SERVICEBULLETIN REVISIONTRANSMITTALSHEET AIRBUSINDUSTRIE CUSTOMER

SERVICESDIRECTORATE 1 Rond Point Raurice BELLONTE 31707 BLAGNACCEDEXFRANCE Tel : (33) 5 61-93-33-33 Telex : AIRBU530526 F TITLE : WINGS- CENTERSECTION- PRESSURIZEDFLOORFITTINGS - CHANGE

MATERIAL. MODIFICATION No. 21282PO1497 ATASYSTEM: 57 This page transmits Revision No. 02 of Service Bulletin No. A320-57-1029.
ADDITIONAL WORK Noadditional work is required by this revision for aircraft modified by any previous revision.
HISTORYOFPREVIOUSREVISIONS Revision No. 1 is issued to replace bolts NSA5464by repair size bolts NSA5479BV.
REASON Revision No. 02 is issued to incorporate Change Notice No. 1-A. and to add information related to removal/installation of fittings. Cl) During removal of fasteners Item (31, there is a risk that bolt head comes in contact with shouldered bush Item (14) installed on beam Item (111, it is necessary to remove these shouldered bushes. (2) At installation of new fitting Item 1, it is necessary to drill fitting to match existing holes on lower surface panel. To facilitate counterdrilling of fastener Item 3 holes, the lower 'fasteners Item 12, of rib flange (FR36) must be removed.

5 DATE: Aug 12/91 REVISION No. : 02 - Jun 16/99 SERVICEBULLETIN No. : A320-57-1029 PAGE: 1 of 3

Prmted I” FranceSERVICEBULLETIN REVISIONTRANSMITTALSHEET CHANGES SERVICEBULLETIN SUMMARY Page 1 of 3 - Para. REASON,NOTE2 added. Page 2 - Para. EFFECTIVITY, Customer ITF deleted.

Para. EFFECTIVITY, sentence "This modification is embodied prior to delivery on A/C MSN105 and subsequent" deleted. Page 3 - Para. MANPOWER :A/C without fuel center tank MANHOURS

becomes 79.0 instead of 40.5 ELAPSEDTIME (HOURS)becomes 34.0 instead of 12 A/C uith fuel center tank added MANHOURS

85.0 ELAPSEDTIME (HOURS)39.0. Para. MATERIALINFORMATIONupdated. SERVICEBULLETIN Pages 1 and 2 - Para. l.A.(l), aircraft model 320-212 added. Para. l.A.(2), effectivity updated. PROPRIETARYRIGHTSstatement added. Page 3 Page 4 Page 5

Page 6
Page 7

Page 8

DATE: Aug 12/91 REVISION No. : 02 - Para. REASON,NOTE2 added. Para. APPROVAL,sentence updated.

- Para. MANPOWER

updated to comply with Para. MANPOWER of SUMMARY.

- Para. MATERIAL- COSTANDAVAILABILITY updated. Para. TOOLING - PRICE ANDAVAILABILITY, Kit TOOL deleted. Para. WEIGHTANDBALANCEupdated.

- Para. REFERENCES,Service Bulletin No. A320-57-1028 and A320-57-1013 added, Structural Repair Manual 51-44-11 added.

- Para. 2.A.(2)(a), Mat. No. II-003 replaced by Mat. No. 11-026. Para. 2.B., refer to Figures 1 and 2 added. Para. Z.B.(l), "Remove the PRaround the fasteners" deleted. NOTEadded.

- Para. 2.B.(l)(a), "12 bushes Item (14)" added. NOTEconcerning the removal of bolts Item (3) deleted.

SERVICEBULLETIN No. : A320-57-1029 Jun 16/99 PAGE: 2
Punted I” FranceSERVICE BULLETIN REVISION TRANSMITTALSHEET Pages 8 thru 10- Para. 2.8.(2) modified : procedure of replacement of the fittings with removal-of the two shouldered bushes of the beam added. Pages II-12 Page 13-14 Page 15 Page 16 Page 17

Page 18 - Text shifted

- Figure 1 modified, Items 12, 13 and 14 added.

- Figure 1, Sheet 2 added.

- Figure 2 added.

- Para. 3.A. modified. ASN-A2036 replaced by ASN-A2536. 12 bolts NSA5357-5-15, 12 bolts NSA5359-5-15 and 12 nuts NSA5050-5 added. 12 bushes D5337080720000 added. Para. 3.8. SPECIALTOOLS, Kit Tool deleted.

- Para. 3. C., Hat. No. II-003 replaced by Mat. No. 11-026.
FILING INSTRUCTIONS Replace pages SUMMARY1of 3 thru 3

SERVICEBULLETIN 1 of 18 thru 18. Put this Revision Transmittal Sheet in front of the Service Bulletin.
REVISIONSEQUENCES ORIGINAL : Aug 12/91 REVISION No. : 1- Nov lo/92 REVISIONNo. : 02 - Jun 16/99

DATE: Aug 12/91 SERVICEBULLETIN No. : A320-57-1029 REVISIONNo. : 02 - Jun 16/99 PAGE: 3
Prmted I” FranceSERVICEBULLETIN SUMMARY AIRBUSINDUSTRIE CUSTOMER



### SERVICESDIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNACCEDEXFRANCE Tel : (33) 5 61-93-33-33 

### Telex : AIRBU530526 F

This summary is for information 

### only and is not approved for

modification on the aircraft. TITLE : 

### WINGS- CENTER

### SECTION- PRESSURIZEDFLOOR

### FITTINGS - CHANGE



### MATERIAL. MODIFICATION No. 21282POl497 REASON/DESCRIPTION/OPERATIONALCONSEQUENCES During the center 

### fuselage fatigue test, damage was found on the pressurized 

### floor fittings at FR36, under the 

### lower surface panel after 102,560 simulated flights. The damage (cracks caused by bending) spread through the thickness 

### and resulted in breakage of the fittings. Therefore, this Service Bulletin recommends replacing the existing aluminium fittings by new titanium fittings 

### on all in service aircraft at 16,000 flights 

### at the latest. NOTE1 : 

### In case of non accomplishment

of this Service Bulletin, it is recommended to perform inspection as per instructions described in Service Bulletin No. A320-57-1028. Accomplishment of this Service 

### Bulletin cancels the instructions described in Service 

### Bulletin No. A320-57-1028. NOTE2 : 

### It is recommended that this

Service Bulletin is 

### accomplished at the same time as the Service 

### Bulletin No. A320-57-1013. ATASYSTEM: 57

STA1869/FR42 STAl590/FR36

SECTION 

### B-B FR36

FR35 

# 0

FWD 5 DATE: Aug 12/91 

### SERVICEBULLETIN No. : A320-57-1029 

### REVISION No. : 02 - Jun 16/99 PAGE: 1of 3

Prmted mFranteSERVICE BULLETIN SUMMARY EFFECTIVITY

I This Service Bulletin is applicable to

these customers :

I AAA, ACA, ADR, AFR, BAW, CYP, DLH, HP,

IAC, NWA, RJA, XP.
SERVICE BULLETIN/MODIFICATION TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY None.

. REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT. : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : NO OTHER : None
NATURE OF THE MODIFICATION AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO
COMPLIANCE Recommended.

DATE : Aug 12/91 SERVICE BULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE : 2
Prmted mFranceSERVICEBULLETIN SUMMARY MANPOWER A/C without fuel center tank TOTALMANHOURS ELAPSEDTIME (HOURS) A/C with fuel center tank TOTALMANHOURS 85.0 ELAPSEDTIME (HOURS) 79.0 34.0

39.0
MATERIAL INFORMATION AIRCRAFTDATA Qty per A/C : 6 fittings, 6 bushes, 12 shouldered bushes, 48 bolts. EQUIPMENTDATA None.
APPENDICES None.

DATE: Aug 12191 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE: 3
Prmted I” FranceSERVICE BULLETIN

AIRBUS INDUSTRIE CUSTOMERSERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61-93-33-33 Telex : AIRBU 530526 F TITLE : WINGS - CENTER SECTION - PRESSURIZED FLOOR FITTINGS - CHANGE

MATERIAL. MODIFICATION No. 21282PO1497 ATA SYSTEM : 57 1. PLANNING INFORMATION A. EFFECTIVITY

I (1) Aircraft models : 320-111, 320-211, 320-212, 320-231.

(2) Aircraft Customer and Fleet No. AAAOOI-006 007,008 ACA201-204 ADROOl AFR001,002 005,007 A01 004-009 014,019,020,021,002,004 A01 010-013 003,010,012,013 A01 015 016 A01 031-036 061,062,063,100,101,102 A01 066-068 033,036,044 A01 305 085 A01 BAWOOl-006 007,008 CYPOOI-004 DLHOOI-006 007-010 HP 620-622 624-629 631-636 637

5 DATE : Aug 12191 SERVICE BULLETIN No. : A320-57-1029 MSN Kit No. 571029 QtY

of Kits 022,023,024,025,026,027 A01 06 029,030 A01 02 059,068,073,084 A01 04 043 A01 01 02 06 04 iii 03 01

. 006,008,011,017,018,039 A01 06 042,103 A01 02 028,035,037,038 A01 04 069,070,071,072,078,083 A01 06 086,093,094,104 A01 04 052,053,054 * 055,064,065,066,067,076 077,081,082,091,092,098 099 A01 A01 A01 A01 03

06
::

REVISION No. : 02 - Jun 16199
Prmted I” France PAGE : 1 of 18SERVICEBULLETIN

. Customer and MSN

. Kit No. 

### Qty Fleet No. 571029 of Kits IACOOI-006 045,046,047,048,049,050 A01 06 007-012 051,056,057,058,074,075 A01 06 014-019 080,089,090,095,096,097 A01 06 NWA301-306 031,032,034,040,041,060 A01 06 RJA001,002 087,088 , A01 02
This modification is embodied prior 

### to delivery on A/C MSN105 and subsequent. This document contains Airbus Industrie PROPRIETARYINFORMATIONand 

### shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie in connection with any information contained in it. 

### It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, 

### shall not be used for any purpose other than that for which it is hereby 

### delivered. It shall not be disclosed in 

### whole or in part to third ' parties and 

### shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie's prior written consent. (3) Spares None.
B. REASON During the center 

### fuselage fatigue test, damage wasfound on the pressurized floor fittings at FR36, under the lower surface panel after 102,560 simulated flights. The damage (cracks caused by bending) spread through the thickness and resulted in breakage of the fittings. Therefore, this Service Bulletin recommends replacing the existing aluminium fittings by newtitanium fittings on 

### all in service aircraft at 16,000 flights at the 

### latest.

DATE: Aug 12/91 

### SERVICEBULLETIN No. : A320-57-1029 

### REVISION No. : 02 - Jun 16/99 PAGE: 2
Prmted I” FranceSERVICEBULLETIN 

# I NOTEI : In-case of non accomplishment of this Service Bulletin, it is

recommended to perform inspection as per instructions described in Service Bulletin No. A320-574028. Accomplishment of this 

### Service Bulletin cancels the instructions described in Service Bulletin No. A320-57-1028. 

# I NOTE2 : It is recommended that this Service 

### Bulletin is accomplished at

the sametime as the Service Bulletin No. A320-57-1013. 

### C. DESCRIPTION Accomplishment of this Service 

### Bulletin consists in carrying out the 

### following jobs on the aircraft : Under the lower surface panel, at FR36, replacing the pressurized floor fittings : Cl)' Removing existing fittings (Material No. ASN-A3050 : aluminium). 

### (2) Installing newfittings (Material No. TA6V : titanium).
D. APPROVAL The 

### technical content of this Service 

### Bulletin has been approved under the authority of the DGACDesign Organisation Approval No. F.JA.02. If an aircraft 

### listed in the effectivity has a modification or repair embodied that is not of Airbus origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service 

### Bulletin.

DATE: Aug 12/91 

### SERVICEBULLETINNo. 

### : A320-57-1029 

### REVISIONNo. : 02 - Jun l6/99 PAGE: 3
Punted tnFranceSERVICEBULLETIN

E. MANPOWER This Service 

### Bulletin is written for an aircraft in a maintenance condition. The manhours/elapsed time estimates do not include the time to prepare for the modification, non-productive elapsed time or administration. A/C without fuel center tank Gain access 1.0

. Removal of 

### 2 shouldered bushes 1.0 Removal of existing fittings 

### 40.0 Installation of newfittings and 2 shouldered bushes 

### 36.0 Close-up 1.0 TOTALMANHOURS 79.0 ELAPSEDTIME (HOURS) 34.0
A/C 

### with fuel center tank .Gain access 1.0 Removal of vapor 

### seal 2.5 Removal of 2 shouldered bushes 1.0 Removal of existing fittings 40.0 

### Installation of newfittings and 2 shouldered bushes 36.0 Tests 1.0 

### ‘Installation of vapor seal 2.5 

### Close-up 1.0 TOTALMANHOURS 85.0 ELAPSEDTIME (HOURS) 39.0

DATE: Aug 12/91 

### SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE: 4
Punted I” FranceSERVICEBULLETIN

F. HATERIAL- COSTANDAVAILABILITY (11' Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to Airbus Industrie. Quote the number of this Service Bulletin. The address is :

AIRBUSINDUSTRIE MATERIELSUPPORTCENTER P-0. BOX63 02 62 22312 HAMBURG GERMANY (2) Cost and availability Kit No. cost Availability : Calendar

(US Dollars) days from receipt of order
571029AOl 5,320.OO 180 The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that wecan try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin.
G. TOOLING - PRICE ANDAVAILABILITY 

# I None.
H. WEIGHT ANDBALANCE

I Manufacturers Empty Weight : + 0.64 kg (+ 1.41 lb)

Effect on balance : + 10.19 kgm (+ 73.70 lb.ft)

. DATE: Aug 12/91 SERVICE BULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE: 5
Prmted I” FranceSERVICEBULLETIN

.I. REFERENCES Aircraft Maintenance Manual (AMM): 06-41-53, 12-11-28, 12-34-24, 20-21-11, 24-41-00, 28-00-00, 28-10-00, 28-11-00, 28-13-42, 28-25-00, 57-17-11

I Service 

### Bulletin : A320-57-1028, A320-57-1013

Structural Repair 

### Manual : 51-44-11 Consumable Material List (CML)
J. PUBLICATIONSAFFECTED Structural Repair Manual (SRM)-: 57-11-29

DATE : bug 12191 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun l6/99 PAGE: 6
Prmted I” FranceSERVICEBULLETIN

2. ACCOMPLISHMENT



### INSTRUCTIONS A. GENERAL (1) Preparation (a) De-energize the aircraft electrical circuits (Refer to AMM24-41-00, P. Block 201) and 

### electrically ground the aircraft (Refer to AMM12-34-24, P. Block 201). (b) Put the access platform in position. WARNING: MAKESURETHATTHESAFETYPRECAUTIONSFORTHEACCESS

TOTHEFUELCENTERTANKANDFORTHEWORKIN THEFUEL CENTERTANKAREFULLYOBEYED(REFERTOAMM

### 28-00-00, 8 P. BLOCK301).

. (c) For the aircraft,with a wing center tank, defuel the center tank (Refer to AMM28-25-00, P. Block 301) and degas it (Refer to AMM28-10-00, P. Block 301). (d) Open the access doors 147A2, 148AZ (Refer to AMM57-17-11, P. Block 4011 and 191KB, 192KB (Refer to AMM06-41-53). 

### (e) In the 

### applicable zone, remove/install the vapor 

### seal (Refer 

### to AMM

### 28-13-42, P. Block 401).

I (2) Standard procedures

' (a) To clean the work areas with Material No. 11-026 (Refer to CML). (b) 

### Toapply tightening torque values (Refer to AMM20-21-11). (c) To renew the protective finish with Mat. No. 09-001, 16-002, 16-006 (Refer to CML).
B. MODIFICATION Under the Lower-surface 

### panel, at FR36, 

### replace the fittings of the
I pressurized 

### floor.

Refer to Figures 1 and 2 (I) Removethe fittings. NOTE: To remove the fittings, it is necessary to remove the shouldered bushes Item (14).

DATE: Aug 

### 12/91 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16199 PAGE: 7
Printed I” FranceSERVICEBULLETIN 

### (a) Remove

### (valid all A/C) : 6 fittings 6 bolts 12 bolts 12 bolts 12 bolts 24 nuts 12 nuts 6 washers 6 cotter pins 6 nuts 12 bushes Item (1) (discard) Item (2) (retain) Item (3) (discard) Item (4) (discard) 

### Item (5) (discard) Item (6) (discard) Item (7) (discard) Item (8) (discard) Item (9) (discard) Item (10) (discard) Item (14) (discard) lb) Clean the area with Mat. No. 11-026 (Refer to CML). 

### (2) Install the 6 newfittings. NOTE: Do6 times the installation procedure of afitting as it is given below. This means that the number of parts must be multiplied by 6. (a) Position on the box (adjust if necessary) : 1 fitting D5713004320295 

### Item 1 Cb) Pilot drill the fitting base 

### Item 1to match the 

### holes in the 

### lower surface 

### panel. 1 

### In order to gain access to transfer 

### holes from the lower surface 

### panel into fitting Item 1for 

### Item 3, it is acceptable to remove fastener Item (12) from FR36. 12 bolts 

### Item (12) (discard) 12 nuts 

### Item (13) (discard) ' (c) Attach the fitting base temporarily. (d) Counterdrill the fitting 

### Item 1. Use suitable drill bush. Ce) Removethe fitting 

### Item 1and drill 1 hole to 14 mm (0.551 in.) minimum dia. and 14.011 mmCO.5515 in.) maximum dia.

DATE: Aug 12/91 

### SERVICEBULLETIN No. 

### : A320-57-1029 

### REVISION No. : 02 - Jun 16/99 PAGE: 8

Prmted I” FranceSERVICEBULLETIN (fl 

### Install on the fitting 

### Item 1 

### : 1 bush D5713004920000 

### Item 2 with 

### loctite 675, Mat. No. 08-029 (Refer to CML). (g) Position the fitting Item 1on the lower surface 

### panel and drill the fitting to match the Lower surface panel : 

### 1 For 

### bolts Items 3 and 4 4 

### holes to 8.10 mmCO.319 in.) dia. 

### 2 For bolts 

### Item 5 2 

### holes to 6.50 mm(0.256 in.) dia. (h) Removethe fitting 

### Item 1 and on bench 

### drill : 1 For bolts 

### Items 3 and 4 4 holes to 8.296 mmCO.3265 in.) minimum dia.

and 8.335 mm(0.328 in.) maximum dia. 

### 1 For 

### bolts Item 5 2 holes to 6.706 mm(0.264 in.) minimum dia. and 6.747 mmCO.2655 in.) maximum dia. Produce a 1 mmCO.039 in.) chamfer to 45" on the 6 holes to accept underhead of radius 

### of bolts Items 3, 4 and-5 (Ref. SRM51-44-11). Ci) 

### In the 

### lower surface panel, drill : 

### 1 For 

### bolts Items 3 and 4 4 

### holes to 8.211 mm(0.323 in.) minimum dia. and 8.245 mm(0.3245 in.) maximum dia. 

### 2 For bolts 

### Item 5 2 holes to 6.622 mm(0.260 in.) minimum dia. and 6.658 mm(0.262 in,) maximum dia.

DATE: Aug 12/91 SERVICEBULLETIN No. : A320-57-1029 

### REVISION No. : 02 - Jun 16/99 PAGE: 9
Prmted I” FranceSERVICEBULLETIN Cj> After cleaning of the area, 

### install the fitting Item 1. Attach it and apply at the sametime Hat. No. 09-025 (Refer to CML)between the surfaces : 2 

### bolts NSA5479BV5-15X Item 3 2 bolts NSA5479BVS-13X 

### Item 4 2

### bolts NSA5479BV4-13X 

### Item 5 4 nuts ASN-A2536-5 

### Item 6 2 nuts ASN-A2536-4 

### Item 7 (k) Torque the nuts (Refer to AMM20-21-12). 

### (1) Install on the beam 

### Item (11) 

### : 2 bushes D5337080720000 

### Item 14 (ml 

### Install the 

### bolt Item (2) with : 1washer NSA5307C5 

### Item 8 1 nut NSA5060C5 

### Item 9 1 cotter pin MS24665-153 

### Item 10 Make sure there is a clearance of 0.2 mm(0.008 in.) (Refer to Fig. 1, Section DD). %Torque the nut 

### to avalue between 0.5 m.daN (44 lb-in.1 and 1.4 m.daN (120 

### lb.in.1. (n) 

### Install on FR36 (the 

### Item 12 is installed with an interference fit) : 

### 1 If the Service 

### Bulletin No. A320-57-1013 has not been embodied I 

### 12bolts NSA5357-5-15 

### Item 12 12 nuts NSASOSO-5 

### Item 13 2 

### If the Service Bulletin No.,A320-57-1013 has been accomplished in advance of this Service 

### Bulletin 12 bolts NSA5359-5-15 Item 12 12 nuts NSASOSO-5 

### Item 13 Co) Dothe sealing of the hardware inside the box and of the fitting base contour on the 

### lower surface 

### panel with Mat. No. 09-001 (Refer to CML).

DATE: Aug 12/91 

### SERVICEBULLETIN No. : A320-57-1029 

### REVISION No. : 02 - Jun 16/99 PAGE: 10
Prmted I” France

### SERVICEBULLETIN

C. TESTS (1) Energite the aircraft electrical circuits (Refer to AMM24-41-00, P. Block 201) and disconnect the aircraft 

### electrical ground ' connection (Refer to AMM12-34-24, P. Block 201). (2) 

### Close the access doors 147AZ and 148AZ (Refer to AMM57-17-11). 

### (3) Refuel the 

### center tank (Refer to AMM12-11-28). 

### (4) Dothe 

### leak test (Ref. AMM28-.11-00, 

### P. Block 501).
D. CLOSE-UP (I) 

### Install the vapor 

### seals (Refer to AMM28-13-42, P. Block 401). (2) Close the access doors 191KB, 192KB (Refer to AMM06-41-53).

DATE: Aug 12/91 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE: 11-12
Prmted mFrance

### 10 9 SERVICE BULLETIN

SECTION 

## D-D AITER 8 CLEARANCE 0.2mm MIN. \ , ((0.008in.)



### 12 13 CLEARANCE 0.2mm MIN. (0.006in.)

FR36 SECTION I c-c .-Avv ’ 

### AFT=ERTlHOLE IN EGEr yT;;l” SURFACE

PANEL

Replacement of Pressurized Floor Fittings at FR36 under Lower Surface Panel

Figure 1, Sheet 2

. DATE : Aug 12/91 SERVICE BULLETIN No. : A320-57-1029 REVISION NO. : 02 - Jun 16/99 PAGE : 15
Prmced I” FranceSERVICE BULLETIN

SECTION

## A-A WITH REMOVAL TOOL IN PLACE

- FllTlNG

- BUSH

BUSHREMOVAL TOOL =

CHAMFER TOOL TO FIT UNDER HEAD OFBUSHANDACTAS ADRIFT

Bush Removal Tooling Example Figure 2

DATE : Aug 12/91 SERVICE BULLETIN No. : A320-57-1029
I REVISION No. : 02 - Jun 16/99 PAGE : 16
Prmted I” FranceSERVICEBULLETIN

3. MATERIAL INFORMATION A. LIST OFCOMPONENTS ii : NEWPARTNo. QTY DESCRIPTION : OLDPARTNo. I: si F4 Fi T
Kit No. 571029 @J 

# 1 3' 4 

# i 7 8 9 10 12 13 14 D5713004320295 D5713004920000 NSA%i?BVS-15X NSA5479BVS-13X NSA5479BV4-13X ASN-A2536-5 ASN-A2536-4 NSA530fC5 NSA5060C5 MS24665-153 NSA5357-5-15 NSA5359-5-15 NSASOSO-5 D5337080720000 6 6 12 12 12 24 12 6 ii Ii 12 12 12 Fitting Bush Bolt Bolt Bolt Nut Nut Washer Nut Pin-Cotter Bolt Bolt Bolt Nut Bush (I) D5713004300000

(3) ASN-A2027VS-15 (4) ASN-A2027V5-13 (5) ASN-A2027V4-13 (6) ASN-A2036-5 (7) ASN-A2036-4 (8) NSA5307C5 (9) NSA5060C5 (IO) MS24665-153 (2) NSA5042COf-285 (12) ASNA2027VS-13 (12) NSA5357-S-15 (13) ASN2036-5
* not re-used ** retained
B. SPECIALTOOLS None. * * * * * * * * * **

DATE: Aug 12/91 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16199 PAGE: 17
Prmted mFranceSERVICEBULLETIN

C. LIST OFMATERIALS- OPERATOR SUPPLIED DESCRIPTION REFERENCE QTYPERA/C CML 

## I 

# I Loctite

Sealant, polysulfide, brush consistency Methyl Ethyl Ketone Polyurethane top coat, grey Primer coating epoxy polyamide chemical Mat. No. 08-029 As required Mat. No. 09-001 As required Mat. No. II-026 As required Mat. No. 16-002 As required Mat. No. 16-006 As required

D. PARTSTOBERE-IDENTIFIED BYOPERATOR None.

DATE: hug 12/91 SERVICEBULLETIN No. : A320-57-1029 REVISION No. : 02 - Jun 16/99 PAGE: 18
Pmted I” France