SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE 

1 Rond Point Raurice 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 

This page transmits Revision No. 02 of Service Bulletin 

No. A320-57-1029. 

ADDITIONAL WORK 

No additional work is required by this revision for aircraft modified by 

any previous revision. 

HISTORY OF PREVIOUS REVISIONS 

Revision No. 1 is issued to replace bolts NSA5464 by 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 

SERVICE BULLETIN No. : A320-57-1029 

PAGE : 1 of 3 

Prmted I” France 
SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

CHANGES 

SERVICE BULLETIN SUMMARY 

Page 1 of 3 - Para. REASON, NOTE 2 added. 

Page 2 - Para. EFFECTIVITY, Customer ITF deleted. 

Para. EFFECTIVITY, sentence "This modification is 

embodied prior to delivery on A/C MSN 105 and 

subsequent" deleted. 

Page 3 - Para. MANPOWER : A/C without fuel center tank 

MANHOURS becomes 79.0 instead of 40.5 

ELAPSED TIME (HOURS) becomes 34.0 instead of 12 

A/C uith fuel center tank added 

MANHOURS 85.0 

ELAPSED TIME (HOURS) 39.0. 

Para. MATERIAL INFORMATION updated. 

SERVICE BULLETIN 

Pages 1 and 2 - Para. l.A.(l), aircraft model 320-212 added. 

Para. l.A.(2), effectivity updated. 

PROPRIETARY RIGHTS statement added. 

Page 3 

Page 4 

Page 5 

Page 6 

Page 7 

Page 8 

DATE : Aug 12/91 

REVISION No. : 02 

- Para. REASON, NOTE 2 added. 

Para. APPROVAL, sentence updated. 

- Para. MANPOWER updated to comply with Para. MANPOWER 

of SUMMARY. 

- Para. MATERIAL - COST AND AVAILABILITY updated. 

Para. TOOLING - PRICE AND AVAILABILITY, Kit TOOL 

deleted. 

Para. WEIGHT AND BALANCE updated. 

- 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 PR around the fasteners" 

deleted. 

NOTE added. 

- Para. 2.B.(l)(a), "12 bushes Item (14)" added. 

NOTE concerning the removal of bolts Item (3) deleted. 

SERVICE BULLETIN No. : A320-57-1029 

Jun 16/99 PAGE : 2 

Punted I” France 
SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

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. SPECIAL TOOLS, Kit Tool deleted. 

- Para. 3. C., Hat. No. II-003 replaced by 

Mat. No. 11-026. 

FILING INSTRUCTIONS 

Replace pages SUMMARY 1 of 3 thru 3 

SERVICE BULLETIN 1 of 18 thru 18. 

Put this Revision Transmittal Sheet in front of the Service Bulletin. 

REVISION SEQUENCES 

ORIGINAL : Aug 12/91 

REVISION No. : 1 - Nov lo/92 

REVISION No. : 02 - Jun 16/99 

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

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

Prmted I” France 
SERVICE BULLETIN 

SUMMARY 

AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

Tel : (33) 5 61-93-33-33 

Telex : AIRBU 530526 F 

This summary is for information only and is not approved for 

modification on the aircraft. 

TITLE : WINGS - CENTER SECTION - PRESSURIZED FLOOR FITTINGS - CHANGE 

MATERIAL. 

MODIFICATION No. 21282POl497 

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 

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. 

NOTE 1 : 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. 

NOTE 2 : It is recommended that this 

Service Bulletin is 

accomplished at the same time 

as the Service Bulletin 

No. A320-57-1013. 

ATA SYSTEM : 57 

STA1869/FR42 

STAl590/FR36 

SECTION B-B 

FR36 

FR35 

0 FWD 

5 DATE : Aug 12/91 SERVICE BULLETIN No. : A320-57-1029 

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

Prmted mFrante 
SERVICE 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 m France 
SERVICE BULLETIN 

SUMMARY 

MANPOWER 

A/C without fuel center tank 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

A/C with fuel center tank 

TOTAL MANHOURS 85.0 

ELAPSED TIME (HOURS) 

79.0 

34.0 

39.0 

MATERIAL INFORMATION 

AIRCRAFT DATA 

Qty per A/C : 

6 fittings, 6 bushes, 12 shouldered bushes, 48 bolts. 

EQUIPMENT DATA 

None. 

APPENDICES 

None. 

DATE : Aug 12191 SERVICE BULLETIN No. : A320-57-1029 

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

Prmted I” France 
SERVICE BULLETIN 

AIRBUS INDUSTRIE 

CUSTOMER SERVICES 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 18 
SERVICE BULLETIN 

. 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 MSN 105 and 

subsequent. 

This document contains Airbus Industrie PROPRIETARY INFORMATION and 

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 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. 

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

REVISION No. : 02 - Jun 16/99 PAGE : 2 

Prmted I” France 
SERVICE BULLETIN 

I NOTE I : 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 NOTE 2 : It is recommended that this Service Bulletin is accomplished at 

the same time 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 new fittings (Material No. TA6V : titanium). 

D. APPROVAL 

The technical content of this Service Bulletin has been approved under 

the authority of the DGAC Design 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 SERVICE BULLETIN No. : A320-57-1029 

REVISION No. : 02 - Jun l6/99 PAGE : 3 

Punted tn France 
SERVICE BULLETIN 

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 new fittings and 2 shouldered bushes 36.0 

Close-up 1.0 

TOTAL MANHOURS 79.0 

ELAPSED TIME (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 new fittings and 2 shouldered bushes 36.0 

Tests 1.0 

‘Installation of vapor seal 2.5 

Close-up 1.0 

TOTAL MANHOURS 85.0 

ELAPSED TIME (HOURS) 39.0 

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

REVISION No. : 02 - Jun 16/99 PAGE : 4 

Punted I” France 
SERVICE BULLETIN 

F. HATERIAL - COST AND AVAILABILITY 

(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 : 

AIRBUS INDUSTRIE 

MATERIEL SUPPORT CENTER 

P-0. BOX 63 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 we can 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 AND AVAILABILITY 

I None. 

H. WEIGHT AND BALANCE 

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” France 
SERVICE BULLETIN 

. 

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. PUBLICATIONS AFFECTED 

Structural Repair Manual (SRM) -: 57-11-29 

DATE : bug 12191 SERVICE BULLETIN No. : A320-57-1029 

REVISION No. : 02 - Jun l6/99 PAGE : 6 

Prmted I” France 
SERVICE BULLETIN 

2. ACCOMPLISHMENT INSTRUCTIONS 

A. GENERAL 

(1) Preparation 

(a) De-energize the aircraft electrical circuits 

(Refer to AMM 24-41-00, P. Block 201) and electrically ground 

the aircraft (Refer to AMM 12-34-24, P. Block 201). 

(b) Put the access platform in position. 

WARNING : MAKE SURE THAT THE SAFETY PRECAUTIONS FOR THE ACCESS 

TO THE FUEL CENTER TANK AND FOR THE WORK IN THE FUEL 

CENTER TANK ARE FULLY OBEYED (REFER TO AMM 28-00-00, 

8 P. BLOCK 301). 

. (c) For the aircraft,with a wing center tank, defuel the center 

tank (Refer to AMM 28-25-00, P. Block 301) and degas it 

(Refer to AMM 28-10-00, P. Block 301). 

(d) Open the access doors 147A2, 148AZ (Refer to AMM 57-17-11, 

P. Block 4011 and 191KB, 192KB (Refer to AMM 06-41-53). 

(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) To apply tightening torque values (Refer to AMM 20-21-11). 

(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) Remove the fittings. 

NOTE : To remove the fittings, it is necessary to remove the 

shouldered bushes Item (14). 

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

REVISION No. : 02 - Jun 16199 PAGE : 7 

Printed I” France 
SERVICE BULLETIN 

(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 new fittings. 

NOTE : Do 6 times the installation procedure of a fitting 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 1 to 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 1 for 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) Remove the fitting Item 1 and drill 1 hole to 14 mm 

(0.551 in.) minimum dia. and 14.011 mm CO.5515 in.) maximum 

dia. 

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

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

Prmted I” France 
SERVICE BULLETIN 

(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 1 on 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 mm CO.319 in.) dia. 

2 For bolts Item 5 

2 holes to 6.50 mm (0.256 in.) dia. 

(h) Remove the fitting Item 1 and on bench drill : 

1 For bolts Items 3 and 4 

4 holes to 8.296 mm CO.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 mm CO.2655 in.) maximum dia. 

Produce a 1 mm CO.039 in.) chamfer to 45" on the 6 holes to 

accept underhead of radius of bolts Items 3, 4 and- 5 

(Ref. SRM 51-44-11). 

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 SERVICE BULLETIN No. : A320-57-1029 

REVISION No. : 02 - Jun 16/99 PAGE : 9 

Prmted I” France 
SERVICE BULLETIN 

Cj> After cleaning of the area, install the fitting Item 1. 

Attach it and apply at the same time 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 AMM 20-21-12). 

(1) Install on the beam Item (11) : 

2 bushes D5337080720000 Item 14 

(ml Install the bolt Item (2) with : 

1 washer 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 a value 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 

12 bolts 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) Do the 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 SERVICE BULLETIN No. : A320-57-1029 

REVISION No. : 02 - Jun 16/99 PAGE : 10 

Prmted I” France 
SERVICE BULLETIN 

C. TESTS 

(1) Energite the aircraft electrical circuits (Refer to AMM 24-41-00, 

P. Block 201) and disconnect the aircraft electrical ground 

' connection (Refer to AMM 12-34-24, P. Block 201). 

(2) Close the access doors 147AZ and 148AZ (Refer to AMM 57-17-11). 

(3) Refuel the center tank (Refer to AMM 12-11-28). 

(4) Do the leak test (Ref. AMM 28-.11-00, P. Block 501). 

D. CLOSE-UP 

(I) Install the vapor seals (Refer to AMM 28-13-42, P. Block 401). 

(2) Close the access doors 191KB, 192KB (Refer to AMM 06-41-53). 

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

REVISION No. : 02 - Jun 16/99 PAGE : 11-12 

Prmted m France 

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=ER 

TlHOLE 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” France 
SERVICE BULLETIN 

SECTION A-A 

WITH REMOVAL TOOL 

IN PLACE 

- FllTlNG 

- BUSH 

BUSH REMOVAL 

TOOL 

= 

CHAMFER TOOL 

TO FIT UNDER HEAD 

OFBUSHANDACTAS 

A DRIFT 

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” France 
SERVICE BULLETIN 

3. MATERIAL INFORMATION 

A. LIST OF COMPONENTS 

ii 

: NEW PART No. QTY DESCRIPTION : OLD PART No. 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. SPECIAL TOOLS 

None. 

* 

* 

* 

* 

* 

* 

* 

* 

* 

** 

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

REVISION No. : 02 - Jun 16199 PAGE : 17 

Prmted m France 
SERVICE BULLETIN 

C. LIST OF MATERIALS - OPERATOR SUPPLIED 

DESCRIPTION REFERENCE QTY PER A/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. PARTS TO BE RE-IDENTIFIED BY OPERATOR 

None. 

DATE : hug 12/91 SERVICE BULLETIN No. : A320-57-1029 

REVISION No. : 02 - Jun 16/99 PAGE : 18 

Pmted I” France