# 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 - ATTACHM ENT 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 re vealed a batch of defective MS21042L3 self-locking nuts used in several areas of t he aircraft. There are no safety-of-flight implications, but inspection a nd 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, instruct ions are provided to replac e suspect nuts in lieu of inspection.
5. Compliance
Compliance with this service bulletin is mandatory at the nex t suitable planned maintenance period within 12 months.
6. Approval

This service bulletin has been r eviewed by the Civil Aviation A uthority of Israel (CAAI). The design content her ein complies with the applicable C iv il 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 ai rcraft 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 Maintenanc e Manual (AMM), Chapters 06, 12, 20, 27, 28, 29, 32, 51, 53, 55 and 57 IAI Document IS951400E R adiographic Inspection of Self-Locking Nuts Gulfstream Aerospace LP Modification G2-03729

NOTE: The design of MOD G2-03729 is configured to a standa rd type certificated configuration aircraft. Approval, by t he local regulatory au thority, of any deviation from the instructions contai ned in this service bulletin must be obtained, if required, in accordance with the relevant local regulations.

12. Other Publications Affected

None
13. Interchangeability or In termixability 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 accompli sh this service bulletin ar e 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 bullet in is performed at other than a Gulfstream G200 Authorized Warranty Repair Facility, t he 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 documentati on 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 de tails, refer to Appendix A) New P/N Keyword Old P/N Qty

MS21042L3 Nut MS21042L3 A/R
MS29513-222 O-ri ng MS29513-222 A/R
MS29513-117 O-ri ng 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 BUNDLE S, CONNECTORS AND SURROUNDING STRUCTURE DURING ANY MAIN TENANCE PROCEDURES FROM SHAVINGS, DEBRIS AND CONTAMIN ATION. MAINTAIN A PROPERLY CLEANED WORK AREA THROUGHOUT THE PROCEDURE TO ENSURE THE INTEGRITY OF THE AFFECTED COMPONENT/SYSTEM. VISUALLY INSPECT WORK AREA US ING ADDITIONAL LIGH T 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 wi ngs. Refer to AMM, Chapter 12.

NOTE: Defueling on the left and ri ght wings is not requir ed 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 indica ted 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, atta ching the slat PDU to the isolator mounts. Refer to Figure 2, Sheet 2, Section I-I.

NOTE: Support slat PDU as requi red to prevent damage.

C. Remove the slat P DU isolator mounts from struct ure. Retain hardware. Replace the top nuts (4 each) . Reinstall the isolat or mounts to structur e 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. Refe r 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 cl ear of foreign objects (FOD).
H. Install access panel, 132H B. 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 positi on. 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 FL AP PDU to the structure. Refer to Figure 2, S heet 4, Section J-J.

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

D. Resecure the FLAP PDU usin g eight new nuts, P/N MS21042L3.
E. Remove and replace jumper wire attachment nut. Refe r 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 cl ear of foreign objects (FOD).
H. Install access panels 143CZ and 144DZ, attached to k eel 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 replac e the twenty nuts (one at a time) on the rudder tab assembly with new nuts, P/N MS21042L3, as depicted in Figure 2, S heet 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 cl ear of foreign objects (FOD).
E. Perform paint touch-up as requir ed 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 seri al numbers 224 through 231 only.

NOTE: Step 7 is applicable to the le ft and right aileron fittings.
A. Remove access panels between rib 15 an d 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 aile rons. Refer to AM M, Chapter 27.
C. Remove and replace nuts (one at a time) on rear sp ar datum area (aileron fittings) with new nu ts , P/N MS21042L3, wet w ith sealant PR 1750 , as depicted in Figure 2, Sheet 5, Deta il 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 hydr aulic lines that pass through the middle aileron fitting, out of the way, to properly access all nuts requiring replacement.

CAUTION: USE EXTREME CAUTION WHEN RE MOVING LINE BLOCK CLAMPS. FAILURE TO COMPLY MAY RESULT IN DAMAGE TO THE LINE BLOCKS. IF LINE BLOCKS AR E DAMAGED, REFER TO IPC, CHAPTER 29 FOR REPLACEMENT LINE BLOCKS.
D. Remove line block clamps, P/N 25 W243003-015/-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 cl ear 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 requir ed to match existing top coat.

H. Install ailerons. Refe r 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 se rial 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 ai rcraft. 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 positio n. Refer to AMM, Chapter 27.

E. Disconnect external electr ical power from aircraft. Refer to AMM, Chapter 12.
F. Disconnect external hydr aulic from aircraft. Re fer to AMM, Chapter 12.
G. Remove access panels between rib 3 and rib 15 on lower skin. Refer to AMM, Chapter 06 and Figu re 1, Sheet 3.

NOTE: It is necessary to open access p anels between rib 3 and rib 7 to facilitate removal of wing ta nk vent pipe to allow pr op er film placement between ribs 7 and 15.
H. Remove and replace nu ts on the vertical p la ne (one at a time) on r ear spar datum area, with new nuts, P/N MS21042L3. Refe r 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 brak es No. 1 through No. 4 fittings (left and right wing rear spar area). Refer to AMM, Chapters 28 and 29.
J. Perform radiographic inspec tion of noted nuts. Refer to Figure 2, Sheet 6, View D. Refer to Appendi x A for inspection procedure.
K. Remove and replace any cracked nuts found during in spection (one at a time) wet with seal ant, PR 1750.

March 30, 2010

# Gulfstream

SERVICE BULLETIN

Service Bulletin No. 200-51-366 Page 8 of 17 NOTE: Prior to install ing 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 reconn ect vent tubes disconnected/released in Step 8.I. above. Refer to AMM, Chapters 28 and 29.

NOTE: Ensure O-rings are replaced on the f uel vent tubes and jettison tubes where disconnected to move tube for film placem ent. Refer to Material Information on page 3 for O-ring P/Ns.

O. Ensure work area is clean and cl ear of foreign objects (FOD)
P. Install access panels between rib 3 an d rib 23. Refer to AMM, Chapter 06, Chapter 28 and Figu re 1, Sheet 3.
Q. Refuel wings and check for leaks from wing acce ss panels, NACA scoops, inboard aileron fittings, air brake fittings, (if nuts were replaced in any air brake fittings) wet area of wing tank and jettis on nozzles. Refer to AMM, Chapter 28.

NOTE: Allow sealant to cure per manufact urers instructions before fueling aircraft. Record compliance with this service bulletin in the aircraft’s permanent maintenance records and retu rn aircraft to flight status.
9. Report compliance with this service bulletin to Gulf stream CMP via electronic transmittal or fill out and fax the attached service reply card.

If technical assistan ce is required, contact your area Gulfstream Field Service Representative or call Gulf stream 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. Bo x 2206, Savannah, Georgia 31402-2206, USA. © 2010 Gulfstream Aerospace. All rights reserved, including the ri ght to reproduce this publication. No part may be reproduced, stored in any retrieval syst em, or transmitted in any part or form or by any means, electronic, photocopying, microfilm, mi crofiche, mechanical, or otherwise, without prior written permission of Gulfstream Aerospace. This technical data is controll ed under the Export Administration Regulations by General License TSU. It may not be transferred to a third party with out 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 BULLETI N 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 ASECURITY 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 SIZEOriginal 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 syst em, a printed copy is uncontrolled. 1. APPLICABILITY Applicable to G150 and G200 projects.

2. SCOPE
2.1. This Inspection Specification (IS) es tablishes 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 inspect ed 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 indica ted, 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 & Qualificat ion of Nondestructive Test Personnel 

### 3.3. American Society for Testing and Materials (ASTM) ASTM E1742 Standard Practice fo r Radiographic Examination

4. ENGINEERING DRAWING CALL-OUT Where required this IS shall be re ferred 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 2IS951400 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 syst em, 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 syst em, 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 w hat 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 connecti ng air brake fittings (left and right wing) between Rib 7 to Rib 11, shown in Figur es 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 radiographi c 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 syst em, 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. 8Original 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 syst em, 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. 9IS951400 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 syst em, 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.10Original 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 syst em, 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. 11IS951400 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 syst em, 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. 13Original 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 syst em, 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. 15IS951400 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 syst em, 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 85mmOriginal 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 syst em, a printed copy is uncontrolled. Figure 7: Sketch of Equipment Positioning X-Ray Tube Area to be inspectedIS951400 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 syst em, a printed copy is uncontrolled. Figure 8: Access Openings for Placing Film Access O p enin g sOriginal 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 syst em, 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 sparIS951400 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 syst em, a printed copy is uncontrolled. Figure 10: Schematic View of Possible Crack Location Crack