								OMB No. 2120-0020	Electronic Tracking Number
			MAJOR REPAIR AND ALTERATION					Exp: 5/31/2018
			(Airframe, Powerplant, Propeller, or Appliance)						For FAA Use Only
		such violation. (49 U.S.C. §46301(a))							INSTRUCTIONS: Print or type all entries. See Tille 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 resort in a civil penshy for each
		Nationality and Registration Mark			Serial No.
1. Alrcraft		UNITED STATES / N188TS					RK-244
	Make		RAYTHEON AIRCRAFT COMPANY		Model	400A			Series
			Name (As shown on registration certificate)		Address				Address (As shown on registration certificate)
2. Owner		THORAIR LLC			City		SANDUSKY		OHIO State
					Zip		44871-2218		UNITED STATES Country
				3. For FAA Use Only

4. Туре				5. Unit Identification
Repair	Alteration	Unit	Make				Model		Serial No.
		AIRFRAME	RAYTHEON AIRCRAFT COMPANY				(As described in Item 1 above)		RK-244
		POWERPLANT
		PROPELLER
		APPLIANCE	Type
			Manufacturer
				6. Conformity Statement
A. Agency’s Name and Address Name	Constant Aviation LLC			B. Kind of Agency U. S. Certificated Mechanic					Manufacturer
Address				Foreign Certificated Mechanic					C. Certificate No.
City	CLEVELAND	USA	OH State	Certificated Repair Station					CRS#WC7R346J
44143 Zip	furnished herein is true and of	Country	have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information	Certificated Maintenance Organization					D. I certify that the repair and/or alteration made to the unit(s) identified in tem 5 above and described on the reverse or attachments hered
Extended range fuel per 14 CFR Part 43 App. B									10/04/2019
					urn to Service
			Pursuant to the authority given persons specified below, the unit identified in item 5 Administrator of the Federal Aviation Administration and is		Approved		was Rejected		inspected in the manner prescribed by the
BY	FAA FIt. Standards Inspector		Manufacturer	Maintenance Organization				Department of Transport	Persons Approved by Canadian
	FAA Designee		Repair Station	Inspection Authorization			Other (Specify)
Certificate or Designation No. CRS#	WC7R346J		Signature/Date of Authorized Individual						10/04/2019
CAA Corm 227 (10/06)

FAA Form 337 (10/06)

NOTICE
Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. M alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.

S. Description of Work Accomplished (Il more space is moulted. attach additional sheets. Identify mitt steal? nationally end registratIon m** end date work completed)
mov2019 UNITED STATESIMOSTS Nationality and RegistraMn 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 FM 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 Arc Attached

	U.S. DEPARTMENT OF TRANSPORTAllON FEDERAL AVIATION ADMINISTRATION		STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS		1. DATE November 30, 2018
			AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MANE Textron Aviation	3. MODEL NO. N541000-004		4. TYPE Mkorst &*e. Propeller, ea) Forebody Assy	Cleveland, Ohio	S. NAME OF APPLICANT Nextant Aerospace LLC
			LIST OF DATA
SLREIffla
NT-EO-1118-31 Rev. IR November 29, 2018	Engine Inlet Rivet Repair.	—
	Notes: 2)		approval Is only for the engineering data. It Indicates the data listed above subparagraph listed below as ’Applicable Requirements.”		1) The structural aspects only of the above listed data are approved herein. This demonstrates compliance only vAth the regulations specified by paragraph and This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair.
SRN R0010 under Nextant Aerospace Work Order No.10585.1.1. 9. APPLICABLE REQUIREMENTS (UM speckle sections) CFR Title 14 Part 25.301(25-23), 25.303(25-23], 25.305(a)(bUcX25-23), 25.307(a125-231, 25.801[25-00), 25.619[25-23]. and 25.625(a)(0XcX25-231.					e. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004, 25.603(aXbXc)(25-38), 25.605(a){25-00), 25.807(25-23), 25.809(eXbX25-00], 25.811(25-2n 25.813(aXbXcX25-00],
re. CERTFICATION - Under minority Pen 193. dots nand above and on ’Bathed appacsoie requirements of the AInvortnIness I (We) Therefore it SIGNATURE(S) OF DESIGNATED ENGINEERING RE PRESENTAttVE(S) 4 Z.–; pre:7 .–	Standards Listed approval of these data ❑ Recommend FrA. Approve these data		12. DESIGNATION NUMBERS(S) DERT-410115-CE		wired bydrecelon of the AdrranIstralor end In accordance with conditions and Ilmitallons of appcdnMsent under 14 CFR sheds numbered _BA, have been emartned in accordance with established procedures all found es coos* et I3. CLASSIFICATION(S) Structures
	FAA Form 8110.3 (03-10) SUPERSEOES PREVIOUS EDITION		File Number. H18777-01		Page 1 of 1

and the state of the state of the states of the states

and the comments of the comments of

and the comments of the comments of the comments of and the same of the same of the same

and the comments of the comments of

1 1. 1. 1.

and the comments of the comments of the comments of the contraction of the contribution of the contribution of the contribution of the contribution of the contribution of the and and the comments of the country

Comments of the comments of the comments of

			MAJOR REPAIR AND ALTERATION					OMB No. 2120-0020 Exp: 5/31/2018		Electronic Tracking Number
			(Airframe, Powerplant, Propeller, or Appliance)						For FAA Use Only
		such violation. (49 U.S.C. §46301(a))	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 ferrired by law (49 U.S.C. §44701). Fallure to report can result in a civil perally for each
		Nationality and Registration Mark UNITED STATES / N188TS			Serial No.	RK-244
1. Aircraft	Make		RAYTHEON AIRCRAFT COMPANY		Model 400A				Series
		Name (As shown on registration certificate)			Address (As shown on registration certificate) Address
2. Ownor		THORAIR LLC			City Zip	SANDUSKY 44871-2218		Country		OHIO State UNITED STATES
				3. For FAA Use Only

4. Туре				5. Unit Identification
Repair	Alteration	Unit	RAYTHEON AIRCRAFT COMPANY	Make Model			RK-244		Serial No.
		AIRFRAME			(As described in Item 1 above)
		POWERPLANT
		PROPELLER
		APPLIANCE	lype Manufacturer
A. Agency’s Name and Address				6. Conformity Statement B. Kind of Agency
Name	Constant Aviation LLC				U. S. Certificated Mechanic				Manufacturer
Address			OH		Foreign Certificated Mechanic				C. Certificate No.
City CLEVELAND 44143 Zip	Country	USA	State		Certificated Repair Station Certificated Maintenance Organization					CRS#WC7R346J
			D. I certify that the repair and/or alteration made to the unit(s) identified in them 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 Avialion 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 specifica persu Administrator of the Federal Aviation Administration and Is		me unu wentified in item 5 Approved	was	Rejected			inspected in the manner prescribed by the
Inspector BY	FAA Fit. Standards		Manufacturer	Maintenance Organization				Department of Transport	Persons Approved by Canadian
	FAA Designee		Repair Station	Inspection Authorization		Other (Specify)
Certificate or Designation No. CRS#	WC7R346J		Signature/Date of Authorized Individual							10/04/2019

FAA Form 33/ ua

NOTICE
Weight and balance or operating limitation changes shall be entered ✓n the appropriate aircraft record. M alteration must be compatible with ail previous alienations to assure continued conformity with the applicable airworthiness requirements.

8. Description of Work Accomplished (f mote space Is reputed. attach additional sheets ;den* Mih sitar* nationality and regisfratton math and date soak completed)
UNITED STATES! NIESTS IW04/2019
Nationality end 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-ED-1118-31 rev IR dated 11/29/2018 with FM 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





















FlAdditional Sheets Are Attached

		STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS		November 30, 2018
		AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION
2. MAKE Textron Aviation	S. MODEL NO. N541000-004	4. TYPE (Aber* Engine, People, art) Forebody Assy	Cleveland, Ohio	& NAME OF APPLICANT Nextant Aerospace LLC
		LIST OF DATA
& PENTIF(GM.PN		7. TITLE
NT-EO-1118-31 Rev. IR November 29, 2018	Engine Inlet Rivet Repair.
—	Notes:	—END
	1) The structural approval is demonstrates subparagraph	aspects only of the above Ilsted only for the engineering data. It Indicates compliance only with the regulations listed below as ’Applicable Requirements.”		data are approved herein. This the data listed above specified by paragraph and
	2) substantiation	This form constitutes FAA approval of all the of compliance to necessary requirements		engineering data necessary for for the entire repair.


		a. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004,

		CFR nee 14 Pad 25.301[25-23], 25.303(25.23], 25.305(a)(b)(cX25-23), 25.307(aX25-23), 25.801[25-00), 25.603(aXb)(c)[25-38], 25.605(a)(25-00), 25.807[25-23), 25.609(a)(bX25-001, 25.811[25-23), 25.613(eXbXcX25-00),
		10. CERTIFICATION - WON surely veiled byAvalon of the Adeninistrstor end I n azeardance WM conekns end IrkatIons of appolnonent under I 4 CFR Pert 163. data bled above and cn attached thetas numbered N/A have been exalted In accordance wilh colablahed procedurea and found to complyv/4h
p	Recommend approval of these data El Approve Omni dale
S/N R0010 under Nextant Aerospace Work Order No.10565.1.1. 9. APPLICABLE REOUREMENTS (LMIIPodfic MadanN 25.619[25-23), and 25.625(aXbXcX25-23). aPIANON requarrmega of the AINronnIness Standards Listed I (We) Therefore I I. SIGNATURES) OF DESIGNATED ENGINEERNO REPRESENTAT1VE(SI		12. DESIGNATION NU)eERS(S)
ptridia ––C.o.		DENT-410115-CE
				13. CLASSFICATION(S) Structures

and the control control control control and the control of

100 million and the states of the states of the states of the states of the states of the states of the states of the states of the states of the states of the states of the

//REIMAGINED //REBUILT //REBORN

ENGINEERING ORDER

EO #: NT-EO-1118-31

Title: Engine Inlet Rivet Repair

		ARTICLE DESCRIPTION
Effectivity (Aircraft Model) Aircraft Serial Number(s) See Remarks Textron Aviation 400A
Dascription and or Reason		The purpose of this EO is a libe installedon of blind rivels (PN: CR3212-5-XX) of appropriate length in place of the damaged solid rivel (PN: MS204264DS-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 inglicity to the following list will read in association of MUOR FAA aggroval is required for all huma classfied as AUCOR.			:
AFM Change O YES & NO	RVSW O YES ZI NO	મહા O YES & NO	Inspection taskslinterval O YES & NO		Previous Major Repair/Altarations
						YES & NO MAJOR MINOR
airworthiness qualities?		Does this EO significantly affect weight, balance, structural strength, aircraft performance, powerplant operation, flight characteristics, or other			L YES	ON NO
					MINOR	MAJOR
	Can this EO be accomplished by accepted practices or elementary operations?				TYES	ONDO
	If impropedy done, could this EO appreciably affect airworthiness?				MAJOR	MINOR
				FAA APPROVAL/ 8110-3	YES	ONO
Classification	MAJOR [ MINOR [ STC (No. STC (No. ST02371LA )	Weight and/or Balance Change O YES & NO			A YES ONO
		GENERAL
Equipmont List Updats YES & NO	Remarks References Intet: P/N: N541000-004 SIN: R0010 WO: 10565.1.1 (Original WO, IR with approval), 13003 (IR.1 WO)
	CherryMax Process Specification: CA-1015
REVIS ON DATE	DESCRIPTION	REVISION
11/29/2018 ાસ્	Initial Proposal				ECRA NA	REVISEO BY P. Avshalumov
10/1/2019 IR.1	NA	P. Avshalumov




ACTION			DATE
Prepared By					10/1/2019
Checked By	10/1/2019
ally signed by Pinkhas Approved By 10/1/2019 alumov 00 2019.10.02 09:53:20 -04’00’

Page 1 of 3 This Document is Uncontrolled Once Printed

Comments of the comments of the comments of

. . . . . . . .

and the comments of the comments of

nextant actrospace

EO #: NT-EO-1118-31

Title: Engine Inlet Rivet Repair

ENGINEERING ORDER

ITEM	PROCEDURES INSTRUCTIONS
1	Visually inspect the engine inlet lip and barrel for any other damaged, missing or loose fasteners. · If no additional discrepancies are detected, confinue with repair as outlined below. · If additional descepancies are noted, contact Nextant Aerospace for disposition.
2	Visually inspect the engine rotor as delined in Sub Task 72-31-20-220-801 of the Williams International LINE MANTENANCE MANUAL - FJ44-3AP 111000-202 (latest revision). - If no additional discrepancies are detected, continue with repair as outlined below. - If additional discrepancies are noted, contact Nextant Aerospace for disposition.		035
3	Locate damaged rivets as shown in Figure 1 and campletely drill out the remaining fastener material, making sure not to damage, oblong, or oversize the fastener hole.
4	Prepare the holes of the missing for installation of CherryMax Rive’s PIN CR3212-5-XX in lieu of nominal solid rivels MS20426AD5-XX. · Prepare holes by drilling and reaming to the required rivel size, as required, per CherryMax document CA-1015. · Determine the correct grip length for the fasteners to be used, reference CherryMax document CA-1015. - Using the manufacturer’s recommended install the rivel fasteners per CherryMax document CA-1015. - Inspect the completed rivel set to verify the looking collar has been inserted and the size with the rivet head. Refer to CherryMax document CA-1015 for inspection and verification.
	——————————————————————————————————————————————————————————








LIMITATIONS
None

INSTRUCTIONS FOR CONTINUING AIRWORTHINESS (ICA’s)
Follow the maintenance inspection processor intervals shall remain as indicated in the sircated in the eirent maintenance manual or operators approved inspection program as appropriate.
COMPLIANCE
AIRCRAFT MODEL	RAFT REGISTRATION


	RS# WC7R346J	10/2/19

Form No. NT-EO-01 / Rev A

Page 2 of 3 This Document is Uncontrolled Once Printed

and and the comments of the country and the state of the same of the same

100000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000 and the control control and the control of the control of

nextant aerospace

//REINiAGiNED //RESULT //MORN

•

EO /: NT-E0:11111-31 I Title: Engine Inlet Rivet Repair

Figure 1: Damaged Rivet Location on RH Engine Inlet Up (Typical Shown)

Page 3 ol 3 Form No. NT•EOA1 I Rev A This Document Is Uncontrolled Once Printed

and the country of the county of the county of

and the control control of the control of

EFTA00011682

											OMB No. 2120-0020 Exp: 5/31/2018		Electronic Tracking Number
				MAJOR REPAIR AND ALTERATION							For FAA Use Only
(Airframe, Powerplant, Propeller, or Appliance)
such violation. (49 U.S.C. §46301(a))			INSTRUCTIONS: Print or type all entries. See Tille 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 resolt in a civil penally for each
			Nationality and Registration Mark UNITED STATES / N188TS				Serial No.		RK-244
1. Aircraft	Make		RAYTHEON AIRCRAFT COMPANY				Model 400A			Serles
Address (As shown on registration certificate) Name (As shown on registration certificate)
2. Owner		THORAIR LLC					Address City		SANDUSKY				State ેમ
							Zip	44871			Country		UNITED STATES
						3. For FAA Uso Only

4. Typo						6. Unit Identification
Repair	Alteration	Unit			Make				Model				Serial No.
		AIRFRAME	RAYTHEON AIRCRAFT COMPANY		(As described in Item 1 above)						RK-244
		POWERPLANT
		PROPELLER
		APPLIANCE	Type Manufacturer
						6. Conformity Statement B. Kind of Agency
A. Agency’s Name and Address Name	CONSTANT AVIATION					U. S. Certificated Mechanic						Manufacturer
Address			ОН				Foreign Certificated Mechanic				C. Certificate No.
CLEVELAND City 44143 Zip		Country	State UNITED STATES			Certificated Repair Station 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 herelo 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			Signa										10/7/2019
						7. Approval for Return to Service
			Pursuant to the authority given persons specified below, the unit identified in item 5 was Administrator of the Federal Aviation Administration and Is				Approved			Rejected			inspected in the manner prescribed by the
BY	FAA FIt. Standards Inspector		Manufacturer			Maintenance Organization					Department of Transport		Persons Approved by Canadian
	FAA Designee		Repair Station			Inspection Authorization				Other (Specify)
Certificate or Designation No.	CRS# WC7R346J		Signature/Date of Authorized Individual										10/7/2019
FAA Form 337 (10/06)

		NOTICE

Weight end balance or operating Nmitallon changes shell 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.

S. Description of Work Accomplished

					al more space is requirec( attach additional sheets. Mandy *eh thrash nationally and registration mark and date oak completed)
					mire, STATES /N1887/3	107/2019
					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

riAdditional Sheets Ne Attached

United States of America Devartment of Transportation Federal Aviation Administration Supplemental Type Certificate

Number: ST11216DS

This certificate issued to: BHE & Associates, Ltd.

San Antonio, TX 78216

certifies that the clunge 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.

Original Product - Type Certificate Number:

See attached approved model list (AML)

Make: See attached AML Model: See attached AML

Date Reissued:

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:

The installer must determine whether this design change is compatible with previously approved 1. modifications.
If the holder agrees to permit another person to use this certificate to alter a product, the holder must give 2. the other person written evidence of that permission.
See attached AML for additional limitations and conditions. 3.

This certificate and the supporting data which is the basis for approval shall remain in effect until surrendered, suspended, and revoled or a termination date is otherwise established by the Administrator of the Federal Aviation Administration.

Date of Application: February 9, 2018

Date of Issuance: June 29. 2018

Date Amended: Title VT DRB Aviation Project ODA Administrator ODA-831473-SW

Any atteration of this certificate is punishable by a fine of not exceeding 3 years, or both. This certificate may transferred or nade available to third persons by licensing agreements in accridance with 14 CFR 21.47. Possession of this Supplemental Type Certificate (STC) document by persons other the STC holder does not constitute rights to the design data not to alteralt, aircraft eng propeller. The STC’s supporting documentation (drawings, instructions, flight manual supplements, etc.) is the property 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 wi permission acceptable to the FAA. (Ref. 14 CFR 21.120)

FAA Form 8110-2 (5/14)

Page 1 of 2

SledStates ofilmen?a Department triansportation ediraf2viationAtfmtnistratthrt Supplemental 75 pe Certificate

1NSTRUCITONS 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):

One etransfer

Signature ?grantor

My alteration of this certificate is punishable by a fine of not exceerfing 51.000. 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 *falls Supplemental Type Certificate (STC) document by persons other than the SIC holder does not constitute rights to the design data nor to alter an aircraft. aircraft engine. or propeller. The Sits supporting documemadon (drevangs. instructions, specifications, flIgM manual supplements, etc.) is the property of the SIC holder. ,M STC holder who allows a parson 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) Page 2 of 2

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

Rerd By VLDRB, FSCM 47M27, Shl 1 of 39, 2019/Marl19

NOTICES AND SIGNATURES

Notices:

Note: Paragraphs and/or figure numbers followed by” I” 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

Record of Revisions

Revision Number	Description of change	Revision Date
IR	Initial Release	5/9/18
A	Page 8, Section 1.1 revised transponder and GPS part numbers. Page 10, Section 2 remove “Flight Hours” from Table 4	6/27/18
B	Page 4, Revised list of aircraft models in Introduction Pages 9, 24-25, 28-29, Revised aircraft models in Tables 3, 7, and 9. Pages 8 and 28, clarified wording for installation.	11/6/18
C	Revised Table 3 on page 9 Revised Table 4 on page 10 Revised Table 5 on page 26 Revised Table 6 on pages 27 & 28 Revised section 6.1.9 on page 31 Revised figures on pages 13 & 20, Added figures on pages 14, 17 & 18	1/18/19
D	Added STC number on page 4. Added figure on page 24. Revised form in Appendix C.	3/19/19

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-600-2Al2, 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.125 Series 8006, Hawker 800XP, Hawker 750, Hawker 850XP, Hawker 900XP
Learjet 60 (STC Aircraft)
Dassault Aviation Falcon 10, Mystere-Falcon 50, Mystere-Falcon 20-05/D5fE5/F5, Mystere-Falcon 200, Mystere-Falcon 900

Type	Description	New CPN	Qty
DO-260B ADS-B Out
TOR-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-40005	GPS Receiver	822-2189- 004/005/006/007/010/011/100	0, 1 or 2
*Either TOR-94 or TDR-94D will be installed.

Table 1: Equipment

The above equipment is installed in accordance with FM 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.

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

DocuSign Envelope ID: CFB62885.6FE84C8Da4E3•5461F982D045

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

4 INTRODUCTION
5 RECORD OF REVISIONS
1 8 SYSTEM DESCRIPTION
1.1 GENERAL
10 2 AIRWORTHINESS LIMITATIONS
10 2.1 Inspection Intervals
22 Inspection Program 2.2
22 Inspection Method 2.3
28 Eddy Current Inspection 2.4
3 29 MAINTENANCE PRACTICES
29 3.1 Removal/Installation
29 Access Location 3.2
30 4 POWER DISTRIBUTION
30 4.1 Circuit Breakers by Bus
31 5 SYSTEM TROUBLESHOOTING
31 6 INSPECTION REQUIREMENTS
31 6.1 Scheduled Inspections and Maintenance Checks
34 Wiring 6.2
Al Appendix A — List of Applicable Publications
Appendix B — Special Tools and Equipment B1
Cl Appendix C — Discrepancy Reporting Form

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

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).See 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 E ul ment List
Type	Description	New CPN	Qty 1
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- 004/005/006/007/010/011/100	0, 1 or 2
•Either TDR-94 or TDR-94D will be installed.

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.

Aircraft	Transponder Installed/Retained/Replaced	GPS Installed/Replaced	, Antenna Installed • I
Learjet 60	TDR-94s or 94Ds	GPS-1203C or GPS 40005	CI 429-200
Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, G150	TDR-94s or 94Ds	GPS-4000S	N/A
Gulfstream G-1159, G-1159B, G-IV, GV	TDR-94s or 94Ds	GPS-1203C or GPS 4000S	CI 429-200
Gulfstream G-1159A	TDR-94s or 94Ds	GPS-40005	N/A
Gulfstream 200	TDR-94s or 94Ds	GPS-4000S	N/A
Textron Aviation 500	TDR-94s or 94Ds	GPS-1203C or GPS 40005	CI 429-200
Textron Aviation 550, 5550, 560	TDR-94s or 94Ds	GPS-1203C or GPS 4000S	CI 429-200
Textron Aviation 400	TDR-94s or 94Ds	GPS-1203C or GPS 4000S	CI 429-200
Textron Aviation 400A	TDR-94s or 94Ds	GPS-4000S	N/A
Textron Aviation 650	TDR-94s or 94Ds	GPS-1203C or GPS 40005	CI 429-200
Bombardier CL-600- 1A11 CL-600-2Al2, CL 600-2616	TDR-94s or 94Ds	GPS-1203C or GPS 40005	CI 429-200
Sabreliner NA-265- 65, NA-265-70, NA-265- 80	TDR-94s or 94Ds	GPS-40005	N/A
Textron Aviation HS.125 700A, BAe.125 800A/800B, Hawker 800XP	TDR-94s or 94Ds	GPS-1203C or GPS 40005	CI 429.200
Textron Aviation 1-15.125 700B, Hawker 750/850XP/900XP	TDR-94s or 94Ds	GPS-4000S	N/A
Dassault Aviation Falcon 10, Mystere Falcon 50, Mystere Falcon 20- C5/D5/ES/FS, Mystere-Falcon 200, Mystere-Falcon 900	TDR-94s or 94Ds	GPS-40005	N/A

		Table 3 Equipment by Aircraft
–	–	—————————––

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 4Inspection Intervals
Inspection requirements are for AML fuselage modification
	Inspection In ervals (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.

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STRUCTIONS FOR CONTINUED AIRWORTHINE

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EPORT No. 584-00-0047, Rev:

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INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

TEXTRON AVIATION INC. 550, S550, 560

REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 13 of 36 Reel By VT-ORB, FSCM 47MZ7, Sht 13 of 39. 2019/Matil9

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ALTERNATE LOCATION

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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.

INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS

tion shown. Inspections icable to all penetration installations

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INSPECTION AREA & METHOD

ion shown. Inspe ble to all antenna installations

IFFC Inspection Area of the fuselage skin. HF inspection includes 2,0 inch detailed visual insp round periphery of the installation 1988 ה מרכז מיני ליני מיני ליינו ביינוני מיני מיני מיני מיני במיני המונדים במוזיק ביותר מ

Typical Installation shown. Inspections are applicable to all antenna installations

skin. the fuselage 195 IQU rea of 0 inch detailed ctron includ ur BBBS stallation 11 Paris 2017 peripher ARCHERS

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.

Aircraft	Manual	Document Number
Learjet 60	Non-Destructive Inspection Manual	NDI-2 (Chapter 3)
Textron (Citation) 500, 550, S550, 560	Series 500 Non-Destructive Testing Manual	5056ND (Part 6, Chapter 20)
Textron (Citation) 650	Model 650 Non-Destructive Testing Manual	65ND (Part 6, Chapter 20)
Textron (Beechjet) 400, 400A	Model 4001400A/400XP Maintenance Manual	128-590001-9C29 (Chapter 20-80-03)
Textron (Beechcraft) HS.125 700A, Bae.125 800A, Bae.125 8006, Hawker 800XP	125 Series 1-800, Hawker 750, 800, 800XP, 850XP, and 900XP Non-Destructive Testing Manual	N/A (General Techniques Part 8)
Challengers	Structural Repair Manual	N/A (Chapter 51)
Gulfstream G-1159, G-1159B, G IV, GV	Structural Repair Manual	N/A (Chapter 51)

Table 5 Manual List

FAA APPROVED: IIIIIIIIII____

Project ODA Administrator

VT DRB Aviation Consultants

A Division of VT San Antonio Aerospace, Inc.

IIII“ISan Antonio, TX 78216

Date

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 (-5)O(), document 523-0821492, Installation Section

3.2 Access Location

Refer to the Aircraft Maintenance Manuals listed in table 9 for additional details.

Location of Access	Access Panels
Nose Avionics Bay	Forward Nose Access Panels (Right & Left)
Cabin EE Racks	N/A
Instrument Panel & Pedestal	N/A
Tail Avionics Bay	Tail Access Panel

Table 6 Access Panel Location

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, Gulfstream 100, 0150	Nose	Nose
Gulfstream 200	Nose	Nose
Gulfstream G-1159, G 1159A, G-1159B, G-IV	RH EE Rack, Cabin	RH EE Rack, Cabin
Gulfstream GV	LH & RH EE Rack, Cabin	LH & RH EE Rack, Cabin
Textron Aviation 500, 550, S550,560	Nose	Nose

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 CL-600-2Al2, CL-600-2B16	Under Floor, Cabin	Under Floor, Cabin
Sabreliner NA-265-65, NA-265-70, NA-265-80	Nose Alternate: FWD EE Shelf	Nose Alternate: FWD EE Shelf
Textron Aviation HS.125 700A/700B, BAe.125 800A/800B, Hawker 750/800X131850X131900XP	Nose Alternate: AFT EE Shelf	Under Floor, Cabin Alternate: AFT EE Shelf
Dassault Aviation Falcon 10, Mystere-Falcon 20- 05/D5/E5/F5, Mystere Falcon 200, Mystere-Falcon 900	Nose	Nose
Dassault Aviation Mystere Falcon 50	Nose	Nose 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.

Equipment/System	Model/Part Number ’	in d Max Loa s Amp
TDR-94	622-9352-502	1.79
TDR-94D	622-9210-502	1.79
GPS RECEIVER GPS1203C	84327-50-XXXX	0.179
GPS RECEIVER GPS-40005	822-2189- 004/005/006/007/010/011/100	0.56

Table 8 New and Upgraded Equipment

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
GPS 4000S	ADS-B GPS	Collins GPS-40005 Global Positioning System Installation Manual, document 523-0780545, Maintenance Section
TDR-94D	TDR	TDR-94/94D ATC/Mode-S Transponder System (-5XX), 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.

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.

Figure 6 - Inspection for Cracks

6.1.8 Verification of cracks

A lOx magnifying glass may be used to confirm the existence or extent of a suspected crack.

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:

Aircraft,	TCDS Model -	Maintenance Manual
Learjet 60	60	P/N MM-103
Bombardier Inc CL-600- 1A11	CL-600-1A11	PSP 601-2
Bombardier Inc CL 6002Al2, CL-6002616	CL-600-2B12, CL-600- 2616	CL 604 AMM
Dassault Aviation Falcon 10	Falcon 10	Dassault Falcon 10 Maintenance Manual
Dassault Aviation Mystere-Falcon 20- C5/D5/E5/F5, Mystere Falcon 200	Mystere Falcon 20- C5/D5/E5/F5	Dassault Fan Jet Falcon Maintenance Manual
Dassault Aviation Mystere-Falcon 50	Mystere Falcon 50	Dassault Falcon 50/50EX Maintenance Manual
Dassault Aviation Mystere-Falcon 900	Mystere Falcon 900	Falcon Dassault 900 Maintenance Manual
Galaxy/Gulfstream G100/SPX	G100/Astra SPX	P/N G100-1001-11-1
Galaxy/Gulfstream 1125 Astra	1125 Astra	P/N 25W-1001-11-1
Galaxy/Gulfstream 200, Gulfstream G150	Gulfstream 200, G150	———
Gulfstream G-1159, G 11596	G-1159, G-1159B	Gulfstream II Maintenance Manual
Gulfstream G-1159A	G-1159A	Gulfstream III Maintenance Manual
Gulfstream G-IV	G-IV	Gulfstream IV Aircraft Maintenance Manual
Gulfstream GV	GV	Gulfstream V Aircraft Maintenance Manual
Textron (Citation) 500/550/S550	500/550/S550	Model 500 Maintenance Manual

Table 9 Maintenance Manual by Aircraft

Textron (Citation) 560	560	Model 560 Maintenance Manual
Textron (Citation) 650	650	Model 650 Maintenance Manual
Textron (Beechjet) 400, 400A	400/400A	P/N 128-590001-9C
Textron (Beechcraft) HS.125 700A, 700B	700A, 700,B	AFMS-125-700
Textron (Beechcraft) BAe 125 800A, 800B	800A, 800B	AFMS-800
Textron (Beechcraft) 750	750	AFMS-800XP
Textron (Beechcraft) 800XP	800XP	AFMS-800XP
Textron (Beechcraft) 850XP	850XP	AFMS-800XP
Textron (Beechcraft) 900XP	900XP	AFMS-800XP
Sabreliner Aviation NA-265-70, NA-265-80	NA-265-70, NA-265-80	P/N SE 0405 MM
Sabreliner Aviation NA-265-65	NA-265-65	P/N SE 0303 MM

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. My 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.
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.
Inappropriatefimproper 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 wom 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 hamess 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.
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.
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.

Appendix A — List of Applicable Publications

NOTE: The latest released revision of the publications listed in the LOAF’ 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, equipment installations and ground test)	584-00-0001
TDR-94/94D ATC/Mode-S Transponder System (-5XX) Install Manual	523-0821492
GPS-4000( ) Global Positioning System Installation Manual	523-0780545
Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor	86764

Appendix B — Special Tools and Equipment

Transponders — Aeroflex IFR-6000 or equivalent test set.

GPS — JCAir 429 or equivalent 429 Bus Reader

GPS - Oscilloscope

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:

Please submit the completed form to the following contact:

											OMB No. 2120-0020 Exp: 5/31/2018		Electronic Tracking Number
					MAJOR REPAIR AND ALTERATION								For FAA Use Only
of Transportation Federal Aviation Administration				(Airframe, Powerplant, Propeller, or Appliance)
													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 resolt in a civil penalty for each
such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No.
1. Aircraft	Make		USA/N493LX					Model		RK-244			Series
				Raytheon Aircraft Company				400A
				Name (As shown on registration certificate)	Address						Address (As shown on registration certificate)
2. Owner	Flight Options							City Richmond Heights					State ОН
								Zip	44143-1453			Country	USA
							3. For FAA Use Only


4. Type							5. Unit Identification
Repair	Alteration		Unit		Make					Model			Serial No.
	×	AIRFRAME		Raytheon Aircraft Company				(As described in Item 1 above)					R96-244
		POWERPLANT
		PROPELLER
		APPLIANCE		Type
				Manufacturer
							6. Conformity Statement
A. Agency’s Name and Address							B. Kind of Agency
Name	Nextant Aerospace						U. S. Certificated Mechanic				Manufacturer
Address City Cleveland				он State		×		Foreign Certificated Mechanic Certificated Repair Station				C. Certificate No.
Zip 44143-1453		USA Country					Certificated Maintenance Organization					CRS# 25NR667B
				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.									D. I certify that the repair and/or atteration made to the unit(s) identified in tem 5 above and described on the reverse or attachments herelo
Extended range fuel				Signature/Date of Authorized Individ
per 14 CFR Part 43 App. B
							7. Approval for
				Administrator of the Federal Aviation Administration and is				x Approved		Rejected			Pursuant to the authority given persons specified in item 5 was inspected in the manner prescibed by the
FAA Fit. Standards Manufacturer Inspector BY							Persons Approved by Canadian Maintenance Organization Department of Transport
	FAA Designee	×		Repair Station			Inspection Authorization			Other (Specify)
Certificate or Designation No. CRS#	25NR667B			Signature/Date of Authorized In

FAA Form 337 (10/06)

. ’ : . -. .

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 Identity kWh aircraft nationality and registration mark and date wan( comma fed ) (if more Spaced required. attach additional sheets
N493&X 12/2912013
Nationality and Registration Mark Dale
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 PHi 100-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

















MAdditiOnal Sheets Are Attached

AA Form 337 (10/06)

Paec 2

	DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION
	STANDARD AIRWORTHINESS CERTIFICATE
NATIONALITY AND REGISTRATION MARKS N188TS	MANUFACTURER AND MODEL 2 Raytheon Aircraft	AIRCRAFT SERIAL NUMBER	CATEGORY
	Company 400A	RK=244	Transport
AUTHORITY AND BASIS FOR ISSUANCE Exceptions:	This aiworthiness centificate is issued pursuant to 40 U.S.C. § 44704 and certifies that, as of the date of issuance, the aircraft to which issued has been inspected and found 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 anworthiness code as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein.
	-None-
TERMS AND CONDITIONS	Unless society sumandered, suspended, or a lemination dato is otherwise established by the FAA, this airworthiness conficate is effective as long as the maintenance, and alterations are performed in accordance with Parts 21, 43, and 91 of the Federal Aviation Regulations, as aporopriate, and the aircraft is registered in the United States.
JATE OF ISSUANCE			DESIGNATION NUMBER
R3/06/2014			GL-25
Any alleration, reproduction, or			ceeding 3 years or both.
A Form 8100-2 (04-11) Supersedes Previous Edition	THIS CERTIFICATE MUST BE DISPLAYED IN THE ARCRAFT IN ACCORDANCE WITH APPUCABLE FEDERAL AVATION REGULATIONS.

. .

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION

· STANDARD AIRWORTHINESS CERTIFICATE

1 NATIONALITY AND REGISTRATION MARKS	2 MANUFACTURER AND MODEL Raytheon Aircraft	3 AIRCRAFT SERIAL NUMBER	4 CATEGORY
188TS	Company 400A	RK-244	Transport

5 AUTHORITY AND BASIS FOR ISSUANCE

-None-

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 delailed airworthiness code as provided by Annax 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions:

AFS-750

copy

TERMS AND CONDITIONS 6 Unless socier surrendered, suspended, or a lemination date is otherwise established by the FAA, this airworthiness certificate is effective as long as the 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 certificale may be punishable by a fine net exceeding 3 years or both.

THIS CERTIFICATE MUST BE DISPLAYED IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.

FAA Form 8100-2 (04-11) Supersedes Previous Edition

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

FAA PMI CLE FSDO

				OMB No. 2120-0020 Exp: 5/31/2018			Electronic Tracking Number
MAJOR REPAIR AND ALTERATION											For FAA Use Only
	(Airframe, Powerplant, Propeller, or Appliance)
		such violation. (49 U.S.C. §46301(a))									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 result in a civil penalty for each
	Nationality and Registration Mark USA / N188TS	Senal No. RK-244
1. Aircraft	Make	RAYTHEON AIRCRAFT COMPANY		Model 400A				Series
		Name (As shown on registration certificate)				Address (As shown on registration certificate)
THORAIR LLC 2. Owner						Address SANDUSKY City			OHIO State
					Zip	44871-2218		Country			UNITED STATES
				3. For FAA Use Only






4. Type Repair	Alteration	Unit	Make	5. Unit Identification			Model				Serial No.
			RAYTHEON AIRCRAFT COMPANY								RK-244
		AIRFRAME					(As described in Item 1 above)
		POWERPLANT
		PROPELLER
			Type
		APPLIANCE	Manufacturer

				6. Conformity Statement
A. Agency’s Name and Address Name	Nextant Aerospace			B. Kind of Agency U. S. Certificated Mechanic						Manufacturer
Address	26460 Curtis Wrigth Parloway				Foreign Certificated Mechanic				C. Certificate No.
Cleveland City			Ohio State		Certificated Repair Station				CRS# WC7R346J
44143 Zip		United States Country		Certificated Maintenance Organization
			D. I certify that the repair and/or atteration 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											0/06/2017
				7. Approval for Return to Service
			Pursuant to the authority given persons specified below, the unit identified in item 5 Administrator of the Federal Aviation Administration and is		Approved		was	Relected			inspected in the manner prescribed by the
FAA Fit. Standards Maintenance Organization Manufacturer Inspector						Persons Approved by Canadian Department of Transport
	BY Other (Specify) Inspection Authorization Repair Station FAA Designee
Certificate or	Designation No. CRS#
	WC7R346J										10/06/2017
FAA Form 337 (10/06)
				Page I

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 sat completed)
		N18878	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 Left Winglet Assembly Right Winglet Assembly	Part Number	NEXT-SA15250LA57-10001 NEXT-SA15250LA57-10002	Serial Number S-N EXT-0001 S-NEXT-0001
Left Winglet Light Assembly Right Winglet Light Assembly	87-03916-001 87-03917-001		00214 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

FlAdditional Sheets Are Attached

Minted States Of Aurrir. Beyartment of Oransportation - Frderal Abintion Administration

upplemental Type Vertificate

Number ST02371LA

This Creeficato issued to Nextant Aerospace, LLC

Richmond Heights. Olio 14143

ovrifies that the change in the lyno tosign for the following product with the limitations and conditions theofore as specified horecan mores the airworthiness requirements of Part 25th of the Federal Swiation Peogulations. “Certification basis is set forth on TCDS A16SW and continuation sheets 3 and 4.

Original Product Typo Corrificato Number: A16SW

Beechcraft Corporation

400A

Desightion of Jyno Design Change: Alteration of a Beecheraft Corporation 400A airplane, to replace Pratt & Whitney JT15D-5 series engines with Williams International FJ44-3AP engines (TCDS E3GL) with Full Authority Digital Engine (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: NXT 1-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

Similations and Conditions. The installation thould not be incorporated in any aircraft unless it is determined that the interrelationship between this mstallation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aireraft. 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 to other person written evidence of that permission.

(CONTINUED on page 3)

This cortificato and the supporting data which is the basis for approval shall remain in of surendored, suspended revolved or a termination dato is otherwise who bedminister of the Federal Aviation Administration

Dato of application .	March 24, 2008
Dato of issuance ;	September 27, 2011	March 10, 2017 Dato amended :
		By direction of the Administrator Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Trile)

Jury aleration of this cetifficate is punishable by a fas exceding $1,000, or inpricement not experising 3 years, or both.

FAR Form 8110-2 (10-60)

Page 1 of

This certiffen .. 11:19 be transferred in accordance with 9,10, 21.47.

Mitted States Of America

Bepartment of Transportation - Mederal Abiation Aduninistration

upplemental Tope Certificate (Continuation Sheet)

Number ST02371LA

Limitations and Conditions (vontinuous

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 Ib 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, LCC Instructions for Continued Airworthiness . clocument 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. 0
- Config. B: NX0047-ICA0-0101, Revision A, or later FAA accepted revisions, 0

Certification Basis

The certification basis for this modification is as follows:

The original certification basis for the Hawker Beechoraft 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 25-10, 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 36-17; 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.

Paga 3 of 4

Jay altention of this cetificate is purishable by a fine of not exceeding $1,000, or ingrisonment not exceeding 3 years, or both.

Hitted States Of Autorica

Bepartment of Orunsportation - Mederal Abiation Administration

lemental Tope Certificate

(Continuation Sheet)

Number ST02371LA

Ecolification 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), 25.61 (25-123), 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), 25.95 (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), 25.49(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), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(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. NXTI-EA-007 Rev A dated 8/24/11 or later FAA approved revisions.

– END –

Jay allonation of this cettificate is purishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

							MAJOR REPAIR AND ALTERATION			Form Approved 11/30/2007	OMB No. 2120-0020		Electronic Tracking Number
		(Airframe, Powerplant, Propeller, or Appliance								For FAA Use Only
	Administration
				for each such violation (Section 901 Federal Aviation Act 1958)			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 result in a civil penally not to exceed $1,000
				Nationality and Registration Mark	N493LX		Serial No.				RK 244
1. Aircraft	Make			Raytheon Aircraft Company				Model		400A		Series
				Name (As shown on registration certificate)			Address (As shown on registration certificate)
2. Owner				Flight Options .LLC					Address
									Richmond Heights State. OH City USA 44143-1453 Country
							3. For FAA Use Only	Zip




	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	Constant Aviation						U.S. Certificated Mechanic				C. Certificate No.	Manufacturer
Address City	Cleveland			State. OH		O ಿಗ	Foreign Certificated Mechanic
Zip	44143-1453	Country	USA			0	Certificated Repair Station Certificated Maintenance Organization				CRS # WC7R346J
				furnished herein is true and correct to the best of my knowledge.			D. I certify that the repair and/or altern made to the unit(s) identified in item 5 above and described on the reverse or attachments hereb have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information
Extended range fuel				Signature/Date of Authorized Individ
per 14 CFR Part 43 App. B													09/Sep/2017
							7. Approval for Return to Service
				Administrator of the Federal Aviation Administration and is			Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the X APPROVED	REJECTED
BY	FAA Fit Standards Inspector			Manufacturer			Maintenance Organization						Person Approved by Canadian Department of Transport
	FAA Designee		X	Repair Station			Inspection Authorization				Other (Specify)
Certificate or Designation No. WC7R346J				Signature/Date of Authorized Individual									09/Sep/2017
FAA Form 337	(10-06)

. .

S. Description of Work Accomplished
	(If more space is required, attach additional sheets. !dentin/ 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 1115D-5 Series Engines.

	Installed the Williams International F144-3AP 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 0PS checks IAW Ground Test Plan 373-00-0024 Rev F.

		End













	’	Additional Sheets Are Attached

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION · STANDARD AIRWORTHINESS CERTIFICATE t

1 NATIONALITY AND	2 MANUFACTURER AND MODEL	3 AIRCRAFT SERIAL	4 CATEGORY
REGISTRATION MARKS	Raytheon Aircraft	NUMBER
18815	Company 400A	RK=244	Transport

AUTHORITY AND BASIS FOR ISSUANCE 5

This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, the arcraft to which issued has been inspected and found 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 Annax 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions:

-None-

6 TERMS AND CONDITIONS
	Unless socrer surrendered, suspended, or a lemination date is otherwise established by the FAA, inis airworltiness certificate
	is effective as long as the 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. Y
DATE OF ISSUANCE	FAA REPRESENTATIVE	DESIGNATION NUMBER
R3/06/2014		GL-25
Any atteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding 3 years or both.

THIS CERTIFICATE MUST BE DISPLAYED IN THE ARCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.

FAA Form 8100-2 (04-11) Supersedes Previous Edition

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 Raytheon Aircraft	NUMBER	Transport
N493LX	Company 400A	RK-244
S AUTHODITY AND DACIC CODICSUANICE

JRITT AND BASIS PUR ISSUANGE

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 certificale 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 Annax 8 to the Convention on International Civil Aviation, except as noted herein.

Exceptions:

None

6 TERMS AND CONDITIONS
	Unless sooner surrendered, suspended, or a termination date is otherwise established by the FAA, this airworthiness certificate
	is effective as long as the maintenance, preventalive 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		DART833943G1
	Any alteration, reportudion, or misuse of this centified by a fine not exceeding $1,000 or imprisonment not exceeding 3 years of both.
	THIS CERTIFICATE MUST BE DISPLAYED IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS.

FAA Form 8100-2 (04-11) Supersedes Previous Edition

–

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 N18815.

Signature of Owner:

Title of Owner: President of ThorSpoft, Inc., ThorAir, LLC. It’s Member

. :

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 U.S. Department U.S. AIRWORTHINESS of Transportation CERTIFICATE Federal Aviation Administration							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 space is required, use attachment. For special flight parmits complete Sections II, VI, and VII as applicable.
	1. REGISTRATION MARK N493LX						2. AIRCRAFT BUILDER’S NAME (Make) Raytheon Aircraft Co				3. AIRCRAFT MODEL DESIGNATION 4. YR. MFR. 400A 1998						FAA CODING
ESCRIPTIO AIRCRA	5. AIRCRAFT SERIAL NO. RK-244				6, ENGINE BUILDER’S NAME (Make) Williams International						7. ENGINE MODEL DESIGNATION FJ44-3AP
	8. NUMBER OF ENGINES 2				9. PROPELLER BUILDER’S NAME (Make)						10. PROPELLER MODEL DESIGNATION				11, AIRCRAFT IS (Check if applicable)
	N/A NIA IMPORT APPLICATION IS HEREBY MADE FOR: (Check applicable itams)
	A 1 B			STANDARD AIRWORTHINESS CERTIFICATE (Indicate catagory) SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items)					FORMAL			UNUM	ACROGATIC			TRANSPORT	COUUUTER	BALL DON OTHER
	7 PRIMARY
		2	LIGHT-SPORT (Indicate Class) 9 Airplane Power-Parachute Weight-Shift-Control Glider UMITED									Lighter than Air
		5		PROVISIONAL (Indicato class)		1		CLASS I
						2 1		CLASS II	AGRICULTURE AND PEST CONTROL					2			ਡ
		3		RESTRICTED (indicate operation(s) to be conducied		4			FOREST (Width conservation)					5		AERIAL SURVEY PATROLLING	હિ	AERIAL ADVERTISING WEATHER CONTROL
ERTIFICATION REQUE						0			OTHER (Specify)
						1 4			RESEARCH AND DEVELOPMENT AIR RACING					2 ਦੇ		AMATEUR BUILT CREW TRAINING	ਤੇ હિ	EXHIBITION MARKET SURVEY
						0			TO SHOW COMPLIANCE WITH THE CFR					7				OPERATING (Primary Catagory) KIT BUILT AIRCRAFT
		4		EXPERIMENTAL (indicate operation(’s)						ક્ષિત								Existing aircraft without an airworthiness certificate & do not meet § 103.1
				to be conducited		ಡಿ			OPERATING LIGHT-SPORT	88 BC			Operating Light-Sport Kit-built cartificate under § 21.190					Operating light-sport previously issued special light-sport category airworthiness
						9			UNMANNED	સિ			RESEARCH AND DEVELOPMENT			8C		CREW TRAINING
							1		AIRCRAFT	ӨӨ			MARKET SURVEY			FERRY FLIGHT FOR REPAIRS, ALTERATIONS, MAINTENANCE, OR STORAGE
		8		SPECIAL FLIGHT PERMIT (Indicate			2		EVACUATE FROM AREA OF IMPENDING DANGER
				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
							ব 8		DELIVERING OR EXPORTING		న్ PRODUCTION FLIGHT TESTING CUSTOMER DEMONSTRATION FLIGHTS
	Cl	B		MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE ‘Restricted Cparation’ and ‘Standard’ or ‘Linited’ as agailed in
	NAME			A. REGISTERED OWNER (As shown on centificate of aircraft registration)							ADORESS		IF DEALER, CHECK HERE
			ThorAir LLC													Sandusky. OH 44871
	B. AIRCRAFT CERTIFICATION BASIS (Chack appleable blocks and complete ilems as indicated AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Glass No. and Revision No.J A16SW Rev 28									AIRWORTHINESS DIRECTIVES (Check if all applicable ADs are complied with and give the numbe of the last AD SUPPLEMENT evailable in the biweekly series as of the date of agglication) Bi Weekly 2014 2/10/2014 - 02/23/2014 SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporation)
OWNER’S CERTIFICA				AIRCRAFT LISTING (Give pege number(a)) NA												See Attached Sheet
				C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS CHECK IF RECORDS IN
				COMPLIANCE WITH 14 CFR section 91,417	TOTAL AIRFRAME HOURS				8616.1 TTAF					3	ar renewed)		N/A	EXPERIMENTAL ONLY (Enter hours nown since last certificate issued
				airworthiness certificate requested.														D. CERTIFICATION - I hereby card on the registered with in the arrant decribed above, that the arcatil is rogistered with the Fooral Availan Admisistion in CONSECTION OF THE UNIO SURE CODE 4 TO LE SERIES AND REGIONS AND THE BECON POST POST POST POST POST POST POST POST AND INVESTIGATION AND INVESTIGATION AND INVESTIGATION AND IN
				DATE OF APPLICATION	NAME AND TITLE (Print ar type)										SIGNAT
				03/06/2014	Anton Koprivnik Agent

This document was truncated for web display. See the linked source PDF for the complete record.

//REIMAGINED //REBUILT //REBORN

ENGINEERING ORDER

Title: Engine Inlet Rivet Repair

nextant actrospace

ENGINEERING ORDER

nextant aerospace

INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT

Transfer Endorsement

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR THE INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT

NOTICE:

BHE & Associates, Ltd. San Antonio, TX 78216 USA CAGE: N/A

NOTICES AND SIGNATURES

Notices:

Approval Signatures:

Record of Revisions

INTRODUCTION

Table 1: Equipment

RECORD OF REVISIONS

STC Holder

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

TABLE OF CONTENTS

LIST OF FIGURES AND TABLES

1 SYSTEM DESCRIPTION

1.1 GENERAL

2 AIRWORTHINESS LIMITATIONS

2.1 Inspection Intervals

TEXTRON AVIATION INC. 550, S550, 560

TEXTRON AVIATION INC. 650

AVIATION

1 59 ( ) ( ) 59B FSTREAM – -

ULFSTREAM GV

2.2 Inspection Program

2.3 Inspection Method

INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS

2.4 Eddy Current Inspection

Table 5 Manual List

3 MAINTENANCE PRACTICES

3.1 Removal/Installation

3.2 Access Location

Table 6 Access Panel Location

Table 7 Equipment Installation Locations by Aircraft

4 POWER DISTRIBUTION

4.1 Circuit Breakers by Bus

Table 8 New and Upgraded Equipment

5 SYSTEM TROUBLESHOOTING

6 INSPECTION REQUIREMENTS

6.1 Scheduled Inspections and Maintenance Checks

6.1.1 Time Limits — Inspection and Maintenance Checks

Note:

6.1.2 Visual Inspections

6.1.3 Corrosion Treatment

6.1.4 Structural Failure Determination.

6.1.5 Cleaning of Structural Parts

6.1.6 Cleaning Other Areas

6.1.7 Crack Detection Technique

Figure 6 - Inspection for Cracks

6.1.8 Verification of cracks

6.1.9 Visual Wiring Inspection

Table 9 Maintenance Manual by Aircraft

6.2 Wiring

CAUTION

Appendix A — List of Applicable Publications

Appendix B — Special Tools and Equipment

Appendix C — Discrepancy Reporting Form

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION

· STANDARD AIRWORTHINESS CERTIFICATE

upplemental Type Vertificate

(CONTINUED on page 3)

Jet A-1 ASTM-D 1655

Certification Basis

lemental Tope Certificate

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION · STANDARD AIRWORTHINESS CERTIFICATE t

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE

None

FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE