SUBJECT

SERVICE BULLETIN

 

NUMBER 200-51-366 

 

 STANDARD PRACTICES AND STRUCTURES 

(ATA 51) - ATTACHMENT HARDWARE - NUT 

REPLACEMENT 

 

MARCH 30, 2010 
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 1 of 17

STANDARD PRACTICES AND STRUCTURES - ATTACHMENT HARDWARE - NUT 

REPLACEMENT

PLANNING INFORMATION

200-51-366

1. Effectivity

Aircraft serial numbers 219 through 231

NOTE: Some Steps are applcable to specific aircraft only. Read entire document to 

ensure unnecessary maintenance is not performed. 

2. Concurrent Requirement

None

3. Reason

Cracked nuts were found on production aircraft during routine post assembly 

inspections. Further investigation revealed a batch of defective MS21042L3 

self-locking nuts used in several areas of the aircraft. There are no safety-of-flight 

implications, but inspection and replacement of suspected nuts in specific areas is 

required.

4. Description

This service bulletin provides instructions to perform a radiographic inspection of 

suspect nuts in certain areas and replace any nuts found cracked. Additionally, where 

readily accessible, instructions are provided to replace suspect nuts in lieu of 

inspection.

5. Compliance

Compliance with this service bulletin is mandatory at the next suitable planned 

maintenance period within 12 months.

6. Approval

This service bulletin has been reviewed by the Civil Aviation Authority of Israel (CAAI). 

The design content herein complies with the applicable Civil Aviation Regulations and 

is CAAI approved.

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 2 of 17

7. Manpower

The following information is for planning purposes only:

Estimated man-hours: 24 for aircraft serial numbers 219-223

227 for aircraft serial numbers 224-231 except 226

215 for aircraft serial number 226

8. Weight and Balance

No change

9. Electrical Load Data

N/A

10. Software Accomplishment Summary

None

11. References

G200 Aircraft Maintenance Manual (AMM), Chapters 06, 12, 20, 27, 28, 29, 

32, 51, 53, 55 and 57

IAI Document IS951400E Radiographic Inspection of Self-Locking Nuts

Gulfstream Aerospace LP Modification G2-03729

NOTE: The design of MOD G2-03729 is configured to a standard type certificated 

configuration aircraft. Approval, by the local regulatory authority, of any 

deviation from the instructions contained in this service bulletin must be 

obtained, if required, in accordance with the relevant local regulations.

12. Other Publications Affected

None 

13. Interchangeability or Intermixability of Parts

None

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 3 of 17

MATERIAL INFORMATION

1. Material - Price and Availability

The parts required to accomplish this service bulletin are available by contacting 

Spare Parts Sales at 800-810-GULF (4853) or 912-965-4178.

2. Opportunity for No-Charge Compliance

This service bulletin will be accomplished at no charge if performed at a Gulfstream 

G200 Authorized Warranty Repair Facility within the recommended compliance time 

stated in this document. If this service bulletin is performed at other than a Gulfstream 

G200 Authorized Warranty Repair Facility, the labor will be an owner responsibility. 

3. Material Necessary for Each Aircraft

NOTE: The parts listed in this section can be substituted with equivalent Israel 

Aerospace Industries (IAI) approved parts. If equivalent part(s) is used, it 

must be accompanied by documentation from IAI stating equivalence.

A. Material to be Procured:

B. Materials Supplied by Operator:

Methyl ethyl ketone (MEK) or equivalent

Sealant PR 1750

Paint to match existing exterior color scheme

4. Reidentified Parts

None

5. Special Tooling

X-Ray unit and boroscope (for details, refer to Appendix A)

New P/N Keyword Old P/N Qty

MS21042L3 Nut MS21042L3 A/R

MS29513-222 O-ring MS29513-222 A/R

MS29513-117 O-ring MS29513-117 A/R

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 4 of 17

ACCOMPLISHMENT INSTRUCTIONS

CAUTION: PROTECT WIRE BUNDLES, CONNECTORS AND SURROUNDING 

STRUCTURE DURING ANY MAINTENANCE PROCEDURES FROM 

SHAVINGS, DEBRIS AND CONTAMINATION. MAINTAIN A PROPERLY 

CLEANED WORK AREA THROUGHOUT THE PROCEDURE TO ENSURE THE 

INTEGRITY OF THE AFFECTED COMPONENT/SYSTEM. VISUALLY 

INSPECT WORK AREA USING ADDITIONAL LIGHT AS NECESSARY TO 

VERIFY ABSENCE OF ANY DEBRIS PRIOR TO COMPLETION OF 

PROCEDURE. FAILURE TO COMPLY MAY RESULT IN DAMAGE TO 

COMPONENTS AND/OR SYSTEMS.

1. Prepare aircraft for safe maintenance. Refer to AMM, Safe Ground Maintenance 

Procedure, Chapter 20.

2. Defuel the left and right wings. Refer to AMM, Chapter 12.

NOTE: Defueling on the left and right wings is not required for aircraft serial 

numbers 219 through 223. 

CAUTION: MAKE SURE ELECTRICAL POWER IS DISCONNECTED FROM AIRCRAFT. 

FAILURE TO COMPLY MAY RESULT IN INJURY TO PERSONNEL AND/OR 

DAMAGE TO AIRCRAFT.

3. Disconnect external electrical power from aircraft. Refer to AMM, Chapter 12.

4. Perform nut replacement in the area depicted in Figure 2, Sheet 2, Detail A, as 

follows:

NOTE: Remove and replace indicated nuts one at a time.

A. Remove access panel, 132HB. Refer to AMM, Chapter 06 and Figure 1, Sheet 1.

B. Remove the four nuts, attaching the slat PDU to the isolator mounts. Refer to 

Figure 2, Sheet 2, Section I-I.

NOTE: Support slat PDU as required to prevent damage. 

C. Remove the slat PDU isolator mounts from structure. Retain hardware. Replace 

the top nuts (4 each). Reinstall the isolator mounts to structure using the existing 

hardware. Refer to Figure 2, Sheet 2, Section I-I.

NOTE: Do not disconnect the flexible shafts from the slat PDU.

D. Resecure the slat PDU to the isolator mounts using four new nuts, P/N 

MS21042L3.

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 5 of 17

E. Remove and replace jumper wire attachment nut. Refer to Figure 2, Sheet 2, 

View H.

F. Tighten nuts to 30.0-35.0 in. lb., targeting 32 in. lb.

G. Ensure work area is clean and clear of foreign objects (FOD).

H. Install access panel, 132HB. Refer to AMM, Chapter 06 and Figure 1, Sheet 1.

5. Perform nut replacement in the area as depicted in Figure 2, Sheet 4, View B, as 

follows:

A. Ensure the main landing gear (MLG) is in the extended position. Refer to AMM, 

Chapter 32.

B. Remove access panels 143CZ and 144DZ, attached to keel beam, BL280. Refer 

to AMM, Chapter 06 and Figure 1, Sheet 2.

C. Remove the eight nuts (one at a time) attaching the FLAP PDU to the structure. 

Refer to Figure 2, Sheet 4, Section J-J.

NOTE: Do not disconnect the flexible shafts from the FLAP PDU.

D. Resecure the FLAP PDU using eight new nuts, P/N MS21042L3.

E. Remove and replace jumper wire attachment nut. Refer to Figure 2, Sheet 4, 

View B.

F. Tighten nuts to 30.0-35.0 in. lb., targeting 32 in. lb.

G. Ensure work area is clean and clear of foreign objects (FOD).

H. Install access panels 143CZ and 144DZ, attached to keel beam, BL280. Refer to 

AMM, Chapter 06 and Figure 1, Sheet 2.

6. Perform nut replacement in the area as depicted in Figure 2, Sheets 1 and 3, View F.

NOTE: Step 6 applies to aircraft serial numbers 224, 225 and 227 through 231 

only.

A. Remove rudder tab assembly. Refer to AMM, Chapter 55.

B. Remove and replace the twenty nuts (one at a time) on the rudder tab assembly 

with new nuts, P/N MS21042L3, as depicted in Figure 2, Sheet 3, View F, Details 

K, L (3 places) and M.

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 6 of 17

C. Tighten nuts to 30.0-35.0 in.- lb., targeting 32 in. lb.

D. Ensure work area is clean and clear of foreign objects (FOD).

E. Perform paint touch-up as required to match existing top coat.

F. Install rudder tab assembly. Refer to AMM, Chapter 55.

7. Perform nut replacement in the area depicted in Figure 2, Sheets 1 and 6, View C.

NOTE: Step 7 applies to aircraft serial numbers 224 through 231 only.

NOTE: Step 7 is applicable to the left and right aileron fittings.

A. Remove access panels between rib 15 and rib 23 on left and right lower wing. 

Refer to AMM, Chapter 06, Chapter 28 and Figure 1, Sheet 3.

B. Remove the left and right ailerons. Refer to AMM, Chapter 27.

C. Remove and replace nuts (one at a time) on rear spar datum area (aileron 

fittings) with new nuts, P/N MS21042L3, wet with sealant PR 1750, as depicted in 

Figure 2, Sheet 5, Detail C, Views V and T.

NOTE: Prior to installing new nuts, ensure fastener area is clean and free of 

debris. Clean using MEK or equivalent if necessary. 

NOTE: It is necessary to move the hydraulic lines that pass through the 

middle aileron fitting, out of the way, to properly access all nuts 

requiring replacement. 

CAUTION: USE EXTREME CAUTION WHEN REMOVING LINE BLOCK CLAMPS. 

FAILURE TO COMPLY MAY RESULT IN DAMAGE TO THE LINE 

BLOCKS. IF LINE BLOCKS ARE DAMAGED, REFER TO IPC, 

CHAPTER 29 FOR REPLACEMENT LINE BLOCKS. 

D. Remove line block clamps, P/N 25W243003-015/-016/-017 and if necessary, 

-018. 

NOTE: Move hydraulic lines as required to gain access to the middle aileron 

fitting nuts that require replacement. Refer to AMM, Chapter 29 and 

Figure 2, Sheet 5, View P. 

E. Tighten nuts to 30.0-35.0 in. lb., targeting 32 in. lb. Seal (back seal) all fasteners 

with PR 1750 on the inner (wet) side of wing at the inner side of aileron inboard 

fitting.

F. Ensure work area is clean and clear of foreign objects (FOD).

March 30, 2010
Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 7 of 17

G. Perform paint touch-up as required to match existing top coat.

H. Install ailerons. Refer to AMM, Chapter 27.

8. Perform nut inspection and replacement as depicted in Figure 2, Sheets 1 and 6, 

Detail D.

NOTE: Steps 8 applies to aircraft serial numbers 224 through 231 only.

NOTE: Step 8 is applicable to the left and right air brake fittings.

A. Connect external electrical power to aircraft. Refer to AMM, Chapter 12.

B. Connect external hydraulic to aircraft. Refer to AMM, Chapter 12

C. Extend the left and right inboard and outboard flaps to the maximum down 

position. Refer to AMM, Chapter 27.

D. Deploy the left and right air brakes to the maximum up position. Refer to AMM, 

Chapter 27.

E. Disconnect external electrical power from aircraft. Refer to AMM, Chapter 12.

F. Disconnect external hydraulic from aircraft. Refer to AMM, Chapter 12.

G. Remove access panels between rib 3 and rib 15 on lower skin. Refer to AMM, 

Chapter 06 and Figure 1, Sheet 3.

NOTE: It is necessary to open access panels between rib 3 and rib 7 to 

facilitate removal of wing tank vent pipe to allow proper film placement 

between ribs 7 and 15. 

H. Remove and replace nuts on the vertical plane (one at a time) on rear spar datum 

area, with new nuts, P/N MS21042L3. Refer to Figure 2, Sheet 6, View Y.

I. Disconnect vent tubes and release hydraulic tubes from line blocks as required to 

gain access to the left and right air brakes No. 1 through No. 4 fittings (left and 

right wing rear spar area). Refer to AMM, Chapters 28 and 29.

J. Perform radiographic inspection of noted nuts. Refer to Figure 2, Sheet 6, 

View D. Refer to Appendix A for inspection procedure.

K. Remove and replace any cracked nuts found during inspection (one at a time) 

wet with sealant, PR 1750.

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 8 of 17

NOTE: Prior to installing new nuts, ensure fastener area is clean and free of 

debris. Clean using MEK or equivalent if necessary. 

L. Tighten nuts to 30.0-35.0 in.lb., targeting 32 in.lb. Seal (back seal) all fasteners 

with PR 1750 on the inner (wet) side of wing.

M. Perform paint touch-up as required to match existing top coat on outer side of 

wing if required.

N. Reattach hydraulic tubes, line blocks and reconnect vent tubes 

disconnected/released in Step 8.I. above. Refer to AMM, Chapters 28 and 29.

NOTE: Ensure O-rings are replaced on the fuel vent tubes and jettison tubes 

where disconnected to move tube for film placement. Refer to Material 

Information on page 3 for O-ring P/Ns. 

O. Ensure work area is clean and clear of foreign objects (FOD)

P. Install access panels between rib 3 and rib 23. Refer to AMM, Chapter 06, 

Chapter 28 and Figure 1, Sheet 3.

Q. Refuel wings and check for leaks from wing access panels, NACA scoops, 

inboard aileron fittings, air brake fittings, (if nuts were replaced in any air brake 

fittings) wet area of wing tank and jettison nozzles. Refer to AMM, Chapter 28.

NOTE: Allow sealant to cure per manufacturers instructions before fueling 

aircraft. Record compliance with this service bulletin in the aircraft’s 

permanent maintenance records and return aircraft to flight status.

9. Report compliance with this service bulletin to Gulfstream CMP via electronic 

transmittal or fill out and fax the attached service reply card. 

If technical assistance is required, contact your area Gulfstream Field Service 

Representative or call Gulfstream Customer Support at 800-810-GULF (4853) or 

912-965-4178 (fax 912-965-4184).

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 9 of 17

Access Panels

Figure 1 (Sheet 1)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 10 of 17

Access Panels

Figure 1 (Sheet 2)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 11 of 17

Access Panels

Figure 1 (Sheet 3)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 12 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 1)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 13 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 2)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 14 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 3)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 15 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 4)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 16 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 5)

March 30, 2010
Gulfstream 

SERVICE BULLETIN

Service Bulletin No. 200-51-366

Page 17 of 17

Nut Inspection and Replacement

Figure 2 (Sheet 6)

March 30, 2010
GULFSTREAM G200 

SERVICE BULLETIN NO. 200-51-366 

SERVICE REPLY CARD

Service Bulletin prepared by Gulfstream Aerospace, 500 Gulfstream Road, P.O. Box 2206, Savannah, Georgia 

31402-2206, USA. © 2010 Gulfstream Aerospace. All rights reserved, including the right to reproduce this publication. 

No part may be reproduced, stored in any retrieval system, or transmitted in any part or form or by any means, 

electronic, photocopying, microfilm, microfiche, mechanical, or otherwise, without prior written permission of 

Gulfstream Aerospace. This technical data is controlled under the Export Administration Regulations by General 

License TSU. It may not be transferred to a third party without the prior written approval of the U.S. Department of 

Commerce. 

PLEASE FAX THIS PAGE TO GULFSTREAM AEROSPACE CMP 

FAX # 800-944-1775 or 912-963-0265.

THE FOLLOWING SERVICE BULLETIN HAS BEEN COMPLIED WITH: 

SB CMP NUMBER A/C AIRCRAFT TYPE COMPLIANCE DATE

983660 Galaxy/Gulfstream G200 

AIRCRAFT HOURS: AIRCRAFT LANDINGS: 

PREVIOUSLY COMPLIED 

WITH: DATE: 

NOT APPLICABLE: DATE: 

 

SIGNATURE TITLE / CERTIFICATE 

NUMBER 

COMPANY 

 

COMMENTS / SUGGESTIONS / ACTIONS TAKEN: 
200-51-366

Appendix A

200-51-366Dec 02/2001

200-51-366

Appendix A
SECURITY CLASS: UNCLASSIFIED

COML. CLASS: UNCLASSIFIED

IS951400.doc PAGE: 0.1 REVISION: A 

The original is in the MANTRA system, a printed copy is uncontrolled.

DOCUMENT IDENTIFIER IS951400E

SUBJECT: RADIOGRAPHIC INSPECTION OF SELFLOCKING NUT P/N MS21042L3 

MATERIAL ENGINEERING & TECHNOLOGY DEVELOPMENT 

ENGINEERING DIVISION / ENGINEERING & DEVELOPMENT GROUP 

PREPARED & APPROVED BY: 

 D. Belo [Level III] _______________ DEPT: 4484 

DATE: 25/1/2010 

This document contains proprietary information of Israel 

Aerospace Industries Ltd., and may not be reproduced, copied, 

disclosed or utilized in any way, in whole or in part, without the 

prior written consent of Israel Aerospace Industries Ltd. 
SECURITY CLASS: UNCLASSIFIED DOCUMENT NO. IS951400E

COML. CLASS: UNCLASSIFIED

PAGE: 0.2 REVISION: A 

The original is in the MANTRA system, a printed copy is uncontrolled.

REVISION STATUS

REV -- A 

DATE 12/09 1/10 

PAGE PAGE PAGE PAGE 

NO. REV SIZE NO. REV SIZE NO. REV SIZE NO. REV SIZE 

0.1 A A40 

0.2 A 

1 A 

2 

3 

4 

5 

6 

7 

8 

9 

10 

11 

12 

13 

14 A A40 

 

ADDED PAGE ADDED PAGE ADDED PAGE ADDED PAGE 

NO. REV SIZE NO. REV SIZE NO. REV SIZE NO. REV SIZE 
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 1 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

1. APPLICABILITY

Applicable to G150 and G200 projects. 

2. SCOPE

2.1. This Inspection Specification (IS) establishes procedure for detecting cracks in the 

self-locking nuts connecting the air brake fittings in both the left and right wings. 

2.2. The 32 self-locking nuts to be inspected are located between Rib 7 to Rib 8, Rib 8 

to Rib 9, Rib 9 to Rib 10, Rib 10 to Rib 11, Rib 12 to Rib 13, Rib 13 to Rib 14 and 

Rib 14 to Rib 15 as shown in the attached photographs. 

3. APPLICABLE DOCUMENTS

Except where a specific issue is indicated, the latest issue of the following 

documents shall be considered as a part of this IS. 

3.1. IAI Ltd

PS810010 Qualification & Certification of Non-Destructive Testing Personnel 

PS811000 Radiographic Non-Destructive Inspection - General 

3.2. Aerospace Industries Association (AIA)

NAS 410 NAS Certification & Qualification of Nondestructive Test Personnel 

3.3. American Society for Testing and Materials (ASTM)

ASTM E1742 Standard Practice for Radiographic Examination 

4. ENGINEERING DRAWING CALL-OUT

Where required this IS shall be referred to by number on the applicable 

Engineering document. 

5. TABLE OF CONTENTS

Para Title Page

1. APPLICABILITY 1 

2. SCOPE 1 

3. APPLICABLE DOCUMENTS 1 

4. ENGINEERING DRAWING CALL-OUT 1 

5. TABLE OF CONTENTS 1 

6. MATERIALS 2 

7. EQUIPMENT 2 
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 2 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

8. INSPECTION PROCEDURE 3 

8.1 Preparation 3 

8.2 Area to be Inspected 3 

8.3 Inspection 3 

LIST OF TABLES

Table 1 Radiographic Inspection Data 10 

LIST OF FIGURES

Figure 1 Area Between Rib #7 and Rib #8 4 

Figure 2 Area Between Rib #8 and Rib #9 5 

Figure 3 Area Between Rib #9 and Rib #10 6 

Figure 4 Area Between Rib #10 and Rib #11 7 

Figure 5 Area Between Rib #12 and Rib #13 8 

Figure 6 Area Between Rib #13, Rib #14, and Rib #15 9 

Figure 7 Sketch of Equipment Positioning 11 

Figure 8 Access Opening for Placing Film 12 

Figure 9 Sketch for Equipment Set-up and Film Placement 13 

Figure 10 Schematic View of Possible Crack Location 14 

6. MATERIALS

6.1. Nut, stainless steel, 8.5 mm. 

6.2. Aluminum skin, 6 mm thick. 

7. EQUIPMENT

7.1. X-Ray Unit: YXLON MG165 or equivalent 

a. Constant potential 160 KV 

b. Double Focal spots size 1mm and 3mm 

7.2. Automatic Film Processor : AGFA STRUCTURIX NDT Seco, or equivalent 

a. Developer time 1.5 minute 

b. Temperature 28oC 

c. Exposure time (film processing) 8 minutes 

7.3. High intensity film viewer. 

7.4. Densitometer. 

7.5. Film: Agfa D4 or equivalent. 
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 3 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

7.6. Boroscope System. 

8. INSPECTION PROCEDURE

8.1. Preparation

8.1.1. Remove wing access panels as required to perform procedure. 

8.1.2. Open metal straps on the two air vents in the wing interior to allow lateral 

movement and access to place film. 

8.1.3. Deploy the air brake to the maximum up position. 

8.1.4. Lower the flaps to maximum down position. 

8.2. Area to be Inspected

8.2.1. Refer to Figures to establish in what areas the 32 self-locking nuts connecting the 

air brake fittings (left and right wing), to be inspected, are located. 

a. Figure 1 - between Rib 7 to Rib 8 

b. Figure 2 - between Rib 8 to Rib 9 

c. Figure 3 - between Rib 9 to Rib 10 

d. Figure 4 - between Rib 10 to Rib 11 

e. Figure 5 - between Rib 12 to Rib 13 

f. Figure 6 - between Rib 13 to Rib 14 and between Rib 14 to Rib 15 

8.2.2. For the 20 self-locking nuts connecting air brake fittings (left and right wing) 

between Rib 7 to Rib 11, shown in Figures 1 thru 4 use a Boroscope system in 

order to ensure that the x-ray film is located in the right place. 

8.3. Inspection

8.3.1. Refer to Table 1 for radiographic data and equipment settings and Figure 7 for 

sketch of equipment positioning and Figure 8 for openings in wing to access inside 

wing to place film. 

8.3.2. Film shall be placed covering nuts to be inspected, as shown inside wing structure 

in Figures 1 thru 6 and in accordance with sketch in Figure 9. 

8.3.3. Film density for each exposure shall be between 2 to 3 at the self-locking nut area. 

8.3.4. Inspect self-locking nuts using the data in Table 1. Refer to Figure 10 for view of 

possible crack location schematic.

8.3.5. Report cracks of any size. 
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 4 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 1: Area Between Rib #7 and Rib #8

(Film Located Covering Nos. 1 thru 4 Self-Locking Nuts) 

3 4

1 2

Rib No. 7 Rib No. 8
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 5 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 2: Area Between Rib #8 and Rib #9

(Film Located Covering Nos. 5 & 6 and 9 & 10 Self-Locking Nuts) 

9 10

5 6 

Rib No. 8 Rib No. 9
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 6 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 3: Area Between Rib #9 and Rib #10

(Film Located Covering Nos. 7 & 8 and 11 & 12 Self-Locking Nuts) 

11 12 

7 8

Rib No. 9 Rib No.10
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 7 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 4: Area Between Rib #10 and Rib #11

(Film Located Covering Nos. 13 thru 20 Self-Locking Nuts) 

17 18 19 20

Air Vents

13 14 15 16

Rib No. 10 Rib No. 11
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 8 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

 

Figure 5: Area Between Rib #12 and Rib #13

(Film Located Covering Nos. 21 thru 23 and 25 thru 27 Self-Locking Nuts) 

25 26 27

21 22 23

Rib No. 12 Rib No. 13
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 9 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

 

Figure 6: Area Between Rib #13, Rib #14 and Rib #15

(Film Located Covering Nos. 24 and 28 thru 32 Self-Locking Nuts) 

25 26 27

24 29 30

Rib No. 13 Rib No. 14

28 

31 32

Rib No. 15 
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 10 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Table 1: RADIOGRAPHIC INSPECTION DATA

EXPOSURE 

NUMBER Kv Ma Time FFD FILM 

TYPE FILM SIZE 

VIEW #1 

Nuts No. 1&3 110 10 2.30 min 100cm AGFA D4 105mm X 100mm 

VIEW #2 

Nuts No. 2&4 110 10 2.30 min 100cm AGFA D4 105mm X 100mm 

VIEW #3 

Nuts No. 5&9 110 10 2.30 min 100cm AGFA D4 100mm X 85mm 

VIEW #4 

Nuts No. 6&10 110 10 2.30 min 100cm AGFA D4 27mm X 85mm 

VIEW #5 

Nuts No. 7&11 110 10 2.30 min 100cm AGFA D4 22mm X 100mm 

VIEW #6 

Nuts No. 8&12 110 10 2.30 min 100cm AGFA D4 105mm X 100mm 

VIEW #7 

Nuts No. 13&17 110 10 2.30 min 100cm AGFA D4 105mm X 100mm 

VIEW #8 

Nuts No. 14&15 

and 18&19 

110 10 2.30 min 100cm AGFA D4 60mm X 100mm 

VIEW #9 

Nuts No. 16&20 110 10 2.30 min 100cm AGFA D4 70mm X 100mm 

VIEW #10 

NUTS No. 21&25 110 10 2.30 min 100cm AGFA D4 50mm X 85mm 

VIEW #11 

Nuts No. 22&26 

and 23&27 

110 10 2.30 min 100cm AGFA D4 50mm X 85mm 

VIEW #12 

Nuts No. 24&28 110 10 2.30 min 100cm AGFA D4 50mm X 85mm 

VIEW #13 

Nuts No. 29&31 110 10 2.30 min 100cm AGFA D4 100mm X 85mm 

VIEW #14 

Nuts No. 30&32 110 10 2.30 min 100cm AGFA D4 100mm X 85mm 
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 11 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 7: Sketch of Equipment Positioning

X-Ray 

Tube 

Area to be 

inspected 
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 12 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 8: Access Openings for Placing Film

Access Openings
Original Issue 

7 Dec. 2009 

Revision A 

RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

IS951400 

25 Jan. 2010 INSPECTION SPECIFICATION Page 13 of 14

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

FWD AFT 

 Upper skin Aft Spar 

 Nut 

 Film 

 Nut 

 

 Lower skin 

 Access panel 

Figure 9: Sketch for Equipment Set-up and Film Placement

Typical X-Ray Beam 

Centerline Direction 

Perpendicular to the 

Two nuts in the Web 

spar 
IS951400 RADIOGRAPHIC INSPECTION OF 

SELF-LOCKING NUT P/N M21042L3 

Original Issue 

7 Dec. 2009 

Revision A 

Page 14 of 14 INSPECTION SPECIFICATION 25 Jan. 2010

THIS DOCUMENT CONTAINS PROPRIETY INFORMATION OF ISRAEL AEROSPACE INDUSTRIES LTD., AND MAY NOT BE REPRODUCED, COPIED 

DISCLOSED OR UTILIZED IN ANY WAY, IN WHOLE OR IN PART, WITHOUT WRITTEN CONSENT OF ISRAEL AEROSPACE INDUSTRIES LTD. 

The original is in the MANTRA system, a printed copy is uncontrolled.

Figure 10: Schematic View of Possible Crack Location 

Crack