 800XP
Testing Manual
- Part B)
N/A
Challengers
Structural Repair Manual
(Chapter 51)
Gulfstream G-1159, G-1159B, G-
N/A
IV, GV
Structural Repair Manual
(Chapter 51)
FAA APPROVED:
Project ODA Administrator
VT DRB Aviation Consultants
A Division of VT San Antonio Aerospace, Inc.
San Antonio, TX 78216
3/21/2019
Date
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
3 MAINTENANCE PRACTICES
3.1 Removal/Installation
The following installation manuals contain complete, detailed instruction for the installation and removal
of equipment. Installation locations for the equipment vary by aircraft, reference tables 6, 7 and 9 for
more details on equipment locations and respective maintenance manuals.
Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor,
document 86764, Installation Section
Collins GPS-4000( Global Positioning System Installation Manual, document 523-0780545,
Installation Section.
TDR-94/94D ATC/Mode-S Transponder System (-5XX), document 523-0821492, Installation
Section
3.2 Access Location
Refer to the Aircraft Maintenance Manuals listed in table 9 for additional details.
Table 6 Access Panel Location
Location of Access
Access Panels
Forward Nose Access Panels
Nose Avionics Bay
(Right & Left)
Cabin EE Racks
N/A
Instrument Panel & Pedestal
N/A
Tail Avionics Bay
Tail Access Panel
Table 7 Equipment Installation Locations by Aircraft
Aircraft
Transponder Location
GPS Location
Learjet 60
Nose
Nose (GPS-4000S)
Cabin (1203C)
Gulfstream Aerospace 1125
Westwind Astra, Astra SPX,
Nose
Nose
Gulfstream 100, G150
Gulfstream 200
Nose
Nose
Gulfstream G-1159, G-
RH EE Rack, Cabin
1159A, G-1159B, G-IV
RH EE Rack, Cabin
Gulfstream GV
LH & RH EE Rack, Cabin
LH & RH EE Rack, Cabin
Textron Aviation 500, 550,
Nose
Nose
S550, 560
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Aircraft
Transponder Location
GPS Location
Textron Aviation 400/400A
Nose
Nose
Textron Aviation 650
Aft Cabin
Nose (GPS-4000S)
Cabin (1203C)
Bombardier CL-600-1A11
Under Floor, Cabin
Under Floor, Cabin
CL-600-2A12, CL-600-2B16
Sabreliner NA-265-65,
Nose
Nose
NA-265-70, NA-265-80
Alternate: FWD EE Shelf
Alternate: FWD EE Shelf
Textron Aviation HS. 125
700A/700B, BAe. 125
Nose
Under Floor, Cabin
800A/800B,
Alternate: AFT EE Shelf
Alternate: AFT EE Shelf
Hawker
750/800XP/850XP/900XP
Dassault Aviation Falcon 10,
Mystere-Falcon 20-
C5/D5/E5/F5, Mystere-
Nose
Nose
Falcon 200, Mystere-Falcon
900
Dassault Aviation Mystere-
Nose
Nose
Falcon 50
Alternate: Aft Avionics Shelf
4 POWER DISTRIBUTION
4.1 Circuit Breakers by Bus
There are multiple options for the installation, the table below shows the possible equipment part
numbers that may have changed with this update and the associated electrical load. The following
equipment part numbers may have changed with this update.
Table 8 New and Upgraded Equipment
Max Load in
Equipment/System
Model/Part Number
Amps
TDR-94
622-9352-502
1.79
TDR-94D
622-9210-502
1.79
GPS RECEIVER GPS1203C
84327-50-XXXX
0.179
822-2189-
GPS RECEIVER GPS-4000S
0.56
004/005/006/007/010/011/100
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
5
SYSTEM TROUBLESHOOTING
For troubleshooting information, refer to the following;
Equipment
Circuit Breaker
Document
GPS1203c
ADS-B GPS
Equipment Installation Manual for the FreeFlight System
Model 1203C GPS/SBAS Sensor
Collins GPS-4000S Global Positioning System Installation
GPS-4000S
ADS-B GPS
Manual, document 523-0780545, Maintenance Section
TDR-94/94D ATC/Mode-S Transponder System (-5XX),
TDR-94D
TDR
Document Number 523-0821492, Maintenance Section
6 INSPECTION REQUIREMENTS
6.1 Scheduled Inspections and Maintenance Checks
This section of the document contains information regarding Time Limits - Inspection and Maintenance
Checks, Overhaul and Replacement Items and Inspection Requirements.
6.1.1 Time Limits - Inspection and Maintenance Checks
Note:
Recommended inspection/maintenance intervals do not guarantee that the item will function
properly between inspection/maintenance checks. The inspection intervals are based on
average usage and environmental conditions. Aircraft operated under extreme conditions,
(extreme hot, extreme cold, high humidity, salty air, etc.) may require more frequent
maintenance than the intervals specified in this document. The aircraft operator may perform
more frequent inspection/maintenance checks based on his usage.
6.1.2 Visual Inspections
The equipment necessary for conducting a visual inspection usually consists of a strong flashlight, a
mirror with a ball joint, and a 2.5x - 4x magnifying glasses. A 10x magnifying glass is recommended
for positive identification of suspected cracks.
6.1.3 Corrosion Treatment
Before attempting a close, visual inspection of any selected part or structural area, it should be checked
for signs of corrosion. Any corrosion found should be tested to discover its extent and severity. Heavy
or severe corrosion requires immediate corrective action. If mild corrosion is present, it should be
carefully, but completely, removed before continuing with preparations for the visual inspection.
6.1.4 Structural Failure Determination.
The first step in a visual inspection should be an examination of the area for deformed or missing
fasteners. These should be identified for subsequent replacement. A close examination for cracks in
the surfaces of structural members should then be made with the aid of a flashlight. The majorities of
cracks start at, and progress from, points of concentrated stress such as sharp corner cutouts and
fastener holes. Cracks may also occur in sheet metal bend radii and similar places that were subjected
to severe forming operations during manufacture.
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6.1.5 Cleaning of Structural Parts
All parts of areas from which mild corrosion has been removed should be thoroughly cleaned using an
approved solvent. (Metal conditioner should not be applied at this time as it may interfere with
subsequent dye penetrant inspection.)
6.1.6 Cleaning Other Areas
All other areas to be inspected should also be cleaned of any deposits that might hinder the discovery
of existing surface flaws. The protective finish need not be removed. The cleaning should be
performed using any approved solvent. For cleaning high heat-treat steel parts, or areas in which a
high heat steel part is installed, use only the approved solvents.
6.1.7 Crack Detection Technique
When looking for surface cracks, the inspector should point his flashlight towards himself and hold it at
an angle of 5° - 45° to the surface. (See Figure 6) The extent of the crack may be traced by directing
the beam at right angles to the crack. Never direct the light beam at such an angle that the reflected
beam shines directly into the eyes. The proper procedure is to keep the eyes above the reflected
beam.
INCIDENT
EYE ABOVE
FLASHLIGHT
LIGHT BEAM
REFLECTED
LIGHT BEAM
LINE OF SIGHT
REFLECTED
LIGHT BEAM
5° TO 45°
CRACK OPEN
TO SURFACE
FAYING
SURFACES
Figure 6 - Inspection for Cracks
6.1.8 Verification of cracks
A 10x magnifying glass may be used to confirm the existence or extent of a suspected crack.
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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
6.1.9 Visual Wiring Inspection
Perform visual inspections of the wiring. These visual inspections should be performed as part of the
existing applicable inspection cycles, not to exceed 1200 hours. (Reference Tables shown on drawing
584-00-0004 for applicable installations based on aircraft model and subsequent Wire Routing drawing
584-00-0005)
Refer to the pertinent Maintenance Document listed below:
Table 9 Maintenance Manual by Aircraft
Aircraft
TCDS Model
Maintenance Manual
Learjet 60
60
P/N MM-103
Bombardier Inc CL-600-
CL-600-1A11
PSP 601-2
1A11
Bombardier Inc CL-
CL-600-2B12, CL-600-
CL 604 AMM
6002A12, CL-6002B16
2B16
Dassault Aviation Falcon
Dassault Falcon 10
Falcon 10
10
Maintenance Manual
Dassault Aviation
Mystere-Falcon 20-
Mystere Falcon 20-
Dassault Fan Jet Falcon
C5/D5/E5/F5, Mystere
C5/D5/E5/F5
Maintenance Manual
Falcon 200
Dassault Aviation
Dassault Falcon 50/50EX
Mystere-Falcon 50
Mystere Falcon 50
Maintenance Manual
Dassault Aviation
Dassault Falcon 900
Mystere-Falcon 900
Mystere Falcon 900
Maintenance Manual
Galaxy/Gulfstream
G100/Astra SPX
P/N G100-1001-11-1
G100/SPX
Galaxy/Gulfstream 1125
1125 Astra
P/N 25W-1001-11-1
Astra
Galaxy/Gulfstream 200,
Gulfstream G150
Gulfstream 200, G150
Gulfstream G-1159, G-
Gulfstream II
1159B
G-1159, G-1159B
Maintenance Manual
Gulfstream III
Gulfstream G-1159A
G-1159A
Maintenance Manual
Gulfstream G-IV
Gulfstream IV Aircraft
G-IV
Maintenance Manual
Gulfstream V Aircraft
Gulfstream GV
GV
Maintenance Manual
Textron (Citation)
Model 500 Maintenance
500/550/S550
500/550/S550
Manual
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Textron (Citation)
Model 560 Maintenance
560
560
Manual
Textron (Citation)
Model 650 Maintenance
650
650
Manual
Textron (Beechjet)
400/400A
P/N 128-590001-9C
400, 400A
Textron (Beechcraft)
700A, 700B
AFMS-125-700
HS.125 700A, 700B
Textron (Beechcraft)
800A, 800B
AFMS-800
BAe 125 800A, 800B
Textron (Beechcraft)
750
AFMS-800XP
750
Textron (Beechcraft)
800XP
AFMS-800XP
800XP
Textron (Beechcraft)
850XP
AFMS-800XP
850XP
Textron (Beechcraft)
900XP
AFMS-800XP
900XP
Sabreliner Aviation
NA-265-70,
NA-265-70,
P/N SE 0405 MM
NA-265-80
NA-265-80
Sabreliner Aviation
NA-265-65
P/N SE 0303 MM
NA-265-65
A "visual inspection" is defined as the process of using the eye, alone or in conjunction with various
aids, as the sensing mechanism from which judgments may be made about the condition of a unit to be
inspected.
This level of inspection is made from within touching distance unless otherwise specified. A mirror may
be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of
inspection is made under normally available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight. A visual inspection may require the removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.
The inspection criteria provided below is intended as general guidance. Conduct special inspection as
deemed appropriate by each operator based on aircraft experience. Any discrepancies found should
be repaired.
6.2 Wiring
The inspection criteria provided below is intended as general guidance. Special inspection should be
conducted as deemed appropriate by each operator. Any discrepancies found should be repaired.
a. Wire/Wire Bundle Inspect for:
Aluminum drill shavings, lint or dust on or inside wire bundles. Aluminum shavings can,
with vibration or other motion, cut through wire insulation and provide a conductive path
between wires in a bundle or to adjacent grounded structure. Lint and dust can
accumulate on wire bundles and may, if subjected to overheated wires, ignite or possibly
feed an electrical fire.
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Wire insulation that has become brittle. Wire may be more susceptible to cracking.
Damaged insulation and/or exposed conductor material of wires. Cracked, chafed and
cut insulation can provide a conductive path between wires in a bundle or to adjacent
grounded structure.
Pinched wires can occur at wire clamps, connector backshell clamps, excessively tight
cable ties, etc.
Inappropriate/improper wiring repairs such as the use of duct tape, electrical tape, poor
crimp splices, etc.
Wire insulation damage due to fluid leaks (i.e. fuel, hydraulic fluid, etc.)
Separation of electrical wires from hydraulic, fuel and oxygen lines. Ensure a minimum
of 0.5-inch separation and any wiring routed within 2.0 inches must be clamped to
provide separation.
Small bend radii of wire. Wiring subjected to excessively tight bend radii may sustain
damage to the wire insulation.
Sagging wire bundles. Ensure bundles are not allowed to droop onto structure,
components, cables, hoses, other bundles, etc.
Wire attached to the outside of a wire bundle using plastic ties instead of being installed
under existing wire clamps. Can cause chafed and cut wire insulation.
Unsupported wires running into conduit or wire supported in such a way as to pull the
wire against the side of the conduit entrance instead of into the center. Can cause
chafed and cut wire insulation.
Proximity to high temperature equipment. Wiring shall be kept separate from high
temperature equipment, such as resistors, exhaust stacks, heating ducts and deicers, to
prevent wire insulation deterioration.
Wires with different insulation types should not be routed together, where possible.
Certain wire insulations may be easily abraded by other types of wire insulation.
b. Wire Harness Clamps - Inspect for:
Condition. Ensure any protective material on the wire clamp (i.e. rubber, plastic, etc.) is
in serviceable and functional condition. Clamps should be secured to structure and wire
bundle should be snug in clamp.
Ensure clamps are not installed over splices.
C. Connectors - Inspect for:
Condition. Make sure connectors are free of corrosion, moisture, dust and metal
shavings. Check for worn environmental seals, loose contact tension, proper contact
locking, missing seal plugs, missing dummy contacts, etc. Drip loops should be
maintained when connectors are below the level of the harness and tight bends at
connectors should be avoided or corrected.
d. Backshells - Inspect for:
Condition: Wires may break at connector backshells due to excessive flexing, lack of
strain relief or improper buildup. Loss of backshell bonding may also occur due to these
and other factors.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
Page 35 of 36
Rel'd By VT-DRB, FSCM 47MZ7, Sht 35 of 39, 2019/Mar/19
EFTA00011721

=== Page 54 ===
DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
e. Electrical Conduits and Sleeving - Inspect for:
Susceptibility to water/moisture entrance: Conduits should not be susceptible to the
entrance of moisture. If moisture going into conduits and sleeving is unavoidable,
provisions should be made in the lower portions of the conduit to drain any moisture and
prevent accumulation.
Condition: Damage to sleeving and conduits, if not corrected, will often lead to wire
damage. Make sure components are free from corrosion, moisture, dust, and metal
shavings. Check that conduit is secured to structure.
f. Terminations - Inspect for:
Condition: Terminal lugs and splices are susceptible to mechanical damage, corrosion,
heat damage and chemical contamination. The buildup and nut torque on wire lugs is
critical to their performance.
g. Grounding Points - Inspect for:
Condition: Grounding points should be checked for security (i.e. tightness) condition of
termination, cleanliness and corrosion. Any grounding points that have corroded or have
lost their protective coating should be repaired and checked for proper resistance.
CAUTION
Use care when disturbing or removing wire harness/bundles to minimize the possibility of wire
insulation damage or cracking. Care must be especially used in areas with severe moisture problems.
During any repair, modification, or installation work in close proximity to wire bundles, mounts,
connectors and systems, ensure that these areas are protected from and/or cleaned of metal shavings
and debris.
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
Page 36 of 36
Rel'd By VT-DRB, FSCM 47MZ7. Sht 36 of 39, 2019/Mar/19
EFTA00011722

=== Page 55 ===
DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Appendix A - List of Applicable Publications
NOTE: The latest released revision of the publications listed in the LOAP constitutes the required information
essential for continued airworthiness for the aircraft.
Document Title
Document Number
Airplane Flight Manual Supplement
584-00-0046
Master Data List (includes wiring diagrams,
584-00-0001
equipment installations and ground test)
TDR-94/94D ATC/Mode-S Transponder System
523-0821492
(-5XX) Install Manual
GPS-4000( ) Global Positioning System
523-0780545
Installation Manual
Equipment Installation Manual for the FreeFlight
86764
System Model 1203C GPS/SBAS Sensor
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
Page A1 of A1
Rel'd By VT-DRB, FSCM 47MZ7, Sht 37 of 39, 2019/Mar/19
EFTA00011723

=== Page 56 ===
DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Appendix B - Special Tools and Equipment
Transponders - Aeroflex IFR-6000 or equivalent test set.
GPS - JCAir 429 or equivalent 429 Bus Reader
GPS - Oscilloscope
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
Page B1 of B1
Rel'd By VT-DRB, FSCM 47MZ7, Sht 38 of 39, 2019/Mar/19
EFTA00011724

=== Page 57 ===
DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B2D045
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Appendix C - Discrepancy Reporting Form
This form to be used by aircraft owner operators and modification centers to report discrepancies with
modifications and repairs approved by the ODA.
DATE DISCREPANCY DISCOVERED: Self explanatory.
DISCREPANCY: Describe the discrepancy in detail.
RECOMMENDED CORRECTIVE ACTION:
Describe what actions you recommend taking to correct the discrepancy.
REPORTED BY: Self explanatory.
COMPANY NAME:
PERSON TO CONTACT:
PHONE
NUMBER:
TITLE:
Self explanatory.
Date:
Signature:
Self explanatory.
Please submit the completed form to the following contact:
VT DRB ODA Unit
San Antonio, TX 78216
USA
Phone:
Email:
REPORT No. 584-00-0047, Rev: D
BHE & Associates, Ltd.
Page C1 of C1
Rel'd By VT-DRB, FSCM 47MZ7, Sht 39 of 39, 2019/Mar/19
EFTA00011725

=== Page 58 ===
EFTA00011726

=== Page 59 ===
OMB No. 2120-0020
Electronic Tracking Number
Exp: 5/31/2018
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
USA/N493LX
RK-244
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Address
2. Owner
Flight Options
City
Richmond Heights
State OH
Zip
44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
Raytheon Alroaft Company
X
AIRFRAME
(As described in Item 1 above)
RK-244
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
44143-1453
Country USA
CRS# 25NR667B
Zip
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individ
per 14 CFR Part 43
App. B
12-29-2013
7. Approval for
04-01-2019
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
x
Approved
Rejected
FAA Flt. Standards
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized In
Designation No. CRS#
25NR667B
12-29-2013
FAA Form 337 (10/06)
04-01-2019
EFTA00011727

=== Page 60 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required attach additional sheets Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
This 337 is amended 01APR2019 to correct a Typo in block 8.
Installed New Pitot Probes in accordance with STC ST10959SC. Nextant Master Drawing List
Document 373-00-0001 Rev CC EO24-11.
Removed Pitot Probes Part Number PH1100-MU-R-1
Removed Pitot Probes Part Number PH1100-MU-L-1
Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803
Installed Pitot Probes Part Number PH1100-MUL-EN Serial Number 1728401
Leak Check carried ouit Beechcraft Aircraft Maintenance Manual Chapter 34-12-00-201
ICA
Continue with Normal Hawker Beech Maintenance Practices for this area.
END
Additional Sheets Are Attached
FAA Form 337 (10/06)
Page 2
EFTA00011728

=== Page 61 ===
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
I NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
N188TS
Company 400A
RK-244
Transport
i AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. $ 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
-None-
I TERMS AND CONDITIONS
Unless sooner surrendered suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43, and
91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered in the United States.
DATE OF ISSUANCE
DESIGNATION NUMBER
R3/06/2014
GL-25
Any alteration, reproduction, or ceeding 3 years or both.
HIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS
A Form 8100-2 (04-11) Supersedes Previous Edition
COPY
FROM AIRCRAFT
EFTA00011729

=== Page 62 ===
СОБА
EFTA00011730

=== Page 63 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
188TS
Company 400A
RK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
AFS-750 copy
-None-
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43, and
91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered in the United States.
DATE OF ISSUANCE
FAA REPRESENTATIVE
DESIGNATION NUMBER
R3/06/2014
GL-25
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.
FAA Form 8100-2 (04-11) Supersedes Previous Edition
EFTA00011731

=== Page 64 ===
EFTA00011732

=== Page 65 ===
U.S. Department
Cleveland Flight Standards District Office
of Transportation
North Olmsted. Ohio 44070
Federal Aviation
Administration
October 9, 2018
Aircraft Registration Branch
AFS-750
To whom it may concern:
During review of AFS-750 records it was found that a discrepancy existed of the
Airworthiness Certificate for N188TS, Make: Raytheon Aircraft Company, Model: 400A,
Serial Number RK-244, it was noted that the Airworthiness Certificate registration number
did not show the required Nationality letter "N". During inspection of the aircraft it was
found that the original Airworthiness Certificate did in fact have the required Nationality
letter. Made a copy of the original Airworthiness Certificate and forwarded to AFS-750.
If you have any questions in this matter, please contact me at
Sincerely
FAA PMI CLE FSDO
EFTA00011733

=== Page 66 ===
EFTA00011734

=== Page 67 ===
OMB No. 2120-0020
Electronic Tracking Number
Exp: 5/31/2018
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
USA / N188TS
RK-244
1. Aircraft
Make
Model
Series
RAYTHEON AIRCRAFT COMPANY
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Address
2. Owner
THORAIR LLC
City SANDUSKY
State OHIO
Zip 44871-2218
Country UNITED STATES
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
RAYTHEON AIRCRAFT COMPANY
AIRFRAME
(As described in Item 1 above)
RK-244
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address 26460 Curtis Wrigth Parkway
Foreign Certificated Mechanic
C. Certificate No.
City Cleveland
State Ohio
Certificated Repair Station
Zip
Country United States
CRS# WC7R346J
44143
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
0/06/2017
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Approved
Rejected
FAA Flt. Standards
Persons Approved by Canadian
Manufacturer
Maintenance Organization
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Designation No. CRS#
10/06/2017
WC7R346J
FAA Form 337 (10/06)
Page I
EFTA00011735

=== Page 68 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N188TS
10/06/2017
Nationality and Registration Mark
Date
STC# ST02371LA Winglet Option Installation
Installed Nextant Aerospace Winglets IAW Nextant Aerospace STC# ST2371LA amended date
3/10/2017, Master Data List# MDL-NXT-001 Rev J, dated 2/14/2017, and minor deviations IAW
EO# NT-EO-0817-09 Rev A and NT-EO-1017-09 Rev IR.
Removed Equipment
Item
Part Number
Serial Number
Left Wingtip Assembly
45A10552-001
Left Strobe/Position Light Assembly
45A88750-22
Wing Tip Lens
8888-170000-01
Right Wingtp Assembly
45A10552-002
Right Strobe/Position Light Assembly
45A88750-22
Wing Tip Lens
8888-170000-02
Tail Strobe Light
4588315-121
Tail Position Light
45A88754-11
Strobe Power Supply
01-790080-00
00575
Installed Equipment
Item
Part Number
Serial Number
Left Winglet Assembly
NEXT-SA15250LA57-10001
S-NEXT-0001
Right Winglet Assembly
NEXT-SA15250LA57-10002
S-NEXT-0001
Left Winglet Light Assembly
87-03916-001
00214
Right Winglet Light Assembly
87-03917-001
00216
Tail Strobe Cover Plate
NX0047-3340-0101-001
Tail Position Cover Plate
NX0047-3340-0102-001
ICA
Follow the maintenance inspection practices in the Nextant Aerospace Instructions for Continued
Airworthiness Document No. NX0047-ICA0-0101 Rev. A, dated 6/20/2016 or later FAA approved
revisions.
AFMS
FAA Approved Airplane Flight Manual Supplement Document No. NX0047-AFMS-0101 Rev. IR,
dated 3/10-2017 or later FAA approved revisions have been added to the Airplane Flight Manual
Weight and Balance
Reference Weight and Balance Report dated 10/06/2017
END
Additional Sheets Are Attached
FAA Form 337 (10/06)
Page 2
EFTA00011736

=== Page 69 ===
Hrited States Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
Number ST02371LA
This Certificate issued to Nextant Aerospace, LLC
Richmond Heights, Ohio 44143
certifies that the change in the type design for the following product with the limitations and conditions
therefore as specified hereon meets the airworthiness requirements of Part 25* of the Federal Aviation
Regulations. *Certification basis is set forth on TCDS A16SW and continuation sheets 3 and 4.
Original Product Original Product Type crtificate. Cumber: A16SW
Make: Beechcraft Corporation
Model: 400A
Description of Type Design Change Alteration of a Beechcraft Corporation 400A airplane, to replace Pratt
& Whitney JT15D-5 series engines with Williams International FJ44-3AP engines (TCDS E3GL) with
Full Authority Digital Engine Control (FADEC) and associated systems (Config. A) and (/or) the
installation of Nextant Winglets (Config. B), in accordance with Nextant Aerospace Master Drawing List
No.: MDL-NXT-001, Revision IR dated 8/22/2011, or later FAA approved revisions and the appropriate
FAA approved Airplane Flight Manual Supplement(s) for the applicable installed configuration(s):
Config. A: NXT1-AFMS, Rev IR, dated September 15, 2011 or later FAA approved revisions
Config. B: NX0047-AFMS-0101, Rev IR, dated March 10, 2017 or later FAA approved revisions
Limitations and Conditions The installation should not be incorporated in any aircraft unless it is
determined that the interrelationship between this installation and any previously approved configuration
will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this
modification applies to the above-noted airplane models only. If the holder agrees to permit another person
to use this certificate to alter the product, the holder shall give the other person written evidence of that
permission.
(CONTINUED on page 3)
This certificate and the supporting data which is the basis for approvals shall remain in effect until
surrendered suspended revoked of a termination date is otherwise stablished by the Administrator of the
Federal Aviation. Administration
Date of application
March 24, 2008
Date reissued:
Date of Essuance:
September 27, 2011
Date amended: March 10, 2017
FEDERAL
NATION
By direction of the Indivinistrator
*
(Signature)
ADMINISTRATION
Manager, Propulsion Branch
Los Angeles Aircraft Certification Office
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisenment not exceeding 3 years, or both.
FAA Form 8110-2(10-60)
Page 1 of 4
This certificate may be transferred in accordance with TAR21.47.
EFTA00011737

=== Page 70 ===
EFTA00011738

=== Page 71 ===
Minited Sinire Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Limitations and Conditions (vontinued)
Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC
ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this
alteration.
The new Vmca and Vmcg values are 94 KIAS and 93 KIAS respectively.
The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of
77°F.
Approved engine fuels are:
Grade
Specification
Jet A
ASTM-D 1655
Jet A-1
ASTM-D 1655
FAA accepted revisions of the Nextant Aerospace, LLC Instructions for Continued Airworthiness
document must be made available to the operator with the installation of the STC configuration(s).
Config. A: NXT1-ICA, Revision IR, or later FAA accepted revisions.
Config. B: NX0047-ICA0-0101, Revision A, or later FAA accepted revisions.
Certification Basis
The certification basis for this modification is as follows:
The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS
A16SW, Revision 26, dated March 17, 2010:
Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by 25-1 through 25-40, plus $$
25.1335, 25.1351(d), 25.1353(c)(5), and 25,1447 of Amendment 25-41; §§ 25.29, 25.255, and 25.1353(c)(6) of
Amendment 25-42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation
Regulations effective December 1, 1969, as amended by 36-1 through 36-17; SFAR 27 effective February 1, 1974. as
amended by 27-1 through 27-5; and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude
Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio
Frequency Energy Protection). (See NOTE 12)
Equivalent Safety Items
(1) Out-of-trim characteristics FAR 25,255
(2) Pilot compartment view FAR 25.773(b)(2)
(3) Passenger compartment door FAR 25.813(e)
(4) Emergency exit marking FAR 25.811(d)(1) and 25.811(d)(2)
Application for amended Type Certificate dated February 18, 1988.
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
PAA Form 8110-2(10-G8)
Page 3 of .
This certificate may be transferred in accordance with FAR_21.47.
EFTA00011739

=== Page 72 ===
EFTA00011740

=== Page 73 ===
Histed States BI America
Department of Transportation - Federal Atriation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Certification Basis (continued)
Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved
Compliance Check List):
Subpart A - General §§ 25.2(25-99)
Subpart B - Flight: $ 25.207(25-121), 25.255(25-42)
Subpart C- Structure: §§ 25.571 (25-96)
Subpart D - Design and Construction: §§ 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112),
25.625(25-72), 25.832(25-72), 25.863(25-46), 25.869(25-123),
Subpart E- Powerplant: §§ 25.901(25-46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125),
25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42),
25.1045(25-57), 25.1091(25-100), 25.1093(25-72), 25.1103(25-46), 25.1141(25-115), 25.1143(25-57),
25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57),
25.1195(25-46), 25.1203(25-123), 25.1207(25-46).
Subpart F- Equipment: §§ 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123),
25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123),
25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41),
Subpart G - Operating Limitations and Information: 5525.1501(25-42), 25.1521(25-72),
25.1527(25-105), 25.1529(25-54), 25.1543(25-72), 25.49(25-40), 25.1551(25-72), 25.1557(25-72),
25.1581(25-72), 25.1583(25-105).
Subpart H - Electrical Wiring interconnection Systems (EWIS): §§ 25.1701(25-123), 25.1703(25-123),
25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123),
25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123),
25.1729(25-123), 25.1731(25-123), 25.1733(25-123).
14 CFR Part 34(34-3): 34.11
14 CFR Part 36 (36-28): 36.1--36.7, 36.101-36.105, 36.1501, 36.1581.
The following Nextant Aerospace Continued Airworthiness Supplements are applicable to airplanes
modified in accordance with this STC:
Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved
revisions.
EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXT1-EA-007 Rev A
dated 8/24/11 or later FAA approved revisions.
--END--
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA Form #110-2(10-68)
Page 4 of 4
This certificate may be transferred in accordance with FAR21.47.
EFTA00011741

=== Page 74 ===
EFTA00011742

=== Page 75 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Constant Aviation
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # WC7R346J
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individ
per 14 CFR Part 43
09/Sep/2017
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individual
Designation No.
09/Sep/2017
WC7R346J
FAA Form 337 (10-06)
EFTA00011743

=== Page 76 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/Sep/2017
Nationality and Registration Mark
Date
This is a revised FAA 337 to correct the Serial Numbers of the Engines that were installed by
Nextant Aerospace CRS # 25NR667B on FAA 337 Dated 05/30/2013
Nextant Aerospace Completed STC # ST02371LA
Removed Pratt and Whitney JT15D-5 Series Engines.
Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance
with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA
Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions.
Installed Left Engine Part Number. 111000-202 Serial No. 252767
Installed Right Engine Part Number 111000-202 Serial No. 252768
ICA
AFM Supplement was installed on Aircraft.
Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted
revisions are included in the Aircraft Maintenance Records.
Carried out Engine Ground Runs and System OPS checks IAW Ground Test Plan 373-00-0024 Rev F.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011744

=== Page 77 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
188TS
Company 400A
RK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
-None-
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43, and
91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered in the United States.
DATE OF ISSUANCE
FAA REPRESENTATIVE
DESIGNATION NUMBER
R3/06/2014
GL-25
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.
FAA Form 8100-2 (04-11) Supersedes Previous Edition
EFTA00011745

=== Page 78 ===

=== Page 79 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
RK-244
Transport
N493LX
Company 400A
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
*None*
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as the maintenance, preventative maintenance, and
ance with Parts 21, 43, and
91 of the Federal Aviation Regulations, as appropriate, and the aircraft
DATE OF ISSUANCE
DESIGNATION NUMBER
03/06/2014
DART833943G
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST 8E DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.
FAA Form 8100-2 (04-11) Supersedes Previous Edition
EFTA00011747

=== Page 80 ===

=== Page 81 ===
4/10/2014
Flight Standards District Office
Great Northern Tech Bldg. II
North Olmstead, Ohio 44070
Cleveland Flight Standards District Office:
ThorAir LLC. would like to request a new airworthiness certificate for Serial number RK-244, Raytheon
Aircraft Company 400A. The reason for requiring an airworthiness certificate change is a new
registration number is being placed on the aircraft. Included with this letter is AC Forum 8050-64 issue
date Apr 03, 2014 showing the change in registration number from N493LX to N188TS.
Signature of Owner:
Title of Owner:
President of ThorSport, Inc., ThorAir, LLC. It's Member
EFTA00011749

=== Page 82 ===

=== Page 83 ===
FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE
Form Approved O.M.B. No. 2120-0018
Expiration Date 02/28/2013
APPLICATION FOR
INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA
U.S. Department
U.S. AIRWORTHINESS
use only. Submit original only to an authorized FAA Representative. If additional
Accepted GS Apr/30/2014
of Transportation
space is required, use attachment For special flight permits complete Sections
Federal Aviation
CERTIFICATE
II, VI, and VII as applicable
Administration
1. REGISTRATION MARK
2. AIRCRAFT BUILDER'S NAME (Make)
3. AIRCRAFT MODEL DESIGNATION
4. YR. MFR.
FAA-CODING
N493LX
Raytheon Aircraft Co
400A
1999
1. AIRCRAFT
DESCRIPTION
5. AIRCRAFT SERIAL NO.
6. ENGINE BUILDER'S NAME (Make)
7. ENGINE MODEL DESIGNATION
RK-244
Williams International
FJ44-3AP
8. NUMBER OF ENGINES
9. PROPELLER BUILDER'S NAME (Make)
10. PROPELLER MODEL DESIGNATION
11. AIRCRAFT IS (Check , applicable)
2
N/A
N/A
IMPORT
APPLICATION IS HEREBY MADE FOR: (Check applicable items)
A
1
STANDARD AIRWORTHINESS CERTIFICATE (Indicate category)
NORMAL
unity
ACROBATIC
TRANSPORT
COMMUTER
BALLOON
OTHER
B
SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)
7
PRIMARY
9
LIGHT-SPORT (Indicate Class)
Airplane
Power-Parachute
Weight-Shift-Contral
Glider
Lighter than Air
2
LIMITED
1
CLASS I
5
PROVISIONAL (Indicate class)
2
CLASS II
1
AGRICULTURE AND PEST CONTROL
2
AERIAL SURVEY
3
AERIAL ADVERTISING
3
RESTRICTED (indicate operation(s)
4
FOREST (Widlife conservation)
5
PATROLLING
to be conducted)
6
WEATHER CONTROL
II. CERTIFICATION REQUESTED
0
OTHER (Specify)
1
RESEARCH AND DEVELOPMENT
2
AMATEUR BUILT
3
EXHIBITION
4
AIR RACING
5
CREW TRAINING
6
MARKET SURVEY
0
TO SHOW COMPLIANCE WITH THE CFR
7
OPERATING (Primary Category) KIT BUILT AIRCRAFT
8A
Existing aircraft without an airworthiness certificate & do not meet $ 103.1
4
EXPERIMENTAL (Indicate operation(s)
to be conducted)
OPERATING
8
8B
Operating Light-Sport Kit-buit
LIGHT-SPORT
8C
Operating light-sport previously issued special light-sport category airworthiness
certificate under 21.190
UNMANNED
9A
RESEARCH AND DEVELOPMENT
9C
CREW TRAINING
9
AIRCRAFT
9B
MARKET SURVEY
1
FERRY FLIGHT FOR REPAIRS, ALTERATIONS, MAINTENANCE, OR STORAGE
SPECIAL FLIGHT PERMIT (Indicate
2
EVACUATE FROM AREA OF IMPENDING DANGER
8
operation to be conducted then complete
Section VI DV VIV as applicable on reverse side)
3
OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT
4
DELIVERING OR EXPORTING
5
PRODUCTION FLIGHT TESTING
6
CUSTOMER DEMONSTRATION FLIGHTS
C
6
MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE Restricted Operation* and "Standard" or "Limited" as applicable)
A. REGISTERED OWNER (As shown on certificate of aircraft registration)
IF DEALER, CHECK HERE
NAME
ADDRESS
ThorAir LLC
Sandusky. OH 44871
B. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated)
AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No and
AIRWORTHINESS DIRECTIVES (Check if of applicable ADs are complied with and give the number
Revision No.)
A16SW Rev 28
of the last AD SUPPLEMENT available in the biweekly series as of the date of application)
III. OWNER'S CERTIFICATION
Bi Weekly 2014 2/10/2014 - 02/23/2014
AIRCRAFT LISTING (Give page number(s))
SUPPLEMENTAL TYPE CERTIFICATE (L/st number of each STC incorporated)
N/A
See Attached Sheet
C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS
CHECK IF RECORDS IN
TOTAL AIRFRAME HOURS
EXPERIMENTAL ONLY (Enter hours flown since last certificate issued
COMPLIANCE WITH
8616.1 TTAF
3
or renewed)
14 CFR section 91.417
N/A
D. CERTIFICATION hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation Administration in
accordance with Title 49 of the United States Code 44101 elseg and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy and eligible for the
airworthiness certificate requested
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNAT
03/06/2014
Anton Koprivnik Agent
A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete the section only if 14 CFR part 21. f83(d) applies
2
14 CFR part 121 CERTIFICATE HOLDER (Give
3
CERTIFICATED MECHANIC (Give Certificate No)
CERTIFICATED REPAIR STATION (Give Certificate
IV. INSPECTION
VERIFICATION
Certificate No)
6
No)
AGENCY
5
AIRCRAFT MANUFACTURER (Give name or firm)
DATE
TITLE
SIGNATURE
(Check ALL applicable block dams A and a)
THE CERTIFICATE REQUESTED
A. I find that the aircraft described in Section I or VII meets requirements for
4
AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE
V. FAA REPRESENTATIVE
B. Inspection for a special flight permit under Section VII
FAA INSPECTOR
FAA DESIGNEE
CERTIFICATION
was conducted by:
CERTIFICATE HOL UNDER
CER part 65
CER
DATE
MIDO/FSDO
FAA INSPECTOR'S
OFFICE
SIGNATURE AND
03/06/2014
GL-25
4
DART833943
FAA Form 8130-6 (4/11) All Previous Editions Superseded
RECEIVED
MAR 10 2014
CLE-GL2E
EFTA00011751

=== Page 84 ===
A. MANUFACTURER
NAME
ADDRESS
VI. PRODUCTION
FLIGHT TESTING
B. PRODUCTION BASIS (Check applicable item)
PRODUCTION CERTIFICATE (Give production certificate number)
TYPE CERTIFICATE
OTHER:
C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNATURE
A. DESCRIPTION OF AIRCRAFT
REGISTERED OWNER
ADDRESS
BUILDER (Make)
MODEL
SERIAL NUMBER
REGISTRATION MARK
B. DESCRIPTION OF FLIGHT
CUSTOMER DEMONSTRATION FUGHTS
(Check if applicable)
FROM
TO
VIA
DEPARTURE DATE
DURATION
C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT
VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST
PILOT
CO-PILOT
FLIGHT ENGINEER
OTHER (Specify)
D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS:
E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment if necessary)
F. CERTIFICATION - hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation
Administration in accordance with Title 49 of the United States Code 44101 91500 and applicable Federal Aviation Regulations: and that the aircraft has been inspected and is
safe for the flight described
DATE
NAME AND TITLE (Print or type)
SIGNATURE
A. Operating Limitations and Markings in Compliance With 14 CFR Section 91.9,
G. Statement of Conformity. FAA Form 8130-9 (Attach when required)
As Applicable
H. Foreign Airworthiness Certification for Import Aircraft
DOCUMENTATION (FAA/DESIGNEE
B. Current Operating Limitations Attached
(Attach when required)
VIII. AIRWORTHINESS
I. Previous Airworthiness Certificate Issued in Accordance With
use only)
C. Data, Drawings, Photographs, etc. (Attach when required)
14 CFR Section 21.191 (f)
CAR
(Original attached)
D. Current Weight and Balance Information Available in Aircraft
J. Current Airworthiness Certificate Issued in Accordance With
E. Major Repair and Alteration, FAA Form 337 (Attach when required)
14 CFR Section 21.183 (d)
(Copy attached)
F. This inspection Recorded in Aircraft Records
K. Light-Sport Aircraft Statement of Compliance, FAA Form 8130-15 (Attach
when required)
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format-PDF
Page 2 of 2
EFTA00011752

=== Page 85 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
COPY
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
N493LX
Company 400A
RK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
*NONE*
6 TERMS AND CONDITIONS
1
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as the maintenance, preventative maintenance,
with Parts 21, 43, and
91 of the Federal Aviation Regulations, as appropriate, and the aircr
DATE OF ISSUANCE
DESIGNATION NUMBER
03/06/2014
DART833943GL
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1 ,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.
FAA Form 8100-2 (04-11) Supersedes Previous Edition
EFTA00011753

=== Page 86 ===
EFTA00011754

=== Page 87 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION
SPECIAL AIRWORTHINESS CERTIFICATE
A
CATEGORY/DESIGNATION
Experimental
PURPOSE
Market Survey
MANU-
NAME
B
N/A
FACTURER
ADDRESS ///
FROM
C
FLIGHT
TO
N- 493LX
SERIAL NO. RK-244
D
BUILDER RaytheonliA rcraft| Co'
MODEL 400A
DATE OF ISSUANCE 05/2014
/
EXPIRY Aug/04/2014
OPERATING LIMITATIONS DATED /05/201 4ARE PART OF THIS CERTIFICATE
E
DESIGNATION OR OFFICE NO.
DART833943GL
Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or
imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT
IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR).
FAA FORM 8130-7 (07/04)
SEE REVERSE SIDE
NSN: 0052-00-693-4000
EFTA00011755

=== Page 88 ===
This airworthiness certificate is issued under the authority of Public Law 104-6, 49 United States Code
A
(USC) 44704 and Title 14 Code of Federal Regulations (CFR).
The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct
B
production flight tests, and only production flight tests, of aircraft registered in his name. No person may
conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or
hire: and/or (2) Carrying persons not essential to the purpose of the flight.
C
This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in
Block A.
This airworthiness certificate certifies that as of the date of issuance, the aircraft to which issued has
been inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet
the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex
D
8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the
reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and
limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign
country without the special permission of that country.
Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the
E
duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217.
EFTA00011756

=== Page 89 ===
ThorAir
March 3, 2014
ThorAir, LLC.
Sandusky, Oh
Re: RK 244 - Agent Authorization
To whom it may concern:
This letter is to confirm that ThorAir, LLC, authorizes Nextant Aerospace, LLC, as ThorAir's agent
for a Beechjet 400A, bearing serial number RK-244 and FAA Registration number N493LX, which is
owned by ThorAir, LLC., and operated by ThorSport, Inc., for any and all authorized FAA actions needed.
Sincerely,
ThorAirLLLC
By:
my commission expires 1AU92016
Notary's Official Signature
Sworn and subscribed to me this day, 3 of March , 2014 b
ThorAir
Sandusky, Ohio 44870
ThorAir
EFTA00011757

=== Page 90 ===
EFTA00011758

=== Page 91 ===
RK-244 STC list (03/05/2014)
Reference 8130-6:
Application for Standard Airworthiness Certificate
Transport Category, dated March 6, 2014
Reference section III owners certification
ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams
International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital
Engine Control (FADEC) and associated systems.
ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight
Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer
Performance with Vertical Guidance (LPV) approach capability and
Universal Avionics System Company (UASC) Terrain Awareness
Warning System (TAWS)
ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed
Internet System with Wireless Local Area Network (WLAN), Astronics
115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System.
ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place
divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one
(1) set of forward pocket door dividers and LED lighting.
STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery
ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum -
(RVSM)
EFTA00011759

=== Page 92 ===

=== Page 93 ===
<00
EFTA000117
B
N493LX
NY

=== Page 94 ===
EFTA00011762

=== Page 95 ===
UMPA
HIGHITA M
STC TYPE:
SERIA
<-244
PRODUCTION
400A
A16S \\\
SERIAL #:
ICATE B
MODEL YE
1/3/22

=== Page 96 ===

=== Page 97 ===
nextant aerospace
STC TYPE:
400XTi
PRODUCTION
is
28
SERIAL #:
RK-244
MODEL YEAR:
2014

=== Page 98 ===

=== Page 99 ===
FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE
Form Approved O.M.B. No. 2120-0018
Expiration Date 02/28/2013
APPLICATION FOR
INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA
U.S. Department
U.S. AIRWORTHINESS
use only. Submit original only to an authorized FAA Representative. If additional
of Transportation
space is required, use attachment For special flight permits complete Sections
Federal Aviation
CERTIFICATE
II, VI, and VII as applicable.
Accepted GS Mar/19/2014
Administration
1. REGISTRATION MARK
2. AIRCRAFT BUILDER'S NAME (Make)
3. AIRCRAFT MODEL DESIGNATION
4. YR. MFR.
FAA CODING
N493LX
Raytheon Aircraft Co
400A
1999
I. AIRCRAFT
DESCRIPTION
5. AIRCRAFT SERIAL NO.
6. ENGINE BUILDER'S NAME (Make)
7. ENGINE MODEL DESIGNATION
RK-244
Williams International
FJ44-3AP
8. NUMBER OF ENGINES
9. PROPELLER BUILDER'S NAME (Make)
10. PROPELLER MODEL DESIGNATION
11. AIRCRAFT IS (Check if applicable)
2
N/A
N/A
IMPORT
APPLICATION IS HEREBY MADE FOR: (Check applicable items)
A
1
STANDARD AIRWORTHINESS CERTIFICATE (Indicate category)
NORMAL
UTILITY
ACROBATIC
TRANSPORT
COMMUTER
BALLOON
OTHER
B
SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)
7
PRIMARY
9
LIGHT-SPORT (Indicate Class)
Airplane
Power-Parachute
Weight-Shift-Control
Glider
Lighter than Air
2
LIMITED
1
CLASS I
5
PROVISIONAL (Indicate class)
2
CLASS If
1
AGRICULTURE AND PEST CONTROL
2
AERIAL SURVEY
3
AERIAL ADVERTISING
3
RESTRICTED (Indicate operation(s)
4
to be conducted)
FOREST (Wildlife conservation)
5
PATROLLING
6
WEATHER CONTROL
II. CERTIFICATION REQUESTED
0
OTHER (Specify)
1
RESEARCH AND DEVELOPMENT
2
AMATEUR BUILT
3
EXHIBITION
4
AIR RACING
5
CREW TRAINING
6
MARKET SURVEY
0
TO SHOW COMPLIANCE WITH THE CFR
7
OPERATING (Primary Category) KIT BUILT AIRCRAFT
8A
EXPERIMENTAL (indicate operation(s)
Existing aircraft without an airworthiness certificate & do not meet $ 103.1
4
to be conducted)
OPERATING
8
88
Operating Light-Sport Kit-built
LIGHT-SPORT
8C
Operating light-sport previously issued special light-sport category airworthiness
certificate under $21.190
UNMANNED
9A
RESEARCH AND DEVELOPMENT
9C
CREW TRAINING
9
AIRCRAFT
98
MARKET SURVEY
1
FERRY FLIGHT FOR REPAIRS ALTERATIONS, MAINTENANCE OR STORAGE
SPECIAL FLIGHT PERMIT (Indicate
2
EVACUATE FROM AREA OF IMPENDING DANGER
8
operation to be conducted, than complete
Section Vf or VII as applicable on reverse side)
3
OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT
4
DELIVERING OR EXPORTING
5
PRODUCTION FLIGHT TESTING
6
CUSTOMER DEMONSTRATION FLIGHTS
C
6
MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE Restricted Operation" and "Standard"or "Limited" as applicable)
A REGISTERED OWNER (As shown on certificate of aircraft registration)
IF DEALER, CHECK HERE
NAME
ADDRESS
Flight Options LLC
Richmond Heights .OH 44143
B. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated)
AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No. and
AIRWORTHINESS DIRECTIVES (Check if all applicable ADs are complied with and give the number
Revision No.)
A16SW Rev 28
of the last AD SUPPLEMENT available in the blweekly series as of the date of application)
III. OWNER'S CERTIFICATION
Bi Weekly 2013-25 12/02/2013 - 12/15/2013
AIRCRAFT LISTING (Give page number(s))
SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporated)
N/A
See attached sheet
C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS
CHECK IF RECORDS IN
TOTAL AIRFRAME HOURS
EXPERIMENTAL ONLY (Enter hours flown since last certificate issued
COMPLIANCE WITH
TTAF 8581.43
3
or renewed)
14 CFR section 417
2.81
D. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation Administration in
accordance with Title 49 of the United States Code 44101 elseg and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy and eligible for the
airworthiness certificate requested.
DATE OF APPLICATION
NAME AND TITI
SIGN
12/29/2013
Agent
A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete the section only if 14 CFR part 21. 183(d) applies)
2
14 CFR part 121 CERTIFICATE HOLDER (Give
CERTIFICATED MECHANIC (Give Certificate No.)
IV. INSPECTION
3
6
CERTIFICATED REPAIR STATION (Give Certificate
No.)
AGENCY
VERIFICATION
Certificate No.)
5
AIRCRAFT MANUFACTURER (Give name or firm)
DATE
TITLE
SIGNATURE
(Check ALL applicable block items A and B)
THE CERTIFICATE REQUESTED
A. I find that the aircraft described in Section I or VII meets requirements for
4
AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE
V. FAA REPRESENTATIVE
B. Inspection for a special flight permit under Section VII
FAA INSPECTOR
FAA DESIGNEE
CERTIFICATION
was conducted by:
CERTIFICATE HOLDER UNDER
14 CFR part 65
14 CFR part 121 OR 135
14 CFR part 145
DATE
MIDO/FSDO
OFFICE
12/29/2013
CLE-25
4
FAA Form 8130-6 (4/11) All Previous Editions Superse
CLE=GL25
EFTA00011767

=== Page 100 ===

=== Page 101 ===
A. MANUFACTURER
NAME
ADDRESS
VI. PRODUCTION
FLIGHT TESTING
B. PRODUCTION BASIS (Check applicable item)
PRODUCTION CERTIFICATE (Give production certificate number)
TYPE CERTIFICATE
OTHER:
C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNATURE
A. DESCRIPTION OF AIRCRAFT
REGISTERED OWNER
ADDRESS
BUILDER (Make)
MODEL
SERIAL NUMBER
REGISTRATION MARK
B. DESCRIPTION OF FLIGHT
CUSTOMER DEMONSTRATION FLIGHTS
(Check if applicable)
FROM
TO
VIA
DEPARTURE DATE
DURATION
C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT
VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST
PILOT
CO-PILOT
FLIGHT ENGINEER
OTHER (Specify)
D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS:
E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment if necessary)
F. CERTIFICATION- I hereby certify that , am the registered owner (or his agent) of the aircraft described above; that the aircraft is registered with the Federal Aviation
Administration in accordance with Title 49 of the United States Code 44101 elseg and applicable Federal Aviation Regulations; and that the aircraft has been inspected and is
safe for the flight described
DATE
NAME AND TITLE (Print or type)
SIGNATURE
A. Operating Limitations and Markings in Compliance With 14 CFR Section 91.9,
G. Statement of Conformity, FAA Form 8130-9 (Attach when required)
As Applicable
H. Foreign Airworthiness Certification for Import Aircraft
DOCUMENTATION (FAA/DESIGNEE
B. Current Operating Limitations Attached
(Attach when required)
VIII. AIRWORTHINESS
I. Previous Airworthiness Certificate Issued in Accordance With
use only)
C. Data, Drawings, Photographs, etc. (Attach when required)
14 CFR Section 21.191 (a) CAR
(Original attached)
D. Current Weight and Balance Information Available in Aircraft
J. Current Airworthiness Certificate Issued in Accordance With
E. Major Repair and Alteration, FAA Form 337 (Attach when required)
14 CFR Section 21.181 (a)
(Copy attached)
F. This inspection Recorded in Aircraft Records
K. Light-Sport Aircraft Statement of Compliance FAA Form 8130-15 (Attach
when required)
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format -PDF
Page 2 of 2
EFTA00011769

=== Page 102 ===

=== Page 103 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
Raytheon Aircraft
NUMBER
N493LX
RK- 244
Company 400A
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which
issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the
Convention on International Civil Aviation, except as noted herein.
Exceptions:
*None*
Copt
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate
is effective as long as and alterations are performed in accordance with Parts 21, 43, and
91 of the Federal Avi
DATE OF ISSUANCE
DESIGNATION NUMBER
EFTA00011771
12/29/2013
DART833943GL
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.

=== Page 104 ===

=== Page 105 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION
SPECIAL AIRWORTHINESS CERTIFICATE
A
CATEGORY/DESIGNATION EXPERIMENTAL
PURPOSE
RESEARCH DEVELOPMENT
MANU-
NAME
B
MRNA
FACTURER
ADDRESS
FROM
C
FLIGHT
MALA
TO
INXAX
N- 493LX
D
SERIAL NO. RK- 244
BUILDER Raytheon Aircraft Company
MODEL
400A
DATE OF ISSUANCE NOV 18 2013\ /
EXPIRY Jan 12. 2014
OPERATING LIMITATIONS DATED Nov 18.2013 ARE PART OF THIS CERTIFICATE
E
DESIGNATION OR OFFICE NO.
DART833943GL
Any alteration reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or
imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT
IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR).
FAA FORM 8130-7 (07/04)
SEE REVERSE SIDE
NSN: 0052-00-693-4000
EFTA00011773

=== Page 106 ===
This airworthiness certificate is issued under the authority of Public Law 104-6, 49 United States Code
A
(USC) 44704 and Title 14 Code of Federal Regulations (CFR).
The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct
B
production flight tests, and only production flight tests, of aircraft registered in his name. No person may
conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or
hire: and/or (2) Carrying persons not essential to the purpose of the flight.
C
This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in
Block A.
This airworthiness certificate certifies that as of the date of issuance, the aircraft to which issued has
been inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet
the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex
D
8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the
reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and
limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign
country without the special permission of that country.
E
Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the
duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217.
EFTA00011774

=== Page 107 ===
RK 244 STC list (12-26-2013)
Reference 8130-6:
Application for Standard Airworthiness Certificate
Transport Category, dated December 26, 2013
Reference section III owners certification
ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams
International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital
Engine Control (FADEC) and associated systems.
ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight
Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer
Performance with Vertical Guidance (LPV) approach capability and
Universal Avionics System Company (UASC) Terrain Awareness
Warning System (TAWS)
ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed
Internet System with Wireless Local Area Network (WLAN), Astronics
115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System.
ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place
divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one
(1) set of forward pocket door dividers and LED lighting.
STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery
ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum -
(RVSM)
EFTA00011775

=== Page 108 ===

=== Page 109 ===
Cleveland, Ohio 44143
flightOptions
December 26, 2013
Nextant Aerospace, LLC
Cleveland, Ohio 44143
Attention:
Re:
RK-244 - Agent Authorization
To whom it may concern:
This letter is to confirm that Flight Options, LLC ("FO") authorizes Nextant Aerospace,
LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration
Number N493LX (also identified as a "Nextant 400XT"), which is owned by FO, for any and all
authorized FAA actions in regards to:
Airworthiness Classification Experimental
X
Airworthiness Classification Standard
Sincerely,
Flight Options, LLC
By:
Vice President, Administration & Contracts
Notary's official Signature
Sworn and subscribed to me this
day 26of December of 2013
by
EFTA00011777

=== Page 110 ===

=== Page 111 ===
D
-
\ theon
O

=== Page 112 ===

=== Page 113 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No
RK-244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
05/30/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
05/30/2013
FAA Form 337 (10-06)
EFTA00011781

=== Page 114 ===
FFTA11

=== Page 115 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Part I of 3
The Following Equipment was removed along with Associated Hardware.
EFD-871
622-9345-203
Electronic Flight Display
EFD-871
622-9345-203
Electronic Flight Display
MFD-871
622-9434-213
Multi Function Display
ICU-85
622-6189-002
Internal Compensation Unit
ICU-85
622-6189-002
Internal Compensation Unit
AHC-85E
622-9336-400
Attitude/Heading Computer
AHC-85E
622-9336-400
Attitude/Heading Computer
SDU-640B
622-9735-001
Sensor Display Unit
SDU-640B
622-9735-001
Sensor Display Unit
DCP-5000
822-1028-011
Display Control Panel
DCP-5000
822-1028-011
Display Control Panel
ARP-851
622-9500-011
Altitude Reference Panel
ARP-851
622-9500-011
Altitude Reference Panel
AAP-851
822-0328-011
Altitude Awareness Panel
AAP-851
822-0328-011
Altitude Awareness Panel
CHP-850
622-7397-002
Course Heading Panel
DBU-4100
822-0014-002
Data Base Unit
DAU-650
622-9344-101
Data Acquisition Unit
SDD-640A
622-9347-001
Sensor Display Driver
IOC-4000 (4)
622-9814-514
Card Assembly
MDC-4000
622-9818-751
Maintenance Computer
CSU-4000 (2)
822-0049-002
Configuration Strapping Unit
FMC-5000 (4)
822-0891-008
Flight Management Computer
PWR-4000 (4)
622-9945-021
IAPS Power Card
GPS-4000
822-0931-003
GPS Receiver
Mounts
622-9430-002
EFD /MFD Mounts
EFB
Electronic Flight Bag Mounting
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00011783

=== Page 116 ===
EFTA00011784

=== Page 117 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
5/30/2013
Nationality and Registration Mark
Date
Page 2 of 3
Installed the Following Equipment along with Associated Hardware.
Model
Part Number
Description
Weight
Arm
CCP-3000
822-1746-002
Cursor Control Panel
2.60
90.0
CCP-3000
822-1746-002
Cursor Control Panel
2.60
90.0
DCU-3001C
822-2362-003
Data Concentrator Unit
5.0
325
DCU-3001C
822-2362-003
Data Concentrator Unit
5.0
325
ECU-3000
822-1200-209
External Compensation Unit
0.40
57.5
ECU-3000
822-1200-209
External Compensation Unit
0.40
57.5
FSU-5010
822-1543-101
File Server Unit (1st IFIS)
6.5
60.83
ECU-3000
822-1200-998
File Server Unit (1st IFIS)
0.40
57.5
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
10852801Y00
Fuel Quantity Conditioner
0.90
324
PC920-2A2000PH-2A1
Fuel Flow Conditioner
1.10
325
GPS-4000S
822-2189-004
GPS Receiver
6.0
37
CI 429-410
GPS Antenna
1.0
166.14
Amp Cluster
N241100-002
DC Voltmeter
1.5
97.4
373-93-1501-1
Speed Switch (2)
0.25
89.2
DBU-5010E
822-3000-202
Data Base Unit
1.60
134.5
PS-835D
501-1228-004
Power Supply
12.5
52.9
MMT-5000
822-1811-003
File Server Unit Rack
0.30
57.5
MMT-3010 (2)
822-1290-003
AHS Mounting Rack
1.80
57.5
XM WR-1000
822-2031-002
XM Weather
1.5
41.0
CHP-3010
822-1280-003
Course Heading Panel
1.30
92.5
Options Configuration Module.
OCM-4100
822-1463-228
0.30
57.5
WAAS/LPV
Options Configuration Module.
OCM-4100
822-1463-228
0.30
57.5
WAAS/LPV
X
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00011785

=== Page 118 ===
EFTA00011786

=== Page 119 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Page 3 of 3
Model
Part Number
Description
Weight
Arm
CSU-4100 (2)
822-1364-002
Configuration Strapping Unit
1.60
55.7
MDC-3110
822-1987-006
Maintenance Data Computer
0.80
55.7
FMC-6000 (2)
822-0868-123
Flight Management Computer
1.90
55.7
ADC-850D (2)
822-0389-468
Air Data Computer
5.30
60.83
AHC-3000A (2)
822-1378-001
Attitude Heading Computer
4.80
57.5
DCP-3030 (2)
822-1828-002
Display Control Panel
1.90
89.96
PWR-4000 (4)
622-9945-022
IAPS Power Card
1.3
55.0
IOC-4100 (4)
822-1362-511
Input/output Concentrator
0.8
55.0
LT-4001-010
Master Caution Panel
1.3
87.0
Rev. Panel
373-91-3203-1
Pilot Reversion Panel
0.2
88.0
Rev. Panel
373-91-3203-3
Co-pilot Reversion Panel
0.2
88.0
9-PED
373-91-3203-9
9-Pedestal Panel
1.8
92.89
345-6196
ELT Switch
0.2
88.0
Annunciator
Led-42-12-BB-E0Y47
AUX BATT (1/2) Annunciator
0.05
88.0
Annunciator (2)
Led-40-18-BB-E0Y45
Pull Up/ Terrain Annunciator
0.05
88.0
Annunciator
2-F840231
Terrain Inhibit/ Terrain Fail
0.05
88.0
In Accordance with STC ST10959SC. See Attached Copy
AFM Supplement, Nextant Aerospace Doc. No. 373-00-0023 Rev IR Dated 09/02/2011 or later FAA approved revision,
installed on Aircraft.
Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad.
NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic
Flight Bags (EFB) per FAA Advisory Circular AC 120-76B par 4-g. Commercial operators are required to obtain authorization
for their use from their managing Flight Standards District Office.
Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document 373-00-0002.Rev C or Later are included in
the Aircraft Maintenance Records
Carried out System Ground Test Plan IAW Master Drawing List (MDL) 373-00-004 Rev C.
Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection
/ Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43
appendix "F" Transponder System checks.
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00011787

=== Page 120 ===

=== Page 121 ===
United States of America
Department of Transportation -- Federal Abiation Administration
Supplemental Type Certificate
Number ST10959SC
This certificate issued to
Nextant Aerospace LLC
Richmond Heights, OH 44143
certifies that the change in the type design for the following product with the Cimilations and conditions therefor as
specified herean meets the airworthiness requirements of Part 25 of the the Federal Aviation Regulations (See Pages 3
and 4 for complete certification basis.)
Original.Product. Product. Type Certificate Number
A16SW
Make
Hawker Beechcraft Corp.
Modeli 400A
Description of Type Prign Change Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument
System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV)
approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System
(TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. 373-00-0001 Revision
W, dated March 29, 2012, or later FAA approved version.
Limitations and Conditions:
1) The installer must determine whether this design change is compatible with previously approved
modifications.
2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must
give that person written evidence of that permission.
3) For aircraft equipped with Pratt & Whitney JT15D Engines FAA approved Airplane Flight Manual
Supplement, Nextant Aerospace LLC Doc. No. 373-00-0008 Revision IR, dated 10/19/2009, or later
FAA approved version, is required on board the modified aircraft.
This certificate and the supporting data which is we Ravio for approval shall remain in effect until surrendered
suspended renched an a termination date is chemise stablished by the Administrator of the Federal Amialian
Administration
Date of application June 26, 2008
Date reisound
Date of insurance October 19. 2009
Date anvended September 26, 2011; April 05, 2012
FEDERAL AVIATION
*
Manager, Systems and Flight Test Branch
Chicago Aircraft Certification Office
ADMINISTRATION
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000. or imprisonment not exceeding , years, or both.
FAA FORM 0110-2(10-68)
PAGE 1 of 4 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011789

=== Page 122 ===

=== Page 123 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST10959SC
Date of issuance October 19, 2009
Date Amended: September 26, 2011; April 05, 2012
Limitations and Conditions (continued):
4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under STC
ST02371LA.
5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual
Supplement, Nextant Aerospace LLC Doc. No. 373-00-0023 Revision IR, dated September 2, 2011,
or later FAA approved version, is required on board the modified aircraft.
6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via:
RK-1 thru RK-117 and RK-119 thru RK-139, Hawker Beechcraft Service Bulletin No. 34-3431.
RK-118, RK-140 thru RK-224, Hawker Beechcraft Service Bulletin Nos. 34-3228 and 34-3431.
RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431.
RK-300 and after as original equipped from Hawker Beechcraft.
7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved
Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0036 Revision IR,
approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft.
8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane
Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0032 Revision IR, approved
March 28,2012, or later FAA approved version, is required on board the modified aircraft.
Certification Basis:
Based on 14 CFR $$21.115 and 21.101, and the FAA policy for significant changes in FAA Order
8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows:
a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS A16SW
for parts not changed or not affected by this change.
b. The certification basis for the parts changed or affected by this change since the reference date of
application, September 29, 2009, is based on TCDS A16SW and §§ 14 CFR Part 25 as shown on
page 4 of 4 of this STC.
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding J years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 3 of 4 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011791

=== Page 124 ===
EFTA00011792

=== Page 125 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Date fissuance October 19, 2009
Date Amended: September 26, 2011; April 05, 2012
Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48,
the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight
Instrument System (EFIS) with Rockwell Collins FMS-6100 modification was determined to be TCDS
A16SW and the following later regulations:
Amdt.[24-4]
Amdt.[25-23]
Amdt.[25-38]
Amdt.[25-40]
Amdt.[25-41]
25.771 (a,e)
25.301; 25.303; 25.581;
25.1309
25.901 (b)(I)(i); 25.1549
25.1321 (a)(b)(c)(e):
25.607; 25.611, 25.773
(a)(b)(c)(d)(e)(g):
(a)(b)(c)
25.1331; 25.1333
(a)(1)(2)(d)
25.1322
Amdt.[25-42]
Amdt.[25-46]
Amdt.[25-54]
Amdt.[25-72]
Amdt.[25-80]
25.1501
25.603; 25.605; 25.613;
25.1529
25.307; 25.571, 25.1307
25.1316
25.1329 (h)
(c)(e): 25.1351 (a)(1)(d):
25.1381; 25.1521 (a)(c);
25.1543 (b): 25.1581;
25.1583 (a)
Amdt.[25-86]
Amdt.[25-90]
Amdt.[25-91]
Amdt.[25-102]
Amdt.[25-105]
25.305
25.1303
25.561
25.981 (a)(b)
25.1585 (a)
Amdt.[25-108]
Amdt.[25-109]
Amdt.[25-113]
Amdt.[25-122]
Amdt.[25-123]
25.1325 (d)
25.1323 (a)(f)(g)
25.869 (a)(4): 25.1431
25.1317 (a)(b)(c)
25.1353 (a)(c)
Based on 14 CFR §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48,
the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS
was determined to be TCDS A16SW and the following later regulations:
Amdt.[Original]
Amdt.[24-4]
Amdt.[25-23]
Amdt.[25-38]
Amdt.[25-40]
25.601, 25.605, 25.609,
25.771 (a)
25.301; 25.303; 25.305,
25.603, 25.1322,
25.1585 (a)
25.613, 25.1301,
25.307, 25.561(c);
25.1583(c)
25.1357, 25.1381,
25.607; 25.611, 25.1307
25.1525,25.1541,
15.1581
Amdt.[25-41]
Amdt.[25-42]
Amdt.[25-46]
Amdt.[25-54]
Amdt.[25-72]
25.1309 (a)(b)(c)(d)(e)(g)
25.1501
25.777(a)(c)
25.1529
25.869(a)(1)
25.1351 (a)(1)
Amdt.[25-102]
Amdt.[25-113]
Amdt.[25-123]
25.981(a)(b)
25.1431(a)
25.1353 (a)(c)
- END -
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 4 of 4 PAGES
This certificate my be transferred in accordance with FAR 21.47.
EFTA00011793

=== Page 126 ===

=== Page 127 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individu
per 14 CFR Part 43
05/30/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individual
Designation No.
05/30/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011795

=== Page 128 ===

=== Page 129 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Nextant Aerospace Completed STC # ST02371LA
Removed Pratt and Whitney JT15D-5 Series Engines.
Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance
with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA
Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions.
Installed Left Engine Part Number. 111000-202 Serial No. 252757
Installed Right Engine Part Number 111000-202 Serial No. 252758
ICA
AFM Supplement was installed on Aircraft.
Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted
revisions are included in the Aircraft Maintenance Records.
Carried out Engine Ground Runs and System OPS checks IAW Ground Test Plan 373-00-0024 Rev F.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011797

=== Page 130 ===

=== Page 131 ===
United States Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
Number ST02371LA
This Certificate issued to
Nextant Aerospace, LLC
Richmond Heights, Ohio 44143
certifies that the change in the type design for the following product with the limitations and conditions
therefore as specified hereon meets the airworthiness requirements of Part 25* oftho Federal Buiation
Regulations. *Certification basis is set forth on TCDS A16SW and continuation sheets 3 and 4.
OriginalProduct Type CertificatoNumber: A16SW
Abake: Hawker Beechcraft
Abodel:
400A
Description of Type Disign Change Replacement of Pratt & Whitney JT15D-5 series engine with Williams
International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and
associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001,
Revision IR dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight
Manual Supplement, NXTI-AFMS, Rev IR, dated September 15, 2011 or later FAA approved revisions.
Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXT1-ICA, Revision IR, or
later FAA accepted revisions must be provided with this STC.
Bimilations and Conditions The installation should not be incorporated in any aircraft unless it is
determined that the interrelationship between this installation and any previously approved configuration
will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this
modification applies to the above-noted airplane models only. If the holder agrees to permit another
person to use this certificate to alter the product, the holder shall give the other person written evidence of
that permission.
(CONTINUED on page 3)
This certificate and the supporting data which w the busis for approvals shall remain in effect until
surrendered suspended revoked " a termination date is otherwise stablished by the Administrator oftho
Federal Bviation Administration
Data of application:
March 24, 2008
Date reissued:
Date of issuance:
September 27, 2011
Date amended:
FEDERAL
NATION
*
(Signature)
ADMINISTRATION
Manager, Propulsion Branch
Los Angeles Aircraft Certification Office
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both
FAA Form 8110-2(10-68)
Page ) of 4
This certificate may be transferred in accordance with FAR21.47.
EFTA00011799

=== Page 132 ===

=== Page 133 ===
INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of
the transfer of this Supplemental Type Certificate.
The FAA will reissue the certificate in the name of the transferee and forward it to him.
TRANSFER ENDORSEMENT
Transfer the ownership of the Supplemental Type Certificate Number
to (Name of transferee)
(Address of transfer)
(Number and street)
(City, State, and Zip code)
from (Name of grantor) (Print or type)
(Address of grantor)
(Number and street)
(City. State, and Zip code)
Extent of Authority (if licensing agreement):
Date of Transfer:
Signature of grantor (In ink):
Page 2 of 4
EFTA00011801

=== Page 134 ===

=== Page 135 ===
United States Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Limitations and Conditions (continued)
Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC
ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this
alteration.
The new Vmca and Vmcg values are 94 KIAS and 93 KIAS respectively.
The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature
of 77°F.
Approved engine fuels are:
Grade
Specification
Jet A
ASTM-D 1655
Jet A-1
ASTM-D 1655
Certification Basis
The certification basis for this modification is as follows:
The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS
A16SW, Revision 26, dated March 17, 2010:
Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by 25-1 through 25-40, plus §§
25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; §§ 25.29, 25.255, and 25.1353(c)(6) of
Amendment 25-42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations
effective December 1, 1969, as amended by 36-1 through 36-17; SFAR 27 effective February 1, 1974, as amended by
27-1 through 27-5; and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at
45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy
Protection). (See NOTE 12)
Equivalent Safety Items:
(1) Out-of-trim characteristics § 25.255
(2) Pilot compartment view § 25.773(b)(2)
(3) Passenger compartment door § 25.813(c)
(4) Emergency exit marking §§ 25.811(d)(1) and 25.811(d)(2)
Application for amended Type Certificate dated February 18, 1988.
Regulation at a later amendments for components and areas affected by the change (Ref. FAA
approved Compliance Check List):
Subpart A - General : 25.2(25-99)
Subpart B- Flight: 25.207(25-121), 25.255(25-42)
Subpart C- Structure: 25.571 (25-96)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA Form 8110-2110-68)
Page 3 of 4
This certificate may be transferred in accordance with FAR21.47.
EFTA00011803

=== Page 136 ===

=== Page 137 ===
United States (If America
Department of Transportation Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Certification Basis (continued)
Subpart D- Design and Construction: 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112),
25.625(25-72), 25.832(25-72), 25.863(25-46), 25.869(25-123),
Subpart E - Powerplant: 25.901(25-46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125),
25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42),
25.1045(25-57), 25.1091(25-100), 25.1093(25-72, 25.1103(25-46), 25.1141(25-115), 25.1143(25-57),
25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57),
25.1195(25-46), 25.1203(25-123), 25.1207(25-46).
Subpart F - Equipment: 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123),
25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123),
25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41),
Subpart G - Operating Limitations and Information: 25.1501(25-42), 25.1521(25-72), 25.1527(25-
105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72),
25.1583(25-105).
Subpart H - Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123),
25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123),
25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123),
25.1729(25-123), 25.1731(25-123), 25.1733(25-123).
14 CFR Part 34 (34-3): 34.11
14 CFR Part 36 (36-28): 36.1--36.7, 36.101-36.105, 36.1501, 36.1581.
The following Nextant Aerospace Continued Airworthiness Supplements are applicable to
airplanes modified in accordance with this STC:
Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved
revisions.
EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXT1-EA-007 Rev
A dated 8/24/11 or later FAA approved revisions.
-END-
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
PAA Form 8110-2(10-68)
Page 4 of $
This certificate may be transferred in accordance with FAR21.47.
EFTA00011805

=== Page 138 ===

=== Page 139 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to/Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
2/29/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011807

=== Page 140 ===

=== Page 141 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant
Aerospace Master Drawing List DB1002067. Revision F.05 Dated: October 9, 2013.
Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated
October 17, 2013. Ref. drawing for parts list.
ICA Requirements.
Ref FAA Order 8100.17
Page 7-5 and 7-6
Use FAA publications such as AC 43.13-1, Acceptable Methods, Techniques, and Practices-Aircraft Inspection and Repair,
and AC 43.13-2, Acceptable Methods, Techniques, and Practices-Aircraft Alterations; part 43 appendix D; or other applicable
aviation standards.
Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess II and ATG 4000 in
Accordance with DB 1001013. Rev E
ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FAA
Accepted Revisions
The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance
activities not covered within this ICA:
Aircell Axxess II Installation Manual D12004 Revision E, dated March 2010 or later applicable revision
Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision
Aircell Axxess II WLAN AFM Supplement DB1002072 Rev IR dated March 22 2012 for the has been Installed in the AFM
Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013
This is Located under the Seat Divan
ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later
FAA Accepted Revision.
Aircraft Flight Supplement DB1109012 has been installed on the Aircraft
See Current Weight and Balance Dated: December 29, 2013
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011809

=== Page 142 ===

=== Page 143 ===
United States of America
Department of Transportation -- Federal Abiation Administration
Supplemental Type Certificate
Number ST03960AT
This certificate issued to
Nextant Aerospace LLC
West Palm Beach, FL 33406
certifies that the change in the type design for the following product with the limitations and conditions
therefor res specified hereon meets the airocrthiness requirements of Derk 25 of the Federal Aviation
Regulations.
Criginal Product Type Certificate Number: A16SW
Make
Hawker Beechcraft Corporation
Model:
400A
Description of Type Drsign Change:
Installation of Rockwell Collins Venue In-Flight Entertainment(IFE), Aircell Axxess Cabin II Iridium Phone
and High Speed Internet System with Wireless Local Area Network (WLAN) Astronics 115VAC 60HZ
Cabin Inverter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master
Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision.
Limitations and Conditions: This approval should not be extended to other aircraft of this model on which
other previously approved modifications are incorporated, unless it is determine by the installer that the
interrelationship between this change and any other previously approved modifications will produce no
adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use
this certificate to alter the product, the holder shall give the other person written evidence of that permission.
This certificate and the supporting data which is the basis for approval shall remain in effect until
surrendered suspended reveked or " termination date is otherwise established by the Administrator of the
Federal Aciation Administration.
Date of application July 28, 2012
Date reissued: /
Date of issuance March 22, 2012
Date amended:
FEDERAL
AVIATION
ADMINISTRATION
Manager
Atlanta Aircraft Certification Office
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2(10-68)
PAGE I of 2 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011811

=== Page 144 ===
EFTA00011812

=== Page 145 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST03960AT
When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015,
Revision A, dated March 22, 2012, or later FAA approved revision, is required.
When the Aircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision
IR, dated March 22, 2012, or later FAA approved revision, is required.
When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012,
Revision IR, dated March 22, 2012, or later FAA approved revision, is required.
This system is intended to provide internet connection and email services to the airplane's cabin using
portable electronic devices (PEDs). Any other intended function of this equipment will require a re-
examination of the certification basis.
When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1002068, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant
Aerospace Document No. DB1105003, Rev A, dated September 22, 2011, or later FAA accepted revisions
must be made available to the operator at the time of installation.
When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1108018, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
When the Emteq LED Cabin Lighting system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1108019, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 2 of 3 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011813

=== Page 146 ===

=== Page 147 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST03960AT
Certification Busis:
The Certification Basis for this installation is per Type Certificate Data Sheet A16SW original Certification
Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25-40 plus
FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR 25.29, FAR 25.255, and
FAR 25.1353(c)(6) of Amendment 25-42; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46.
In addition the following specified rules amendment levels were used for this installation.
25.571
25.1353(a)(c)
25.1357
25.1431
25.1529
[25-54]
[25-123]
[25-123]
[25-113]
[25-54]
[-] Indicates amendment level
END
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding J years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 3 of 3 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011815

=== Page 148 ===

=== Page 149 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for Instructions
and disposition of this form. This report Is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
N493LX
RK244
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Flight Options, LLC
2. Owner
Addres
City Richmond Heights
StateOhio
2
CountryUSA
3. For FAA Use Only
4. Type
6. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
NameConstant Aviation
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
cayCleveland
StateOhio
X
Certificated Repair Station
CRS#WC7R346J
Zip44135
CountryUnited States
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified In item 5 above and described on the reverse or attachments hereto
have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein Is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
Date: December 30, 2013
App. B
Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date of A
Designation No.
Date: December 30, 2013
CRS#WC7R346J
FAA Form 337 (10-06)
EFTA00011817

=== Page 150 ===
EFTA00011818

=== Page 151 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous allerations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/30/2013
Nationality and Registration Mark
Date
ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION
THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED:
Repainted, recovered control columns with Matte Black Leather Accordance with Beechjet 400A AMM 20-70-00-701. 25-00-00-001
Removed and Replaced Glare shield and Eyebrow panel material with Malte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201.
Removed and Replaced Cockpit Sidewall material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201.
Leather. Removed and replaced Pilot Seat Part Number TABH100PM0001 Serial Number 62, Foam and recovered with Garrett Sheepskin Oak and Excell Cappuccino
Removed and replaced Co-Pilot Seat Part Number TABH100CM00-01 Serial Number 246, Foam and recovered with Garrett Sheepskin Oak and Excell
Cappuccino Leather.
Removed and Replaced Left Hand #4 Passenger Seat Part Number 2524-014(-530A) Serial Number 990719-4 Foam and recovered with Townsend Leather
(Heritage Brown)
Removed and replaced Right Hand #5 Passenger Seat Part Number 2524-014(-530B) Serial Number 990426-7 Foam and recovered with Townsend
Leather(Heritage Brown)
Removed and Replaced Left Hand #6 Passenger Seat Part Number 2524-014(530B)Serlal Number 030618-6 Foam and recovered with Townsend Leather
(Heritage Brown)
Removed and replaced Right Hand #7 Passenger Seat Part Number 2524-014(530A) Serial Number 030708-2 Foam and recovered with Townsend Leather
(Heritage Brown)
THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF REFURBISHMENT:
Skandia Flammability Test S254976 as approved by FAA DER Jane Biberstein (DERY 832780-CE) on FAA form 8110-3 dated 4/23/2013
Flame Out Flammability Test 4311 as approved by FAA DER Herb Reed II (DERT-230293-CE) on FAA Form 8110-3 dated 12/23/2013.
Skandia Flammability Test Report TP 22081 Rev A as approved by FAA DER Jane Biberstein( DERY-832780-CE) on FAA Form 8110-3 dated 05/02/2013
Three Place Divan installation:
Installed (3) place divan part Number 32-0396(A60PT)T123.KO2 S/N 003702 In Accordance with Aviation Fabricators STC# ST01572WI and Skandia Flammibility
test report S254976 per Jane Biberstein FAA DER (DERY-832780-CE) dated 4/23-2013
THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED:
L/H Gally Assy. R/H Galley Assy, Divan Assy. L/H Galley Assy and Install per Delta G drawing DGD-CA01-101 Rev D. DGD-CA01-101 EO E-1, L/H Galley Install
DGD-CA01-501 Rev EO A-1, DGD-CA01-501 Rev IR as approved on FAA form 8110-3 per FAA DER Donald Gillesple (DERT-750136-SW) dated March 25 2013.
R/H Galley Assy and Install per Delta G drawings DGD-CA02-101 Rev B, DGD-CA02-501 Rev IR as approved on FAA form 8110-3 by FAA DER Donald Gillesple
(DERT-750135-SW) dated March 25, 2013. Divan Assy per Delta G drawings DGD-CA09-101 Rev C and DGD-CA09-101 EO D-1 as approved on FAA form
8110-3 per FAA DER Donald Gillesple (DERT 750135-SW) dated March 25, 2013, Bonner Kit Sidewall assy drawing 2553-0038 Rev C, Bonner Sideledge assy
drawing 2532-0002 Rev C, Bonner Kit Foldout Table assy drawings 2553-0041 Rev C and 2553-0040 Rev B, Bonner XTI liner Kit Instl drawing 2553-0037 Rev C
as approved on FAA form 8110-3 per Stephen Forness DERT-230238-CE dated Dec 26, 2013.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS:
THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE THERE ARE NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO
INSPECT IAW MANUFACTURERS AMM, SRM, OR CMM AS APPLICABLE
AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011819

=== Page 152 ===
EFTA00011820

=== Page 153 ===
U.S. DEPARTMENT OF TRANSPORTATION
DATE
FEDERAL AVIATION ADMINISTRATION
Dec 26, 2013
STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
MAKE
MODEL
TYPE (Airplane, Radio, Helicopter,
NAME OF APPLICANT
Beechcraft Corporation
400A
etc.) AIRPLANE
NEXTANT Aerospace
Cleveland OH.
LIST OF DATA
IDENTIFICATION
TITLE
REPORT:
RKG3282
BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION
Rev. IR, 8-28-2013
2553-0037
BEECHJET 400A
Rev C, dated 8-30-2013
XTI LINER KIT INSTL.
Beechjet 400A, Aircraft Serial No. RK-244
Certification Bases for this aircraft modification is per Type Certificate Number A16SW
Revision 28 dated April 12,2013
PURPOSE OF DATA
DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION
ON BEECHJET 400A, AIRCRAFT SERIAL NO. RK-244
APPLICABLE REQUIREMENTS List specific sections)
14 CFR Part 25 $.301, 303, 305, 307a), 365, 561, 571, 601, 603, 605, 609, 613
CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations
of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered
have been examined in accordance with established procedures and found to comply with applicable
requirements of the Federal Aviation Regulations.
I (We) Therefore
Recommend approval of these data
X
Approve these data
SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
DESIGNATION NUMBER(S)
CLASSIFICATION(S)
DERT-230238-CE
STRUCTURES AND
DAMAGE TOLERANCE
FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION
GPO 901-613
EFTA00011821

=== Page 154 ===

=== Page 155 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011823

=== Page 156 ===

=== Page 157 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant
Aerospace Master Drawing List DB1002067. Revision F.05 Dated: October 9, 2013.
Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated
October 17, 2013. Ref. drawing for parts list.
ICA Requirements.
Ref FAA Order 8100.17
Page 7-5 and 7-6
Use FAA publications such as AC 43.13-1, Acceptable Methods, Techniques, and Practices-Aircraft Inspection and Repair,
and AC 43.13-2, Acceptable Methods, Techniques, and Practices-Aircraft Alterations; part 43 appendix D; or other applicable
aviation standards.
Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess Il and ATG 4000 in
Accordance with DB 1001013. Rev E
ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FAA
Accepted Revisions
The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance
activities not covered within this ICA:
Aircell Axxess II Installation Manual D12004 Revision E, dated March 2010 or later applicable revision
Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision
Aircell Axxess Il WLAN AFM Supplement DB1002072 Rev IR dated March 22 2012 for the has been Installed in the AFM
Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013
This is Located under the Seat Divan
ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later
FAA Accepted Revision.
Aircraft Flight Supplement DB1109012 has been installed on the Aircraft
See Current Weight and Balance Dated: December 29, 2013
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011825

=== Page 158 ===

=== Page 159 ===
United States of America
Department of Transportation Federal Abiation Administration
Supplemental Type Certificate
Number ST03960AT
This certificate issued to
Nextant Aerospace LLC
3800 Southern Blvd.
West Palm Beach, FL 33406
certifies that the change in the type design for the following product with the limitations and conditions
therefor as specified herean meets the airworthiness requirements of Tert25 of the Federal Aviation
Regulations.
Criginal Product Type Certificate Number: A16SW
Make:
Hawker Beechcraft Corporation
Model:
400A
Description of Type Design Change:
Installation of Rockwell Collins Venue In-Flight Entertainment(IFE), Aircell Axxess Cabin II Iridium Phone
and High Speed Internet System with Wireless Local Area Network (WLAN) Astronics 115VAC 60HZ
Cabin Inverter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master
Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision.
Bimitations and Conditions: This approval should not be extended to other aircraft of this model on which
other previously approved modifications are incorporated, unless it is determine by the installer that the
interrelationship between this change and any other previously approved modifications will produce no
adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use
this certificate to alter the product, the holder shall give the other person written evidence of that permission.
This certificate and the supporting data which A the basis for approval shull remain in effect until
surrendered. respended receked or to termination date is otherwise established by the Administrator of the
Federal Aviation Administration
Date of application July 28, 2012
Date reissued:
Date of issuance - March 22, 2012
Date amended:
FEDERAL AVIATION
ler
ADMINISTRATION
Manager
Atlanta Aircraft Certification Office
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2(10-68)
PAGE 1 of 2 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011827

=== Page 160 ===
EFTA00011828

=== Page 161 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number
ST03960AT
When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015,
Revision A, dated March 22, 2012, or later FAA approved revision, is required.
When the Aircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision
IR, dated March 22, 2012, or later FAA approved revision, is required.
When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012,
Revision IR, dated March 22, 2012, or later FAA approved revision, is required.
This system is intended to provide internet connection and email services to the airplane's cabin using
portable electronic devices (PEDs). Any other intended function of this equipment will require a re-
examination of the certification basis.
When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1002068, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant
Aerospace Document No. DB1105003, Rev A, dated September 22, 2011, or later FAA accepted revisions
must be made available to the operator at the time of installation.
When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1108018, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
When the Emteq LED Cabin Lighting system is installed Instructions for Continued Airworthiness (ICA),
Nextant Aerospace Document No. DB1108019, Rev IR, dated September 22, 2011, or later FAA accepted
revisions must be made available to the operator at the time of installation.
Any alteration of this certificate is punishable by # fine of not exceeding $1,000, or imprisonment not exceeding J years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 2 of 3 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011829

=== Page 162 ===

=== Page 163 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST03960AT
Certification Basis:
The Certification Basis for this installation is per Type Certificate Data Sheet A16SW original Certification
Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25-40 plus
FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR 25.29, FAR 25.255, and
FAR 25.1353(c)(6) of Amendment 25-42; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46.
In addition the following specified rules amendment levels were used for this installation.
25.571
25.1353(a)(c)
25.1357
25.1431
25.1529
[25-54]
[25-123]
[25-123]
[25-113]
[25-54]
[-] Indicates amendment level
END
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 3 of 3 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00011831

=== Page 164 ===

=== Page 165 ===
Nextant Aerospace LLC
Report No: DB1002067
Revision F.05
West Palm Beach FL 33406
Master Drawing List
Document Number: DB1002067
Revision: F.05 10/18/2013
In-Flight Entertainment
HAWKER BEECHCRAFT 400A Aircraft
FAA STC ST03960AT
Approved By
Date 1-4-2013
Page 1 of 7
EFTA00011833

=== Page 166 ===

=== Page 167 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011835

=== Page 168 ===

=== Page 169 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Upper Aft Baggage Panel Mod
Modified Baggage Ceiling Panel to Accommodate the Engine FADEC wire harness.
1. Fabricated two panel pieces, N251103-001 and N251103-002.
2. Installed N251103-001 to existing baggage compartment structure 128-440095-1 using two screws and install N251103-002
as shown with a trim to fit honeycomb piece fabricated from interiors using potted inserts.
3. Attached honeycomb baggage panel to N251103-001 in upper aft baggage area using three 40S5-21 Camloc quarter- turn
fasteners and 214-16D receptacles. Secured N251203-002 to existing upper aft baggage panel with two Camloc 40S5-21
quarter - turn fasteners and 214-16D receptacles.
See attached FAA Form 8110-3 Signed by DERT-410115-CE
on February 12, 2013 using Nextant Aerospace
Engineering Order EO 029. Rev E Dated February 8, 2013
ICA
Weight change is Negligible.
Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures for this Area
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011837

=== Page 170 ===

=== Page 171 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
February 12, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 029
Upper Aft Baggage Panel Mod.
Rev. E
February 8, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This
approval is only for the engineering data. It indicates the data listed above
demonstrates compliance only with the regulations specified by paragraph and
subparagraph listed below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire alteration.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23],
25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23],
25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32].
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13107-06
Page 1 of 1
EFTA00011839

=== Page 172 ===

=== Page 173 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011841

=== Page 174 ===

=== Page 175 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Installed New Pitot Probes in accordance with STC ST10159SC. Nextant Aerospace Master Drawing List
Document 373-00-0001 Rev CC EO24-11
Removed Pitot Probes Part Number PH1100-MU-R-1
Removed Pitot Probes Part Number PH1100-MU-L-1
Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803
Installed Pitot Probe Part Number PH1100-MUL-EN Serial Number 1728401
Leak Check carried out IAW Beechcraft Aircraft Maintenance Manual Chapter 34-12-00-201.
ICA
Continue with Normal Hawker Beech Maintenance Practices for this Area
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011843

=== Page 176 ===

=== Page 177 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State, OH
X
Certificated Repair Station
Zip 44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to-Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
12/29/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011845

=== Page 178 ===
EFTA00011846

=== Page 179 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Provisions for J9107 in Cockpit Sidewall at FS122.735
Added Mount provisions for J9107 in bracket assy. 45A88588-3 at Flight Station 122.735 provided in Structure
Repair Manual Document 53-20-05-001. Use receptacle MS3470W18.
See attached FAA Form 8110-3 Signed By DERT-410115-CE
Dated December 28, 2012 using
Nextant Aerospace Engineering Order 115-12 Rev C, Dated November 27, 2012 for details.
ICA
Weight change is Negligible.
Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011847

=== Page 180 ===

=== Page 181 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
December 28, 2012
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 115-12
Mount Provisions for J9107.
Rev. C
November 27, 2012
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire alteration.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-
00], 25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H12740-03
Page 1 of 1
EFTA00011849

=== Page 182 ===
FFTA00011850

=== Page 183 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011851

=== Page 184 ===

=== Page 185 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Title: Ice Detector Master Caution / Master Warning Light on Constantly
Re-Installed the previously removed components (Ref S/B 30-2600, Rev 2)
1.) Isolation Relay K255 P/N: 50-380048-1
2.) Diode CR654, P/N: 132408-22
3.) Ground stud GS151A P/N: MS35206-246 (Stud may be marked GS152)
As shown in chapter 30-01-01-01 of AMM.
4.) Wire number corrections on wiring diagram 30-01-01-01 Page 1 correct drawing errors on original
drawing. Inspect, verify and correct wiring per EO corrections on EO page 2
See attached FAA Form 8110-3 signed by Daniel Buzz DERT-230019-CE. Dated 8/13/2012 using Nextant
Aerospace Engineering Order EO 0130 Rev D. Dated 7/18/2012
ICA
Weight and Balance Changes are Negligible
Continue to Use Existing Beechjet 400/400A Maintenance Manuals Inspection Procedure for this Area
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011853

=== Page 186 ===
EFTA00011854

=== Page 187 ===
U.S. DEPARTMENT OF TRANSPORTATION
1, DATE
FEDERAL AVIATION ADMINISTRATION
8-13-2012
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter,
5. NAME OF APPLICANT
awker Beechcraft
400A
etc.)
Nextant Aerospace LLC
S/N RK-244 Only
Airplane
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Nextant Aerospace
Engineering Order
Document 130-12
Ice Detector MC/MW Light On Constantly
dated 7-18-12
Rev. D
END
This approval is for the electrical systems aspects only.
8. PURPOSE OF DATA
Support major alteration to aircraft Hawker Beechcraft 400A RK-244 Only.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR 25.1301(a) (Orig)
Note: Compliance has been found to the amendment levels indicated on Hawker Beechcraft TCDS Revision 26 Part 25 Amendment 25-1
through 25-40 to the above applicable requirements.
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and firnitations of appointment
under 14 CFR Part 183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered N/A have been examined in
accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed.
I (We) Therefore approve these data.
11. SIGNATURE(S) OF DESIGNATER/ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-230019-CE
Systems and Equipment
AA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
GPO 901-613
EFTA00011855

=== Page 188 ===
EFTA00011856

=== Page 189 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip 44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
12/29/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011857

=== Page 190 ===

=== Page 191 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Antenna Repair Patch
After removing the forward lower "L" Band Antenna, Instead of removing the Antenna doubler and filling the
connector hole with a coin patch and installing nut plate plugs P/N. DB1105020-189-25, the antenna repair
doubler P/N. DB104042-001 was installed on the existing antenna doubler and two coin repair patches P/n.
DB1104042-002 were installed, one on top of the other to allow for a flush skin repair. The existing nut plate holes
were filled with 4 screws P/N. AN525-10R7.
See Attached FAA Form 8110-3 signed by DERT-410115-CE
dated August 15, 2012 using Nextant
Aerospace Engineering Order 139-12 Rev C Dated August 03, 2012 for details.
ICA
Weight and Balance change is Negligible.
Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011859

=== Page 192 ===

=== Page 193 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
August 15, 2012
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 139-12
Antenna Repair Patch (L-Band Antenna Moved).
Rev. C
August 3, 2012
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form does not constitute FAA approval of all the engineering data
necessary for substantiation of compliance to necessary requirements for the
entire alteration. The electrical requirements are not included in this approval
and require separate approval.
8. PURPOSE OF DATA: Engineering data in support of FAA STC ST03960AT.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23],
25.365(a)(b)(c)(d)(f)(g)[25-00] 25.562(c)[25-23], 25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00],
25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)[25-23],
and 25.789[25-32].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H12418-02
Page 1 of 1
EFTA00011861

=== Page 194 ===
EFTA00011862

=== Page 195 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011863

=== Page 196 ===

=== Page 197 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Title: Pedestal cover extension Modification
After STC modification of pedestal per 373-94-1000 B, existing pedestal close out tray needs to be extended to cover
appropriate areas. Modification of the close out tray is required. Modify the pedestal close out tray per drawing NX251-
10002.
See attached FAA Form 8110-3 signed by
DERT - 410115-CE. Dated 11/8/2013 using
Nextant Aerospace Engineering Order EO 1018 Rev F. Dated 10/9/2013
ICA
Weight and Balance Changes are Negligible
Continue to Use Existing Beechjet 400/400AMaintenance Manuals Inspection Procedure for this Area
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011865

=== Page 198 ===
EFTA00011866

=== Page 199 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
November 8, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 1018
Pedestal Cover Extension Modification.
Rev. F
October 9, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire alteration.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23],
25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23],
25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13817-04
Page 1 of 1
EFTA00011867

=== Page 200 ===
EFTA00011868

=== Page 201 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011869

=== Page 202 ===
EFTA00011870

=== Page 203 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
DEACTIVATE CLOCKS
For Pilots Clock Deactivation:
1.) Removed PLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load
side wires.
2.) At Radio Junction Box:
a.) disconnected wire W78-19 from 3931J25 PIN R & S.
b.) Spliced wire W78-19 from pin R with 3931J22 wire W71-3 (20) pin D*.
For Co-Pilots Clock Deactivation:
4.) Removed COPLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load
side wires.
5.) At Radio Junction Box:
a.) disconnected wire W78-45 from 3931TB1 3931R3 pin 3.
b.) cap and stowed wire.
c.) Installed jumper from pin 3 to 3931J22 pin F* (splice with wire W71-4 (20))
6.) Tested all WOW interface circuits at #1 & #2 DCU, #1 & #2 DCP,# & #2 PFD,#1 & #2 MFD, DAU, #1 &#2 ADC, #1
& #2 GPS, #1 & #2 FSU, #1 & #2 TDR.
7.) Changed power wiring for ELT from #2 Clock to #2 Audio panel. Disconnected wire from inline fuse ELTFI feed side
and connected to Audio power input 2350P4 pin 8 (spliced with wire W965-019 (20)). Tested ELT.
This removal was electrically approved by
FAA DERT-230019-CE using a FAA 8110-3 Dated
November 15, 2013 Using Nextant Engineering order 1165 Rev B Dated 11/13/2013
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011871

=== Page 204 ===

=== Page 205 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
11-15-2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter,
5. NAME OF APPLICANT
Hawker Beechcraft
400A
etc.)
Nextant Aerospace LLC
S/N RK-244 Only
Airplane
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Nextant Aerospace
Engineering Order
Document EO 1165
Deactivate Clocks
dated 11-13-13
Rev. B
END
This approval is for the electrical systems aspects only.
8. PURPOSE OF DATA
Support major alteration to aircraft Hawker Beechcraft 400A RK-244 Only.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR 25.1301(a) [Orig]
Note: Compliance has been found to the amendment levels indicated on Hawker Beechcraft 400A TCDS Revision 26 Part 25 Amendment 25-
1 through 25-40 to the above applicable requirements.
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment
under 14 CFR Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered N/A have been examined in
accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed.
I (We) Therefore approve these data.
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-230019-CE
Systems and Equipment
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
GPO 901-613
EFTA00011873

=== Page 206 ===
EFTA00011874

=== Page 207 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Inspector
Manufacturer
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011875

=== Page 208 ===

=== Page 209 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
TITLE: Aircraft Windshield Sealing Process Deviation:
Allow Deviation from AMM 56-10-00-201 for the sealing of the aircraft windshield process.
Temporary fasteners are not necessary during the sealing of the windshield. Original & typical bolts for installation
may be used during the process, to keep retainers and shims in place during the entire sealing & installation of
the windshield.
After proper sealing time had elapsed, torqued bolts for installation of windshield per AMM.
See attached FAA Form 8110-3 Signed By DERT-410115-CE
Dated June 12, 2013 using Nextant
Aerospace Engineering Order 1257, Rev. A, Dated May 21, 2013 for details.
ICA
Weight change is Negligible.
Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011877

=== Page 210 ===
EFTA00011878

=== Page 211 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
June 12, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 1257
Aircraft Windshield Sealing Process Deviation.
Rev. A
May 21, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire repair.
8. PURPOSE OF DATA: Engineering data in support of major repair to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-
00], 25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13367-01
Page 1 of 1
EFTA00011879

=== Page 212 ===
EFTA00011880

=== Page 213 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
X
Certificated Repair Station
Zip 44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
2/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
2/29/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011881

=== Page 214 ===

=== Page 215 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Requested for use of new processes & materials for the removal and installation of Main & Side Windscreen,
deviation from HBC AMM
When performing the removal and installation of the windscreen and/or cockpit side windows, the following
deviations from the HBC AMM are allowed & recommended:
1. During the removal & installation of the main windscreen, reference FO-AMMS document, chapter 56-10-01
for the main windscreen installation using AVDEC materials. This document correctly defines the processes and
materials to be used for the removal and installation of the main windscreen.
2. During the removal and installation of the cockpit side windows, reference Flight Options FO-AMMS
Document, chapter 56-10-10 & 56-10-11 for the replacement of the side window inner rubber gasket. This
document correctly defines the processes and materials to be used for the replacement of the cockpit side
windows inner rubber gasket.
NOTE: TG8498 & HT3935-7 may not be used on exterior surfaces unless sealant is to be painted after curing for
protection against UV light. PERMISSIBLE TO PAINT OUTER WINDSHIELD RETAINER WITH Chevron White JET
GLO, CM0570513 (Sherwin-Williams)
This Alteration was FAA Approved by
FAA DERT-410115-CE using an FAA Form 8110-3 dated
December 28, 2013. Using Nextant Aerospace Engineering Order 1303 Rev B Dated November 13, 2013
ICA
Continue with Normal Hawker Beech Maintenance manual Inspection Requirements for this Area
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011883

=== Page 216 ===

=== Page 217 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
December 28, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 1303
Process & Material Deviation for the Removal and Installation of the Main & Side
Rev. B
Windscreens.
November 13, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This
approval is only for the engineering data. It indicates the data listed above
demonstrates compliance only with the regulations specified by paragraph and
subparagraph listed below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire alteration.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23],
25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23],
25.613(a)(b)(c)(25-00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32].
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13949-01
Page 1'of 1
EFTA00011885

=== Page 218 ===

=== Page 219 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Manufacturer
Inspector
Maintenance Organization
Person Approved by Canadian
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011887

=== Page 220 ===
EFTA00011888

=== Page 221 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Title : Replace MD-302 with Round Style Standby Gauges
Aircraft with MD302 digit SAM instruments must be reverted back to using round standby gauges until
issues are resolved.
Modified Instrument Panel (373-92-4110-14) to allow the installation of the original round standby
gauges per drawing NX311-10007-03 Rev A
Fabricated round indictor subpanel per drawing NX311-10007-01 Rev B
Installed instruments into subpanel and install subpanel into main instrument panel per drawing
NX311-10007.
See Attached 8110-3 DERT 410115-CE
dated November 8, 2013 per Nextant Aerospace
EO 1543 Rev D dated October 23, 2013
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011889

=== Page 222 ===

=== Page 223 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
November 8, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 1543
Replace MD-302 With Round Style Gauges.
Rev. D
October 23, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form does not constitute FAA approval of all the engineering data
necessary for substantiation of compliance to necessary requirements for the
entire alteration. The electrical requirements are not included in this approval
and require separate approval.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23],
25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23],
25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13818-01
Page 1 of 1
EFTA00011891

=== Page 224 ===

=== Page 225 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State. OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
12/29/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00011893

=== Page 226 ===

=== Page 227 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Spoiler Linkage Closeout Modification
Modified the Cockpit Floor Close out Panels Part Number: LH 45A30839-7 (Pilots) and
Part Number: RH 45A30839-7 (Co-Pilots) Installed Nextant Aerospace Closeout Panel Part Number NX532-
1004-1 between these Panels to allow room for the New Throttle Quadrant to fit under the Center Pedestal
This Alteration was FAA Approved by
FAA DERT-410114-CE using a FAA 8110-3 Dated December
28, 2013 using Nextant Aerospace Engineering Order 1563 Rev. B Dated December 24, 2013
ICA
Continue with Normal Hawker Beech Maintenance Manual Inspection Requirements for this Area
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00011895

=== Page 228 ===

=== Page 229 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
December 28, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
EO 1563
Spoileron Linkage Closeout Modification.
Rev. B
December 24, 2013
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire alteration.
8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-
00], 25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION . Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13950-01
Page 1 of 1
EFTA00011897

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=== Page 231 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
12/29/2013
App. B
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Manufacturer
Person Approved by Canadian
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
12/29/2013
FAA Form 337 (10-06)
EFTA00011899

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=== Page 233 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/29/2013
Nationality and Registration Mark
Date
Nextant Aerospace Carried out a Repair to the Horizontal Stabilizer Ribs
Using Nextant Aerospace Kit Part Number NXK-128-6200 Rev B. Dated July16. 2012.
The following Ribs were replaced.
NXR-45A21112-007
Rib - H Stab Cant STA 13.779.
NXR-45A21113-007
Rib - H Stab Cant STA 29.921.
NXR-45A21101-021
Rib - H Stab Cant STA 46.063.
NXR-45A21116-007
Rib - H Stab Cant STA 62.205
NXR-45A21117-007
Rib - H Stab Cant STA 78.346
The following Ribs were not Replaced as there was not Damaged.
NXR128-620020-001
NXR128-620020-002
This Kit was FAA Approved by
DER-T 410115-CE Structures on an FAA 8110-3. Dated June
12, 2013. Using Nextant Aerospace Engineering Drawing NXR-128-6200 Rev B Dated July 16.2012
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
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=== Page 235 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
June 12, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
NXR-128-6200
Kit - Horizontal Stabilizer Rib Replacement Installation Instructions.
Rev. B
July 16, 2012
NXR-45A21112-007
Rib - H Stab Cant STA 13.779.
Rev. C
July 13, 2012
NXR-45A21113-007
Rib - H Stab Cant STA 29.921.
Rev. B
July 13, 2012
NXR-45A21114-007
Rib - H Stab Cant STA 46.063.
Rev. B
July 13, 2012
NXR-45A21115-007
Rib - H Stab Cant STA 46.063.
Rev. C
July 13, 2012
NXR-45A21101-021
Rib Assy - H Stab Cant STA 46.063.
Rev. A
July 19, 2012
NXR-45A21116-007
Rib - H Stab Cant STA 62.205.
Rev. B
July 13, 2012
NXR-45A21117-007
Rib - H Stab Cant STA 78.346.
Rev. B
July 13, 2012
8. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on
Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-
00], 25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered 2 have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13370-01
Page 1 of 2
EFTA00011903

=== Page 236 ===

=== Page 237 ===
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
June 12, 2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Aircraft, Engine, Propeller, etc.)
5. NAME OF APPLICANT
Hawker Beechcraft
400A
Aircraft
Nextant Aerospace LLC
Corporation
Richmond Heights, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
END
Notes:
1) The structural aspects only of the above listed data are approved herein. This approval
is only for the engineering data. It indicates the data listed above demonstrates
compliance only with the regulations specified by paragraph and subparagraph listed
below as "Applicable Requirements."
2) This form constitutes FAA approval of all the engineering data necessary for
substantiation of compliance to necessary requirements for the entire repair.
8. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on
Hawker Beechcraft 400A, S/N RK-244.
9. APPLICABLE REQUIREMENTS (List specific sections)
CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.601[25-00],
25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25-
00], 25.619[25-23], and 25.625(a)(b)(c)[25-23].
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered 3 have been examined in accordance with established procedures and found to comply with
applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-410115-CE
Structures
FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number: H13370-01
Page 2 of 2
EFTA00011905

=== Page 238 ===

=== Page 239 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
N493LX
RK244
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
Flight Options, LLC
2. Owner
Address
City Richmond Heights
StateOhio
tip44143-1453
CountryUSA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
NameConstant Aviation
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
cityCleveland
StateOhio
X
Certificated Repair Station
CRS#WC7R346J
Zip44135
CountryUnited States
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
Date: December 30, 2013
App. B
to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date 0
Designation No.
Date: December 30, 2013
CRS#WC7R346J
FAA Form 337 (10-06)
EFTA00011907

=== Page 240 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
12/30/2013
Nationality and Registration Mark
Date
ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION
THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED:
Repainted, recovered control columns with Matte Black Leather Accordance with Beechjet 400A AMM 20-70-00-701, 25-00-00-001
Removed and Replaced Glare shield and Eyebrow panel material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201
Removed and Replaced Cockpit Sidewall material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201
Removed and replaced Pilot Seat Part Number TABH100PM0001 Serial Number 62, Foam and recovered with Garrett Sheepskin Oak and Excell Cappuccino
Leather.
Removed and replaced Co-Pilot Seat Part Number TABH100CM00-01 Serial Number 246, Foam and recovered with Garrett Sheepskin Oak and Excell
Cappuccino Leather.
Removed and Replaced Left Hand #4 Passenger Seat Part Number 2524-014(-530A) Serial Number 990719-4 Foam and recovered with Townsend Leather
(Heritage Brown)
Removed and replaced Right Hand #5 Passenger Seat Part Number 2524-014(-530B) Serial Number 990426-7 Foam and recovered with Townsend
Leather(Heritage Brown)
Removed and Replaced Left Hand #6 Passenger Seat Part Number 2524-014(530B)Seria Number 030618-6 Foam and recovered with Townsend Leather
(Heritage Brown)
Removed and replaced Right Hand #7 Passenger Seat Part Number 2524-014(530A) Serial Number 030708-2 Foam and recovered with Townsend Leather
(Heritage Brown)
THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF REFURBISHMENT:
Skandia Flammability Test S254976 as approved by FAA DER Jane Biberstein (DERY 832780-CE) on FAA form 8110-3 dated 4/23/2013
Flame Out Flammability Test 4311 as approved by FAA DER Herb Reed II (DERT-230293-CE) on FAA Form 8110-3 dated 12/23/2013
Skandia Flammability Test Report TP 22681 Rev A as approved by FAA DER Jane Biberstein( DERY-832780-CE) on FAA Form 8110-3 dated 05/02/2013.
Three Place Divan installation:
Installed (3) place divan part Number 32-0396(A60PT)T123.KO2 S/N 003702 In Accordance with Aviation Fabricators STC# ST01572WI and Skandia Flammibility
test report S254976 per Jane Biberstein FAA DER (DERY-832780-CE) dated 4/23-2013
THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED:
L/H Gally Assy, R/H Galley Assy, Divan Assy. L/H Galley Assy and Install per Delta G drawing DGD-CA01-101 Rev D, DGD-CA01-101 EO E-1, L/H Galley Install
DGD-CA01-501 Rev EO A-1, DGD-CA01-501 Rev IR as approved on FAA form 8110-3 per FAA DER Donald Gillespie (DERT-750135-SW) dated March 25 2013.
R/H Galley Assy and Install per Delta G drawings DGD-CA02-101 Rev B, DGD-CA02-501 Rev IR as approved on FAA form 8110-3 by FAA DER Donald Gillespie
(DERT-750135-SW) dated March 25, 2013. Divan Assy per Delta G drawings DGD-CA09-101 Rev C and DGD-CA09-101 EO D-1 as approved on FAA form
8110-3 per FAA DER Donald Gillespie (DERT 750135-SW) dated March 25, 2013, Bonner Kit Sidewall assy drawing 2553-0036 Rev C, Bonner Sideledge assy
drawing 2532-0002 Rev C, Bonner Kit Foldout Table assy drawings 2553-0041 Rev C and 2553-0040 Rev B, Bonner XTI liner Kit Instl drawing 2553-0037 Rev C
as approved on FAA form 8110-3 per Stephen Forness DERT-230238-CE dated Dec 26, 2013.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS:
THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE THERE ARE NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO
INSPECT IAW MANUFACTURERS AMM, SRM, OR CMM AS APPLICABLE
AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
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=== Page 241 ===
U.S. DEPARTMENT OF TRANSPORTATION
DATE
FEDERAL AVIATION ADMINISTRATION
Dec 26, 2013
STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
MAKE
MODEL
TYPE (Airplane, Radio, Helicopter,
NAME OF APPLICANT
Beechcraft Corporation
400A
etc.) AIRPLANE
NEXTANT Aerospace
Cleveland OH.
LIST OF DATA
IDENTIFICATION
TITLE
REPORT:
RKG3282
BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION
Rev. IR, 8-28-2013
2553-0037
BEECHJET 400A
Rev C, dated 8-30-2013
XTI LINER KIT INSTL.
Beechjet 400A, Aircraft Serial No. RK-244
Certification Bases for this aircraft modification is per Type Certificate Number A16SW
Revision 28 dated April 12,2013
PURPOSE OF DATA
DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION
ON BEECHJET 400A, AIRCRAFT SERIAL NO. RK-244
APPLICABLE REQUIREMENTS ( List specific sections)
14 CFR Part 25 $.301, 303, 305, 307a), 365, 561, 571, 601, 603, 605, 609, 613
CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations
of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered
have been examined in accordance with established procedures and found to comply with applicable
requirements of the Federal Aviation Regulations.
I (343) Therefore
Recommend approval of these data
X
Approve these data
SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
DESIGNATION NUMBER(S)
CLASSIFICATION(S)
DERT-230238-CE
STRUCTURES AND
DAMAGE TOLERANCE
FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION
GPO 901-613
EFTA00011909

=== Page 242 ===
---

=== Page 243 ===
LEE
products engineering
services, inc.
Wichita Kansas 67216
STRUCTURAL ANALYSIS REPORT
Forward Calley Cabinet Modifications
- Beechcraft Model 400A, RK-244 & RK-305
Document No: 313-ST-001
Revision IR
PREPARED BY:
Date: December 24, 2013
APPROVED BY:
APPROVED BY:
Manager - Design Engineering
President
THIS DOCUMENT CONTAINS INFORMATION OF A PROPRIETARY NATURE AND SHALL NOT BE
TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT THE EXPRESS WRITTEN PERMISSION
OF LEE PRODUCTS ENGINEERING SERVICES, INC. ADDITIONALLY, USE OF THE INFORMATION IS
PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY LEE PRODUCTS ENGINEERING SERVICES, INC.
EFTA00011911

=== Page 244 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE ii
REVISION RECORD
Revision
Date
Description
Approval
IR
12/24/13
Initial Release
See Cover Sheet
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=== Page 245 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE iii
TABLE OF CONTENTS
1. INTRODUCTION
1
2. REFERENCES
2
2.1 CONSTANT AVIATION DRAWINGS
2
2.2 APPLICABLE SUPPLIER DRAWINGS (AVIATION FABRICATORS)
2
2.3 APPLICABLE LPESI REPORTS
2
2.4 APPLICABLE GOVERNMENT DOCUMENTS
2
3. CERTIFICATION BASIS
2
4. DESCRIPTION
3
4.1 GENERAL
3
4.2 RH FORWARD GALLEY ASSY & INSTL
3
4.3 RH FORWARD DIVAN MODIFICATION
4
4.4 LH FORWARD GALLEY ASSY & INSTL
5
4.5 LH AFT LAVATORY EXTENSION
7
5. STRUCTURAL SUBSTANTIATION
7
5.1 LH FORWARD GALLEY ASSY & INSTL
7
6. CONCLUSION
8
APPENDIX A
A.1
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=== Page 246 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 1
1. INTRODUCTION
The purpose of this report is to demonstrate the structural substantiation to
applicable 14 CFR Part 25 regulations as they relate to the installation and
modification of various interior cabinets on Beechcraft Model 400A, S/N's RK-
244 and RK-305, for a FAA Form 337 major alteration, performed by Constant
Aviation at their Cleveland, OH facility.
The installations consist of the replacement of new RH and LH forward galleys,
and modification to the existing closet frame, an extension of the aft lavatory,
and a modification to the side-facing divan with the manufacturer's approval.
Everything except the new LH forward galley has been accomplished on a
previous modification as documented in LPESI Report 222-ST-001. Therefore,
only the new galley will be discussed and analyzed in this report. The floorplan
for the two (2) Beechcraft Model 400A aircraft is as shown below.
STA
STA
STA
STA
STA
STA
156.1
176.1
196.1
223.8
247.8
271.8
EXIT
14/26
-
001
100
GALLEY
CLOSET
LAV
GALLEY
EXIT
8
8
STA
STA
STA
STA
STA
STA
STA
STA
STA
137.05
150.60
166.14
181.30
196.48
212.00
240.75
208.70
295.67
Figure 1-1 - Floorplan
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=== Page 247 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 2
2. REFERENCES
2.1 Constant Aviation Drawings
Drawing No.
Rev.
Title
NXT0213-01
IR
LH Galley Assembly
NXT0213-02
IR
LH Galley Installation
NXT0213-05
IR
Weight Placard Installation
NXT0313-01
IR
RH Galley Assembly
NXT0313-02
IR
RH Galley Installation
NXT0313-03
IR
Divan Assembly
NXT0313-07
IR
4" Lav Ext
2.2 Applicable Supplier Drawings (Aviation Fabricators)
Drawing No.
Rev.
Title
D-10666
A
3 Place Divan Installation (STC ST01572WI)
2.3 Applicable LPESI Reports
Drawing No.
Rev.
Title
Miscellaneous Cabinet Modifications - Beechcraft
222-ST-001
B
Model 400A
2.4 Applicable Government Documents
Document
Rev
Title
14 CFR Part 25
See
Airworthiness Standards: Transport Category
Sect. 3
Airplanes
ANM-115-09-017
1/28/10
Interaction of Interior Structures, Including Seats
3. CERTIFICATION BASIS
The Beechcraft Model 400A certification basis is defined Type Certificate Data
Sheet (TCDS) A16SW, Rev. 28, the Certification Basis is 14 CFR Part 25 dated
February 1, 1965, including Amendments 25-1 through 25-40. The individual
14 CFR Part 25 subparagraphs that will be discussed herein are:
25.301(a)(b)(c) Loads (Amdt. 25-23)
25.303
Factors of Safety (Amdt. 25-23)
25.305(a)(b)
Strength and Deformation (25-23)
25.307(a)
Proof of Structure (Amdt. 25-23)
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Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 3
25.341(c)
Gust Loads (No Amdt.)
25.561(a)(b)(c)
Emergency Landing Loads - General (Amdt 25-23)
25.601
Design and Construction - General (No Amdt.)
25.603(a)(b)
Materials and Workmanship (Amdt. 25-38)
25.605
Fabrication Methods (No Amdt.)
25.607(a)(b)
Fasteners (Amdt. 25-23)
25.609(a)(b)
Protection of Structure (No Amdt.)
25.613(a-e)
Materials Strength Properties (No Amdt.)
25.625(a)(b)(c)
Fitting Factors (Amdt. 25-23)
25.787(a)(b)
Stowage Compartments (Amdt. 25-38)
25.789
Retention of Items of Mass (Amdt. 25-32)
4. DESCRIPTION
4.1 General
The modification of the Model 400A aircraft consists of replacing the existing
RH and LH forward cabinets with new assemblies, modifying the RH forward 3-
place side-facing divan by refurbing the divan, and modifying the existing LH
aft lavatory cabinet by extending its cabinet structure to close out the area
around it. All but the new LH galley are previously installed and certified on
previous 400A aircraft, and analyzed in LPESI Report 222-ST-001.
4.2 RH Forward Galley Assy & Instl
The NXT0313-01 RH forward galley assembly (installed per NXT0313-02) is
the same as that previously installed on other Model 400A aircraft. An
illustration of the galley in Figure 4-1.
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Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 4
Figure 4-1 - RH Forward GalleyAssy
(Contact Pad on Upper Area Not Shown)
The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP-
501F2 Nomex/fiberglass composite panels from AAR Composites, and
fabricated using ATR panel pin construction.
The RH forward galley is installed between the existing RH forward structural
partition (which separates the flight deck with the cabin) forward of it and the
3-place side-facing divan immediately aft of it. The lower wider section of the
cabinet also encloses the aircraft's air conditioning evaporator mounted
separately to the floor structure underneath.
4.3 RH Forward Divan Modification
The NXT0313-03 3-place side-facing divan assembly consists of new drawer and
fascia door panels onto the existing structural divan frame (Aviation Fabricators
D-10666 STC'd Installation Kit - STC ST01572WI). It has also been installed in
previous Model 400A aircraft, and analyzed in LPESI Report 222-ST-001. An
illustration of the divan assembly is provided in Figure 4-2.
EFTA00011917

=== Page 250 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 5
Figure 4-2 - RH Forward Divan Mod
The divan closeout panels are manufactured from strong lightweight 0.50-
inch thick ATR-FP-501F2 Nomex/fiberglass composite panels from AAR
Composites, and fabricated using ATR panel pin construction.
The STC'd divan frame installation consists of a structural frame (bottom
only - no seat backs, cushions form the divan backs), restraint systems
consisting of lap belts and shoulder harnesses for all three (3) seated
positions, and a D-106699 floorboard modification installation underneath
the divan. The frame installed in eight (8) places into the existing cabinet
"Brownline" seat track extrusions (inboard and outboard).
4.4 LH Forward Galley Assy & instl
The NXT0213-01 LH forward galley assembly is a traditional aircraft galley
and is located between the flight deck and the entry door, directly aft of the
existing LH forward structural partition (bulkhead). The new galley
replaces an existing galley of similar design and the same size. In fact, this
new galley assembly is the same as previously installed in other Model
400A aircraft, and analyzed in LPESI Report 222-ST-001, except for a
minor change to the upper forward portion of the cabinet. As can be seen
in a comparison of the galley illustrations below and Fig. 4-3 of 222-ST-
001, the change consists of eliminating the small recessed condiment tray
drawer and extending (down) the existing compartment to compensate.
The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP-
501F2 Nomex/fiberglass composite panels from AAR Composites, and
fabricated using ATR panel pin construction.
An illustration of the LH forward galley is provided in Figure 4-3.
EFTA00011918

=== Page 251 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 6
B
9
B
B
1
E
Figure 4-3 - LH Forward Galley Assy
The LH forward galley is installed per NXT0213-02 and is installed utilizing
the same existing installation attachments - five (5) screw/insert
attachments into the existing partition and four (4) floor attachments (2
into the existing seat track and 2 into existing floorboard mounts, and is
the same as the previous NXT0313-05 installation analyzed in LPESI Report
222-ST-001.
The empty cabinet weights 86.15 pounds (less than the 90.61 pound galley
analyzed in LPESI Report 222-ST-001) and the total placarded content
weight (Ref. NXT0213-05) of 141.0 pounds (only 1.0 pound more than the
222-ST-001 analyzed galley). Therefore, the total installation weight of the
NXT0213-02 galley is 3.46 pounds lighter than that analyzed in LPESI
Report 222-ST-001, and is therefore structurally substantiated by
comparison.
EFTA00011919

=== Page 252 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 7
4.5 LH Aft Lavatory Extension
The NXT0313-07 LH aft lavatory modification consists of augmenting the
toilet cabinet with new panels and compartments between the existing
cabinet and the RH aft partition. An illustration of the modification to
the aft lavatory is shown in Figure 4-4 (new components in gray).
New
New
flew
New
New
New
New
FWD
Figure 4-4 - LH Aft Lavatory Extension
This is the same as previously analyzed in LPESI Report 222-ST-001.
5. STRUCTURAL SUBSTANTIATION
The structural analysis will be generated using traditional means based on
conservative assumptions.
In determining the Margin of Safety (MS), the resulting analytical result will be
subtracted from 1.0 so that any MS greater than 0.0 is considered a positive
margin. Also, MS's greater than 3.0 will be listed as +Ample".
5.1 LH Forward Galley Assy & Instl
The critical loadings for the LH forward galley are the 9.0g forward and 3.5g
side load conditions. However, since the new galley weighs 3.5 pounds less
than the previously analyzed galley, is of similar shape and design, includes
that same installed equipment, and utilizing the same aircraft attachment
points, the new galley assembly and installation is therefore structural
substantiated by comparison.
EFTA00011920

=== Page 253 ===
Lee Products Engineering Services, Inc.
313-ST-001
REV. IR
STRUCTURAL ANALYSIS REPORT
PAGE 8
The largest placarded drawer is the top, center drawer in the lower section of
the galley, which is placarded for 45.0 pounds. The drawer is restrained by a
standard Actron paddle latch, P/N A23511-1S. The applied load to the latch is
(the drawer itself + hardware is 5.0 pounds):
Applied Load = (5.0 lbs + 45.0 lbs) X 3.5g X 1.15ff = 201.3 pounds
The minimum load rating for the A23511 paddle latch by its manufacturer is
225.0 pounds. The resulting margin of safety is:
M.S. = 225.0 lbs / 201.3 lbs) - 1.0 = +0.12
6. CONCLUSION
Based on the above structural analysis, the new cabinets and modification and
their installations, listed in Sect. 2.1, into the aircraft have been shown to be
compliant with the applicable 14 CFR Part 25 regulations, as defined in Sect. 3
with positive margins of safety.
EFTA00011921

=== Page 254 ===
4
3
2
1
REVISIONS
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DESCRIPTION
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AG THEM INC. AND SUBMITTED UNDER COMPIDENTIAL
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DATE
RELATIONSHIP, EXCEPT FOR USES EXPRESSA Y GRANTED IN WRIT-
INC. ALL RIGHTS ARE RESERVED BY ACTRON MFG. NO
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STRUCTURAL ANALYSIS REPORT
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Lee Products Engineering Services, Inc.
COLT PROJECTION
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313-ST-001
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EFTA00011922

=== Page 255 ===
U. S. DEPARTMENT OF TRANSPORTATION
1.DATE
FEDERAL AVIATION ADMINISTRATION
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
4/23/2013
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2.MAKE
3.MODEL NO.
4.TYPE(Airplane, Engine. Propeller, etc.)
5.NAME OF APPLICANT
Raytheon
400A
Airplane
Constant Aviation-CLM
LIST OF DATA
6.IDENTIFICATION
ZTITLE
Design Data S254976
Skandia, Inc. Flammability Test Results
Rev NC
Bunsen Burner Testing
Test Specimen P/N's Cont.
25 (represents main entry door trim)
27 (represents upper med surround)
28 (represents lower med, lower med surround, Ih aft blkhd)
29 (represents pax seat back shrouds, arms, crash pad)
30 (represents seat shrouds)
31 (represents entry steps, cockpit ped step)
33 (represents cntrl column boots, rudder boots)
34 (represents ckpt defog vent closeout)
35 (represents table shrouds)
36 (represents dado and aircell closeout)
39 (represents crew seats)
Notes:
1) Work accomplished under Skandia Inc. wo # 254976-13, Ref Document ID 93650.
2) Flammability test witnessing only, does not constitute installation approval of materials.
3) IAW Skandia Flammability Streamline Testing Test Plan 21306, Rev IR, Dated 11/03/11
Page 2
8,PURPOSE OF DATA
Demonstration of compliance with material flammability requirements for S/N RK-244
.APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Rart 25.853 (a) Amdt 25-116 Appendix F Part I (a)(1)(i) Amdt 25-111
14 CFR Part 25,853 (a) Amdt 25-116 Appendix F Part I (a)(1)(ii)
14 CFR Part 25.855 Amdt 25-116 Appendix F Part I (6)
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations
of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered -2
have been
examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness
Standards listed.
I (We) Therefore
Recommend approval of these data
Approve these data
11, SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE
DESIGNATION NUMBER(S)
13.CLASSIFICATION(S)
DERY-832780-CE
Structural Special
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011923

=== Page 256 ===
EFTA00011924

=== Page 257 ===
13DLG-CON-0325D
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
March 25, 2013
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter, etc.)
5. NAME OF APPLICANT
Beechjet
400A
AIRPLANE
Constant Aviation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Document No.
DGD-CA08-501 REV: IR
ARMREST RH INSTL
Dated: 6/13/12
DGD-CA09-101 REV: C
DIVAN ASSY
Dated: 1/25/13
DGD-CA09-101 EO: D-1
DIVAN ASSY
Dated: 2/28/13
DGD-CA13-101 REV: IR
CARD TABLE ASSY
Dated: 2/28/13
DGD-CA14-101 REV: IR
LAV CLOSET FRAME MOD
Dated: 1/31/13
End of Data
NOTES:
1.
This approval is for Beechjet model 400A (Nextant 400XT varlant) S/N RK-244 only.
2.
This approval is for the structural design aspects only on the above listed data and
does not constitute an Installation approval.
3.
Approval is only for regulations specified in the "Applicable Requirements" block.
Compliance with additional regulations not listed herein may be required. This form
does not constitute FAA approval of all engineering design data for the entire
alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance,
Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other
disciplines.
4.
For certification basis, refer to TC data sheet No. A16SW
5.
Structural Approvals are provided separately.
8. PURPOSE OF DATA
To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval
is for design data only on a major alteration and is not an Installation approval.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (a)(b)(c) Amdt
25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(b)(c)(d)(e)(f) Amdt 25-32, 25.789 Amdt 25-32
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply
with applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S)OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-750135-SW
STRUCTURAL
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011925

=== Page 258 ===

=== Page 259 ===
13DLG-CON-0325E
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
March 25, 2013
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter, etc.)
5. NAME OF APPLICANT
Beechjet
400A
AIRPLANE
Constant Aviation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Document No.
DGD-CA01-SS-07
SUBSTANTIATION ANALYSIS of the Interior on an Hawker Beechcraft 400A Aircraft
REV: IR
Dated: 3/6/13
End of Data
NOTES:
1.
This approval is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only.
2.
This approval is for the structural design aspects only on the above listed data and
does not constitute an installation approval.
3.
Approval is only for regulations specified In the "Applicable Requirements" block.
Compliance with additional regulations not listed herein may be required. This form
does not constitute FAA approval of all engineering design data for the entire
alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance,
Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other
disciplines.
4.
For certification basis, refer to TC data sheet No. A16SW
B. PURPOSE OF DATA
Structural substantiation in support of FAA Form 337 for aircraft S/N RK-244. This approval is for design data only
on a major alteration and is not an installation approval.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Part 25.301[Amdt. 25-23], 303|Amdt. 25-23], 305(a)(b)[Amdt. 25-23], .307[Amdt 25-23], 341[Amdt. 25-0], .561|Amdt. 25-23],
.601[Amdt. 25-0], .603(a)(b)[Amdt. 25-38], .605|Amdt. 25-0], .609[Amdt. 25-0], .611[Amdt. 25-23], .613(a)(b)(c)[Amdt. 25-0], .625 [Amdt. 25-
23], .785(a)(b)(c)(d)(e)(f)|Amdt. 25-32), .787(a)[Amdt 25-32], .789[Amdt. 25-32]
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply
with applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(SLOF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-750135-SW
STRUCTURAL
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011927

=== Page 260 ===

=== Page 261 ===
13DLG-CON-0325B
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
March 25, 2013
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter, etc.)
5. NAME OF APPLICANT
Beechjet
400A
AIRPLANE
Constant Aviation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Document No.
DGD-CA02-101 REV: B
RH GALLEY ASSY
Dated: 1/25/13
DGD-CA02-501 REV: IR
RH GALLEY INSTL
Dated: 6/13/12
DGD-CA13-501 REV: IR
CARD TABLE INSTL
Dated: 12/21/12
DGD-CA13-501 EO: A-1
CARD TABLE INSTL
Dated: 2/28/12
DGD-CA04-101 REV: IR
SIDE LEDGE ASSY
Dated: 6/13/12
End of Data
NOTES:
1.
This approval is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only.
2.
This approval is for the structural design aspects only on the above listed data and
does not constitute an Installation approval.
3.
Approval Is only for regulations specified in the "Applicable Requirements" block.
Compliance with additional regulations not listed herein may be required. This form
does not constitute FAA approval of all engineering design data for the entire
alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance,
Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other
disciplines.
4.
For certification basis, refer to TC data sheet No. A16SW
5.
Structural Approvals are provided separately.
8. PURPOSE OF DATA
To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval
is for design data only on a major alteration and is not an Installation approval.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (a)(b)(c) Amdt
25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(b)(c)(d)(e)(f) Amdt 25-32, 25.789 Amdt 25-32
10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183. data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply
with applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S OE DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-750135-SW
STRUCTURAL
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011929

=== Page 262 ===

=== Page 263 ===
13DLG-CON-0325A
U.S. DEPARTMENT OF TRANSPORTATION
1. DATE
FEDERAL AVIATION ADMINISTRATION
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
March 25, 2013
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE
3. MODEL NO.
4. TYPE (Airplane, Radio, Helicopter, ofc.)
5. NAME OF APPLICANT
Beechjet
400A
AIRPLANE
Constant Aviation
Cleveland, Ohio
LIST OF DATA
6. IDENTIFICATION
7. TITLE
Document No.
DGD-CA01-101 REV: D
LH GALLEY ASSY
Dated: 3/5/13
DGD-CA01-101 EO: E-1
LH GALLEY ASSY
Dated: 3/6/13
DGD-CA01-501 REV: IR
LH GALLEY INSTL
Dated: 6/13/12
DGD-CA01-501 EO: A-1
LH GALLEY INSTL
Dated: 1/29/13
DGD-CA01-501 EO: A-2
LH GALLEY INSTL
Dated: 3/5/13
End of Data
NOTES:
1.
This approval is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only.
2.
This approval is for the structural design aspects only on the above listed data and
does not constitute an Installation approval.
3.
Approval is only for regulations specified in the "Applicable Requirements" block.
Compliance with additional regulations not listed herein may be required. This form
does not constitute FAA approval of all engineering design data for the entire
alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance,
Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other
disciplines.
4.
For certification basis, refer to TC data sheet No. A16SW
5.
Structural Approvals are provided separately.
8. PURPOSE OF DATA
To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval
is for design data only on a major alteration and is not an installation approval.
9. APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (a)(b)(c) Amdt
25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(b)(c)(d)(e)(f) Amdt 25-32, 25.789 Amdt 25-32
10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR
Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply
with applicable requirements of the Airworthiness Standards Listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11-SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
12. DESIGNATION NUMBERS(S)
13. CLASSIFICATION(S)
DERT-750135-SW
STRUCTURAL
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011931

=== Page 264 ===

=== Page 265 ===
Aviation Fabricators, Inc.
Clinton, Missouri 64735
Report # AF-475FTP
August 09, 2010
Rev (A)
Functional Test Procedure
for STC # ST01572WI
Hawker Beechcraft Cabin Configuration
Applicable Aircraft Model:
Hawker Beechcraft 400, 400A
EFTA00011933

=== Page 266 ===
Aviation Fabricators, Inc.
AF-475FTP
08-09-10
Clinton, Missouri 64735
Rev (A)
Page 2 of 4
Revision Log
Date
Rev
Pages
Description
Approved by
08-09-10
A
1
-Added model 400A
G.R. Lowe III
-Changed data list # to AF-475MDL
EFTA00011934

=== Page 267 ===
Aviation Fabricators Inc.
Clinton, MO. 64735
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
For
Interior Cabin Configurations
Document No.: AF-528
Revision "IR"
Revision Date: 11/21/11
Applicable to:
Hawker Beechcraft model 400A
Modified by FAA STC ST01572WI
The information in the Instructions for Continued Airworthiness is FAA accepted material and complies with
14 CFR 25.1529, Instructions for Continued Airworthiness. It supersedes or adds to that provided in the
Maintenance Manual for the Hawker Beechcraft 400A Aircraft, only where covered in the items contained
herein. For limitations and procedures not contained in the Supplement, consult the Component
Maintenance Manual, or other approved airplane data.
Page 1 of 15
EFTA00011935

=== Page 268 ===
avfab
RK-244
AVIATION FABRICATORS
Fax
SN# 003702
Nov 7, 2012
)
CERTIFICATE OF CONFORMANCE
This certifies that Aviation Fabricators, Divan, 3 Place with stowage provisions, Beechjet, part number,
32-0396(A60P)T123.K-02, serial number, 003702, was manufactured in, or determined to be in
conformity to and with approved design data and is in a condition for safe operation for installation on
aircraft.
Vice-President
Aviation Fabricators Central Airmotive
EFTA00011936

=== Page 269 ===
REVISION PAGE
Document Title:
Instructions for Continued Airworthiness
Prepared By: Todd Pogue
Reviewed By: Jeffrey R. Lowe
Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of
revisions and the effective pages will be listed below.
Log of Revisions
REV.
EFFECTED
DESCRIPTION
DATE
APPROVED
NO.
PAGE(S)
BY
All
Initial Release
11/21/11
JRL
IR
Per the requirement of Appendix H of 14 CFR Part 25 paragraph H25.1 (c), the changes
made to the ICA by the applicant will be distributed via mail by means of paper copy
Page 2 of 15
EFTA00011937

=== Page 270 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
TABLE OF CONTENTS
DESCRIPTION
PAGE
REVISION PAGE
2
TABLE OF CONTENTS
3
ABBREVIATIONS AND DEFINITIONS
4
1.0
INTRODUCTION
5
2.0
INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE
9
3.0
DIMENSION AND ACCESS:
11
4.0
LIFTING AND SHORING
11
5.0
LEVELING AND WEIGHING
11
6.0
TOWING AND TAXIING
11
7.0
PARKING AND MOORING
11
8.0 PLACARDS AND MARKINGS
12
9.0
SERVICE INFORMATION
13
10.0 AIRWORTHINESS LIMITATIONS
15
11.0 TROUBLESHOOTING INFORMATION
15
Page 3 of 15
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=== Page 271 ===
REVISION PAGE
Document Title:
Instructions for Continued Airworthiness
Prepared By:
Reviewed By:
Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of
revisions and the effective pages will be listed below.
Log of Revisions
REV.
EFFECTED
DESCRIPTION
DATE
APPROVED
NO.
PAGE(S)
BY
All
Initial Release
11/21/11
JRL
IR
Per the requirement of Appendix H of 14 CFR Part 25 paragraph H25.1 (c), the changes
made to the ICA by the applicant will be distributed via mail by means of paper copy
Page 2 of 15
EFTA00011939

=== Page 272 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
TABLE OF CONTENTS
DESCRIPTION
PAGE
REVISION PAGE
2
TABLE OF CONTENTS
3
ABBREVIATIONS AND DEFINITIONS
4
1.0
INTRODUCTION
5
2.0
INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE
9
3.0
DIMENSION AND ACCESS:
11
4.0
LIFTING AND SHORING
11
5.0
LEVELING AND WEIGHING
11
6.0
TOWING AND TAXIING
11
7.0
PARKING AND MOORING
11
8.0
PLACARDS AND MARKINGS
12
9.0
SERVICE INFORMATION
13
10.0 AIRWORTHINESS LIMITATIONS
15
11.0 TROUBLESHOOTING INFORMATION
15
Page 3 of 15
EFTA00011940

=== Page 273 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
ABBREVIATIONS AND DEFINITIONS
Abbreviations
Definitions
AML
FAA Approved Model List (AML)
Detailed
An intensive examination of a specific item, installation or assembly
Inspection (DET)
to detect damage, failure or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirrors,
magnifying lenses, etc. may be necessary. Surface cleaning and
elaborate access procedures may be required.
FAA
Federal Aviation Administration
FAA MIDO
FAA Manufacturing Inspection District Office
General Visual
A visual examination of an interior or exterior area, installation or
Inspection (GVI)
assembly to detect obvious damage, failure or irregularity. This level
of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all
exposed surfaces in the inspection area. This level of inspection is
made under normally available lighting conditions such as daylight,
hangar lighting, flashlight or droplight and may require removal or
opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
ICA
Instructions for Continued Airworthiness
Special Detailed
An Intensive examination of a specific item, installation, or
Inspection (SDI)
assembly to detect damage, failure or irregularity. The examination
is likely to make extensive use of specialized Inspection Techniques
and/or equipment. Intricate cleaning and substantial access or
disassembly procedure may be required.
STC
Supplemental Type Certificate
Page 4 of 15
EFTA00011941

=== Page 274 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
1.0
INTRODUCTION
The purpose of this Maintenance Manual Supplement and Instructions for Continued
Airworthiness (ICA) is to provide the maintenance technician with the information
necessary to ensure the continued airworthiness of the Aviation Fabricators cabin
configuration, per installation number 400-3, when installed in the aircraft passenger
cabin in accordance with Aviation Fabricators design data included on Master Data
List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI.
Modifications to an aircraft obligates the operator to include the maintenance
information provided by this document into the operators aircraft Maintenance Manual
and operator's aircraft scheduled maintenance program. This document defines
supplementary maintenance operations and frequencies recommended by Aviation
Fabricators Inc., to ensure the aircraft's airworthiness.
The information contained herein addresses the requirements specified in 14 CFR
25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane
Maintenance Manual only in those areas listed as pertains to the installation of divan
assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For
limitations and procedures not contained in this supplement, consult the basic Airplane
Maintenance Manual.
DATA
All information to support the continued airworthiness of this modification is contained
in:
STC ST01572WI.
Master Data List: AF-475MDL.
Installation: 3 Place Divan (Ref. installation number 400-3),
Installation Instructions D-10666 for P/N 32-0396K-X
Parts:
P/N 32-0396K-X, 3 Place Divan Installation
The new divan assembly (with restraint system) is a self contained complete assembly
that mounts to the existing seat track, using standard fittings, in accordance with FAA
approved floor plans. The (restraint system) seat belts are attached to the seat track
with typical tie down fittings and the inertia reel shoulder harness is bolted to the divan
frame on the outboard side using standard aircraft hardware.
Design Change Control
All data and changes to the parts and assemblies will be tracked per Master Data List AF-
475MDL Rev C or later FAA approved revision.
Applicable Aircraft
Beechjet 400A
Page 5 of 15
EFTA00011942

=== Page 275 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
ABBREVIATIONS AND DEFINITIONS
Abbreviations
Definitions
AML
FAA Approved Model List (AML)
Detailed
An intensive examination of a specific item, installation or assembly
Inspection (DET)
to detect damage, failure or Irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirrors,
magnifying lenses, etc. may be necessary. Surface cleaning and
elaborate access procedures may be required.
FAA
Federal Aviation Administration
FAA MIDO
FAA Manufacturing Inspection District Office
General Visual
A visual examination of an interior or exterior area, installation or
Inspection (GVI)
assembly to detect obvious damage, failure or irregularity. This level
of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all
exposed surfaces in the inspection area. This level of inspection is
made under normally available lighting conditions such as daylight,
hangar lighting, flashlight or droplight and may require removal or
opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
ICA
Instructions for Continued Airworthiness
Special Detailed
An intensive examination of a specific item, installation , or
Inspection (SDI)
assembly to detect damage, failure or irregularity. The examination
is likely to make extensive use of specialized Inspection Techniques
and/or equipment. Intricate cleaning and substantial access or
disassembly procedure may be required.
STC
Supplemental Type Certificate
Page 4 of 15
EFTA00011943

=== Page 276 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
1.0
INTRODUCTION
The purpose of this Maintenance Manual Supplement and Instructions for Continued
Airworthiness (ICA) is to provide the maintenance technician with the information
necessary to ensure the continued airworthiness of the Aviation Fabricators cabin
configuration, per installation number 400-3, when installed in the aircraft passenger
cabin in accordance with Aviation Fabricators design data included on Master Data
List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI.
Modifications to an aircraft obligates the operator to include the maintenance
information provided by this document into the operators aircraft Maintenance Manual
and operator's aircraft scheduled maintenance program. This document defines
supplementary maintenance operations and frequencies recommended by Aviation
Fabricators Inc., to ensure the aircraft's airworthiness.
The information contained herein addresses the requirements specified in 14 CFR
25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane
Maintenance Manual only in those areas listed as pertains to the installation of divan
assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For
limitations and procedures not contained in this supplement, consult the basic Airplane
Maintenance Manual.
DATA
All information to support the continued airworthiness of this modification is contained
in:
STC ST01572WI.
Master Data List: AF-475MDL.
Installation: 3 Place Divan (Ref. installation number 400-3),
Installation Instructions D-10666 for P/N 32-0396K-X
Parts:
P/N 32-0396K-X, 3 Place Divan Installation
The new divan assembly (with restraint system) is a self contained complete assembly
that mounts to the existing seat track, using standard fittings, in accordance with FAA
approved floor plans. The (restraint system) seat belts are attached to the seat track
with typical tie down fittings and the inertia reel shoulder harness is bolted to the divan
frame on the outboard side using standard aircraft hardware.
Design Change Control
All data and changes to the parts and assemblies will be tracked per Master Data List AF-
475MDL Rev C or later FAA approved revision.
Applicable Aircraft
Beechjet 400A
Page 5 of 15
EFTA00011944

=== Page 277 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
3 Place Divan
P/N 32-0396K-X (Top not shown for clarity)
WASHER
VERIHER
WASHER
MASHER
WASHER
DOLY
WASHER
BOLT
WASHER
BOLT
BOLT
WASHER
INT-
KVT
MR
FOOT
MAY
INVOICE
BRD CENTER FEET
AFT FLET
2PLGS
SPICE
RMCS
ALROOT
6' FOOT
FOOT
2 PLCS
PJII :
P/M
USERVING CENTERPEET
PIN
SNR61 THRU RK-109
EXCEPT RK83
2PLGS
FOOT ATTACHMENT TO DIVAN
AUCHOR BOLT
ANCHOR SOLT
ANCHOR BOLT
T POOP
LIFOOT
1649
CHECK WIT
MD CENTER 00 FEET
TRACK GAR
PACE
3PLCS
IND CENTER PECT
$' FOOT
IPLGS
USE IN END CENTER PEET
LOCATION RMCS 01
FOOT ATTACHMENT TO TRACKWIHGAP
00 IND CENTER FEET
FOOT ATTACHMENT TOTRACK
mos
CO FEET
Figure 1.0A
Page 6 of 15
EFTA00011945

=== Page 278 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
Inertia Reel Attachment
DIVAN FRAME
NUT
WASHER
INERTIA REEL
INERTIA REEL
BOLT
Figure 1.0B
Seat Belt Attachment
SEAT BELT
TIE DOWN FITTING
SEAT TRACK
REF
Figure 1.0C
Page 7 of 15
EFTA00011946

=== Page 279 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
3 Place Divan
P/N 32-0396K-X (Top not shown for clarity)
IVVD
WASHER
WASHER
WASHER
WASHER
WASHER
DOLT
WASHER
GOLT
WASHER
BOLT
BOLT
WASHER
KVT-
N/A
INT-
FOOT
I/I
PROPERT
BRO CENTER FEET
AFT FLET
IN
2MGS
FOOT
IND CENTER FEET
ITEMS
21%
FOOT
PLCS
room
PJM
P/M 310525-19
UNITED CENTERPEET
P/N
SN R/61 THRU RK-09
OH
EXCEPT RK00
2PLGS
FOOT ATTACHMENT TO DIVAN
ANCHOR BOLY
AND KA BOLT
ANCHOR BOLT
T FOOP
CHECK IN/T
FOOP
CHECK ANT
36 09 FEET
TRACK GAN
2PLCS
3 PLCS
FOR
EPLES
USE
LOCATION
SPECE
FOOT ATTACHMENT TOTRACKWTH GAP
os IND CENTERFECT
FOOT ATTACHMENT TOTRACK
not
PARTIBLAIL CO FEET
Figure 1.0A
Page 6 of 15
EFTA00011947

=== Page 280 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
Inertia Reel Attachment
DIVAN FRAME
NUT
WASHER
INERTIA REEL
INERTIA REEL
BOLT
Figure 1.0B
Seat Belt Attachment
SEAT BELT
TIE DOWN FITTING
SEAT TRACK
REF
Figure 1.0C
Page 7 of 15
EFTA00011948

=== Page 281 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
DIVAN WIDTH
SEAT BACK
ASSEMBLY
FOAM
COVERING
SEAT BOTTOM
MATERIAL
VELCRO HOOK
ASSEMBLY
COVERING
MATERIAL
VELCRO LOOP
VELCRO
LOOP
VELCRO HOOK
DNANWOTH
FOAM
CUSHION ASSEMBLY REFERENCE
Figure 1.0D
Page 8 of 15
EFTA00011949

=== Page 282 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
2.0
INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE
1. To comply with 14 CFR 25.1529, continue the new divan assembly (with restraint
system) on the same inspection and maintenance schedule used per the Hawker
Beechcraft Maintenance Manual for cabin section inspections.
a. The new cabin configuration components require no service other than inspection
at normal inspection interval of 200 hours.
b. The safety belts require no service other than inspection at normal inspection
interval of every 200 hours.
C. Perform a detailed visual inspection of each passenger seat bottom and back
cushions and covering of all cabin interior components to detect apparent or
obvious defects or irregularities.
On the cushion assembly, check for cracks and punctures within a 4" diameter
circle. The cushion assembly can have no more than three defects found within
the 4" diameter circle. If a cushion develops a "lump", check to see if there are no
more than two lumps within a 4" diameter circle. Any damage to the cushions
outside of the described limits will require them to be replaced.
Visually inspect the covering assemblies for holes, punctures, and tears. If the
damage to the covering is holes smaller than 1/2" in diameter or a cut at a maximum
of 2" in length then the covering is satisfactory. The sewing of the cover
assemblies is not to exceed 1" tearing. Any damage to the covering assemblies
outside of the described limits will require them to be replaced.
d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and
deformation. Damaged conditions could be detected as a crack at the edge of the
tube or along the length of the tubes or as a crack, tear or cut found on the seat
bottom or back diaphragm. Visually inspect all hardware for excessive wear
before and after installation.
Replace the seat back and bottom diaphragm if two cracks or deformations are
found with a 4" diameter circle. If a tear or cut is found with a maximum of 6",
replace the diaphragm.
There shall be no broken tubes. There shall be no sharp corners, edges, or
protrusions that may injure passengers. Replace the tubes if they are bent in such
a way that they are more than 2" off center. Replace the seat tubes if crack length
is found to be 125" or greater. Replace the tube if a dent is found running longer
than 3". Replace the seat tubes if deformation is greater than .25" the overall
thickness of the tube diameter.
Cracked or broken fasteners or fittings are to be replaced with new immediately.
Page 9 of 15
EFTA00011950

=== Page 283 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
DIVAN WIDTH
SEAT BACK
ASSEMBLY
FOAM
COVERING
SEAT BOTTOM
MATERIAL
VELCRO HOOK
ASSEMBLY
COVERING
MATERIAL
VELCRO LOOP
VELCRO
LOOP
VELCRO HOOK
DIVANVIDTH
FOAM
CUSHION ASSEMBLY REFERENCE
Figure 1.0D
Page 8 of 15
EFTA00011951

=== Page 284 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
2.0
INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE
1. To comply with 14 CFR 25.1529, continue the new divan assembly (with restraint
system) on the same inspection and maintenance schedule used per the Hawker
Beechcraft Maintenance Manual for cabin section inspections.
a. The new cabin configuration components require no service other than inspection
at normal inspection interval of 200 hours.
b. The safety belts require no service other than inspection at normal inspection
interval of every 200 hours.
C. Perform a detailed visual inspection of each passenger seat bottom and back
cushions and covering of all cabin interior components to detect apparent or
obvious defects or irregularities.
On the cushion assembly, check for cracks and punctures within a 4" diameter
circle. The cushion assembly can have no more than three defects found within
the 4" diameter circle. If a cushion develops a "lump", check to see if there are no
more than two lumps within a 4" diameter circle. Any damage to the cushions
outside of the described limits will require them to be replaced.
Visually inspect the covering assemblies for holes, punctures, and tears. If the
damage to the covering is holes smaller than 1/2" in diameter or a cut at a maximum
of 2" in length then the covering is satisfactory. The sewing of the cover
assemblies is not to exceed 1" tearing. Any damage to the covering assemblies
outside of the described limits will require them to be replaced.
d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and
deformation. Damaged conditions could be detected as a crack at the edge of the
tube or along the length of the tubes or as a crack, tear or cut found on the seat
bottom or back diaphragm. Visually inspect all hardware for excessive wear
before and after installation.
Replace the seat back and bottom diaphragm if two cracks or deformations are
found with a 4" diameter circle. If a tear or cut is found with a maximum of 6",
replace the diaphragm.
There shall be no broken tubes. There shall be no sharp corners, edges, or
protrusions that may injure passengers. Replace the tubes if they are bent in such
a way that they are more than 2" off center. Replace the seat tubes if crack length
is found to be 125" or greater. Replace the tube if a dent is found running longer
than 3". Replace the seat tubes if deformation is greater than .25" the overall
thickness of the tube diameter.
Cracked or broken fasteners or fittings are to be replaced with new immediately.
Page 9 of 15
EFTA00011952

=== Page 285 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
For repair or replacement of damaged or broken parts or assemblies contact
Aviation Fabricators Inc.
2. Inspection Time Limit for the cabin configuration installations:
200 +/- hour inspection for the new cabin configuration components
Task
Schedule
Date
Mech
Insp
Code
AFI-100
a.
Inspect for damage to upholstery.
AFI-101
b.
Inspect safety belts for wear, cuts,
fraying, damage, and deterioration.
AFI-102
C.
Inspect safety belt attachment fittings
for wear and damage
AFI-103
d.
Inspect foot fittings for damage,
security, and function.
AFI-104
e.
Inspect seat frame for damage, and
corrosion.
AFI-105
f.
Inspect overall seat for fit and
function.
A. The new divan assembly and restraint system are on the same inspection and
maintenance schedule used per the Hawker Beechcraft Maintenance Manual for
passenger seats.
Page 10 of 15
EFTA00011953

=== Page 286 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
3.0
DIMENSION AND ACCESS:
The installation of this cabin configuration does not change the dimensions of the
aircraft or alter the access to any existing aircraft system.
4.0
LIFTING AND SHORING
No change.
5.0
LEVELING AND WEIGHING
Divan
Maximum Allowable Seat Weight
=
80 lbs
w/ Seat Bottom Upholstery
Base Weight of Divan Assembly w/ Restraint System = 50 lbs
(includes empty drawer weight)
)
6.0
TOWING AND TAXIING
No change.
7.0
PARKING AND MOORING
No change.
Page 11 of 15
EFTA00011954

=== Page 287 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
For repair or replacement of damaged or broken parts or assemblies contact
Aviation Fabricators Inc.
2. Inspection Time Limit for the cabin configuration installations:
200 +/- hour inspection for the new cabin configuration components
Task
Schedule
Date
Mech
Insp
Code
AFI-100
a.
Inspect for damage to upholstery.
AFI-101
b.
Inspect safety belts for wear, cuts,
fraying, damage, and deterioration.
AFI-102
C.
Inspect safety belt attachment fittings
for wear and damage
AFI-103
d.
Inspect foot fittings for damage,
security, and function.
AFI-104
e.
Inspect seat frame for damage, and
corrosion.
AFI-105
f.
Inspect overall seat for fit and
function.
A. The new divan assembly and restraint system are on the same inspection and
maintenance schedule used per the Hawker Beechcraft Maintenance Manual for
passenger seats.
Page 10 of 15
EFTA00011955

=== Page 288 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
3.0
DIMENSION AND ACCESS:
The installation of this cabin configuration does not change the dimensions of the
aircraft or alter the access to any existing aircraft system.
4.0
LIFTING AND SHORING
No change.
5.0
LEVELING AND WEIGHING
Divan
Maximum Allowable Seat Weight
=
80 lbs
w/ Seat Bottom Upholstery
Base Weight of Divan Assembly w/ Restraint System = 50 lbs
(includes empty drawer weight)
)
6.0
TOWING AND TAXIING
No change.
7.0
PARKING AND MOORING
No change.
Page 11 of 15
EFTA00011956

=== Page 289 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
8.0
PLACARDS AND MARKINGS
Three (3) placards are required in conjunction with this modification:
1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be
installed in plain view of the seat occupants on the forward divider.
LIFE VEST LOCATED IN
UNDER SEAT COMPARTMENT
P/N 15-0288
FASTEN SEATBELT AND SHOULDER HARNESS
FOR TAXI, TAKEOFF AND LANDING
35.5
P/N 32-0377-20
FLOOR
Figure 8.0A
2. A placard stating "to install harness over seat occupant's fwd shoulder" is sewn on to
restraint system part numbers 3088-7-061-2396 and should be legible and easily
viewed by the seat occupant.
HARRIES 10 DE INSTALLED
STUDE ESCEPANTS
FORWARD SEOULDER
330
Figure 8.0B
Page 12 of 15
EFTA00011957

=== Page 290 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
9.0
SERVICE INFORMATION
Typical Passenger Seating Service Instructions:
A. Upholstery Cleaning:
Service Instructions
1. Remove seat back and seat bottom cushion assemblies from the interior
seating components.
2. Clean the cushions in accordance with instructions issued by the company
responsible for the upholstery covering so that knowledge of the upholstery
material's fire retardant properties are known and will not be compromised.
3. Clean and inspect restraint system for damage, fraying, cuts or seam
deterioration.
4. Inspect all attachment fittings and replace if necessary.
5. Inspect overall interior component for fit and function.
Typical Maintenance Instructions:
Divan Assembly
The divans are self contained complete assemblies that mount to the existing aircraft
cabin seat track using standard fittings in accordance with approved floor plans. Refer
to Figure 1.0A.
Divan Installation
Installation of the divan requires aligned the feet on the existing seat track and
attaching the divan legs using standard hardware. Refer to Installation Instruction
drawing D-10666 for complete installation details and hardware part numbers.
Divan Removal
Removal of the divan requires loosening the attaching hardware and lifting the divan
from its location on the seat track. The feet will be slid forward or aft to the end of the
seat track or a gap in the track for their removal.
Cushions
Seat back and seat bottom cushion assemblies are removed by simply pulling the
cushion inboard away from the Velcro on the sidewall or up away from the Velcro on
the pan of the divan assembly, respectively. All covering and upholstery materials
must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476.
The cushion design and layout were determined & manufactured by the seat installer
to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for
Cushion Assembly Reference for basic assemblies.
Page 13 of 15
EFTA00011958

=== Page 291 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
8.0
PLACARDS AND MARKINGS
Three (3) placards are required in conjunction with this modification:
1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be
installed in plain view of the seat occupants on the forward divider.
LIFE VEST LOCATED IN
UNDER SEAT COMPARTMENT
P/N 15-0288
FASTEN SEATBELT AND SHOULDER HARNESS
FOR TAXI, TAKEOFF AND LANDING
35.5
P/N 32-0377-20
FLOOR
Figure 8.0A
2. A placard stating "to install harness over seat occupant's fwd shoulder" is sewn on to
restraint system part numbers 3088-7-061-2396 and should be legible and easily
viewed by the seat occupant.
HARNESS TO
BIERTRE ELEMENTS
FORWARD SEQUIRER
Figure 8.0B
Page 12 of 15
EFTA00011959

=== Page 292 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
9.0
SERVICE INFORMATION
Typical Passenger Seating Service Instructions:
A. Upholstery Cleaning:
Service Instructions
1. Remove seat back and seat bottom cushion assemblies from the interior
seating components.
2. Clean the cushions in accordance with instructions issued by the company
responsible for the upholstery covering so that knowledge of the upholstery
material's fire retardant properties are known and will not be compromised.
3. Clean and inspect restraint system for damage, fraying, cuts or seam
deterioration.
4. Inspect all attachment fittings and replace if necessary.
5. Inspect overall interior component for fit and function.
Typical Maintenance Instructions:
Divan Assembly
The divans are self contained complete assemblies that mount to the existing aircraft
cabin seat track using standard fittings in accordance with approved floor plans. Refer
to Figure 1.0A.
Divan Installation
Installation of the divan requires aligned the feet on the existing seat track and
attaching the divan legs using standard hardware. Refer to Installation Instruction
drawing D-10666 for complete installation details and hardware part numbers.
Divan Removal
Removal of the divan requires loosening the attaching hardware and lifting the divan
from its location on the seat track. The feet will be slid forward or aft to the end of the
seat track or a gap in the track for their removal.
Cushions
Seat back and seat bottom cushion assemblies are removed by simply pulling the
cushion inboard away from the Velcro on the sidewall or up away from the Velcro on
the pan of the divan assembly, respectively. All covering and upholstery materials
must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476.
The cushion design and layout were determined & manufactured by the seat installer
to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for
Cushion Assembly Reference for basic assemblies.
Page 13 of 15
EFTA00011960

=== Page 293 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
Inertia Reel
Inertia reel removal is accomplished by loosening attaching hardware and removing
from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for
complete installation details and hardware part numbers.
Refer to Figure 1.0B.
Seat Belt
Seat belt and removal is accomplished by loosening attaching hardware and removing
from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666
for complete installation details and hardware part numbers.
Refer to Figure 1.0C.
B. RECOMMENDED OVERHAUL PERIODS
No additional overhaul time limitations and requirements apply to the Aviation
Fabricators' interior cabin configuration.
Page 14 of 15
EFTA00011961

=== Page 294 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
10.0 AIRWORTHINESS LIMITATIONS
The Airworthiness Limitations section is FAA approved and specifies maintenance
required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an
alternative program has been FAA approved.
There are no new (or additional) Airworthiness Limitations associated with this equipment
and /or installation.
11.0 TROUBLESHOOTING INFORMATION
Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan
installation that is required beyond the information found on the installation drawing
D-10666.
For replacement parts or repair of damage parts:
Contact Aviation Fabricators at
Troubleshooting this installation should only be accomplished by FAA approved repair
stations with the appropriate ratings or appropriately rated operator/individuals, with required
test equipment and service data.
Page 15 of 15
EFTA00011962

=== Page 295 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
Inertia Reel
Inertia reel removal is accomplished by loosening attaching hardware and removing
from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for
complete installation details and hardware part numbers.
Refer to Figure 1.0B.
Seat Belt
Seat belt and removal is accomplished by loosening attaching hardware and removing
from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666
for complete installation details and hardware part numbers.
Refer to Figure 1.0C.
B. RECOMMENDED OVERHAUL PERIODS
No additional overhaul time limitations and requirements apply to the Aviation
Fabricators' interior cabin configuration.
Page 14 of 15
EFTA00011963

=== Page 296 ===
Aviation Fabricators Inc.
ICA Document No.: AF-528
Revision (IR)
Clinton, MO. 64735
Date: November 21, 2011
10.0 AIRWORTHINESS LIMITATIONS
The Airworthiness Limitations section is FAA approved and specifies maintenance
required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an
alternative program has been FAA approved.
There are no new (or additional) Airworthiness Limitations associated with this equipment
and /or installation.
11.0 TROUBLESHOOTING INFORMATION
Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan
installation that is required beyond the information found on the installation drawing
D-10666.
For replacement parts or repair of damage parts:
Contact Aviation Fabricators at
Troubleshooting this installation should only be accomplished by FAA approved repair
stations with the appropriate ratings or appropriately rated operator/individuals, with required
test equipment and service data.
Page 15 of 15
EFTA00011964

=== Page 297 ===
U.S. DEPARTMENT OF TRANSPORTATION
1.DATE
FEDERAL AVIATION ADMINISTRATION
5/02/2013
STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2.MAKE
3.MODEL NO.
4. TYPE(Airplane. Engine, Propeller, etc.)
5.NAME OF APPLICANT
Raytheon
400A
Airplane
Constant Aviation-CLM
LIST OF DATA
6.IDENTIFICATION
7.TITLE
TP 22681
Skandia, Inc. Flammability Test Report
Rev A
Oil Burner Testing and Vertical Burner Testing
Dated 05/02/2013
Notes:
1) Work accomplished under Skandia Inc. wo # 254987-13, Ref Document ID 93685.
2) Flammability test witnessing only, does not constitute installation approval of the
materials.
8.PURPOSE OF DATA
Demonstration of compliance with material flammability requirements for S/N RK-244
9.APPLICABLE REQUIREMENTS (List specific sections)
14 CFR Part 25.853 (a) Amdt 25-116 Appendix F Part I (a)(1)(ii)
14 CFR Part 25.853 (c) Amendment 25-116 Appendix F Part II
10.CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations
of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered
have been
examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness
Standards listed.
Recommend approval of these data
I (We) Therefore
X
Approve these data
11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE
12.DESIGNATION NUMBER(S)
13.CLASSIFICATION(S)
DERY-832780-CE
Structural Special
FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION
EFTA00011965

=== Page 298 ===

=== Page 299 ===
FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE
Form Approved O.M.B. No. 2120-0018
Expiration Date 02/28/2013
APPLICATION FOR
INSTRUCTIONS Print or type. Do not write in shaded areas; these are for FAA
U.S. Department
U.S. AIRWORTHINESS
use only. Submit original only to an authorized FAA Representative If additional
Accepted GS Jan/27/2014
of Transportation
space is required, use attachment For special flight permits complete Sections
Federal Aviation
CERTIFICATE
II, VI, and VII as applicable.
Administration
1. REGISTRATION MARK
2. AIRCRAFT BUILDER'S NAME (Make)
3. AIRCRAFT MODEL DESIGNATION
4. YR. MFR.
FAA CODING
N493LX
Raytheon Aircraft Co
400A
1999
L AIRCRAFT
DESCRIPTION
5. AIRCRAFT SERIAL NO.
6. ENGINE BUILDER'S NAME (Make)
7. ENGINE MODEL DESIGNATION
RK-244
Williams International
FJ44-3AP
8. NUMBER OF ENGINES
9. PROPELLER BUILDER'S NAME (Make)
10. PROPELLER MODEL DESIGNATION
11. AIRCRAFT IS (Check if applicable)
2
N/A
N/A
IMPORT
APPLICATION IS HEREBY MADE FOR: (Check applicable items)
A
1
STANDARD AIRWORTHINESS CERTIFICATE (Indicate category)
NORMAL
UTILITY
ACROBATIC
TRANSPORT
COMMUTER
BALLOON
OTHER
B
SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)
7
PRIMARY
9
LIGHT-SPORT (Indicate Class)
Airplane
Power-Parachute
Weight-Shift-Control
Glider
Lighter than Air
2
LIMITED
1
CLASS
5
PROVISIONAL (Indicate class)
2
CLASS 12
1
AGRICULTURE AND PEST CONTROL
2
AERIAL SURVEY
3
AERIAL ADVERTISING
3
RESTRICTED (Indicate operation(s)
4
to be conducted)
FOREST (Widlife conservation)
5
PATROLLING
6
WEATHER CONTROL
II. CERTIFICATION REQUESTED
0
OTHER (Specify)
1
RESEARCH AND DEVELOPMENT
2
AMATEUR BUILT
3
EXHIBITION
4
AIR RACING
5
CREW TRAINING
6
MARKET SURVEY
o
TO SHOW COMPLIANCE WITH THE CFR
7
OPERATING (Primary Category) KIT BUILT AIRCRAFT
8A
Existing aircraft without an airworthiness certificate & do not meet $ 103.1
4
EXPERIMENTAL (Indicate operation(s)
to be conducted)
OPERATING
8
8B
Operating Light-Sport Kit-built
LIGHT-SPORT
8C
Operating light-sport previously issued special light-sport category airworthiness
certificate under 21,190
UNMANNED
9A
RESEARCH AND DEVELOPMENT
9C
CREW TRAINING
9
AIRCRAFT
98
MARKET SURVEY
1
FERRY FLIGHT FOR REPAIRS, ALTERATIONS MAINTENANCE OR STORAGE
SPECIAL FLIGHT PERMIT (Indicate
2
EVACUATE FROM AREA OF IMPENDING DANGER
8
operation to be conducted than complete
Section VI or VII as applicable on reverse side)
3
OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT
4
DELIVERING OR EXPORTING
5
PRODUCTION FLIGHT TESTING
6
CUSTOMER DEMONSTRATION FLIGHTS
C
6
MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE "Restricted Operation" and "Standard" or "Limited" as applicable)
A. REGISTERED OWNER (As shown on certificate of aircraft registration)
IF DEALER, CHECK HERE
NAME
ADDRESS
Flight Options LLC
Richmond Heights OH 44143
B. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated)
AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No. and
AIRWORTHINESS DIRECTIVES (Check if of applicable ADs are complied with and give the number
Revision No.)
N/A
of the last AD SUPPLEMENT available in the blweekly series as of the date of application)
EII. OWNER'S CERTIFICATION
Bi Weekly 2013-22 10/21/2013 - 11/03/2013
AIRCRAFT LISTING (Give page number(s))
SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporated)
N/A
N/A
C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS
CHECK IF RECORDS IN
TOTAL AIRFRAME HOURS
EXPERIMENTAL ONLY (Enter hours flown since last certificate issued
COMPLIANCE WITH
TTAF 8578.62
3
or renewed)
14 CFR section 91.417
14.82
D. CERTIFICATION - hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation Administration in
accordance with Title 49 of the United States Code 44101 et seq and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy and eligible for the
airworthiness certificate requested
DATE OF APPLICATION
NAME AND TITLE (Print or (voe).
11/18/2013
Agent
A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete the section only if
2
14 CFR part 121 CERTIFICATE HOLDER (Give
CERTIFICATED MECHANIC (Give Certificate No.)
CERTIFICATED REPAIR STATION (Give Certificate
IV. INSPECTION
VERIFICATION
Certificate No)
3
6
No.)
AGENCY
5
AIRCRAFT MANUFACTURER (Give name or firm)
DATE
TITLE
SIGNATURE
(Check ALL applicable block forms A and B)
THE CERTIFICATE REQUESTED
A. I find that the aircraft described in Section I or VII meets requirements for
4
AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE
V. FAA REPRESENTATIVE
B. Inspection for a special flight permit under Section VII
FAA INSPECTOR
FAA DESIGNEE
CERTIFICATION
was conducted by:
CERTIFICATE HOLDER UNDER
14 CFR part 65
14 CFR part 121 OR 135
14 CFR part 145
DATE
MIDO/FSDO
OFFICE
11/18/2013
CLE-25
4
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format -PDF
RECEIVED
DEC 10 2013
CLE- 012"
EFTA00011967

=== Page 300 ===
EFTA000119

=== Page 301 ===
A. MANUFACTURER
NAME
ADDRESS
VI. PRODUCTION
FLIGHT TESTING
B. PRODUCTION BASIS (Check applicable item)
PRODUCTION CERTIFICATE (Give production certificate number)
TYPE CERTIFICATE
OTHER:
C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNATURE
A. DESCRIPTION OF AIRCRAFT
REGISTERED OWNER
ADDRESS
BUILDER (Make)
MODEL
SERIAL NUMBER
REGISTRATION MARK
B. DESCRIPTION OF FLIGHT
CUSTOMER DEMONSTRATION FLIGHTS
(Check if applicable)
FROM
TO
VIA
DEPARTURE DATE
DURATION
C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT
VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST
PILOT
CO-PILOT
FLIGHT ENGINEER
OTHER (Specify)
D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS:
E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment if necessary)
F. CERTIFICATION - hereby certify that I am the registered owner (or his agent) of the aircraft described above: that the aircraft is registered with the Federal Aviation
Administration in accordance with Title 49 of the United States Code 44101 etseg and applicable Federal Aviation Regulations and that the aircraft has been inspected and is
safe for the flight described
DATE
NAME AND TITLE (Print or type)
SIGNATURE
A. Operating Limitations and Markings in Compliance With 14 CFR Section 91.9.
G. Statement of Conformity, FAA Form 8130-9 (Attach when required)
As Applicable
H. Foreign Airworthiness Certification for Import Aircraft
DOCUMENTATION (FAA/DESIGNEE
B. Current Operating Limitations Attached
(Attach when required)
VIII. AIRWORTHINESS
C. Data, Drawings, Photographs etc. (Attach when required)
I. Previous Airworthiness Certificate Issued in Accordance With
use only)
14 CFR Section 21.191 (a) CAR
(Original attached)
D. Current Weight and Balance Information Available in Aircraft
J. Current Airworthiness Certificate Issued in Accordance With
E. Major Repair and Alteration FAA Form 337 (Attach when required)
14 CFR Section 21.191 (a)
(Copy attached)
F. This inspection Recorded in Aircraft Records
K. Light-Sport Aircraft Statement of Compliance FAA Form 8130-15 (Attach
when required)
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format-PDF
Page 2 of 2
EFTA00011969

=== Page 302 ===

=== Page 303 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION
SPECIAL AIRWORTHINESS CERTIFICATE
A
CATEGORY/DESIGNATION
EXPERIMENTAL
PURPOSE
RESEARCH & DEVELOPMENT
B
MANU-
NAME
I//N/A
FACTURER
ADDRESS /// N/A
FROM
C
FLIGHT
TO
N/A
11771
D
N- 4931X
SERIAL NO. RK-244
BUILDER Raytheon Aircraft Company
MODEL
400A
DATE OF ISSUANCE Nov 18.2013 \ /
EXPIRY Jan 12. 2014
OPERATING LIMITATIONS DATED Nov 18.2013 ARE PART OF THIS CERTIFICATE
E
DESIGNATION OR OFFICE NO.
DART833943GL
Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or
imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT
IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR).
FAA FORM 8130-7 (07/04)
SEE REVERSE SIDE
NSN: 0052-00-693-4000
EFTA00011971

=== Page 304 ===
This airworthiness certificate is issued under the authority of Public Law 104-6, 49 United States Code
A
(USC) 44704 and Title 14 Code of Federal Regulations (CFR).
The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct
B
production flight tests, and only production flight tests, of aircraft registered in his name. No person may
conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or
hire: and/or (2) Carrying persons not essential to the purpose of the flight.
C
This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in
Block A.
This airworthiness certificate certifies that as of the date of issuance, the aircraft to which issued has
been inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet
the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex
D
8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the
reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and
limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign
country without the special permission of that country.
E
Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the
duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217.
EFTA00011972

=== Page 305 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION
SPECIAL AIRWORTHINESS CERTIFICATE
CATEGORY/DESIGNATION EXPERIMENTAL
A
PURPOSE
Research and Development
MANU-
NAME
B
N/A
FACTURER
ADDRESS
N/A
FROM
C
N/A
PED
FLIGHT
TO
N/A
N-
D
493LX
SERIAL NO. RK244
BUILDER
Raytheon Aircraft Company
MODEL 400A
DATE OF ISSUANCE MAY/20/2013
EXPIRY NOV/16/2013
OPERATING LIMITATIONS DATEQMAY/20/2013
ARE PART OF THIS CERTIFICATE
E
DESIGNATION OR OFFICE NO.
DARF-400148-CE
Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or
imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT
IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR).
FAA Form 8130-7 (04/2011) Previous Edition 07/04 May be Used until Depleted
SEE REVERSE SIDE NSN: 0052-00-693-4000
EFTA00011973

=== Page 306 ===
A
This airworthiness certificate is issued under the authority of Public Law 104-6, 49 United States Code
(USC) 44704 and Title 14 Code of Federal Regulations (CFR).
The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct
B
production fight tests, and only production flight tests, of aircraft registered in his name. No person may
conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or
hire: and/or (2) Carrying persons not essential to the purpose of the flight.
C
This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in
Block A.
This airworthiness certificate certifies that as of the date of issuance, the aircraft to which issued has been
inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet the
requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to
D
the Convention On International Civil Aviation. No person may operate the aircraft described on the
reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and
limitations which may be prescribed by the FAA as part of this certificate; (2) over any foreign country
without the special permission of that country.
E
Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the
duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217.
EFTA00011974

=== Page 307 ===
FAA Cleveland FSDO
U.S. Department
of Transportation
Federal Aviation
North Olmsted, Ohio 44070
Administration
EXPERIMENTAL OPERATING LIMITATIONS
For Research and Development (R&D)
REG. NO.
MAKE:
MODEL
SERIAL NO:
N493LX
Raytheon Aircraft .Co
400A
RK 244
THESE OPERATING LIMITATIONS SHALL BE ACCESSIBLE TO THE PILOT
1. No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certificate, is
displayed at the cabin or cockpit entrance and visible to passengers or flight crew members.
2. No person may operate this aircraft for other than the purpose of Research and Development to
accomplish the flight operation outlined in the applicant's program letter Dated November 13.2013, which
describes compliance with14 CFR 21.193 (d) and made available to the pilot in command of the aircraft In
addition, this aircraft shall be operated in accordance with applicable air traffic and general Operating rules
of 14 CFR part 91, and all additional limitationsherein prescribed under the provisions of 14 CFR 91.319 (i).
3. R&D flights must be conducted IAW Nextant Aerospace's Program Letter Dated November 13. 2013,
within the geographical area described in the program letter:
R&D flights will be conducted in North America
4. Except for takeoffs and landings, this aircraft must not be operated over densely populated areas or in
congested airways.
5. This aircraft must not be operated unless it is maintained and inspected in accordance with the appropriate
military technicalpublications and/or manufacturer's recommendation. The owner/operator must select,
establish, identify, and use an inspection program set forth in 14 CFR 91.409 (e), (f), (g), and (h).
This inspection program must be recorded in the aircraft maintenance records.
6. The Pilot In Command of this aircraft must hold an appropriate category/class rating. If required for the type of
aircraft to be flown, the Pilot In Command also must hold either an appropriate type rating or a Letter of
Authorization issued by an FAA Flight Standards Operations Inspector.
7. This aircraft may be operated under VFR, day and/or night.
8. This Aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance
with 14 CFR 91.205.
9. No person may operate this aircraft for carrying persons or property for compensation or hire.
10. No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight.
11. The Pilot In Command of this aircraft must advise each passenger of the experimentalnature of this aircraft,
And explain that it does not meet the certification requirements of a standard certified aircraft.
12. This Aircraft must contain the Beech Model 400A Flight Manual with Nextant 400XT AFM Section
Insert. Placards, markings, etc. (or other operating instructions developed for an STC modification), as
required by14 CFR 91.9.
13. This Aircraft is Prohibited from Aerobatic Flight, that is an Intentional Maneuver involving an Abrupt change in the
Aircrafts attitude, an abnormal attitude, or abnormal acceleration not necessary for normal flight, unless part of
show compliance flight testing
14. This aircraft shall not be used for glider towing, banner towing, or intentionalparachute jumping.
Page 1 of 2
EFTA00011975

=== Page 308 ===
EFTA00011976

=== Page 309 ===
FAA Cleveland FSDO
of Transportation
North Olmstead
Federal Aviation
Administration
15. No person shall operate this aircraft unless within the preceding 12 Calendar months it has had a condition
inspection performed in accordance with 14 CFR Part 43, appendix D, or other FAA approved programs, and
was found to be in a condition for safe Operation. This inspection will be recorded in the aircraft maintenance
records.
16. FAA-certificated Repair Stations and FAA Certified mechanics with appropriate ratings, as authorized by 14
CFR 43.3 may perform inspections required by these limitations.
17. Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded
statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the
scope and detail of 14 CFR part 43, appendix D, or other FAA approved programs and found to
be in a condition for safe operation." The entry will include the aircraft's totaltime-in-service, and the
name, signature, certificate number, and type of certificate held by the person performing the inspection.
18. If the aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made in
the aircraft records.
19. This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements
of 14 CFR Part 43.
20. This aircraft must display the word "EXPERIMENTAL" in accordance with 14 CFR 45.23(b).
21. The Pilot In Command of this aircraft must notify air traffic control of the experimental nature of this aircraft
when operating into or out of airports with operating control towers. The Pilot In Command must plan routing that
will avoid densely populated areas and congested airways when operating VFR.
22. This aircraft does not meet the requirements of the applicable, comprehensive, and detailed Airworthiness code
as provided by Annex 8 of the International Convention of Civil Aviation. The Owner/Operator of this aircraft
must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to
operating this aircraft in or over that country. That written permission must be carried aboard the
aircraft together with the U.S. airworthiness certificate and, upon request, be made available to an FAA
inspector or the CAA in the country of operation.
23. Aircraft instruments and equipment installed and used under 14 CFR 91205 must be inspected and maintained
in accordance with the requirements of 14 CFR parts 43 and 91. Any maintenance or inspection of this
equipment must be recorded in the Aircraft Maintenance records.
24. Application must be made to the geographically responsible FSDO or MIDO for any revision to these operating
limitations.
25. 14 CFR 47.45 requires that the FAA Aircraft Registry must be notified within 30 days of any change in the
aircraft registrant's address. Such notification is to be made by submitting Aeronautical Center Form 8050-1,
Aircraft Registration Application, to AFS-750 in Oklahoma City, OK.
26. Condition Inspections must be performed in Accordance with 14 CFR Part 43 Appendix D at least every 100 Hrs
Flight Hours. This Inspection must be performed by an FAA Certified Mechanic with the Appropriate Ratings as
deemed in 14 CFR. 43.3
27. The Special Airworthiness Certificate and Operation Limitations will expire on. Jan 12.2014
Designated Airworthiness Representative
DART833943GL
Issued at Cuyahoga Airport
Date Issued: November 18 2013
Page 2 of 2
EFTA00011977

=== Page 310 ===

=== Page 311 ===
nextant aerospace
Quality Assurance Department
To:
Federal Aviation Administration
Date: November 13, 2013
Flight Standards District Office
North Olmsted, Ohio 44070
From:
Chief Inspector
Nextant Aerospace
Subject: FAA Program letter for Beech Jet 400A, Serial number RK-244, Registration Number N493LX.
Ref: FAA order 8130.2G
1. Registered Owner: Flight Options LLC. Address:
Richmond Heights, Ohio 44143
2. Aircraft Description: Twin Engine Light Jet
a. Registration: N493LX
b. Aircraft Builder Raytheon Aircraft Co
c. Year mfg.: 1999
d. Aircraft Serial Number: RK-244
e. Aircraft Model Designation: Beech Jet 400A
3. The program purpose for the aircraft will be used To complete the flight performance profile in Research
& Development Category in support of FAA Project SA 15250LA-T (Replacement of Wingtips)
4. Program Duration
a. List the estimated flight hours required for program: 20 Hrs
b. Number of flights: 20
C. Number of days: 60
5. Describe the areas over which the flights to be conducted and address of base operation:
The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be
conducted in North America.
6. Describe the aircraft configuration:
This Aircraft is a standard Beech Jet 400A with new Williams FJ44-3AP engines and upgraded avionics with
full authority digital engine controls (FADEC)
a. Maintenance Program
1. Hawker Beechcraft Maintenance Manual Chapter 5 Rev C22 or later with the exception of the
JT15D Engines.
2. Williams International recommended FJ44 3A Maintenance manual (FADEC maintenance is
covered in 71-00-00 of this manual)
3. Maintenance Requirements for the Throttle Quadrant is addressed in the Instructions for
Continued Airworthiness on the FJ44-3AP STC.
430
Chief inspector
NEXTANT
Nextant Aerospace
202
Tel Work
INSPECT
Cell
EFTA00011979

=== Page 312 ===

=== Page 313 ===
Cleveland, Ohio 44143
flightOptions
November 13, 2013
Nextant Aerospace, LLC
Cleveland, Ohio 44143
Attention:
Re:
RK-244 - Agent Authorization
To whom it may concern:
This letter is to confirm that Flight Options, LLC ("FO") authorizes Nextant Aerospace,
LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration
Number N493LX (also identified as a "Nextant 400XT"), which is owned by FO, for any and all
authorized FAA actions in regards to:
X
Airworthiness Classification Experimental
Airworthiness Classification Standard
Sincerely,
Flight Options, LLC
By:
Vice President, Administration & Contracts
NOT ARIAL SEAL
NOTARY PUBLIC
STATE OF OHIO
11/13/13
STATE
OF
OHIO
My Comm. Expires April 24, 2016
EFTA00011981

=== Page 314 ===
MARK
EFTA00011982

=== Page 315 ===
FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE
Form Approved O.M.B. No. 2120-0018
Expiration Date 02/28/2013
APPLICATION FOR
INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA
U.S. Department
U.S. AIRWORTHINESS
use only. Submit original only to an authorized FAA Representative. If additional
Accepted GS Jun/28/2013
of Transportation
space is required, use attachment For special flight permits complete Sections
Federal Aviation
CERTIFICATE
II, VI, and VII as applicable
Administration
1. REGISTRATION MARK
2. AIRCRAFT BUILDER'S NAME (Make)
3. AIRCRAFT MODEL DESIGNATION
4. YR. MFR.
FAA CODING
N493LX
Raytheon Aircraft Co
400A
1999
IL AIRCRAFT
DESCRIPTION
5. AIRCRAFT SERIAL NO.
6. ENGINE BUILDER'S NAME (Make)
7. ENGINE MODEL DESIGNATION
RK244
Williams International
FJ44-3AP
8. NUMBER OF ENGINES
9. PROPELLER BUILDER'S NAME (Make)
10. PROPELLER MODEL DESIGNATION
11. AIRCRAFT IS (Check if applicable)
2
N/A
N/A
IMPORT
APPLICATION IS HEREBY MADE FOR: (Check applicable items)
A
1
STANDARD AIRWORTHINESS CERTIFICATE (indicate category)
NORMAL
UTILITY
ACROBATIC
TRANSPORT
COMMUTER
BALLOON
OTHER
B
SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)
7
PRIMARY
9
LIGHT-SPORT (Indicate Class)
Airplane
Power-Parachute
Weight-Shift-Control
Glider
Lighter than Air
2
LIMITED
1
CLASS I
5
PROVISIONAL (Indicate class)
2
CLASS II
1
AGRICULTURE AND PEST CONTROL
2
AERIAL SURVEY
3
AERIAL ADVERTISING
3
RESTRICTED (Indicate operation(s)
4
FOREST (Widlife conservation)
5
PATROLLING
6
WEATHER CONTROL
II. CERTIFICATION REQUESTED
to be conducted)
0
OTHER (Specify)
1
RESEARCH AND DEVELOPMENT
2
AMATEUR BUILT
3
EXHIBITION
4
AIR RACING
5
CREW TRAINING
6
MARKET SURVEY
0
TO SHOW COMPLIANCE WITH THE CFR
7
OPERATING (Primary Category) KIT BUILT AIRCRAFT
BA
Existing aircraft without an airworthiness certificate & do not meet $ 103.1
4
EXPERIMENTAL (Indicate operation(s)
to be conducted)
OPERATING
8
88
Operating Light-Sport Kit-built
LIGHT-SPORT
8C
Operating light-sport previously issued special light-sport category airworthiness
certificate under § 21.190
UNMANNED
9A
RESEARCH AND DEVELOPMENT
9C
CREW TRAINING
9
AIRCRAFT
98
MARKET SURVEY
1
FERRY FLIGHT FOR REPAIRS ALTERATIONS MAINTENANCE OR STORAGE
SPECIAL FLIGHT PERMIT (Indicate
2
EVACUATE FROM AREA OF IMPENDING DANGER
8
operation to be conducted then complete
Section VI or VII as applicable on reverse side)
3
OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT
4
DELIVERING OR EXPORTING
5
PRODUCTION FLIGHT TESTING
6
CUSTOMER DEMONSTRATION FLIGHTS
C
6
MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE Restricted Operation* and "Standerd" or "Limited" as applicable)
A. REGISTERED OWNER (As shown on certificate of aircraft registration)
IF DEALER, CHECK HERE
NAME
ADDRESS
Flight Options. Flight Options LLC
Richmond Heights OH 44143
B. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated)
AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No and
AIRWORTHINESS DIRECTIVES (Check if of applicable ADs are complied with and give the number
Revision No.)
of the last AD SUPPLEMENT available in the biweekly series as of the date of application)
III. OWNER'S CERTIFICATION
N/A
Bi-Weeky 2013-09, 04/22/2013 - 05/05/2013
AIRCRAFT LISTING (Give page number(s))
SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporated)
N/A
N/A
C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS
CHECK IF RECORDS IN
TOTAL AIRFRAME HOURS
EXPERIMENTAL ONLY (Enter hours flown since last certificate issued
COMPLIANCE WITH
14 CFR section 91.417
8563.80
3
or renewed)
D. CERTIFICATION hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation Administration in
accordance with Title 49 of the United States Code 44101 elseg and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy, and eligible for the
airworthiness certificate requested
DATE OF APPLICATION
05/13/2013
A. THE AIRCRAFT DESCRIBED ABOVE
2
14 CFR part 121 CERTIFICATE HOLDER (Give
3
CERTIFICATED MECHANIC (Give Certificate No.)
CERTIFICATED REPAIR STATION (Give Certificate
IV. INSPECTION
VERIFICATION
Certificate No.)
6
No.)
AGENCY
5
AIRCRAFT MANUFACTURER (Give name or firm)
DATE
TITLE
SIGNATURE
(Check ALL applicable block items A and B)
x
THE CERTIFICATE REQUESTED
A. I find that the aircraft described in Section I or VII meets requirements for
4
AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE
V. FAA REPRESENTATIVE
B. Inspection for a special flight permit under Section VII
FAA INSPECTOR
FAA DESIGNEE
CERTIFICATION
was conducted by:
CERTIFICATE HOLDER UNDER
14 CFR part 65
14 CFR part 121 OR 135
14 CFR part 145
DATE
MIDO/FSDO
OFFICE
MAY/20/2013
CE-48
4
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format -PDF
Page 1 of 2
EFTA00011983

=== Page 316 ===

=== Page 317 ===
A. MANUFACTURER
NAME
ADDRESS
VI. PRODUCTION
FLIGHT TESTING
B. PRODUCTION BASIS (Check applicable item)
PRODUCTION CERTIFICATE (Give production certificate number)
TYPE CERTIFICATE
OTHER:
C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNATURE
A. DESCRIPTION OF AIRCRAFT
REGISTERED OWNER
ADDRESS
BUILDER (Make)
MODEL
SERIAL NUMBER
REGISTRATION MARK
B. DESCRIPTION OF FLIGHT
CUSTOMER DEMONSTRATION FLIGHTS
(Check if applicable)
FROM
TO
VIA
DEPARTURE DATE
DURATION
C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT
VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST
PILOT
CO-PILOT
FLIGHT ENGINEER
OTHER (Specify)
D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS:
E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment if necessary)
F. CERTIFICATION- hereby certify that I am the registered owner (or his agent) of the aircraft described above; that the aircraft is registered with the Federal Aviation
Administration in accordance with Title 49 of the United States Code 44101 etseg and applicable Federal Aviation Regulations and that the aircraft has been inspected and is
safe for the flight described
DATE
NAME AND TITLE (Print or type)
SIGNATURE
x
A. Operating Limitations and Markings in Compliance With 14 CFR Section 91.9,
G. Statement of Conformity, FAA Form 8130-9 (Attach when required)
As Applicable
H. Foreign Airworthiness Certification for Import Aircraft
VIII. AIRWORTHINESS
DOCUMENTATION (FAA/DESIGNEE
X
B. Current Operating Limitations Attached
(Attach when required)
I. Previous Airworthingss Certificate Issued in Accordance With
use only)
C. Data, Drawings, Photographs, etc. (Attach when required)
X
14 CFR Section 21.183(a)
CAR
(Original attached)
X
D. Current Weight and Balance information Available in Aircraft
J. Current Airworthiness Certificate Issued in Accordance With
E. Major Repair and Alteration, FAA Form 337 (Attach when required)
x
14 CFR Section 21.191(a)
(Copy attached)
X
F. This inspection Recorded in Aircraft Records
K. Light-Sport Aircraft Statement of Compliance FAA Form 8130-15 (Attach
when required)
FAA Form 8130-6 (4/11) All Previous Editions Superseded
Electronic Format- PDF
Page 2 of 2
EFTA00011985

=== Page 318 ===

=== Page 319 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION . FEDERAL AVIATION ADMINISTRATION
SPECIAL AIRWORTHINESS CERTIFICATE
CATEGORY/DESIGNATION EXPERIMENTAL
A
PURPOSE
Research and Development
MANU-
NAME
N/A
B
FACTURER
ADDRESS
N/A
FROM
C
N/A
FLIGHT
TO
N-
D
493LX
SERIAL NO. RK244
BUILDER
Raytheon Aircraft Company
MODEL 400A
DATE OF ISSUANCE MAY/20/2013
EXPIRY NOV/16/2013
OPERATING LIMITATIONS DATEMAY/20/2013
ARE PART OF THIS CERTIFICATE
E
DESIGNATION OR OFFICE NO.
DARF-400148-CE
Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or
imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT
IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR).
FAA Form 8130-7 (04/2011) Previous Edition 07/04 May be Used until Depleted
SEE REVERSE SIDE NSN: 0052-00-693-4000
EFTA00011987

=== Page 320 ===
A
This airworthiness certificate is issued under the authority of Public Law 104-6, 49 United States Code
(USC) 44704 and Title 14 Code of Federal Regulations (CFR).
The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct
B
production fight tests, and only production flight tests, of aircraft registered in his name. No person may
conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or
hire: and/or (2) Carrying persons not essential to the purpose of the flight.
C
This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in
Block A.
This airworthiness certificate certifies that as of the date of issuance, the aircraft to which issued has been
inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet the
requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to
D
the Convention On International Civil Aviation. No person may operate the aircraft described on the
reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and
limitations which may be prescribed by the FAA as part of this certificate; (2) over any foreign country
without the special permission of that country.
E
Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the
duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217.
EFTA00011988

=== Page 321 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
NUMBER
Raytheon Aircraft Co.
N493LX
400A
RK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to the Federal Aviation Act of 1958 and certifies that, as of the date of issuance, the aircraft
to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention
on International Civil Aviation, except as noted herein.
Exceptions:
None
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, this airworthiness
certificate is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43.
and 91 of the Federal Aviati
is registered in the United States.
DATE OF ISSUANCE
DESIGNATION NUMBER
R 10/01/1999
AEA-FSD0-23
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or Imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS
FAA Form 8100-2 (3-08)
EFTA00011989

=== Page 322 ===
T1

=== Page 323 ===
Cleveland, Ohio 44143
flightOptions
May 8, 2013
VIA HAND DELIVERY
Nextant Aerospace, LLC
Cleveland. Ohio 44143
Attention:
Re:
RK-244 - Agent Authorization
Ladies and Gentlemen:
This letter is to confirm that Flight Options, LLC ("Flight Options") authorizes Nextant
Aerospace, LLC, as Flight Options' agent, for a Beechjet 400A, bearing serial number RK-244 and
FAA Registration Number N493LX, which is owned by Flight Options, for any and all authorized
FAA actions.
Sincerely,
FLIGHT OPTIONS, LLC
Vice President of Whole Aircraft
Acquisitions and Sales
NOTARIAL
NOTARY PUBLIC
STATE OF OHIO
STATE
OHIO
My Comm. Expires April 24, 2016
OF
5/17/13
EFTA00011991

=== Page 324 ===
EFTA00011992

=== Page 325 ===
U.S. Department
of Transportation
Federal Aviation
Administration
EXPERIMENTAL OPERATING LIMITATIONS
PURPOSE
Research and Development
MAKE
Raytheon Aircraft
MODEL
400A
Company
SERIAL
REGISTRATION
N493LX
RK244
NUMBER
1) No person may operate this aircraft unless FAA Form 8130-7 is displayed at the cabin or cockpit entrance and
is visible to passengers or flightcrew members.
2) No person may operate this aircraft for other than the purpose of RESEARCH AND DEVELOPMENT to
accomplish the flight operation outlined in the program letter, dated May 13, 2013, which describes compliance
with 14 CFR $21.193(d) and has been made available to the pilot-in-command of the aircraft. In addition, this
aircraft must be operated in accordance with applicable air traffic and general operating rules of 14 CFR Part
91, and all additional limitations herein prescribed under the provisions of 14 CFR $ 91.319(i).
3) All flights must be conducted within the 48 contiguous United States of America, except for takeoffs and
landings, this aircraft must not be operated over densely populated areas or in congested airways except when
otherwise directed by Air Traffic Control or in an emergency situation.
4) N/A
5) N/A
6) N/A
7) This aircraft must not be operated unless it is inspected and maintained in accordance with appropriate military
technical publications and/or manufacturer's recommendations. The owner/operator must select, establish,
identify, and use an inspection program as set forth in 14 CFR $91.409(e), (f), (g) and (h). This inspection
program must be recorded in the aircraft maintenance records.
8) The Pilot in Command of this aircraft must hold an appropriate category/class rating. If required for the type of
aircraft to be flown, the Pilot in Command must also hold either an appropriate type rating or a letter of
authorization issued by an FAA Flight Standards Operations Inspector.
9) N/A
10) N/A
11) This aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance
with 14 CFR § 91.205. All test maneuvers must be conducted during day Visual Meteorological Conditions
(VFR).
12) No person may operate this aircraft for carrying persons or property for compensation or hire.
13) No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight.
14) N/A
15) The pilot in command of this aircraft must advise each passenger of the experimental nature of this aircraft, and
explain that it does not meet the certification requirements of a standard certificated aircraft.
16) This aircraft must contain the placards, markings, etc., (or other operating instructions developed for an STC
modification) as required by 14 CFR $91.9.
Total Pages:
3
EFTA00011993

=== Page 326 ===

=== Page 327 ===
EXPERIMENTAL OPERATING LIMITATIONS
PURPOSE
Research and Development
MAKE
Raytheon Aircraft
MODEL
400A
Company
SERIAL
REGISTRATION
N493LX
RK244
NUMBER
Page 2 of
3
17) This aircraft is prohibited from aerobatic flight; that is, an intentional maneuver involving an abrupt change in
the aircraft's attitude, an abnormal attitude, or abnormal acceleration not necessary for normal flight.
18) This aircraft may conduct aerobatic flight in accordance with 14 CFR $ 91.303. Aerobatics must not be
attempted until sufficient flight experience has been gained to establish that the aircraft is satisfactorily
controllable and in compliance with 14 CFR 91.319(b). Aerobatic maneuvers intended to be performed must
be satisfactorily accomplished and recorded in the aircraft records during the flight test period.
19) N/A
20) This aircraft must not be used for glider towing, banner towing, or intentional parachute jumping.
21) No person must operate this aircraft unless within the preceding 12 calendar months it has had a condition
inspection performed in accordance with the scope and detail of 14 CFR part 43 appendix D, or other FAA-
approved programs and was found to be in a condition for safe operation. This inspection will be recorded in
the aircraft maintenance records.
22) FAA-certificated repair stations and FAA-certificated mechanics with appropriate ratings as authorized by 14
CFR $43.3 may perform inspections required by these operating limitations.
23) Inspections must be recorded in the aircraft maintenance records showing the following or a similarly worded
statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the scope and
detail of 14 CFR part 43, appendix D, or other FAA-approved programs, and was found to be in a
condition for safe operation." The entry will include the aircraft total time-in-service, and the name,
signature, certificate number and type of certificate held by the person performing the inspection.
24) If aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made in the
aircraft records.
25) This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements of
14 CFR Part 43.
26) This aircraft must display the word EXPERIMENTAL in accordance with 14 CFR $45.23(b).
27) The pilot-in-command of this aircraft must notify Air Traffic Control of the experimental nature of this aircraft
when operating into or out of airports with operating control towers. The pilot in command must plan routing
that will avoid densely populated areas and congested airways when operating VFR.
28) This aircraft does not meet the requirements of the applicable, comprehensive and detailed airworthiness code
as provided by Annex 8 to the Convention on International Civil Aviation (ICAO). The owner/operator of this
aircraft must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to
operating this aircraft in or over that country. That written permission must be carried aboard the aircraft
together with the U.S. airworthiness certificate, and upon request, be made available to an FAA inspector or the
CAA in the country of operation.
29) Aircraft instruments and equipment installed and used under 14 CFR $91.205 must be inspected and maintained
in accordance with the requirements of parts 14 CFR parts 43 and 91. Any maintenance or inspection of this
equipment must be recorded in the aircraft maintenance records.
30) Application must be made to the geographically responsible MIDO (Cleveland, OH MIDO) for any revision to
these operating limitations.
31) 14 CFR $ 47.45 requires that the FAA Aircraft Registry must be notified within 30 days of any change in the
aircraft registrant's address. Such notification is to be made by submitting Aeronautical Center Form 8050-1 to
AFS-750 in Oklahoma City, Oklahoma.
32) Condition inspections must be performed in accordance with 14 CFR part 43, appendix D at least every 100
flight hours. The inspections must be performed by an FAA-certificated mechanic with appropriate ratings as
defined in 14 CFR 8 43 3
EFTA00011995

=== Page 328 ===
EFTA00011996

=== Page 329 ===
EXPERIMENTAL OPERATING LIMITATIONS
PURPOSE
Research and Development
MAKE
Raytheon Aircraft
MODEL
400A
Company
SERIAL
REGISTRATION
N493LX
RK244
NUMBER
Page 3 of
3
33) Familiarization flights must be conducted only over sparsely populated areas. If aerobatics are involved, the
applicant must inform the local FAA office and additional limitations may be imposed as necessary.
DARF-400148-CE
May 20, 2013
Signature
EFTA00011997

=== Page 330 ===

=== Page 331 ===
nextant aerospace
Quality Assurance Department
To:
Federal Aviation Administration
Date: May 13, 2013
Flight Standards District Office
North Olmsted, Ohio 44070
From:
Director of Quality Assurance
Nextant Aerospace
Subject: FAA Program letter for Beech Jet 400A, Serial number RK244, Registration Number N493LX.
Ref: FAA order 8130.2G
1. Registered Owner: Flight Options LLC. Address:
Richmond Heights, Ohio 44143
2. Aircraft Description: Twin Engine Light Jet
a. Registration: N493LX
b. Aircraft Builder Raytheon Aircraft Co
c. Year mfg.: 1999
d. Aircraft Serial Number: RK244
e. Aircraft Model Designation: Beech Jet 400A
3. The program purpose for the aircraft will be used To complete the flight performance profile in Research
& Development Category in support of FAA Project SA 15250LA-T (Replacement of Wingtips)
4. Program Duration
a. List the estimated flight hours required for program: 300 Hrs
b. Number of flights: 100
C. Number of days: 180
5. Describe the areas over which the flights to be conducted and address of base operation:
The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be
conducted in North America.
6. Describe the aircraft configuration:
This Aircraft is a standard Beech Jet 400A with new Williams FJ44-3AP engines and upgraded avionics with
full authority digital engine controls (FADEC)
a. Maintenance Program
1. Hawker Beechcraft Maintenance Manual Chapter 5 Rev C22 or later with the exception of the
JT15D Engines.
2. Williams International recommended FJ44 3A Maintenance manual (FADEC maintenance is
covered in 71-00-00 of this manual)
3. Maintenance Requirements for the Throttle Quadrant is addressed in the Instructions for
Continued Airworthiness on the FJ44-3AP STC.
Senior Inspector
Nextant Aerospace
EFTA00011999

=== Page 332 ===
EFTA00012000

=== Page 333 ===
LOG BOOK ENTRY
from Designated Airworthiness Representative (DAR)
REGISTRATION
AIRCRAFT
SERIAL No.
TT/TSN
LANDINGS/CYCLES
NUMBER
MAKE/MODEL
N493LX
Raytheon Aircraft Company
RK244
8563.8
7115
400A
I find that the aircraft meets the requirements for the certification requested and have issued a Special Airworthiness
Certificate dated May 20, 2013 for the purpose of Research and Development. Limitations dated May 20, 2013 and issued
with this certificate must be complied with.
The aircraft must be maintained in accordance with manufacturer's requirements unless another FAA approved maintenance
program is utilized. Issuance of this certificate does not eliminate or replace any required maintenance requirements.
The Special Airworthiness Certificate has been issued as required to support Research and Development flight-testing as
defined in the applicant's program letter. The Standard Airworthiness Certificate dated R 10/01/1999 has been superseded.
MAY/20/2013
Date
EFTA00012001

=== Page 334 ===
EFTA00012002

=== Page 335 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No
RK-244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options .LLC
City
Richmond Heights
State OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
05/30/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Designation No.
CRS # 25NR667B
05/30/2013
FAA Form 337 (10-06)
EFTA00012003

=== Page 336 ===

=== Page 337 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Part I of 3
The Following Equipment was removed along with Associated Hardware.
EFD-871
622-9345-203
Electronic Flight Display
EFD-871
622-9345-203
Electronic Flight Display
MFD-871
622-9434-213
Multi Function Display
ICU-85
622-6189-002
Internal Compensation Unit
ICU-85
622-6189-002
Internal Compensation Unit
AHC-85E
622-9336-400
Attitude/Heading Computer
AHC-85E
622-9336-400
Attitude/Heading Computer
SDU-640B
622-9735-001
Sensor Display Unit
SDU-640B
622-9735-001
Sensor Display Unit
DCP-5000
822-1028-011
Display Control Panel
DCP-5000
822-1028-011
Display Control Panel
ARP-851
622-9500-011
Altitude Reference Panel
ARP-851
622-9500-011
Altitude Reference Panel
AAP-851
822-0328-011
Altitude Awareness Panel
AAP-851
822-0328-011
Altitude Awareness Panel
CHP-850
622-7397-002
Course Heading Panel
DBU-4100
822-0014-002
Data Base Unit
DAU-650
622-9344-101
Data Acquisition Unit
SDD-640A
622-9347-001
Sensor Display Driver
IOC-4000 (4)
622-9814-514
Card Assembly
MDC-4000
622-9818-751
Maintenance Computer
CSU-4000 (2)
822-0049-002
Configuration Strapping Unit
FMC-5000 (4)
822-0891-008
Flight Management Computer
PWR-4000 (4)
622-9945-021
IAPS Power Card
GPS-4000
822-0931-003
GPS Receiver
Mounts
622-9430-002
EFD /MFD Mounts
EFB
Electronic Flight Bag Mounting
X
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00012005

=== Page 338 ===

=== Page 339 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
5/30/2013
Nationality and Registration Mark
Date
Page 2 of 3
Installed the Following Equipment along with Associated Hardware.
Model
Part Number
Description
Weight
Arm
CCP-3000
822-1746-002
Cursor Control Panel
2.60
90.0
CCP-3000
822-1746-002
Cursor Control Panel
2.60
90.0
DCU-3001C
822-2362-003
Data Concentrator Unit
5.0
325
DCU-3001C
822-2362-003
Data Concentrator Unit
5.0
325
ECU-3000
822-1200-209
External Compensation Unit
0.40
57.5
ECU-3000
822-1200-209
External Compensation Unit
0.40
57.5
FSU-5010
822-1543-101
File Server Unit (1st IFIS)
6.5
60.83
ECU-3000
822-1200-998
File Server Unit (1st IFIS)
0.40
57.5
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
AFD-3010E
822-1753-416
Adaptive Flight Display
12.90
89.2
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
IMT-3010
822-1140-401
AFD Mounting Rack
4.40
85.0
10852B01Y00
Fuel Quantity Conditioner
0.90
324
PC920-2A2000PH-2A1
Fuel Flow Conditioner
1.10
325
GPS-4000S
822-2189-004
GPS Receiver
6.0
37
CI 429-410
GPS Antenna
1.0
166.14
Amp Cluster
N241100-002
DC Voltmeter
1.5
97.4
373-93-1501-1
Speed Switch (2)
0.25
89.2
DBU-5010E
822-3000-202
Data Base Unit
1.60
134.5
PS-835D
501-1228-004
Power Supply
12.5
52.9
MMT-5000
822-1811-003
File Server Unit Rack
0.30
57.5
MMT-3010 (2)
822-1290-003
AHS Mounting Rack
1.80
57.5
XM WR-1000
822-2031-002
XM Weather
1.5
41.0
CHP-3010
822-1280-003
Course Heading Panel
1.30
92.5
Options Configuration Module.
OCM-4100
822-1463-228
0.30
57.5
WAAS/LPV
OCM-4100
Options Configuration Module.
822-1463-228
0.30
57.5
WAAS/LPV
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00012007

=== Page 340 ===

=== Page 341 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Page 3 of 3
Model
Part Number
Description
Weight
Arm
CSU-4100 (2)
822-1364-002
Configuration Strapping Unit
1.60
55.7
MDC-3110
822-1987-006
Maintenance Data Computer
0.80
55.7
FMC-6000 (2)
822-0868-123
Flight Management Computer
1.90
55.7
ADC-850D (2)
822-0389-468
Air Data Computer
5.30
60.83
AHC-3000A (2)
822-1378-001
Attitude Heading Computer
4.80
57.5
DCP-3030 (2)
822-1828-002
Display Control Panel
1.90
89.96
PWR-4000 (4)
622-9945-022
IAPS Power Card
1.3
55.0
IOC-4100 (4)
822-1362-511
Input/output Concentrator
0.8
55.0
LT-4001-010
Master Caution Panel
1.3
87.0
Rev. Panel
373-91-3203-1
Pilot Reversion Panel
0.2
88.0
Rev. Panel
373-91-3203-3
Co-pilot Reversion Panel
0.2
88.0
9-PED
373-91-3203-9
9-Pedestal Panel
1.8
92.89
345-6196
ELT Switch
0.2
88.0
Annunciator
Led-42-12-BB-E0Y47
AUX BATT (1/2) Annunciator
0.05
88.0
Annunciator (2)
Led-40-18-BB-E0Y45
Pull Up/ Terrain Annunciator
0.05
88.0
Annunciator
2-F840231
Terrain Inhibit/ Terrain Fail
0.05
88.0
In Accordance with STC ST10959SC. See Attached Copy
AFM Supplement, Nextant Aerospace Doc. No. 373-00-0023 Rev IR Dated 09/02/2011 or later FAA approved revision,
installed on Aircraft.
Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad.
NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic
Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization
for their use from their managing Flight Standards District Office.
Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document 373-00-0002.Rev C or Later are included in
the Aircraft Maintenance Records
Carried out System Ground Test Plan IAW Master Drawing List (MDL) 373-00-004 Rev C.
Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection
/ Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43
appendix "F" Transponder System checks.
Additional Sheets Are Attached
Form 337 (10-06)
EFTA00012009

=== Page 342 ===

=== Page 343 ===
United States of America
Department of Transportation -- Federal Abiation Administration
Supplemental Type Certificate
Number ST10959SC
This certificate issued to
Nextant Aerospace LLC
Richmond Heights, OH 44143
certifies that the change in the type design for the following product with the limitations and conditions therefor as
specified hereen meets the airworthiness requirements of Parl 25 of the Federal Aviation Regulations (See Pages 3
and 4 for complete certification basis.)
Original Product Type Certificate. Number
A16SW
Make
Hawker Beechcraft Corp.
Model 400A
Description of Type Drign Change Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument
System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV)
approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System
(TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. 373-00-0001 Revision
W, dated March 29, 2012, or later FAA approved version.
Bimilations and Conditions:
1) The installer must determine whether this design change is compatible with previously approved
modifications.
2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must
give that person written evidence of that permission.
3) For aircraft equipped with Pratt & Whitney JT15D Engines FAA approved Airplane Flight Manual
Supplement, Nextant Aerospace LLC Doc. No. 373-00-0008 Revision IR, dated 10/19/2009, or later
FAA approved version, is required on board the modified aircraft.
This certificate and the supporting data which is the Rasin for approval shall remain in offert until surrendered
inspended reverfed ~ a termination date is thereise stablished Ry the Administrator of the Federal Amiation
Administration
Date of application June 26, 2008
Date reisound
Date of October 19. 2009
Date amended September 26, 201 April 05, 2012
By directing of you.
FEDERAL
AVIATION
Manager, Systems and Flight Test Branch
ADMINISTRATION
Chicago Aircraft Certification Office
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000. or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2(10-68)
PAGE 1 of 4 PAGES
This certificate may be transferred in accordance with FAR 21.47. .
EFTA00012011

=== Page 344 ===

=== Page 345 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST10959SC
Date of issuance October 19, 2009
Date Amended: September 26, 2011; April 05, 2012
Bimilations and Conditions (continued):
4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under STC
ST02371LA.
5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual
Supplement, Nextant Aerospace LLC Doc. No. 373-00-0023 Revision IR, dated September 2, 2011,
or later FAA approved version, is required on board the modified aircraft.
6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via:
RK-1 thru RK-117 and RK-119 thru RK-139, Hawker Beechcraft Service Bulletin No. 34-3431.
RK-118, RK-140 thru RK-224, Hawker Beechcraft Service Bulletin Nos. 34-3228 and 34-3431.
RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431.
RK-300 and after as original equipped from Hawker Beechcraft.
7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved
Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0036 Revision IR,
approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft.
8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane
Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0032 Revision IR, approved
March 28,2012, or later FAA approved version, is required on board the modified aircraft.
Certification Basis:
Based on 14 CFR $21.115 and 21.101, and the FAA policy for significant changes in FAA Order
8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows:
a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS A16SW
for parts not changed or not affected by this change.
b. The certification basis for the parts changed or affected by this change since the reference date of
application, September 29, 2009, is based on TCDS A16SW and §§ 14 CFR Part 25 as shown on
page 4 of 4 of this STC.
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 3 of 4 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00012013

=== Page 346 ===

=== Page 347 ===
United States of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Date of issuance October 19, 2009
Date Amended: September 26, 2011: April 05, 2012
Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48,
the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight
Instrument System (EFIS) with Rockwell Collins FMS-6100 modification was determined to be TCDS
A16SW and the following later regulations:
Amdt.[24-4]
Amdt.[25-23]
Amdt.[25-38]
Amdt.[25-40]
Amdt.[25-41]
25.771 (a,e)
25.301; 25.303; 25.581;
25.1309
25.901 (b)(1)(i); 25.1549
25.1321 (a)(b)(c)(c):
25.607; 25.611, 25.773
(a)(b)(c)(d)(e)(g):
(a)(b)(c)
25.1331; 25.1333
(a)(1)(2)(d)
25.1322
Amdt.[25-42]
Amdt.[25-46]
Amdt.[25-54]
Amdt.[25-72]
Amdt.[25-80]
25.1501
25.603; 25.605; 25.613;
25.1529
25.307; 25.571, 25.1307
25.1316
25.1329 (h)
(c)(e); 25.1351 (a)(1)(d);
25.1381: 25.1521 (a)(c);
25.1543 (b): 25.1581:
25.1583 (a)
Amdt.[25-86]
Amdt.[25-90]
Amdt.[25-91]
Amdt.[25-102]
Amdt.[25-105]
25.305
25.1303
25.561
25.981 (a)(b)
25.1585 (n)
Amdr.[25-108]
Amdt.[25-109]
Amdt.[25-113]
Amdt.[25-122]
Amdt.[25-123]
25.1325( (d)
25.1323(a)(f)(g)
25.869 (a)(4); 25.1431
25.1317(a)(b)(c)
25.1353(a)(c)
Based on 14 CFR §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48,
the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS
was determined to be TCDS A16SW and the following later regulations:
Amdt.[Original]
Amdt.[24-4]
Amdt.[25-23]
Amdt.[25-38]
Amdt.[25-40]
25.601, 25.605, 25.609.
25.771 (a)
25.301; 25.303; 25.305,
25.603. 25.1322,
25.1585(a)
25.613. 25.1301,
25.307, 25.561(c);
25.1583(c)
25.1357, 25.1381,
25.607; 25.611, 25.1307
25.1525. 25.1541.
15.1581
Amdt.[25-41]
Amdt.[25-42]
Amdt.[25-46]
Amdt.[25-54]
Amdt.[25-72]
25.1309 (a)(b)(c)(d)(e)(g)
25.1501
25.777(a)(c)
25.1529
25.869(a)(1)
25.1351 (a)(I)
Amdt.[25-102]
Amdt.[25-113]
Amdt.[25-123]
25.981(a)(b)
25.1431(a)
25.1353 (a)(c)
- END -
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2-1(10-69)
PAGE 4 of 4 PAGES
This certificate may be transferred in accordance with FAR 21.47.
EFTA00012015

=== Page 348 ===

=== Page 349 ===
Form Approved
Electronic Tracking Number
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
11/30/2007
U.S Department of
Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act 1958)
Nationality and Registration Mark
Serial No.
RK 244
N493LX
1. Aircraft
Make
Model
Series
Raytheon Aircraft Company
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
Address
Flight Options LLC
City
Richmond Heights
State. OH
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial Number
X
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name
Nextant Aerospace
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City
Cleveland
State OH
X
Certificated Repair Station
Zip
44143-1453 Country USA
Certificated Maintenance Organization
CRS # 25NR667B
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individ
per 14 CFR Part 43
05/30/2013
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Fit Standards
Person Approved by Canadian
Manufacturer
Inspector
Maintenance Organization
Department of Transport
BY
Other (Specify)
FAA Designee
X
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individua
Designation No.
05/30/2013
CRS # 25NR667B
FAA Form 337 (10-06)
EFTA00012017

=== Page 350 ===
EFTA00012018

=== Page 351 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
N493LX
05/30/2013
Nationality and Registration Mark
Date
Nextant Aerospace Completed STC # ST02371LA
Removed Pratt and Whitney JT15D-5 Series Engines
Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance
with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA
Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions.
Installed Left Engine Part Number. 111000-202 Serial No. 252757
Installed Right Engine Part Number 111000-202 Serial No. 252758
ICA
AFM Supplement was installed on Aircraft.
Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted
revisions are included in the Aircraft Maintenance Records.
Carried out Engine Ground Runs and System OPS checks IAW Ground Test Plan 373-00-0024 Rev F.
End
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00012019

=== Page 352 ===
EFTA00012020

=== Page 353 ===
United States Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
Number ST02371LA
This Certificate issued to
Nextant Aerospace, LLC
Richmond Heights, Ohio 44143
certifies that the change in the type design for the following product with the limitations and conditions
therefore as specified hereon meets the airworthiness requirements of Part 25* oftho Federal Buiation
Regulations. *Certification basis is set forth on TCDS A16SW and continuation sheets 3 and 4.
Original Product Type Certificate A16SW
Abaka: Hawker Beechcraft
Abodel:
400A
Description of Types Design Change Replacement of Pratt & Whitney JT15D-5 series engine with Williams
International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and
associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001,
Revision IR dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight
Manual Supplement, NXTI-AFMS, Rev IR, dated September 15, 2011 or later FAA approved revisions.
Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXTI-ICA, Revision IR, or
later FAA accepted revisions must be provided with this STC.
Bimilations and Conditions The installation should not be incorporated in any aircraft unless it is
determined that the interrelationship between this installation and any previously approved configuration
will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this
modification applies to the above-noted airplane models only. If the holder agrees to permit another
person to use this certificate to alter the product, the holder shall give the other person written evidence of
that permission.
(CONTINUED on page 3)
This certificate and the supporting data which is the basis for approval shall remain in effect until
surrendered suspended revoked or a termination date is otherwise established by the Administrator of the
Federal Aviation Administration
Date of application:
March 24, 2008
Date reissued:
Date of issuance:
September 27, 2011
Date amended:
FEDERAL
AVIATION
ministrator
(Signature)
ADMINISTRATION
Manager, Propulsion Branch
Los Angeles Aircraft Certification Office
(Title)
Any afteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
FAA Form 8110-2(10-68)
Page 1 of 4
This certificate may be transferred in accordance with FAR21.47.
EFTA00012021

=== Page 354 ===
EFTA00012022

=== Page 355 ===
INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of
the transfer of this Supplemental Type Certificate.
The FAA will reissue the certificate in the name of the transferee and forward it to him.
TRANSFER ENDORSEMENT
Transfer the ownership of the Supplemental Type Certificate Number
to (Name of transferee)
(Address of transfer).
(Number and street)
(City, State, and Zip code)
from (Name of grantor) (Print or type)
(Address of grantor)
(Number and street)
(City, State, and Zip code)
Extent of Authority (if licensing agreement):
Date of Transfer:
Signature of grantor (In ink):
Page 2 of 4
EFTA00012023

=== Page 356 ===
EFTA00012024

=== Page 357 ===
United States Of America
Department of Transportation - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Bimilations and Conditions (continued)
Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC
ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this
alteration.
The new Vmca and Vmcg values are 94 KIAS and 93 KIAS respectively.
The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature
of 77°F.
Approved engine fuels are:
Grade
Specification
Jet A
ASTM-D 1655
Jet A-1
ASTM-D 1655
Certification Busis
The certification basis for this modification is as follows:
The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS
A16SW, Revision 26, dated March 17, 2010:
Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by 25-1 through 25-40, plus §§
25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; §§ 25.29, 25.255, and 25.1353(c)(6) of
Amendment 25-42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations
effective December 1, 1969, as amended by 36-1 through 36-17; SFAR 27 effective February 1, 1974, as amended by
27-1 through 27-5: and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at
45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy
Protection). (See NOTE 12)
Equivalent Safety Items:
(1) Out-of-trim characteristics § $ 25.255
(2) Pilot compartment view $ 25.773(b)(2)
(3) Passenger compartment door § 25.813(c)
(4) Emergency exit marking §§ 25.811(d)(1) and 25.811(d)(2)
Application for amended Type Certificate dated February 18, 1988.
Regulation at a later amendments for components and areas affected by the change (Ref. FAA
approved Compliance Check List):
Subpart A- General 25.2(25-99)
Subpart B - Flight: 25.207(25-121), 25.255(25-42)
Subpart C- Structure: 25.571 (25-96)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both
FAA Form 8110-2110-60)
Page , of 4
This certificate may be transferred in accordance with FAR 21.47.
EFTA00012025

=== Page 358 ===

=== Page 359 ===
United States Of America
Department of Transportation - - Federal Abiation Administration
Supplemental Type Certificate
(Continuation Sheet)
Number ST02371LA
Certification Busis (continued)
Subpart D - Design and Construction: 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112),
25.625(25-72), 25.832(25-72), 25.863(25-46), 25.869(25-123),
Subpart E- Powerplant: 25.901(25-46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125),
25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42),
25.1045(25-57), 25.1091(25-100), 25.1093(25-72, 25.1103(25-46), 25.1141(25-115), 25.1143(25-57),
25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57),
25.1195(25-46), 25.1203(25-123), 25.1207(25-46).
Subpart F - Equipment: 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123),
25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123),
25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41),
Subpart G- Operating Limitations and Information: 25.1501(25-42), 25.1521(25-72), 25.1527(25-
105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72),
25.1583(25-105).
Subpart H- - Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123),
25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123),
25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123),
25.1729(25-123), 25.1731(25-123), 25.1733(25-123).
14 CFR Part 34 (34-3): 34.11
14 CFR Part 36 (36-28): 36.1--36.7, 36.101-36.105, 36.1501, 36.1581.
The following Nextant Aerospace Continued Airworthiness Supplements are applicable to
airplanes modified in accordance with this STC:
Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved
revisions.
EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXT1-EA-007 Rev
A dated 8/24/11 or later FAA approved revisions.
-END-
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both
PAA Form 8110-2(10-68)
Page 4 of 4
This certificate may be transferred in accordance with FAR21.47.
EFTA00012027

=== Page 360 ===

=== Page 361 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
11/30/2007
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Foderal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for
each such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
USA, N493LX
RK-244
1. Aircraft
Make RAYTHEON AIRCRAFT COMPANY
Model
Series
ICAO AIRCRAFT ADDRESS CODE:51416115
400A
Not Applicable
Name (As shown on registration certificate)
Address (As shown on registration certificate)
FLIGHT OPTIONS LLC
Address
2. Owner
FLIGHT OPTIONS LLC
City
RICHMOND HEIGHTS
State OHIO
Zip 44143-1453
3, For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Flight Options LLC
U.S. Certificated Mechanic
Manufacturer
Address
Foreign Certificated Mechanic
C. Certificate No.
City Binghamton
State NY
Certificated Repair Station
DJFA206D
Zip 13904
USA
X
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of A
per 14 CFR Part 43
App. B
7. Approval for Retarn Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
Approved
Rejected
FAA Flt. Standards
X
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Author
Designation No. DJFA 206D
FAA Form 337 (10-06)
EFTA00012029

=== Page 362 ===
EETA00012030

=== Page 363 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N493LX
4/3/2012
Nationality and Registration Mark
Date
Removed EFB Mount Assembly that was previously installed under Engineering Order M25-10/05-011.
The aircraft weight and balance has been updated.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: None
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00012031

=== Page 364 ===
EFTA00012032

=== Page 365 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
NUMBER
Raytheon Aircraft Co.
N493LX
400A
RK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is Issued pursuant to the Federal Avistion Act of 1958 and certifies that, as of the date of Issuance. the aircraft
to which Issued has been Inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention
on International CMI Aviation. except as noted herein.
Exceptions:
6 TERMS AND CONDITIONS
None Copy
Unless sooner surrendered, suspended, revoked. or a termination date is otherwise establishe by the Administrator, this airworthiness
certificate is effective as long as the maintenarys, preventative maintenance, and alterations are performed in accordance with Parts 21, 43.
and 91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered in the United States.
DATE OF ISSUANCE
DESIGNATION NUMBER
R 10/01/1999
AEA-FSDO-23
Any afterstion, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or Imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERALAVIATION REGULATIONS.
FAA Form 8100-2 (3-08)
EFTA00012033

=== Page 366 ===
\
-
n

=== Page 367 ===
OPTIONS
ENGINEERING ORDER
On - Higher Plane
Aircraft Type
Aircraft Number
Serial Number
Station
Engineering Order Number
Revision Number
Date
Page 1 of:
M25-10/05-011
Original
10-19-2005
1
ENGINEERING ORDER TITLE
Electronic Flight Bag Mount Installation - Beechjet 400 Fleet
Effectivity:
Aircraft serial numbers RK-123 and after
Description:
To install a fabricated mount assembly near the co-pilots map light
rheostat to hold the electronic flight bag computer
Accompanying
Work Compliance Instructions Form, DER approved Engineering
Documents:
Directive EDW01-5, FAA forms 337 and 8110-3,
Reason:
For the effective aircraft to obtain a paperless cockpit environment
Prepared By
Signature
Date
Keith Gawsyszawski
10-19-2005
Quality Assurance
Date
Robert Beaumont
10:21-05
Approved By
Date
Todd Hattaway
10/21/05
Regulatory Compliance
X
Major Repair
Minor Repair
FAA Approval
X
Yes
No
Weight
Arm
Weight & Balance Affected
X
Yes
No
4 lb increase
108
Parts Required
Equipment List Update
Yes, FG3500-400N, EFB mount assembly, 4
each AN3-5A bolts, 4 each NAS1149F0363P
Yes
X
No
washers, 1 each -11 placard
Drawings Required
RVSM Status Affected
Yes, 1175TA, rev A, 5245D, rev B, 5244FC,
Yes
X
No
rev B (included in the Engineering Directive)
Publications Affected
AD List Affected
None
Yes
X
No
Estimated Cost
Estimated Labor Hours
$176.00
4.0 hours
Distribution
Remarks / References
X
Maintenance Planning
The planning department shall add this EO to a
scheduled work order whenever an effective aircraft
X
Maintenance
is located at one of the Raytheon dedicated
X
Quality Assurance
maintenance facilities and adequate down time
X
Operations
permits.
Procurement
Priority Code (check all that apply)
Aircraft Manufacturer
X
Federal Aviation Administration
Urgent
X
Mandatory
Attrition
FO-09
GMM Revision 1
09/2005
EFTA00012035

=== Page 368 ===
EFTA00012036

=== Page 369 ===
OPTIONG
WORK COMPLIANCE INSTRUCTIONS
On . Higher Plane
Page:
Aircraft Number:
Station:
Work Order #
Effectivity
1 of 2
RK-123 and after
X
Engineering Order Number:
Fleet Campaign Directive Number:
OR
M25-10/05-011
TITLE
Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet
400A's
Item
Work Description
Mechanic
Inspected
Document the maintenance action on a Flight Options maintenance
01
transaction report form, FO-501 with the following statement in the
discrepancy side: "Accomplishment of Flight Options EO M25-10/05-011
Installation of the Electronic Flight Bag, FG3500 mount assembly is due".
02
Remove electrical power from aircraft and disconnect main aircraft
battery.
Loosen the upper glare shield and right side cover (which contains the
03
reading light and air-cell phone assemblies) by removing the mounting
screws and separating the Velcro strips.
04
Remove the three screws and 90 degree cover panel form the aft edge of
the right side cover panel and discard.
With the glare shield and right side cover disconnected, locate the pre-
existing fastener holes located on the shelf just below the copilots
05
windshield and temporarily install the Electronic Flight Bag (EFB) mount
assembly using the four AN3-5A bolts and NAS1149F0363P plain
washers (included in the kit) to the pre-existing fastener holes. Snug but
do not tighten bolts at this time.
06
Adjust the position of the EFB mount assembly to provide sufficient
clearance between the existing ashtray and the EFB mount thumbscrew.
When proper clearance is achieved in step five, (thumbscrew does not
07
touch the ashtray when rotated). tighten mounting bolts to 22 to 28 inch
pounds (AMM Chap 20).
Reinstall the right side panel. Trim the aft edge of the panel as necessary
to provide clearance between the panel and the 1175TA bracket, as
08
identified in engineering Directive EDW01-5, figure 2, on page 3. Trim
leather covering as necessary and secure with adhesive (contact cement
or equivalent).
09
Verify condition of Velcro on the upper glareshield and right side panel for
proper security. Secure as necessary.
10
Install the EFB computer (Fujitsu) into the holder bracket.
With the EFB mount installed, loosen the thumbscrew knob on the mount
11
assembly ½ to one full turn maximum (do not allow the "Hold-It arm to
separate from the mechanical stop pin in the drawing number 1175 mount
bracket).
With the EFB mount assembly arm loose; verify the co-pilots control
column and wheel does not come in contact with the EFB mount
assembly using the following procedure: Perform this task by moving the
12
control column full travel forward and aft and rotating the control wheel full
left and right while also rotating the EFB mount assembly in all possible
configurations. Verify that the EFB mount assembly does not make
contact with any part of the control yoke and wheel. If contact does not
occur, proceed to step 17 and N/A and initial blocks 13 through 16.
Form Completed By:
Date:
Log Page:
FO-10
GMM Revision 1
09/2005
EFTA00012037

=== Page 370 ===
EFTA00012038

=== Page 371 ===
WORK COMPLIANCE INSTRUCTIONS
On . Higher Mane
Page:
Aircraft Number:
Station:
Work Order #
Effectivity
2 of 2
RK-123 and after
X
Engineering Order Number:
Fleet Campaign Directive Number:
OR
M25-10/05-011
TITLE
Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet
400A's
Item
Work Description
Mechanic
Inspected
If contact occurs, remove the mount assembly "Hold-It" arm, identified in
figure 2 of engineering directive EDW01-5, page 3, by completely
13
removing the thumbscrew. Take note not to lose the wedge shaped
bushing located in the eye of the "Hold-It" arm which supplies the locking
feature of the mount assembly.
Locate the small Allen type set screws and adjust as necessary to move
14
the arm towards the more vertical position. Make 1/4 turn adjustments at a
time.
Reinstall the "Hold-It" arm assembly, taking note to install the wedge
bushing with the tapered end first into the eye of the arm assembly and
15
tighten the thumbscrew. Caution: Make sure the mechanical stop pin
located on the drawing number 1175 mount bracket fits within the
machined slot on the inside part of the eye portion of the "Hold-It" arm
assembly.
16
Repeat steps 10 through 14 until proper clearance between the control
yoke and the EFB is achieved.
After the final adjustments are made to the Allen type set adjustment
17
screws, apply a small amount of Loctite 242 to the screw threads to
secure from loosening.
18
Resecure the upper glareshield to the right side panel by reinstalling the
mounting screws and resecuring the Velcro strips.
19
Attach the power plug to the EFB computer.
Install the fabricated "-11" placard as stated in the engineering directive
20
EDW01-5, page 2, to the right cockpit side wall panel just below the side
window.
21
Reconnect the main aircraft battery. Secure as necessary.
Complete the corrective action side of the Flight Options aircraft
maintenance transaction form FO-501 with the following statement:
22
"Complied with Flight Options EO M25-10/05-011, installation of the
Electronic Flight Bag assembly FG3500-400N in accordance with DER
approved Engineering Directive EDW01-5, see FAA form 8110-3 dated 8-
12-05 and Flight Options Work Compliance Instructions".
Complete the accompanying Engineering Directive checklist on page 2
and the previously FAA field approved form 337 by completing blocks 6
and 7 in its entirety. When completed, forward one copy of the 337 and
23
the complete Engineering Directive package and Form 8110-3 to the
Quality Assurance Department in Binghamton, New York and one copy of
the FAA form 337 and 8110-3 to the local Flight Standards District Office
via US mail within two business days after completion of the installation.
-END-
Form Completed By:
Date:
Log Page:
FO-10
GMM Revision 1
09/2005
EFTA00012039

=== Page 372 ===
EFTA00012040

=== Page 373 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
11/30/2007
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 4701). Failure to report can result in a civil penalty for
each such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
N493LX
RK-244
1. Aircraft
Make
Model
Series
HAWKER BEECHCRAFT CORP
BEECHJET
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
FLIGHT OPTIONS LLC
Address
2. Owner
SHMITKA AIR INC
City
Richmond Heights
State OH
SOUTHEASTERN MILLS INC
ET AL
Zip
44142-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Flight Options, LLC
U.S. Certificated Mechanic
Manufacturer
Address 27 Link Drive Suite B
Foreign Certificated Mechanic
C. Certificate No.
City Binghamton
State NY
Certificated Repair Station
DJFA206D
Zip 13904
Country USA
X
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
 Approved
Rejected
FAA Flt. Standards
X
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FLIGHT OPTIONS
FAA Designee
Repair Station
Inspection Authorization
135 AIR CARRIER CERTIFICATE
Certificate or
Designation No. DJFA 206D
FAA Form 337 (10-06)
EFTA00012041

=== Page 374 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N493LX SN-244
4/11/2011
Nationality and Registration Mark
Date
REPAIRED LEFT FUSELAGE SKIN ABOVE PYLON IAW US TECHNICAL EO6110 227227. 8110-3
DATED MARCH 27, 2011. (WORK ORDER # 227277 SQ-208)
WEIGHT AND BALANCE NEGLIGIBLE
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE
PRACTICES FOR THE LT AFT FUSELAGE SKIN ASSEMBLY REPAIR AS CALLED OUT IN THE
BEECHJET 400A MAINTENANCE MANUAL
EFTA00012042

=== Page 375 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
11/30/2007
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for
each such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
N493LX
RK-244
1. Aircraft
Make
Model
Series
HAWKER BEECHCRAFT CORP
BEECHJET
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
FLIGHT OPTIONS LLC
Address
2. Owner
SHMITKA AIR INC
City
Richmond Heights
State OH
SOUTHEASTERN MILLS INC
ET AL
Zip
44142-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Flight Options, LLC
U.S. Certificated Mechanic
Manufacturer
Address 27 Link Drive Suite B
Foreign Certificated Mechanic
C. Certificate No.
City Binghamton
State NY
Certificated Repair Station
DJFA206D
Zip 13904
Country USA
X
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
per 14 CFR Part 43
App. B
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
$
Approved
Rejected
FAA Flt. Standards
X
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FLIGHT OPTIONS
FAA Designee
Repair Station
Inspection Authorization
135 AIR CARRIER CERTIFICATE
Certificate or
Designation No. DJFA 206D
FAA Form 337 (10-06)
EFTA00012043

=== Page 376 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N493LX SN-244
3/8/2011
Nationality and Registration Mark
Date
REPAIRED LEFT ELEVATOR IAW US TECHNICAL EO5770 226648. 8110-3 DATED APRIL 19
2010 (WORK ORDER # 227277 SQ-97)
WEIGHT AND BALANCE NEGLIGIBLE
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE
PRACTICES FOR THE ELEVATOR AS CALLED OUT IN THE BEECHJET 400A
MAINTENANCE MANUAL
EFTA00012044

=== Page 377 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
11/30/2007
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for
each such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
N493LX
RK-244
1. Aircraft
Make
Model
Series
HAWKER BEECHCRAFT CORP
BEECHJET
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
SHMITKA AIR INC
ET-AL
Address
2. Owner
SOUTHEASTERN MILLS INC
C/O FLIGHT OPTIONS LLC
City
Richmond Heights
State OH
ASCENT 11 LLC
PRIME TIME ASSOCIATES LLC
Zip
44142-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name Flight Options, LLC
U.S. Certificated Mechanic
Manufacturer
Address 27 Link Drive Suite B
Foreign Certificated Mechanic
C. Certificate No.
City Binghamton
State NY
Certificated Repair Station
DJFA206D
Zip 13904
Country USA
X
Certificated Maintenance Organization
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individual
per 14 CFR Part 43
App. B
10-19-2010
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Approved
Rejected
FAA Flt. Standards
X
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FLIGHT OPTIONS
FAA Designee
Repair Station
Inspection Authorization
135 AIR CARRIER CERTIFICATE
Certificate or
Signature/Date of Authorized Individual
Designation No. DJFA 206D
10-19-2010
FAA Form 337 (10-06)
EFTA00012045

=== Page 378 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N493LX SN-244
10/19/2010
Nationality and Registration Mark
Date
SUBSTITUTED FASTENERS IN H-STAB LOWER SKIN PER EO5938 227277IFAD FROM US
TECHNICAL 8110-3 DATED 10/18/2010
WEIGHT AND BALANCE NEGLIGIBLE
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: NORMAL MAINTENANCE PRACTICES
FOR THE HORIZONTAL STABILIZER ASSEMBLY AS CALLED OUT IN THE BEECHJET 400A
MAINTENANCE MANUAL
EFTA00012046

=== Page 379 ===
Form Approved
Electronic Tracking Number
OMB No. 2120-0020
2/28/2011
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See Title 14 CFR $43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. $44701). Failure to report can result in a civil penalty for each
such violation. (49 U.S.C. $46301(a))
Nationality and Registration Mark
Serial No.
USA N493LX
RK- 244
1. Aircraft
Make
Model
Series
RAYTHEON AIRCRAFT COMPANY
BEECHJET
400A
Name (As shown on registration certificate)
Address (As shown on registration certificate)
AIR GHISLAINE INC
Address
2. Owner
SOUTHEASTERN MILLS INC
City
RICHMOND HEIGHTS
State OHIO
ASCENT II LLC
Zip 44143-1453
Country USA
3. For FAA Use Only
4. Type
5. Unit Identification
Repair
Alteration
Unit
Make
Model
Serial No.
AIRFRAME
(As described in Item 1 above)
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
Name FLIGHT OPTIONS LLC
U.S. Certificated Mechanic
Manufacturer
Address 27 LINK DRIVE SUITE B
Foreign Certificated Mechanic
C. Certificate No.
City BINGHAMTON
State NY
Certificated Repair Station
Zip 13904
Country USA
Certificated Maintenance Organization
DJFA 206 D
D. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Extended range fuel
Signature/Date of Authorized Individual
per 14 CFR Part 43
App. B
FEB FEB 04 2010
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
s
Approved
Rejected
FAA Flt. Standards
Manufacturer
Maintenance Organization
Persons Approved by Canadian
Inspector
Department of Transport
BY
Other (Specify)
FAA Designee
Repair Station
Inspection Authorization
Certificate or
Signature/Date of Authorized Individual
Designation No.
DJFA 206 D
FEB FEB 04 2010
FAA Form 337 (10-06)
EFTA00012047

=== Page 380 ===

=== Page 381 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
USA N493LX
FEB 04 2010
Nationality and Registration Mark
Date
ACCOMPLISHED INSTALLATION OF MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL
NUMBER 137 AS DESCRIBED IN ENGINEERING ORDER EO M32-10/08-023.
ALL WORK ACCOMPLISHED I/A/W HBC MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL
NUMBER 137 AND ENGINEERING ORDER M32-10/08-023 REV. A DATED 11-13-08.
WEIGHT AND BALANCE NEGLIGIBLE.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: INSPECT THE HEAT SHIELD BLANKETS AND COVERS
I/A/W FLIGHT OPTIONS INSPECTION PROGRAM OR THE MANUFACTURES INSPECTION PROGRAM AS
APPROPRIATE.
END
Additional Sheets Are Attached
FAA Form 337 (10-06)
EFTA00012049

=== Page 382 ===
EFTA00012050

=== Page 383 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
NUMBER
Raythoon Aircraft Co.
N4931X
400g
EK-244
Transport
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate la issued pursuant to the Federal Aviation Act of 1958 and certifies that, as of the date of issuance, the aircraft
to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been
shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention
on International CMI Aviation, except as noted herein.
Exceptions:
None
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, this airworthiness
certificate is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43,
and 91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered In the United States.
DATE OF ISSUANCE
FAA REPRESEN ATIVE
DESIGNATION NUMBER
10/01/1993
Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both.
THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.
FAA Form 8100-2 (3-08)
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
NATIONALITY AND
2. MANUFACTURER AND MODEL
3. AIRCRAFT SERIAL
4. CATEGORY
REGISTRATION MARKS
NUMBER
RAYTHEON AIRCRAFT COMPANY
N793TA
400A
RK-244
TRANSPORT
AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to the Federal Aviation Act of 1958 and certifies that as of the date of issuance the
aircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe
operation and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as
provided by Annex 8 to the Convention on International Civil Aviation. except as noted herein.
Exceptions
NONE
6 TERMS AND CONDITIONS
Unless sooner surrendered suspended revoked or a termination date is otherwise established by the Administrator. this
airworthiness certificate is effective as long as the maintenance preventative maintenance and alterations are performed in
accordance with Parts 21. 43. and 91 of the Federal Aviation Regulations as appropriate and the aircraft is registered in the United
States
DATE OF ISSUANCE
FAAREPRESENTATIVE
DESIGNATION NUMBER
R-10/01/99
ACE-FSDO-07
Any alteration reproduction or misuse or this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3
years. or both THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL
VIATION REGULATIONS
Form 8100-2 (8-82)
U.S. G.P.O.:1998 669-038
EFTA00012051

=== Page 384 ===
EFTA00012052

=== Page 385 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
3 AIRCRAFT SERIAL
4 CATEGORY
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
NUMBER
REGISTRATION MARKS
RAYTHEON AIRCRAFT COMPANY
N793TA
400A
RK-244
TRANSPORT
5. AUTHORITY AND BASIS FOR ISSUANCE
This sirworthiness certificate is esued pursuant to the Federal Avigtion Act of 1958 and certifies that, as of the date of issuance the
a-rcraft to which issued nas been Inspected and lound to conform to the type certificate therefor. to be 5 condition for safe
operation and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as
provided by Annex 8 to the Convention on International Civil Aviation except as noted herein.
Exceptions:
NONE
6 TERMS AND CONDITIONS
Unless soonsr surrendered suspended. revolsed or # terminstion date M otherwise established by the Administrator. that
airworthiness certificate " attactive us tong-as the maintenance preventative maintenance. and alterations are performed in
accordance with Palts 21. 43. and 91 of the Federal Assistion Regulations. as appropriate. and the sucraft 13 registered in the United
States.
DESIGNATION NUMBER
DATE OF ISSUANCE
R-10/01/99
ACE-FSDO-07
Any alleration. reproduction. or misuse of this certificate may be punishable by otine not exceeding $1,000, or imprisonment not exceeding 3
years. or both THIS CERTIFICATE MUST BE DISPLAYED IN, THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL
VIATION REGULATIONS.
* U.S. G.P.O.1998 689-038
EFTA00012053

=== Page 386 ===
Z
EFTA00012054

=== Page 387 ===
CURRENTED
Form Approved
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Office Identification
Ju
Administration
ACA-F5D0-23
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
Beechcraft
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
NORTH CHANNEL LLC
C/O Flight Options LLC
2. Owner
ET-AL
Richmond Heights OH 44143-1494
3. For FAA Use Only
THE TECHNICAL DATA IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICABLE AIRWORTHINESS
TO CONFORMITY INSPECTION BY A PERSON IN 14 CFR PART 43.7.
REQUIREMENTS AND IS HEREBY APPROVED FOR USE ONLY ON Jess THE ABOVE DESCRIBED A(RCRAFT, SUBJECT
APPROVING INSPECTOR
DATE 30 JUN 2004
AEA ESDO 23
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
X
U.S. Certificated Mechanic
C/O Flight Options LLC
Foreign Certificated Mechanic
A&P 278825845
Richmond Heights, OH 44143
Certificated Repair Station
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the
information furnished herein is true and correct to the best of my knowledge.
Date
Signature of Authorized Individual
12-22-04
-
n
7. Approval for Return To Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
Inspector
BY
FAA Designee
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Air Carrier Certificate
Date of Approval or Rejection
Certificate or
Signature of
12/28/04
Designation No.
AJFA206D
FAA Form 337 (12-88)
EFTA00012055

=== Page 388 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
Installed the following equipment in Beechcraft 400A S/N RK-244:
Equipment
Install Manual
Maintenance Manual
Pilot's Guide
009-18001-001
009-18000-001
TAWS 8000 (Class B)
N/A
Current Revision
Current Revision
Installed Goodrich Avionics Systems Landmark TAWS8000 system (TSO-C151a Class B) using Flight Options LLC electrical drawing
400-3446-20-01 and applicable manufacturers installation manuals listed above.
This installation includes the optional Terrain Display function.
FAA Approved Flight Manual Supplement 400-3446-20 must be on board the aircraft when the Class B TAWS 8000 system is in use.
The TAWS 8000 system has been previously approved for multiple Beechjet aircraft under STC ST01881CH-D, with the Terrain
Display function enabled. This installation has been inspected and found to conform to the operational and technical characteristics of
STC ST01881CH-D with minor deviations in location of switching relays and wiring interface points as depicted on Flight Options LLC
drawing 400-3446-20-01. Similarity to STC ST01881CH-D is the basis for this request for field approval.
Using the respective manufacturer's instructions for post-installation ground tests, performed operational checks on all systems. The systems performed to
manufacturer's specifications and no interference to existing aircraft systems was noted.
In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, all physical mounting considerations were made with
reference to AC 43.13-2A, Chapter 1, Chapter 2, Chapter 3, and Chapter 11 as they apply to this installation. Regarding attachment to additional structure all
alterations were inspected to comply with the aircraft manufacturer's structural repair and alteration specifications.
In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, wire bundles were fabricated using MIL-SPEC, Tefzel
wire, that meets the acceptability requirements of AC43.13-1B, Chapter 11, Section 7, Paragraph 11-85 (a) and/or (b). paragraph 11-88, and paragraph 11-89.
All wiring was marked in accordance with AC43.13-1B, Chapter 11, Section 16, Para. 11-206, 11-207, 11-208 (a) and/or (b) and 11-210 (a) and (b). Individual
wires were formed into bundles by lacing and tying using the techniques described in AC43.13-1B, Chapter 11, Section 12, paragraph 11-158 (a) and (b).
Cables were routed and secured in the aircraft using AC43.13-1B, Chapter 11, Section 8, Para. 11-96, (a) through (gg) as a guide.
An electrical load analysis was performed per AC43.13-1B Chapter 11 Section 3 Paragraph 36. The maximum probable continuous electrical load does not
exceed 80% of the generator(s) output capacity. All compasses aboard this aircraft were checked for accuracy on completion of this installation. The aircraft
equipment list and weight and balance were updated.
Instructions for continued airworthiness (ICA) for this aircraft alteration and Interfacing components are as follows;
(1) Introduction to the aircraft altered is explained above.
(2) Description of the major alteration is explained above.
(3) -Operation Information is described in the documents listed above for each perticular product.
(4) Servicing, (8) Diagrams and access plates, (9) Special Inspection requirements, (10) Application of protective treatments, (11) Data, (12) List of Special
Tools, (14) Recommended Overhaul Periods, and (15) Airworthiness limitation section are not applicable.
(5) Maintenance, (6) troubleshooting information, (7) Removal and Replacement, and (13) for commuter category aircraft of the products listed, will be IAW
the appropriate and current manufacturers Installation manuals.
(16) Revision will be In accordance with the manufacturers' maintenance manuals and submitted to the local FSDO.
Antennas and other parts and materials Installed such as wiring, circult breakers, switches, annunciators, clamps, doublers, shelves, and racks will be
Inspected In conjunction with the Raytheon Beechjet 400A Phase C Inspection program, for condition, security of attachment, evidence of damage, and
normal operation IAW FAR 25.1529 and/or applicable manufacturers service Instructions
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012056

=== Page 389 ===
JAN 03 2005,
Form Approved
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Office Identification
Ju
Administration
ACA-F500-23
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
Beechcraft
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
NORTH CHANNEL LLC
C/O Flight Options LLC
ET-AL
Richmond Heights OH 44143-1494
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
Lynn H. Huyen
X
U.S. Certificated Mechanic
C/O Flight Options LLC
Foreign Certificated Mechanic
A&P 278825845
Richmond Heights OH 44143-1494
Certificated Repair Station
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the
information furnished herein is true and correct to the best of my knowledge.
Date
Signature of Authorized Individual
12-22-04
n
7. Approval for Return To Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
Inspector
BY
FAA Designee
Repair Station
Person Approved/by Transport
Canada Airworth/ness Group
Airlarrier Certificate
Date of Approval or Rejection
Certificate or
S
FAA 12/28/04 Form 337 (12-86)
Designation DJFA206D No.
EFTA00012057

=== Page 390 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
Removed existing MK-VI GPWS system in conjunction with installation of new TAWS (EGPWS) system reference
FAA form 337 dated 12-22-04.
Aircraft weight and balance and equipment list data have been revised.
END
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012058

=== Page 391 ===
AW
Form Approved
7
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
For FAA Use Only
US Department
of
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Office GL05 TBV
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
BEECHJET
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK244
N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
FLIGHTOPTIONS
2. Owner
RICHMOND HTS., OHIO 44143
3. For FAA Use Only
4. Unit Identification
5. Type
Make
Model
Serial No.
Repair
Alteration
Unit
AIRFRAME
(As described in item 1
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
U.S. Certificated Mechanic
CLASSIC INTERIOR COMPLETIONS INC.
Foreign Certificated Mechanic
R4GR031Y
CLEVELAND, OHIO 44143
X
Certificated Repair Station
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse and or that attachments the
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations
information furnished herein is true and correct to the best of my knowledge.
Signature of Authorized Individual
Date
12-10-2004
7. Approval for Return To Service
Pursuant to the authority given persons specified-below, the X unit APPROVED identified in item REJECTED 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
Other (Specify)
FAA Flt.
Manufacturer
Inspection Authorization
Standards
BY
Person Approved by
RECEIVED
FAA Designee
X
Repair Station
Transport
Certificate or
Signature of Authorized Individual
DEC 16 2004
Date of Approval or Rejection
Designation No.
12-10-2004
R4GR031Y
CLE-GL25
FAA Form 337 (12-88)
EFTA00012059

=== Page 392 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
AIRCRAFT: BEECHJET 400A N793TA RK-244
FABRICATED AND INSTALLED THE FOLLOWING USING APPROVED DER DRAWINGS SEE FAA FORM
8110-3 DATED 12-08-2004
1) R/H Galley
2) a) Assembly drawing #36G-200A006
b) Installation drawing #36G-200F006
There are no additional inspections required for continued airworthiness other than those prescribed by the
aircraft manufacturer during regular inspections.
END
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012060

=== Page 393 ===
Form Approved
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Administration
J4
Offic AEA-FSDO
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result
il penalty not
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
RAYTHEON
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
USA N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
SAMAIR INC
ET-AL
WICHITA, KS 67207
3. For FAA Use Only
THE TECHNICAL DATA IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICABLE AIRWORTHINESS
REQUIREMENTS AND IS HEREBY APPROVED FOR USE ONLY ON TH
BJECT
TO CONFORMITY INSPECTION BY A PERSON IN 14 CFR PART 43.7.
DATE 6/25/03
APPROVING INSPECTOR
AEA FSDO 23
4. Unit Identification
ype
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
STEPHEN J. MAIDEN
X
U.S. Certificated Mechanic
C/O FLIGHT OPTIONS LLC
Foreign Certificated Mechanic
A 297605039
Certificated Repair Station
RICHMOND HEIGHTS, OH 44143
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the
information furnished herein is true and correct to the best of my knowledge.
Date
JUNE 10, 2003
7. Approval for Return To Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Other (Specify) OPTIONS FLIGHT SUPPORT,
Manufacturer
Inspector
Inspection Authorization
BY
INC., d/b/a FLIGHT OPTIONS
FAA Designee
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Signature of Authorized Individual
Designation No.
JUNE 10, 2003
KEITH GAWSYSZAWSKI
DJFA206D
FAA Form 337 (12-88)
EFTA00012061

=== Page 394 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D,
MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE
6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS
TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS
INSTALLATION INSTRUCTIONS AS LISTED ON AML # ST00881WI-D.
AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL.
NO CHANGE TO WEIGHT AND BALANCE.
END
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012062

=== Page 395 ===
13 JUN 2003
Form Approved
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Office Identification ILL
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent AEA-FSDO sevision
Administration
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result 23 penalty not
Make
Model
RAYTHEON
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
USA N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
SAMAIR INC
ET-AL
WICHITA, KS 67207
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
Stephen J. Maiden
X
U.S. Certificated Mechanic
C/O FLIGHT OPTIONS LLC
Foreign Certificated Mechanic
A297605039
Certificated Repair Station
RICHMOND HEIGHTS, OH 44143
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the
information furnished herein is true and correct to the
Date
10 June, 03
7. Approvan
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify) FLIGHT OPTIONS LLC
Inspector
BY
AIR AGENCY CERTIFICATE
FAA Designee
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Designation No.
JUNE 10, 2003
DJFA206D
FAA Form 337 (12-88)
EFTA00012063

=== Page 396 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. 0927-A3A
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D,
MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE
6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS
TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS
INSTALLATION INSTRUCTIONS AS LISTED ON AML # ST00881WI-D.
AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL.
NO CHANGE TO WEIGHT AND BALANCE.
END
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012064

=== Page 397 ===
United States of America
Department of Transportation Federal Abiation Administration
Supplemental Type Certificate
Number ST00881WI-D
This certificate. issued to
Rockwell Collins, Inc.
400 Collins Road NE, MS 164-100
Cedar Rapids, IA 52498
certifies that the change in the type design for the following product with the limitations and conditions
therefor as specified hereen meets the aircrethiness requirements of Tan of the
Regulations
Original Product Type Certificate Number
*See attached FAA Approved Model List (AML)
Make
No. ST00881WI-D for list of approved airplane models
Model:
and applicable airworthiness regulations.
Description of Type Drign Change Modification of Collins TCAS Il or TCAS 94 (TCAS II) system installation
with Collins TTR-920 Change 6.04a Receiver Transmitter to a Collins TCAS II or TCAS 94 (TCAS II) system
installation with Collins TTR-920 or Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS Il Receiver Transmitter
and optional TPR-901 in accordance with Collins Installation Instructions as listed on AML No. ST00881WI-D,
Revision or later FAA approved revisions.
Bimitations and Conditions (1) Approval of this change in type design applies to the above model aircraft only.
(2) Compatibility of this design change with previously approved modifications must be determined by the installer.
(3) A copy of this Certificate and FAA Approved Model List (AML) No. ST00881WI-D issued June 30, 2000, or later
FAA approved revision, must be maintained as part of the permanent records for the modified aircraft. (4) Prior
installation and approval of a Collins TTR-920 Change 6.04a Receiver Transmitter is a prerequisite to this STC. (5) If
the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other
person written evidence of that permission.
This certificate and the supporting data which is the basis for approval shall remain in effect until
surrended supported revoked. or a termination date is thereise stablished by the Administrator of the
Frieral Aviation Administration
Date of application June 29, 2000
Date reissued
Date of issuance June 30, 2000
Date amended July 14, 2000, December 1, 2000
Bu direction of the Administrator
FEDERAL AVIATION
ADMINISTRATION
Administrator, DAS-500864-CE
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000. or imprisonment not exceeding 3 years, or both.
FAA FORM 8110-2(10-68)
PAGE 1
This certificate may be transferred in accordance with FAR 21.47.
EFTA00012065

=== Page 398 ===

=== Page 399 ===
Avionics Certification Center
Cedar Rapids IA 52498
Rockwell
Collins
May 14, 2003
WO030737.DOC
Flight Options
Cleveland, OH 44143
Tel: (216) 797-3500
Attention:
Mr. Jody Kremsreiter/
Mr. Richard Fine (Collins on-site)
Subject:
STC ST00881WI-D Modification of Collins TCAS II System Installation
with Collins TTR-920 Change 6.04a Receiver Transmitter and TPR-900
Mode S to a Collins TCAS Il System Installation with Collins TTR-920,
Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS II Receiver
Transmitter and optional TPR-901 in Part 25 Aircraft
Dear Mr. Kremsreiter:
Enclosed is a compact disk with one copy each of the following FAA approved STC data:
1.
STC ST00881WI-D Certificate, dated December 1, 2000.
2.
FAA Approved Model List (AML) Number ST00881WI-D, amended
April 15, 2003.
3.
Drawing Index 992-4358-001, Revision M.
4.
One copy of each drawing listed on Drawing Index 992-4358-001.
5.
Airplane Flight Manual Supplement, ACC-00-105, Revision
This letter is our authorization for Flight Options to use this STC as basis for the installation
of our equipment in your airplanes based on the following model and serial numbers
provided by Mr.
of Rockwell Collins.
EFTA00012067

=== Page 400 ===
EFTA00012068

=== Page 401 ===
Flight Options
WO030737.DOC
STC ST00881WI-D
May 14, 2003
Page 2
STC ST00881WI-D
Model
MSN
MSN
400A
RK006
RK248
RK016
RK252
RK022
RK257
RK027
RK260
RK030
RK264
RK031
RK265
RK045
RK268
RK062
RK271
RK093
RK273
RK146
RK274
RK161
RK276
RK168
RK279
RK178
RK282
RK180
RK284
RK186
RK289
RK189
RK292
RK195
RK295
RK198
RK297
RK201
RK301
RK202
RK305
RK209
RK307
RK222
RK310
RK230
RK317
RK234
RK324
RK237
RK327
RK239
RK328
RK244
RK334
RK245
Please return a record of any additional aircraft serial number(s) to me for installations
performed using this STC. My fax number is
Collins needs to receive this
data before we can authorize additional installations.
EFTA00012069

=== Page 402 ===
EFTA00012070

=== Page 403 ===
Flight Options
WO030737.DOC
STC ST00881WI-D
May 14, 2003
Page 3
Flight Options is responsible for the regulatory approval of any deviations from STC
ST00881WI-D.
Instructions explaining how to access the data on the CD have been inserted inside the
jewel case.
Customer satisfaction is important to us, and we would appreciate your input.
Please complete and return the enclosed questionnaire or email me at
and let us know how we can best serve you.
We trust this data will fulfill your installation requirements. However, if you have any
questions, please call me at
Sincerely
Collins Avionics Certification Center
/pah
Enclosure
EFTA00012071

=== Page 404 ===

=== Page 405 ===
Form Approved
OMB No. 2120-0020
MAJOR REPAIR AND ALTERATION
US Department
For FAA Use Only
of
(Airframe, Powerplant, Propeller, or Appliance)
Office Identification
Federal Aviation
Administration
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for
instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not
to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
Beechjet
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK- 244
USA N 793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
SAM AIR INC
2. Owner
ET-AL
WICHITA, KS 67207
3. For FAA Use Only
The data identified herein complied with applicable airworthines
The above described aircraft subject to conformity inspection
This approval is only for this aircraft make; mod
Date
Approving Inspector
APR-2 3 2002 APR 2002
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
Keith Gawsyszawski
X
U.S. Certificated Mechanic
Flight Options. Inc.
Foreign Certificated Mechanic
AP 287603483
Richmond Hts., OH 44143
Certificated Repair Station
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments
hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the
information furnished herein is true and correct to the best of my knowledge.
Date
April 5, 2002
7. Approval for Return To Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Other (Specify)
Manufacturer
Inspector
x
Inspection Authorization
BY
FAA Designee
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Designation No.
MAY 6,2002
AP287603483IA
FAA Form 337 (12-88)
EFTA00012073

=== Page 406 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
1. Removed existing Tail Navigation Light Assembly including the rubber shock mount.
2. Installed Whelen Engineering, Inc. Model 70805-01 Tail Position Light Assembly in accordance with part number
04-0112558-00 instruction sheet to include installation procedures and drawing number 70805.
3. The light assembly will be operationally tested under Flight Options Continuous Airworthiness Maintenance
Program under Phases IC, 9C and 17C.
4. Weight and Balance change found negligible.
END
Additional Sheets Are Attached
*U.S.GPO:1994-568-012/00019
EFTA00012074

=== Page 407 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
U.S. Department
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
of Transportation
Office Identification
Federal Aviation
Administration
SWIT PR
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
1. Aircraft
RAYTHEON AIRCRAFT
400A
Serial No.
Nationality and Registration Mark
RK-244
USA
N793TA
Name (As shown on registration certificate)
Address
(As shown on registration certificate)
2. Owner
KETTLER ROBERT, MICHELS PIPELINE
CONSTRUCTION INC, SOUTHEASTERN MILLS
WICHITA KS 67207-1315
INC, REI AIR LLC, ET-AL
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
RAYTHEON AIRCRAFT SERVICES
U.S. Certificated Mechanic
CRS-XA14605K
Foreign Certificated Mechanic
LIMITED AIRFRAME
X
Certificated Repair Station
SAN ANTONIO TEXAS 78216
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
12-10-01
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
BY
Inspector
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Designation No.
12-10-01
CRS-XA14605K
FAA Form 337 (12-88)
EFTA00012075

=== Page 408 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
MAKE: RAYTHEON 400A
S/N: RK-244
REG: N793TA
DATE: 12-10-01
ALL SEVEN CABIN SEATS AND THE LAVATORY SEAT WERE FIREBLOCKED IN ACCORDANCE WITH
FAR 25.853 (a) APPENDIX F PART I (a) (1) (ii) AND FAR 25.853 (c) APPENDIX F PART II AMENDMENT
25-83. THE FIREBLOCKING WAS ACCOMPLISHED IN ACCORDANCE WITH THE SKANDIA INC. TEST
PLAN #8335 REV. IR DATED 12-04-01, REFERENCE THE FORM 8110-3 DATED 12-04-01 APPROVED BY
DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL
SPECIAL. SEE THE FORM 8110-3 DATED 10-09-01 AS REFERENCE FOR THE FIREBLOCKING
FLAMMABILITY TEST RESULTS OF THE SEATS THAT WAS PREVIOUSLY TESTED AND APPROVED ON
THE SKANDIA INC. TEST PLAN #8118 REV. IR DATED 10-01-01 FOR P/N 8118-1 AND 8118-2 ONLY,
APPROVED BY
DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE,
STRUCTURAL SPECIAL.
END
X
Additional Sheets Are Attached
U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157
EFTA00012076

=== Page 409 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
U.S. Department
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
of Transportation
Federal Aviation
Office Identification
Administration
SWIT M
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
1. Aircraft
RAYTHEON AIRCRAFT
400A
Serial No.
Nationality and Registration Mark
RK-244
USA
N793TA
Name (As shown on registration certificate)
Address
(As shown on registration certificate)
2. Owner
KETTLER ROBERT, MICHELS PIPELINE
CONSTRUCTION INC, SOUTHEASTERN MILLS
WICHITA KS 67207-1315
INC, REI AIR LLC, ET-AL
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
RAYTHEON AIRCRAFT SERVICES
U.S. Certificated Mechanic
CRS-XA14605K
Foreign Certificated Mechanic
LIMITED AIRFRAME
X
Certificated Repair Station
SAN ANTONIO TEXAS 78216
Manufacturer
RADIO CLASS 1,11,111
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
12-10-01
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
BY
Inspector
FAA Designee
x
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Designation No.
12-10-01
CRS-XA14605K
FAA Form 337 (12-88)
EFTA00012077

=== Page 410 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
MAKE: RAYTHEON 400A
S/N: RK-244
REG: N793TA
DATE: 12-10-01
MODIFIED THE EXISTING RIGHT HAND FORWARD GALLEY/CLOSET CABINET IN ACCORDANCE
WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #528-2526-001 REV. A DATED 07-27-00, REFERENCE
THE FORM 8110-3 DATED 12-07-01 APPROVED
DESIGNATED ENGINEERING
REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE MODIFICATION CONSISTED OF
INSTALLING ELECTRICAL PROVISIONS FOR A MAPCO, CUP HOLDERS AND LIGHTING IN THE
FORWARD SECTION OF THE BAGGAGE CABINET. THE ELECTRICAL WIRING FOR THE
GALLEY/CLOSET CABINET WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT
SERVICES DWG. #RAS-73-0112 REV. IR DATED 12-05-01, REFERENCE THE FORM 8110-3 DATED
12-07-01 APPROVED BY
DESIGNATED ENGINEERING REPRESENTATIVE,
#DERT-710137-SW, SYSTEMS AND EQUIPMENT. THE MODIFIED GALLEY/CLOSET CABINET HAS A
NEW WEIGHT OF 84.5 Lbs. AND A MOMENT OF 12844.0. THE WEIGHT AND BALANCE FORM AND
THE EQUIPMENT LIST HAVE BEEN REVISED AND BOTH FORMS HAVE BEEN INSERTED IN THE
AIRCRAFT FLIGHT MANUAL.
END
X
Additional Sheets Are Attached
U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157
EFTA00012078

=== Page 411 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
U.S. Department
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
of Transportation
Office Identification
Federal Aviation
Administration
swll m
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
1. Aircraft
RAYTHEON AIRCRAFT
400A
Serial No.
Nationality and Registration Mark
RK-244
USA
N793TA
Name (As shown on registration certificate)
Address
(As shown on registration certificate)
2. Owner
KETTLER ROBERT, MICHELS PIPELINE
CONSTRUCTION INC, SOUTHEASTERN MILLS
WICHITA KS 67207-1315
INC, REI AIR LLC, ET-AL
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
RAYTHEON AIRCRAFT SERVICES
U.S. Certificated Mechanic
CRS-XA14605K
1115 PAUL WILKINS ROAD
Foreign Certificated Mechanic
LIMITED AIRFRAME
X
Certificated Repair Station
SAN ANTONIO TEXAS 78216
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
12-10-01
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
BY
Inspector
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Designation No.
12-10-01
CRS-XA14605K
FAA Form 337 (12-88)
EFTA00012079

=== Page 412 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
MAKE: RAYTHEON 400A
S/N: RK-244
REG: N793TA
DATE: 12-10-01
FABRICATED AND INSTALLED A NEW THE LIFE VEST CONTAINER IN THE TOILET CABINET IN
ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #562-3832-001 REV. IR DATED
08-22-00, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED BY
DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE LIFE VEST
CONTAINER WAS FABRICATED USING AAR COMPOSITES FLAT NOMEX PANEL P/N ATR-FP-251F2,
REFERENCE THE FORM 8110-3 DATED 07-01-99 APPROVED BY
DESIGNATED
ENGINEERING REPRESENTATIVE, #CHI-410, STRUCTURAL SPECIAL. THE MODIFICATION OF THE
CONTAINER WAS FOR THE INSTALLATION OF A NEW EASTERN AERO MARINE LIFE VEST, P/N
PO1074-113. THE WEIGHT CHANGE IS NEGLIGIBLE. THE EQUIPMENT LIST HAS BEEN REVISED TO
REFLECT THE NEW LIFE VEST AND HAS BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL.
END
X
Additional Sheets Are Attached
U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157
EFTA00012080

=== Page 413 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
US Department
of Transportation
For FAA Use Only
App
(Airframe, Powerplant, Propeller, or Appliance)
Federal Aviation
Office Identification
Administration
DPA-FSDO
DCS
INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
2000
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed
$1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
RAYTHEON
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
AIRCAP LLC
WICHITA, KS 67207-1315
3. For FAA Use Only
THE DATA IDENTIFIED HEREIN COMPLIES WITH APPLICABLE AIRWORTHINESS REQUIREMENTS AND IS APPROVED ONLY FOR
THE ABOVE DESCRIBED AIRCRAFT SUBJECT TO CONFORMITY INSPECTION BY A PERSON AUTHORIZED IN FAR 43.7
APR 0 4 2000
DATE
ECTOR
DPA-FSDO
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
U.S. Certified Mechanic
Elliott Aviation
Foreign Certified Mechanic
X
Certificated Repair Station
CGHR812C
Moline, IL 61266-0100
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
Signature of Authorized Individual
3/29/2000
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Other (Specify)
Manufacturer
Inspector
Inspection Authorization
BY
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Signature of Authorized Individual
4/14/2000
Designation No.
CGHR812C
FAA Form 337 (12-88)
EFTA00012081

=== Page 414 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible
with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets, Identify with aircraft nationality and registration mark and date work accomplished.)
1. INSTALLED PENNY & GILES PASSENGER DIGITAL CABIN DISPLAY MODEL 2700.
2. THE CABIN DISPLAY WAS FLUSH MOUNTED IN THE FWD RH CLOSET/GALLEY CABINET AT 152.0 INCHES AFT OF DATUM
FACING AFT. CONNECTED UNIT TO FACTORY PROVISION HARNESS LOCATED IN THE CABINET. THE UNIT WILL DISPLAY
TEMPERATURE, TRUE AIRSPEED, ALTITUDE AND E.T.A. INFORMATION. THE DISPLAY IS FAA/PMA CERTIFIED. THE CABIN
DISPLAY WAS INSTALLED IN ACCORDANCE WITH B&D INSTALLATION MANUAL P/N 2700-003-026 REV o DATED DECEMBER
19,1996.
3. PERFORMED EMI INTERFERENCE TEST IN ACCORDANCE WITH AC43.13-1B SECTION 8 PARAGRAPH 11-107 AND FAR
23.1309 AND 23.1431.
4. WEIGHT AND BALANCE DATA, EQUIPMENT LIST AND AIRFRAME LOGBOOKS WERE REVISED TO REFLECT THIS
INSTALLATION.
5. FOR THE ABOVE INSTALLED SYSTEM NO ADDITIONAL MAINTENANCE IS REQUIRED BEYOND THE REQUIREMENTS OF 14
CFR PART 91 SUBPART E MAINTENANCE, PREVENTATIVE MAINTENANCE AND ALTERATIONS PER THE FOLLOWING
INSTALLATION MANUAL:
(1) B&D INSTALLATION MANUAL P/N 2700-003-026 REV O DATED DECEMBER 19,1996
5. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CHECKLIST
(1) INTRODUCTION-REF THIS 337 FORM BLOCK 1
(2) DESCRIPTION-REF THIS 337 FORM BLOCK 8
(3) CONTROL OPERATION INFORMATION- REF THIS 337 FORM BLOCK 8
(4) SERVING INFORMATION-NOT APPLICABLE
(5) MAINTENANCE INSTRUCTIONS-REF THIS 337 FORM BLOCK 8
(6) TROUBLESHOOTING INFORMATION-REF THIS 337 FORM BLOCK 8
(7) REMOVAL AND REPLACEMENT-REF THIS 337 FORM BLOCK 8
(8) DIAGRAMS- NOT APPLICABLE
(9) SPECIAL INSPECTION REQUIREMENTS-NOT APPLICABLE
(10) APPLICATION OF PROTECTIVE TREATMENTS-NOT APPLICABLE
(11) DATA-NOT APPLICABLE
(12) LIST OF SPECIAL TOOLS-NOT APPLICABLE
(13) COMMUTER CATERGORY A/C- ELECTRICAL LOAD ANALYSIS-NOT APPLICAPLE
(14) NO ADDITIONAL OVERHAUL TIME LIMITATIONS
(15) AIRWORTHINESS LIMITATIONS SECTION-NOT APPLICABLE
(16) REVISION-IF A REVISION TO THIS ICA IS NECESSARY A LETTER WILL BE SUBMITTED TO THE LOCAL FSDO WITH A
COPY OF THE REVISED FAA FORM 337 AND REVISED ICA.
END
Additional Sheets Are Attached
* U.S. G.P.O 1990-761-753
EFTA00012082

=== Page 415 ===
APR 2 1 2008
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
US Department
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Administration
Office Identification DPA-FSDO
INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed
$1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
BEECH
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
N793TA
Name (As shown on registration certificate)
Address (As shown on registration certificate)
AIRCAP LLC
2. Owner
WITCHA KS 67207-1315
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
U.S. Certified Mechanic
Elliott Aviation
Foreign Certified Mechanic
X
Certificated Repair Station
CGHR812C
Moline, IL 61266-0100
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
Si
4/14/00
7. Approval for Return to Service
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Other (Specify)
Inspector
Manufacturer
Inspection Authorization
BY
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
4/14/00
Designation No.
CGHR812C
FAA Form 337 (12-88)
EFTA00012083

=== Page 416 ===
EFTA00012084
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible
with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
B. Description of Work Accomplished
(If more space is required, attach additional sheets, Identify with aircraft nationality and registration mark and date work accomplished.)
400A, RK-244, N793TA, 4/14/00
Removed all the interior and the cabinetry items to facilitate a complete refurbishment of the interior per the customer's request.
Removed all the finishes and material's as required. Recovered the cabin headliner, the left and right hand window panels, the
emergency exit panel and the cabin door upper panel with Douglas Interior products: Fabric, DEF 9135, PN 04, Ivory, D/L # 12777,
REF # 402396-402545. See the burn test report WO #45065-00 and the form 8110-3, Both dated 03/03/00 and approved by
D.E.R. #DERY 405020-CE, Structural special. Recovered the left and right hand drink ledge consoles with Rogers &
Goffigon: Fabric, FRET #9103-05, Baroque, Treated at Skandia, REF treatment #SKFP41539. See the burn test report WO #46487-
00 and the FORM 8110-3, both dated 04-13-00 and approved by Judy Boggs, D.E.R. #DERY - 405020-CE structural special.
Recovered both crew seats, seven cabin seats, the lavatory seat with leather Townsend leather: Leather, Classic pecan, Part #CL-
17, D/L #11428. See the burn test report WO# 44969-00 and the form 8110-3, both dated 03-01-00 and approved by Judy Boggs,
D.E.R. #405020-CE, structural special. The lower door panel aft side of the left hand partitian and both game table inserts with
leather
pecan, TF-17 D/L 11429.See bum test report Wo # 44969-00 dated 03/01/00 and approved by Judy
Boggs DER # DERY 405020-CE. Recovered the aft right hand partition, the outboard side of the aft stub partition. the three panels
of the aft baggage compartment and the inside of the fwd closet/galley cabinet with aircraft interior products, fabric, grospoint #440,
beige, lot #8817-8824, treated at Skandia, Ref. Treatment #SKFP15268, see the burn test report WO#35268 dated 06-24-99 and
the form 8110-3 dated 07-16-99, both approved by
D.E.R. #CHI-410, Structural special. Cut, fitted, surged and
installed new carpet throughout the cockpit and cabin area using aircraft interior products, CTM Pattern NO40669 carpet. color: ultra
suede 034. See the burn test report #AIP stock and the form 8110-3 both dated 3-03-00 and approved by
D.E.R.
#SO-572, structures (interiors).. Removed the pilot and copilot crew seat restraint systems. Both restraint systems were sent out to
Am Safe, Inc. for rework. Installed both crew seat restraint systems P/N 504246-401-2291 after work was accomplished by Am-
Safe, Inc. Reference both 8130-3 Forms dated 04-07-00 from Am-Safe, Inc. Removed the lavatory seat and all cabin seat belt
assemblies and inertia reels. Sent all out to Belt Makers, Inc. for rewebbing. Installed the rewebbed lavatory seat and all cabin seat
belt assemblies and inertia reels, see the certification paperwork, WO #31888R. The galley/closet, upright storage cabinet, fwd and
aft bulkheads, game tables, drink ledges and the vanity cabinet was covered with Carl F. Booth & Co. Waterfall Buginga Veneer.,
reference the burn test report #22702 dated 04-15-00 approved by
D.E.R. #DERY405020-CE, for the flammability
requirements. All seven cabin seats and the lavatory seat were fireblocked in accordance with FAR 25.853 (a) appendix F part I (a)
(1) (II) and FAR 25.85] (c) appendix F part II amendment 25-83. The fireblocking was accomplished in accordance with the
Skandia, Inc. test plan #5880 Rev. new dated 04-13-00, reference the form 8110-3 dated 04-13-00 approved by
D.E.R. #DERY-405020-CE, structural special. Reference the FAA Form 337 dated 04-14-00. Complied with AD 74-08-09 R2
Transport category that have one or more lavatories equipped with paper or linen waste receptacles by installing placards as
required by this AD. AD 98-25-10R1 Aircraft Belts, Inc. Seat restraint system does not apply due to aircraft belts being AM-Safe inc.
aircraft seat belts. The work performed on this aircraft has been inspected in accordance with the current maintenance rules of the
Federal Aviation Regulations and for the work performed this aircraft is approved for return to service. Weigh and balance change
negligible.
END
Additional Sheets Are Attached
* U.S. G.P.O 1990-761-753

=== Page 417 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
US Department
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Office Identification
Administration
ACE FSDO-07 SHW
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each violation (Section 901 of Federal Aviation Act of 1958).
Make
Model
Raytheon
400A
1. Aircraft
Serial No.
Nationality and Registration Mark
RK-244
N428HR
Name (As shown on registration certificate)
Address (As shown on registration certificate)
See Attached Copy
2. Owner
Wichita, KS 67201
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
WICHITA FSDO
APPLIANCE
THA -8 Pill 1:06
RECEIVED
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
Kenneth W. Chitty
X
U.S. Certificated Mechanic
454944057
101 S. Webb
Foreign Certificated Mechanic
P.O. Box 2902
Certified Repair Station
Witchita, Ks 67201-2902
Manufacturer
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have
been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
Signature of Autl
03-06-00
7. Approval for Return
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the
Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
X
Inspector
Inspection Authorization
Other (Specify)
BY
FAA Designee
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
Signature of
03-06-00
Designation No.
454944057
FAA Form 337 (12-88)
EFTA00012085

=== Page 418 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
Installed Dog Harness P/N CS-H-1 in accordance with Aerodesign Engineering Report 1912-1 Rev.IR,
6-9-96, ( Faa Form 8110-3 dated 03-03-2000 is the Approved Data ) "Structual Substantiation, Restraint
Harness for a Dog, installed into an Aircraft."
This installation meets FAR 25.853b-2 Flammability requirements.
This harness will be stored with the A/C loose equipment and a copy of the Engineering report will be placed in
the Flight Manual, instructions are in paragraph 3.0
No Weight & Balance change.
Additional Sheets are Attached
EFTA00012086

=== Page 419 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1. NATIONALITY AND
2. MANUFACTURER AND MODEL
3. AIRCRAFT SERIAL
4. CATEGORY
REGISTRATION MARKS
NUMBER
RAYTHEON AIRCRAFT COMPANY
N793TA
400A
RK-244
TRANSPORT
5. AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate is issued pursuant to the Federal Aviation Act of 1958 and certifies that, as of the date of issuance, the
aircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe
operation, and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as
provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein.
Exceptions:
NONE
6 TERMS AND CONDITIONS
Unless sooner surrendered. suspended, revoked, or a termination date is otherwise established by the Administrator, this
airworthiness certificate is effective as long as the maintenance. preventative maintenance. and alterations are performed in
accordance with Parts 21. 43, and 91 of the Federal Aviation Regulations. as appropriate, and the aircraft is registered in the United
States.
DATE OF ISSUANCE
DESIGNATION NUMBER
R-10/01/99
ACE-FSD0-07
Any alteration, reproduction, or misuse of this certificate may be punishabl by a fine not exceeding $1,000. or imprisonment not exceeding 3
years. or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL
AVIATION REGULATIONS.
FAA Form 8100-2 (8-82)
U.S. 1998 669-038
EFTA00012087

=== Page 420 ===
a
EFTA00012088

=== Page 421 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
RAYTHEON AIRCRAFT COMPANY
NUMBER
N428HR
400A
RK-244
TRANSPORT
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate IS issued pursuant to the Federal Aviation Act of 1958 and certifies that, as of the date of issuance, the
aircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe
operation. and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as
provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein.
Exceptions:
NONE
6 TERMS AND CONDITIONS
Unless sooner surrendered. suspended. revoked. or a termination date IS otherwise established by the Administrator, this
airworthiness certificate IS effective as long as the maintenance, preventative maintenance. and alterations are performed in
accordance with Parts 21. 43. and 91 of the Federal Aviation Regulations. as appropriate. and the aircraft IS registered in the United
States.
DATE OF ISSUANCE
DESIGNATION NUMBER
10-01-99
DMIR CE-501157
Any alteration, reproduction. or misuse of this certificate may be punishable by a fine not exceeding $1,000. or imprisonment not exceeding 3
years. or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL
AVIATION REGULATIONS.
FAA Form 8100-2 (8-82)
# U.S. GOVERNMENT PRINTING OFFICE: 1991 668-228
EFTA00012089

=== Page 422 ===
EFTA00012090

=== Page 423 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
U.S. Department
of Transportation
(Airframe, Powerplant, Propeller, or Appliance)
For FAA Use Only
Federal Aviation
Office Identification
Administration
SW FSDO 17
BRR
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
1. Aircraft
RAYTHEON
400A
Serial No.
Nationality and Registration Mark
RK-244
USA
N428HR
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
RAYTHEON AIRCRAFT COMPANY
WICHITA, KANSAS 67201-0085
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
RAYTHEON AIRCRAFT SERVICES
U.S. Certificated Mechanic
CRS-XA14605K
Foreign Certificated Mechanic
SAN ANTONIO TEXAS 78216
X
LIMITED AIRFRAME
Certificated Repair Station
Manufacturer
RADIO CLASS I,II,III
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
12-22-99
7
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
BY
Inspector
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
12-22-99
Designation No.
CRS-XA14605K
FAA Form 337 (12-88)
EFTA00012091

=== Page 424 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
MAKE: RAYTHEON 400A
S/N: RK-244
REG: N428HR
DATE: 12-22-99
INSTALLED AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM CONSISTING
OF THE FOLLOWING EQUIPMENT:
MOD/MFG
DESCRIPTION
P/N
WEIGHT
ARM
RT-18D
REC/TRANSMITTER W/RACK
400-0125-2000
7.8
47.8
WH-10
HANDSET
400-0123-112
1.5
106.3
WH-10
HANDSET W/CORD
400-0123-112
2.5
252.0
AT-462
ANTENNA
121-014378-01
0.5
365.1
THE ALLIEDSIGNAL FLITEFONE VI SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE BEECH
AIRCRAFT CORPORATION DWG. #128-340675, REV. ORIGINAL, DATED 11-13-95 AND THE CHANGE
ORDER #G76866 DATED 10-11-96. THE ELECTRICAL WIRING FOR THIS INSTALLATION WAS
INSTALLED IN ACCORDANCE WITH THE BEECH AIRCRAFT CORPORATION DWG. 128-340606 REV. A
DATED 10-27-94.
A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR
25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING
SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE
AIRCRAFT.
THE ALLIEDSIGNAL FLITEFONE VI OPERATORS MANUAL P/N: 006-08834-0000 AND THE
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS DOC. #FF VI-ICA-RK-244 DATED 12-22-99 HAVE
BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFTS PERMANENT RECORDS.
THE AIRCRAFT WEIGHT AND BALANCE FORM AND EQUIPMENT LIST HAVE BEEN REVISED TO
REFLECT THIS MODIFICATION AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT
MANUAL.
END
Additional Sheets Are Attached
U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157
EFTA00012092

=== Page 425 ===
-RAYTHEON AIRCRAFT SERVICES
PAGE 1 OF 2
SAN ANTONIO, TX.
DOCUMENT NO. FF VI-ICA-RK-244
DATE: 12-22-99
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
FOR A BEECHCRAFT MODEL 400A
WITH AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM
1. INTRODUCTION: THIS MAJOR ALTERATION TO THIS AIRCRAFT OBLIGATES THE AIRCRAFT OPERATOR TO
INCLUDE THE FOLLOWING MAINTENANCE INFORMATION PROVIDED BY THIS DOCUMENT IN THE
OWNER/OPERATOR'S AIRCRAFT MAINTENANCE MANUAL AND THE OWNER/OPERATOR'S AIRCRAFT
SCHEDULED MAINTENANCE PROGRAM.
2. DESCRIPTION: THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM CONSISTS OF A
RECEIVER/TRANSMITTER INCLUDING ITS MOUNTING RACK, TWO HANDSETS INCLUDING MOUNTING RACKS,
TWO RETRACT CORDS, AN ANTENNA, ASSOCIATED WIRING, AND ANY RELATED HARDWARE. THE BASIC
RADIOTELEPHONE SYSTEM IS A MOBILE COMMUNICATION SYSTEM FOR AIRCRAFT. IT OPERATES IN A
FREQUENCY RANGE BETWEEN 454.675 454.975 Mhz 13 CHANNELS TO RECEIVE AND 459.675 459.975 Mhz 13
CHANNELS TO TRANSMIT.
3. CONTROL, OPERATION INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI INSTALLATION MANUAL,
REV. E, REPORT 1362, BASIC ISSUE DATED SEP. 1/90 AND THE ALLIEDSIGNAL FLITEFONE VI OPERATOR'S
MANUAL P/N 006-08834-0000.
4. SERVICING INFORMATION: THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM IS ON
CONDITION AND THERE IS NO PERIODIC, PREVENTIVE, OR SCHEDULED MAINTENANCE REQUIRED FOR
CONTINUED OPERATION OF THIS SYSTEM.
5. MAINTENANCE INSTRUCTIONS: THE SCHEDULED MAINTENANCE TASKS REQUIRED BY THIS MODIFICATION
FOLLOWS: TO BE ADDED TO THE AIRCRAFT OWNER/OPERATORS APPROPRIATE AIRPLANE MAINTENANCE PROGRAM AS
a. PERFORM, ON AT LEAST AN ANNUAL BASES, A PERIODIC INSPECTION OF THE EQUIPMENT RACK,
EQUIPMENT MOUNTINGS, ASSOCIATED WIRING, CABLES, CONNECTORS, HARDWARE, ANTENNA AND
RELATED AIRCRAFT STRUCTURE FOR INTEGRITY, SECURITY, WEAR, CHAFFING, AND ETC.. SPECIAL
ATTENTION SHOULD BE GIVEN TO THE AIRCRAFT PRIMARY STRUCTURE WITH REGARDS TO FATIGUE AND
STRESS CRACKING, CORROSION, AND ETC..
6. TROUBLESHOOTING INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE
SYSTEM MAINTENANCE MANUAL P/N 150-1364-000 REV. E, DATED SEP. 90 OR LATER REVISION.
7. REMOVAL AND REPLACEMENT INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE
RADIOTELEPHONE SYSTEM MAINTENANCE MANUAL P/N 150-1364-000 REV. E, DATED SEP. 90 OR
LATER REVISION. SHOULD IT BECOME NECESSARY TO REMOVE THE FLITEFONE VI, SECURE THE ASSOCIATED
CABLES AND WIRING, COLLAR THE APPLICABLE CIRCUIT BREAKERS, PLACARD THE AIRCRAFT THAT THE UNIT
HAS BEEN REMOVED, REVISE THE WEIGHT & BALANCE AND THE EQUIPMENT LIST AND MAKE A LOGBOOK ENTRY
THE UNIT HAS BEEN REMOVED FOR SERVICE, REFER TO 91.213 OF TITLE 14 OF THE CODE OF FEDERAL
REGULATIONS AND/OR THE AIRCRAFT'S MEL.
8. DIAGRAMS: THERE ARE NO ACCESS PLATES THAT NEED TO BE REMOVED FOR INSPECTION.
9. SPECIAL INSPECTION REQUIREMENTS: SPECIAL INSPECTION REQUIREMENTS ARE NOT APPLICABLE.
10. APPLICABLE. APPLICATION OF PROTECTIVE TREATMENTS: APPLICATION OF PROTECTIVE TREATMENTS ARE NOT
11. DATA: INSTALLATION REQUIREMENTS MAY BE FOUND WITHIN THE ACCEPTED INDUSTRY PRACTICES
CHAPTERS 1, 2, 3, 11, AND 13.
CONTAINED WITHIN AC 43.13-1B CHAPTERS 4, 6, 7, 11, AND 12, AND IN ACCORDANCE WITH AC 43.13-2A
EFTA00012093

=== Page 426 ===

=== Page 427 ===
:RAYTHEON AIRCRAFT SERVICES
PAGE 2 OF 2
SAN ANTONIO, TX.
DOCUMENT NO. FF VI-ICA-RK-244
DATE: 12-22-99
12. LIST OF SPECIAL TOOLS: SPECIAL TOOLS ARE NOT REQUIRED.
13. FOR COMMUTER CATEGORY AIRCRAFT: NOT APPLICABLE, THIS AIRCRAFT NOT COMMUTER CATEGORY
AIRCRAFT
a. ELECTRICAL LOADS: THE RAYTHEON AIRCRAFT SERVICES ELECTRICAL LOAD ANALYSIS DOCUMENT
#
REV.
DATED
AND THE RAYTHEON AIRCRAFT SERVICES EMI/RFI GROUND
TEST PROCEDURES DOCUMENT #
REV.
DATED
HAVE BEEN PLACED IN THE AIRCRAFT
AS PART OF THE AIRCRAFT's PERMANENT RECORDS.
b. METHODS OF BALANCING FLIGHT CONTROLS: N/A TO THIS INSTALLATION
C. IDENTIFICATION OF PRIMARY AND SECONDARY STRUCTURES: N/A TO THIS INSTALLATION
d. SPECIAL REPAIR METHODS APPLICABLE TO THE AIRPLANE: N/A TO THIS INSTALLATION
14. RECOMMENDED OVERHAUL PERIODS: THERE ARE NO ADDITIONAL OVERHAUL TIME LIMITATIONS.
15. AIRWORTHINESS LIMITATION SECTION: THERE ARE NO ADDITIONAL AIRWORTHINESS LIMITATIONS.
16. REVISION: THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CHECKLIST (ICA) MAY BE REVISED BY
SUBMITTING A LETTER TO THE LOCAL FSDO WITH A COPY OF THE REVISED FAA FORM 337 AND REVISED ICA.
THE FAA INSPECTOR ACCEPTS THE CHANGE BY SIGNING BLOCK 3 AND INCLUDING THE FOLLOWING
STATEMENT: (DATE "THE ATTACHED REVISED/NEW INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
) FOR THE ABOVE AIRCRAFT OR COMPONENT MAJOR ALTERATION HAVE BEEN ACCEPTED BY
THE FAA, SUPERSEDING THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (DATE
)." ONCE THE
ITS LOCATION AND DATE OF THE FORM 337.
REVISION HAS BEEN ACCEPTED, A MAINTENANCE RECORD ENTRY WILL BE MADE, IDENTIFYING THE REVISION,
17. ASSISTANCE: NOT APPLICABLE.
18. IMPLEMENTATION AND RECORD KEEPING:
a. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH FAA FIELD APPROVAL POLICY, THE
OWNER/OPERATOR OPERATING UNDER PART 91 IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE
PART OF THE APPLICABLE SECTION 91.409 INSPECTION PROGRAM FOR THEIR AIRCRAFT. THIS IS
ACCOMPLISHED WHEN A MAINTENANCE ENTRY IS MADE IN THE AIRCRAFT'S MAINTENANCE RECORD IN
ACCORDANCE WITH SECTION 43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE
ORIGINAL REQUIREMENTS. ICA LOCATION (e.g., BLOCK 8 OF FAA FORM 337) ALONG WITH A INSPECTION/MAINTENANCE
b. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH A FIELD APPROVAL ON AIR CARRIER
AIRCRAFT, THE AIR CARRIER OPERATOR IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE PART OF THE
APPLICABLE INSPECTION/MAINTENANCE PROGRAM FOR THEIR AIRCRAFT. IF A PROCEDURE IS NOT
CURRENTLY INCLUDED IN THE OPERATOR'S MANUAL TO INCORPORATE ICA, THIS PROCESS WILL NEED TO
BE APPROPRIATELY ADDRESSED (i.e. THE OPERATOR SUBMITS A REVISION TO ITS MAINTENANCE PROGRAM
TO THE APPLICABLE CERTIFICATE-HOLDING DISTRICT OFFICE (CHDO).
C. FOR AIRCRAFT INSPECTED UNDER AN APPROVED AIRCRAFT INSPECTION PROGRAM (AAIP), THE OPERATOR
WILL SUBMIT A CHANGE TO THE CHDO IN ACCORDANCE WITH SECTION 135.419B.
d. FOR AIR CARRIER AIRCRAFT INSPECTED USING AN ANNUAL 100 HOUR INSPECTION PROGRAM, A REFERENCE
TO NEW ICA WILL BE MADE IN THE AIRCRAFT'S MAINTENANCE RECORD IN ACCORDANCE WITH SECTION
ICA ARE LOCATED/ATTACHED TO BLOCK 8 OF FAA FORM 337). IN ADDITION, THE OPERATOR WILL
43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE ORIGINAL ICA LOCATION (e.g.,
REQUEST A REVISION TO THE OPERATOR'S OPERATIONS SPECIFICATIONS, ADDITIONAL MAINTENANCE
REQUIREMENTS, WHICH INCORPORATES THE ICA INTO THE INSPECTION PROGRAM.
EFTA00012095

=== Page 428 ===

=== Page 429 ===
Form Approved
MAJOR REPAIR AND ALTERATION
OMB No. 2120-0020
U.S. Department
(Airframe, Powerplant, Propeller, or Appliance)
of Transportation
For FAA Use Only
Federal Aviation
Office Identification
Administration
SW FSDO 17
BPR
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions
and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000
for each such violation (Section 901 Federal Aviation Act of 1958).
Make
Model
1. Aircraft
RAYTHEON
400A
Serial No.
Nationality and Registration Mark
RK-244
USA
N428HR
Name (As shown on registration certificate)
Address (As shown on registration certificate)
2. Owner
RAYTHEON AIRCRAFT COMPANY
WICHITA, KANSAS 67201-0085
3. For FAA Use Only
4. Unit Identification
5. Type
Unit
Make
Model
Serial No.
Repair
Alteration
AIRFRAME
(As described in Item 1 above)
X
POWERPLANT
PROPELLER
Type
APPLIANCE
Manufacturer
6. Conformity Statement
A. Agency's Name and Address
B. Kind of Agency
C. Certificate No.
RAYTHEON AIRCRAFT SERVICES
U.S. Certificated Mechanic
CRS-XA14605K
Foreign Certificated Mechanic
SAN ANTONIO TEXAS 78216
X
LIMITED AIRFRAME
Certificated Repair Station
Manufacturer
RADIO CLASS I,II,III
D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto
have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
furnished herein is true and correct to the best of my knowledge.
Date
12-22-99
Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the
Administrator of the Federal Aviation Administration and is
X
APPROVED
REJECTED
FAA Flt. Standards
Manufacturer
Inspection Authorization
Other (Specify)
BY
Inspector
FAA Designee
X
Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection
Certificate or
12-22-99
Designation No.
CRS-XA14605K
FAA Form 337 (12-88)
EFTA00012097

=== Page 430 ===
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
MAKE: RAYTHEON 400A
S/N: RK-244
REG: N428HR
DATE: 12-22-99
INSTALLED A SUNDSTRAND MK-VI GROUND PROXIMITY WARNING SYSTEM CONSISTING OF THE
FOLLOWING EQUIPMENT:
MOD/MFG
DESCRIPTION
P/N
WEIGHT
ARM
MK-VI
GPWS COMPUTER
965-0686-020
4.2
33.1
ADC-500
CONVERTER
500-8020
2.3
38.2
BRACKET & PLATE
0.5
36.1
WIRING & CONNECTOR
3.5
54.0
THE SUNDSTRAND MK-VI GPWS SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE STC
#SA3322SO ISSUED 09-18-92 AND REISSUED 10-04-95 AND THE HANGER ONE MASTER DRAWING LIST
#11892-GPWS, REV. D DATED 03-22-93. THE ELECTRICAL WIRING WAS INSTALLED IN ACCORDANCE
WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #RAS-67-9917 REV. IR DATED 11-05-99,
REFERENCE THE FORM 8110-3 DATED 11-23-99 APPROVED BY ROBERT M. HURLEY, DESIGNATED
ENGINEERING REPRESENTATIVE #DERT-710137-SW, SYSTEMS AND EQUIPMENT.
A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR
25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING
SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE
AIRCRAFT.
THE SUNDSTRAND MK-VI GPWS APPROVED FLIGHT MANUAL SUPPLEMENT, REV. B DATED 03-30-93
HAS BEEN INSERTED IN THE SUPPLEMENT SECTION OF THE AIRCRAFT FLIGHT MANUAL AND THE
GPWS PILOTS GUIDE P/N 060-4087-000 REV. A DATED 10-96 HAS BEEN INSERTED IN THE AIRCRAFT
AS PART OF THE AIRCRAFTS PERMANENT RECORDS.
THE AIRCRAFT WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST WERE REVISED TO
REFLECT THIS MODIFICATION AND BOTH FORMS WERE INSERTED IN THE AIRCRAFT FLIGHT
MANUAL.
END
X
Additional Sheets Are Attached
*
U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157
EFTA00012098

=== Page 431 ===
Hnited States of America
Department of Transportation-Federal Abiation Administration
Supplemental Tupe Certificate
Number
SA3322SO
Raytheon Aircraft Services, Inc.
This lificate, issued to
Fulton County Airport-Brown Field
Atlanta, Georgia 30336
cortifies that the change in the type design for the following product with the limitations and conditions
therefor ass recified hereon meels the airwor thiness requirements of Purk
25 oftho
Federal Aviation
Regulations
Original Product Type Certification Number:
A16SW
Make:
Beech
Medel:
400A
Description Type Design Chango: Installation of a Sundstrand MK VI GPWSm accordance with Jangar
One. Drawing List No. 11892-GPWS, Rev. B, dated September 17, 1992, or later FAA Approved revision.
Limilations and Conditions:
This approval should not be extended to other aircraft of this model on which
other previously approved modifications are incorporated unless it is determined by the installer that the
interrelationship between this change and any of those other previously approved modifications will produce no
adverse effect upon the airworthiness of that aircraft. FAA Approved Airplane Flight Manual Supplement,
dated September 18, 1992, is a required part of this STC.
This tificate and the parting data which is the basis for approval in effect. until sur-
rendereds. suy spendeds roockeds or a termination date is otherwise as lablished by the Adminis is trator of the
Federal Aviation Administrations
Date Date of application:
August 5, 1992
Take missund:
October 4, 1995
Date of fissuance:
September 18, 1992
amended:
FEDERAL AVIATION
*
*
ADMINISTRATION
Associate Manager, ACE-116A
Atlanta Aircraft Certification Office
(Title)
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
This certificate may be transferred in accordance with FAR 21.47.
FAA Fotm 8110-2(10-68)
EFTA00012099

=== Page 432 ===
T

=== Page 433 ===
DNAWING LIST
DWG. LIST NO. 11892-GPWS
DATE 9/1/92
REV. D
DATE 3/22/93
ET 1 OF 1 SYSTEM SUNDSTRAND MK-VI GPWS
AIRCRAFT TYPE BEECHJET 400F
F.A.A. PROJECT NO. CE-115A-2970
STC SA3322S0
DATED 9/18/92
REVISION
DRAWING NO.
TITLE
SHTS
LTR
PAGE
DATE
EO/REMAR
TRI-92-108
9-2-92
STRUCTURAL SUBSTANIATION REPORT GPWS
AFMS
B
3/22/93
AIRPLANE FLIGHT MANUAL SUPPLEMENT
6
060-3942
6/92
INSTALLATION DESIGN GUIDE
11892-2
A
3/22/93
INSTALLATION PROCEDURES
11892-3
A
3/22/93
BLOCK DIAGRAM
1
1
11892-4
D
3/22/93
WIRING DIAGRAMS
2
1&2
11892-5
8-29-92
PARTS LIST & GENERAL NOTES
11892-6
8-29-92
GPWS MOUNTING PLATE
11892-7
8-31-92
ADC-500 MOUNTING PLATE
11 -8
8-29-92
SUPPORT BRACKET
892-1
A
3/22/93
GROUND TEST PROCEDURES
060-3956-000
D
9/17/92
FLIGHT TEST PROCEDURES
500-8000-RO
8/29/92
DESIGN SPECIFICATIONS ADC-500
EFTA00012101

=== Page 434 ===

=== Page 435 ===
U.S. DEPARTMENT OF TRANSPORTATION
DATE
FEDERAL AVIATION ADMINISTRATION
11/23/99
STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS
AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
MAKE
MODEL NO.
TYPE (Arplane, Radio, Helscopter.
NAME OF APPLICANT
etc)
Beech
400A
Airplane
Raytheon Aircraft Services
LIST OF DATA
IDENTIFICATION
TITLE
Raytheon Drawings
RAS-67-9917
Rev IR
Sundstrand Mk-VI Ground Proximity Warning Sys
Dated 11/05/99
Note: This approval is for the Electrical aspects of the engineering
design data only, and is not installation approval.
Approval for aircraft S/N RK-244 only.
Approval for GPWS is for only the minor deviations
to FAA STC SA3322SO.
After modification is complete, perform EMI/RFI
test in accordance with Raytheon report
RAS-GF-9714, EMI/RFI Test Procedure.
PURPOSE OF DATA
In support of a modification to install a GPWS in serial number RK-244.
APPLICABLE REQUIREMENTS (Lass specific sections)
FAR 25.1301 a,b,c
FAR 25.1359 d
FAR 25.1431 C
CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations
of appointment None under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered
requirements of the Federal Aviation Regulations.
have been examined in accordance with established procedures and found to comply with applicable
I (xx) Therefore
Recommend approval of these data
X
Approve these data
SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)
DESIGNATION NUMBERS(S)
CLASSIFICATION(S)
DERT-710137-SW
Systems & Equipment
FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION
GPO 901-
11-23-99 13:55
RECEIVED FROM:512 989-2998
P.03
EFTA00012103

=== Page 436 ===

=== Page 437 ===
Form Approved
O.M.B. No. 2120-0018
APPLICATION FOR
INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA
use only. Submit original only to an authorized FAA Representative. If additional
us Department
AIRWORTHINESS
space is required, use an attachment. For special flight permits complete Sections
of Transportation
CERTIFICATE
II and VI or VII as applicable
Federal Aviation
Administration
REGISTRATION MARK
AIRCRAFT BUILDER'S NAME (Make)
3. AIRCRAFT MODEL DESIGNATION
4. YR. MFR
FAA CODING
N428HR
RAYTHEON AIRCRAFT COMPANY
400A
1999
DESCRIPTION
7150010
I. AIRCRAFT
5. AIRCRAFT SERIAL NO.
6. ENGINE BUILDER'S NAME (Make)
7. ENGINE MODEL DESIGNATION
RK-244
Pratt & Whitney Canada
JT15D-5
52113
4
8. NUMBER OF ENGINES
9. PROPELLER BUILDER'S NAME (Make)
10. PROPELLER MODEL DESIGNATION
2
11. AIRCRAFT IS (Check if applicable)
N/A
N/A
IMPORT
APPLICATION IS HEREBY MADE FOR: (Check applicable items)
A
1
X
STANDARD AIRWORTHINESS CERTIFICATE (Indicate category)
NORMAL
UTILITY
ACROBATIC
X
TRANSPORT
GLIDER
BALLOON
B
SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)
2
LIMITED
5
1
CLASS I
PROVISIONAL (Indicate class)
II. CERTIFICATION REQUESTED
2
CLASS II
1
AGRICULTURE AND PEST CONTROL
2
AERIAL SURVEYING
3
AERIAL ADVERTISING
3
RESTRICTED (Indicate operation(s) to
be conducted)
4
FOREST (Wildlife conservation)
5
PATROLLING
6
WEATHER CONTROL
7
CARRIAGE OF CARGO
0
OTHER (Specify)
1
RESEARCH AND DEVELOPMENT
2
AMATEUR BUILT
3
EXHIBITION
EXPERIMENTAL (Indicate operation(s)
4
to be conducted)
4
RACING
5
CREW TRAINING
MKT. SURVEY
0
TO SHOW COMPLIANCE WITH FAR
1
FERRY FLIGHT FOR REPAIRS, ALTERATIONS, MAINTENANCE OR STORAGE
SPECIAL FLIGHT PERMIT (Indicate
operation to be conducted. then
2
8
EVACUATE FROM AREA OF IMPENDING DANGER
complete Section VI or VII as
3
applicable on reverse side)
OPEATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT
4
DELIVERING OR EXPORT
5
PRODUCTION FLIGHT TESTING
6
CUSTOMER DEMONSTRATION FLIGHTS
C
6
MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE "Restricted Operation" and "Standard" or "Limited." as applicable.)
A. REGISTERED OWNER (As shown on certificate of aircraft registration)
IF DEALER, CHECK HERE-
X
NAME
ADDRESS
RAYTHEON AIRCRAFT COMPANY
P.O. BOX 85 WICHITA, KS 67201
B. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated)
AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No.
and Revision No.) A16SW, Rev. 19
AIRWORTHINESS DIRECTIVES (Check if all applicable AD's complied with and give
X
X
latest AD No.)
ISSUE 99-20
III. OWNER'S CERTIFICATION
AIRCRAFT LISTING (Give page number(s))
N/A
SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporated)
N/A
C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS
CHECK IF RECORDS IN
TOTAL AIRFRAME HOURS
EXPERIMENTAL ONLY (Enter hours flown since last certificate
X
COMPLIANCE WITH
6:40
3
issued or renewed)
N/A
FAR 91.473. 417
D. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above; that the aircraft is registered with the Federal Aviation
Administration in accordance with Section 501 of the Federal Aviation Act of 1958, and applicable Federal Aviation Regulations; and that the aircraft has been inspected and is
airworthy and eligible for the airworthiness certificate requested.
DATE OF APPLICATION
10-01-99
Eugene Hainstock- Administrative Staff QA
A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete this Section
FAR PART 121 OR 127 CERTIFICATE HOLDER (Give
IV. INSPECTION
CERTIFICATED MECHANIC (Give
AGENCY
VERIFICATION
2
Certificate No.)
3
Certificate No.)
CERTIFICATED REPAIR STATION (Give Certificate
6
No.)
AIRCRAFT MANUFACTURER (Give name of firm)
5
DATE
TITLE
SIGNATURE
(Check ALL applicable blocks in items A and B)
X
THE CERTIFICATE REQUESTED
A. I find that the aircraft described in Section I or VII meets requirements for
4
AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE
B. Inspection for a special permit under Section VII
FAA INSPECTOR
FAA DESIGNEE
V. /.FAA
REPRESENTATIVE
CERTIFICATION
was conducted by:
CERTIFICATE HOLDER UNDER:
FAR 65
FAR 121, 127 OR 135
FAR 145
DATE
DISTRICT OFFICE
FAA INSPECTOR'S SIGNATURE
4
10-01-99
CE-43
1
FAA Form 8130-6 (11-88) SUPERSEDES PREVIOUS EDITION
*U.S. GPO:1989-241-672/90913
EFTA00012105

=== Page 438 ===
EFTA00012106
A. MANUFACTURER
NAME
ADDRESS
VI. PRODUCTION
FLIGHT TESTING
B. PRODUCTION BASIS (Check applicable item)
PRODUCTION CERTIFICATE (Give production certificate number)
TYPE CERTIFICATE ONLY
APPROVED PRODUCTION INSPECTION SYSTEM
C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS
DATE OF APPLICATION
NAME AND TITLE (Print or type)
SIGNATURE
A. DESCRIPTION OF AIRCRAFT
REGISTERED OWNER
ADDRESS
BUILDER (Make)
MODEL
SERIAL NUMBER
REGISTRATION MARK
B. DESCRIPTION OF FLIGHT
CUSTOMER DEMONSTRATION FLIGHTS
(Check if applicable)
FROM
TO
VIA
DEPARTURE DATE
DURATION
C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT
PILOT
CO-PILOT
NAVIGATOR
OTHER (Specify)
VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST
D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS:
E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment if necessary)
F. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above; that the aircraft is registered with the Federal Aviation Administration in
accordance with Section 501 of the Federal Aviation Act of 1958, and applicable Federal Aviation Regulations; and that the aircraft has been inspected and is airworthy for the flight
described.
DATE
NAME AND TITLE (Print or type)
SIGNATURE
X
A. Operating Limitations and Markings In Compliance with FAR 91.9
G. Statement of conformily. FAA Form 8130-9 (Attach when required)
91,31-9 as Applicable
H. Foreign Airworthiness Certification for Import Aircraft
VIII. AIRWORTHINESS
DOCUMENTATION
(FAA use only)
B. Current Operating Limitations Attached
(Attach when required)
C. Data, Drawing. Photographs, etc. (Attached when required)
1. Previous Airworthiness Certificate Issued in Accordance with
X
D. Current Weight and Balance Information Available in Aircraft
FAR
CAR
(Original Attached)
E. Major Repair and Alteration, FAA Form 337 (Attached when required)
X
J. Current Airworthiness Certificate Issued in Accordance with
X
F. This inspection Recorded in Aircraft Records
FAR 21,183 (a) per 183.31 (Copy attached)

=== Page 439 ===
UNITED STATES OF AMERICA
DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
STANDARD AIRWORTHINESS CERTIFICATE
1 NATIONALITY AND
2 MANUFACTURER AND MODEL
3 AIRCRAFT SERIAL
4 CATEGORY
REGISTRATION MARKS
RAYTHEON AIRCRAFT COMPANY
NUMBER
N428HR
400A
RK-244
TRANSPORT
5 AUTHORITY AND BASIS FOR ISSUANCE
This airworthiness certificate IS issued pursuant to the Federal Aviation Act of 1958 and certifies that, as of the date of issuance, the
aircraft to which issued has been inspected and lound to conform to the type certificate therefor, to be in condition for safe
operation. and has been shown 10 meet the requirements of the applicable comprehensive and detailed airworthiness code as
provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein.
Exceptions.
NONE
6 TERMS AND CONDITIONS
Unless sooner surrendered, suspended. revoked. or a termination date IS otherwise established by the Administrator, this
airworthiness certificate is effective as long as the maintenance, preventative maintenance, and allerations are performed in
accordance with Parts 21.43. and 91 of the Federal Aviation Regulations as appropriate and the aircraft IS registered in the United
States.
DATE OF ISSUANCE
DESIGNATION NUMBER
10-01-99
DMIR CE-501157
Any alteration, reproduction. or misuse of this certificate may be punishable by a fine not exceeding 1,000, or imprisonment not exceeding 3
years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL
AVIATION REGULATIONS.
FAA Form 8100-2 (8-82)
* U.S. GOVERNMENT PRINTING OFFICE: 1991 668-228
EFTA00012107

=== Page 440 ===
1
EFTA00012108

=== Page 441 ===
1. Country Pays
2.
T<E
Transport
Transports
L/H
Form
3. Certificate Ref. No. N° de référence du bon
Canada
Canada
CANADA
Formulaire
24-0078
AUTHORIZED RELEASE CERTIFICATE BON DE SORTIE AUTORISÉ
SEE BLOCK 5
4 Organization Organisme
5 Work Order/Contract/invorce Bon de travadicontrat/facture
Pratt & Whitney Canada
Longueuil, Quebec J4G 1A1
P.O. # 4000014605
Une società de United Technologies United Technologies Company
6 Item
7 Description
8 Part No N° de pièce
9 Eligibility Admissibilité
10. Qty Qté
11. Senal/Batch No N° de sénefit
12. Status/Work État/travail
1
FREE TURBINE
3030100
VARIOUS
1
PCE-JA0256
MANUFACTURED
TURBOFAN
JT15D-5
13 Remarks Remarques
CANADIAN TYPE APPROVAL E-11, FAA TYPE CERTIFICATE E25EA.
THIS ENGINE CONFORMS TO ITS UNITED STATES TYPE DESIGN (TYPE CERTIFICATE NUMBER E25EA) AND IS IN CONDITION FOR SAFE OPERATION
THIS ENGINE HAS BEEN SUBJECTED BY THE MANUFACTURER TO A FINAL OPERATION CHECK AND IS IN A PROPER STATE OF AIRWORTHINESS.
14 New Parts Pièces neuves
AWM
Chapter 551
19. Used Parts Pièces usagées
CAR
571.10 Maintenance Release
M de N
Chapitre 561
RAC
571 10 Certification après maintenance
Certified that the part(s) identified above, except as
. est certifié que la (les) piéce(s) identifiée(s) chaut
Certified that the maintenance specified above has been
otherwise specified in block 13. has (have) been
II est certifié que la maintenance spécifiée chaut, a été
sauf & autrement spécifié à la case 13. a (ont) été
performed in accordance with the applicable standards
manufactured/inspected in accordance with the
construte(s)inspectée(s) conformément aux données de
effectuée conformément aux normes de navigabilité
of airworthiness Except as otherwise specified in block
applicable, design data and with the airworthiness
applicables Sauf si autrement spécifié. à la case 13, la
conception pertinentes et aux règlements de navigabilité
13, the part(s) IS (are) released for service.
la remise en service de la (des) pièce(s) est autonsée.
diqué.
16. Approval Ref. No. Ref. d'autonsation
20. Signature
21. Approval Ref. No Ref d'autonsation
DOT APPROVAL 4 58
10. Date
22 Name (typed or printed) Nom (dactylographie ou imprimé)
23 Date
MAY 1 8 1999
Installer must cross-check eligibility with applicable technical data Le monteur doit vérifier l'admissibilité avec les données techniques pertinentes.
USER/INSTALLER RESPONSIBILITIES
RESPONSABILITÉS DE L'USAGER/MONTEUR
It is important to understand that the existence of this document alone does not automatically constitute authority to
. est important de bien comprendre que de par son existence ce document ne constitue pas forcément
install the part/component/assembly
l'autorisation d'instailer la piéce/composant/ensemble.
Where the user/installer works in accordance with the national regulations of an Airworthiness Authority different than
Lorsque Tusager/monteur(euse) travaille conformément aux réglements nabonaux d'une autorité de
the Airworthiness Authority of the country specified in block 1 if IS essenbal that the userfinstatter ensures that his/her
navigabrité, autre que rautorité de navigabilité inscrite à la case 1, a est essentel que fusager/monteur(euse)
Anworthiness Authority accepts parts/components/assembles from the Airworthiness Authority of the country specified
an block 1.
s'assure que son autonté de navigabilité accepte les piéces/composants/ensembles de Tautorité de
navigabile inscrite a la case 1.
Statements 14 and 19 do not constitute installation certification In all cases the aircraft technical maintenance record
Les déclarations apparaissant Bux cases 14 et 19 ne constituent pas une certification de montage En tout
must contain a maintenance installation certification issued in accordance with the national regulation by the
temps le dossier technique de l'aéronef dod contenir une certification après maintenance émise selon les
userfinstaller before the aircraft may be nown
règlements nationaux, par Fusager/monteur(euse). avant que l'aéronet puisse décoller.
24-0078(1996-10)
EFTA00012109

=== Page 442 ===
R/H
2.
I*E
Transport
Transports
Form
3. Certificate Ref. No N° de réference du bon
Canada
Canada
Formulaire
24-0078
AUTHORIZED RELEASE CERTIFICATE BON DE SORTIE AUTORISÉ
SEE BLOCK 5
10
5 Work Order/Contract/Invoice Bon de traval/contrat/facture
:t & Whitney Canada
- de United Technologies United Technologies Company
Longueuil, Quebec J4G 1A1
P.O. # 4000016693
8 Part No N° de pièce
9 Eligibility Admissibilité
10 Qty Qté
11. Senal/Batch No N° de séne/lot
12. Status/Work État/travail
FREE TURBINE
3030100
VARIOUS
1
PCE-JA0257
MANUFACTURED
TURBOFAN
JT15D-5
PPROVAL E-11, FAA TYPE CERTIFICATE E25EA.
FORMS TO ITS UNITED STATES TYPE DESIGN (TYPE CERTIFICATE NUMBER E25EA) AND IS IN CONDITION FOR SAFE OPERATION
BEEN SUBJECTED BY THE MANUFACTURER TO A FINAL OPERATION CHECK AND IS IN A PROPER STATE OF AIRWORTHINESS.
ves
AWM
Chapter 561
19 Used Parts Pièces usagées
CAR
571.10 Maintenance Release
Mde N
Chapse 561
RAC
571.10 Certification après maintenance
dentified above. except as
II est certifié que la (les) piéce(s) identifiée(s) c-haut,
Certified that the maintenance specified above has been
II est certifié que la maintenance spécifiée ci-haut a doe
ock 13. has (have) been
sauf SI autrement spécifié à la case 13, a (ont) eté
performed in accordance with the applicable standards
effectuée conformément aux normes de navigabilité
n accordance with the
construte(s)/nspectée(s) conformément aux données de
of airworthiness Except as otherwise specified in block
applicables. Sauf si autrement spécifié, à la case 13, la
nd with the anworthiness
conception pertinentes et aux réglements de navigab.ité
13. the part(s) IS (are) released for service.
la remise en service de la (des) piece(s) est autorisée.
diqué.
16. Approval Ref. No. Ref. d'autonsation
20. Signature
21. Approval Ref. No. Ref. d'autorisation
DOT APPROVAL 4 58
18. Date
MAY 1 9 1999
22. Name (typed or printed) Nom (dactyfographie ou imprimé)
23, Date
Installer must cross-check eligibility with applicable technical data Le monteur doit vénfier admissibilité avec les données techniques pertinentes.
USER/INSTALLER RESPONSIBILITIES
RESPONSABILITÉS DE L'USAGER/MONTEUR
1 that the existence of this document alone does not automatically constitute authority to
II est important de bien comprendre que de par son existence ce document me constitue pas forcément
sembly.
Tautorisation d'installer la piêce/composant/ensemble.
ks in accordance with the national regulations of an Airworthiness Authority different than
Lorsque fusager/monteur(euse) travaille conformément aux règlements nationaux d'une autorité de
X the country specified in block 1 it IS essential that the user/installer ensures that his/her
navigabilité, autre que Fautonté de navigabile inscrite à la case 1, il est essenbel que Fusager/monteur(euse)
pts parts/components/assemblies from the Airworthiness Authority of the country specified
s'assure que son autorité de navigabilité accepte les pièces/composants/ensembles de l'autorité de
navigabilité inscrite à to case 1.
at constitute installation certification in all cases the awcraft technical maintenance record
Les déclarations apparaissant aux cases 14 et 19 ne construent pas une certification de montage En tout
ce installation certification issued in accordance with the national regulation by the
temps le dossier technique de Taéronet dot contens une certification après maintenance émise selon les
aft may be flown
réglements nationaux, par "usagerimonteur(euse). avant que Taéronet puisse décoller.
EFTA00012110


