GA300 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

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 WING BOX - INSPECT CENTER WING BOTTOM SKIN FOR 

CORROSION AT RIB 1. 

MODIFICATION No. NONE (INSPECTION) ATA SYSTEM : 57 

This page transmits Revision No. 01 of Service Bulletin 

No. A300-57-0204. 

ADDITIONAL WORK 

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

any previous revision. 

HISTORY OF PREVIOUS REVISIONS 

No previous revisions. 

REASON 

Revision No. 1 issued to inform the operators that the compliance has 

changed into mandatory, clarify the permissible limits of rework and 

update the effectivity. 

SERVICE BULLETIN SUMMARY 

Page 1 of 4 - Para. REASON, Airworthiness Directive No. 97-006-210(B) 

added. 

Page 2 - Para. EFFECTIVITY, customers updated. 

Para. COMPLIANCE, Recommended becomes Mandatory. 

SERVICE BULLETIN 

Pages 1 of 101 to 3 - Para. l.A.(2), effectivity updated. 

PROPRIETARY RIGHTS statement added. 

Page 6 

: ., 

Para. l.B.(5), Airworthiness Directive 

No. 97-006~21&B) added. 

5 DATE : Dee O4/95 SERVIC;BULLETIN No. : A300-57-0204 

REVISION.No. : 01 - Apr 02/99 PAGE : 1 of 2 

Printed in France 
Page 8 

Page 9 

Page 40 

Page 11 

Page 17 

Page 19 

Page 20 

Pages 21 thru 23 

Page 31-32 

Page 101 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

- Para l.C.(3)(a)(b), permissible rework limits 

clarified and NOTE added. 

Para. l-D., sentence updated and sentence 

concerning the approval for a possible adaptation 

added. 

- Para. l.G.(2), reference modified. 

Para. l-I., SRM reference'added. 

Para. 1-J., MPD reference modified. 

- Para. Z.A., WARNING added. 

- Para. 2.B.(l)(a), application of Mat. No. 13-002 

cancelled. 

- Para. 2-B.(2)(a), application of Mat. No. 13-002 

cancelled. 

- Para. 2.8.(2)(b), application of Mat. No. 13-002 

cancelled. 

- Para. 2.B.C3), text and references modified, 

application of Mat. No. 13-002 cancelled. 

- Figure 5, Views A and'B minimum thicknesses 

clarified. NOTE 2 updated. 

- Para. 3-C., Mat. No. 13-002 deleted. 

FILING INSTRUCTIONS 

Replace pages SUMMARY 1 of 4 and 2 

SERVICE BULLETIN 1 of 101, 2, 3, 6, 8, 9, IO, 11, 17, 19, 

20, 21, 22, 23, 31-32 and 101. 

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

REVISION SEQUENCES 

ORIGINAL : Dee 04195 

REVISION NO. : 01 - Apr 02199 

DATE : Dee 04195 

REVISION No. : 01 - Apr 02/99 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 2 

Printed in France 
, AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE GA300 

1 Rand Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

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

Telex : AIRBU 530526 F SUMMARY 

This summary is for information only and is not approved for 

modification on the aircraft. 

TITLE : WINGS - CENTER WING BOX - INSPECT CENTER WING BOTTOM SKIN FOR 

CORROSION AT RIB .I. 

MODIFICATION No. NONE (INSPECTION) ATA SYSTEM : 57 

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 

Eight operators of A300 aircraft have reported 20 cases of corrosion on 

the lower wing root joint during scheduled maintenance. The aircraft 

have been in-service between 4 and 10 years. The corrosion was located 

in the wing bottom skin inboard and outboard of the external lower 

surface splice. Most of the corrosion was found in the area aft of FR43, 

although some corrosion has also been found forward of this area, and 

around the fasteners starting from the edges of the countersinks. 

This Service Bulletin recommends a detailed visual inspection of the 

wing bottom skin, inboard and outboard of the rib 1 external lower 

surface splice, between FR40 and FR47. Repair of the corrosion damage is 

by local blend-out and spotfacing. 

Once the corrosion has been removed, if the corrosion damage exceeds a 

certain limit, there would be a reduction in strength margins which 

could lead to cracking from the fastener holes. Non Destructive Testing 

or detailed visual inspections are then necessary to detect the presence 

of cracks around the fastener holes. A fatigue program inspection has 

been developed in this Service Bulletin to cover this possibility. 

Accomplishment of this Service Bulletin permits detection of corrosion 

in the lower wing root at an early stage. This will avoid extensive 

corrosion damage, resulting in extensive rework and/or repairs and 

possible fatigue cracks in the future. 

The'corrosion inspection is recommended on aircraft which have been 

in-service for 5 years or more from the date of delivery. The inspection 

is to be repeated every 5 years. 

After corrosion removal, a repetitive inspection for possible fatigue 

damage is recommended. The thresholds and intervals given for the 

fatigue inspection depend on the results of the corrosion inspection. 

This Service Bulletin is rendered mandatory by Airworthiness Directive 

(Consigne de Navigabilite) No. 97-006-210(B). 

5 DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 1 of 4 

Printed in France 
G A300 

SERVICE BULLETIN 

SUMMARY 

EFFECTIVITY 

This Service Bullet in is applicable to the following operators : 

AFR, AIC, AJM, AUS, 

IRA, ITF, JAS, KAL, 

TAR, THA, VIA, VSP. 

AZA, CAL, COA, DLH, EAL, FIN, GIA, HLF, IAC, IBE, 

LGL, MAS, MSR, OAL, OYC, PAA, PAL, PIA, RKA, SAA, 

SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY 

None. 

REFERENCES/REPERCUSSIONS 

TFU 

OEB 

AOT 

SIL. 

LIFE LIMIT 

: 53-15-00-021 

: None 

: None 

: 38-013 

: None 

LINE MAINTENANCE AFFECTED : NO 

OTHER : None 

NATURE OF THE WORK 

AIRCRAFT : YES 

EQUIPMENT : NO 

COMPLIANCE 

I 

Mandatory. 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 2 

Printed in France 
SERVICE BULLETIN 

SUMMARY 

MANPOWER 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

7.5 

3.5 

MATERIAL INFORMATION 

AIRCRAFT DATA 

None. 

EQUIPMENT DATA 

None. 

APPENDICES 

None. 

DATE : Dee O4/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 3 

Printed in France 
SERVICE BULLETIN 

SUMMARY 

u 

ARES TO INSPECT 

DATE : Dee 04195 

REVISION No’. : 

SERVICE BULLETIN No. : ASOO-57-0204 

PAGE : 4 
AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE GA300 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

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

Telex : AIRBU 530526 F 

TITLE : WINGS - CENTER WING BOX - INSPECT CENTER WING BOTTOM SKIN FOR 

CORROSION AT RIB 1. 

MODIFICATION No. NONE (INSPECTION) ATA SYSTEM : 57 

1. PLANNING INFORMATION 

A. EFFECTIVITY 

(1) Aircraft models : B2-1C, B2-203, B2K-3C, B4-2C, 84-103, B4-120, 

84-203, 84-220, C4-203, F4-203. 

(2) Aircraft 

Customer and 

Fleet No. 

AFR051-054 

056-060 

062 

064 

MSN 

019,023,045,047 

074,078,100,129,145 

175 

183 

Kit No. Qty 

None of Kits 

AICIOI-103 

AJMOOl-004 

AUSOOl 

003-005 

177,180,190 

127,131,109,143 

134 

157,196,218 

. Ai!A101,102 

151-162 

049,051 

101,106,107,123,139,140 

142,173,067,118,120,068 

CALOOI-006 193,197,221,232,179,171 

COA966-968 117,121,126 

970-972 250,262,289 

DLHOOI-007 071,084,085,141,149,249 

265 

' EAL201,202 041,042 

204-206 044,065,066 

209,210 086,087 

212 091 

220,221 124,152 

5 DATE : Dee 04195 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 1 of 101 

Printed in France 
Customer and 

Fleet No. 

EAL223-235 

FIN001,002 299,302 

GIAOOI-007 

cm9 

HLF307 083 

IAC002-009 

051,052 

IBE251-256 130,133,135,136,156,170 

281,282 076,077 

IRAOOI-003 061,080,185 

005,006 187,226 

ITF034-037 027,062,097,112 

042,043 050,132 

092-094 057,020,017 

096 012 

JASOOI-009 

101-108 

KAL007 

101,102 

LGLOOI 

MASOOl-004 

. MSR002-005 

007,008 

OALOOI-008 

OYC201,202 

204 

DATE : pet 04/95 SERVICE BULLETIN No. : A300-57-0204 

SERVICE BULLETIN 

MSN Kit No. Qty 

None of Kits 

154,155,158,161,204,207 

211,216,220,259,261,271 

274 

159,164,165,166,167,168 

213 

215 

036,038,059,060,088,111 

113,026 

181,182 

082,089,090,160,163,176 

209,244,253 

256,151,169,174,110,194 

239,178 

031 

277,292 

269 

073,093,095,147 

116,150,199,200 

240,255 

046,056,058,103,105,148 

184,189 

079,094 

128 

REVISION No. : 01 - Apr 02/99 PAGE :2 

Printed inFrance 
Customer and 

Fleet No. 

PAAOOI-012 

PALOOI-005 

PIAOOI-004 

010-012 

014 

RKASSI-553 

SAAOOl-004 

051-053 

101 

TAR001 

THAOOI-004 

VIA001,002 

VSPOOI-003 

. Unassigned 

SERVICE BULLETIN 

MSN Kit No. Qty 

None of Kits 

195,227,198,247,234,236 

304,305,238,235,208,210 

063,069,125,203,219 

096,098,099,114 

064,144,268 

146 

137,243,282 

032,037,039,040 

138,192,222 

212 

188 

033,035,054,055 

053,075 

202,205,225 

003 

This Service Bulletin is applicable to A/C listed above. 

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. 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 3 

Printed in France 
GA300 

SERVICE BULLETIN 

B. REASON 

(I) History 

Eight operators of A300 aircraft have reported 20 cases of 

corrosion in the area of the lower wing root joint during scheduled 

maintenance. The corrosion was located mainly in the wing bottom 

skin inboard and outboard of the external lower surface splice. 

Most of the corrosion was found in the area aft of FR43, although 

corrosion has also been found forward of this area. 

One operator of an A310 aircraft has also reported severe corrosion 

in the same area. At one location, the remaining material thickness 

after removal of the corrosion was only 20 percent of the nominal 

thickness. However, Airbus Industrie has reported that this 

aircraft had a history of fluid leaks coming from the forward 

toilet service-panel, that were not repaired. This aircraft had 

also been stored without the correct weather protection. The 

operator report also suggests that previous storm damage may have 

also contributed to corrosion, as large areas of missing and 

flaking paint were found. 

The corrosion was discovered on aircraft which have been in-service 

between 4 and 10 years. The A310 has been in-service for just over 

9 years. 

The corrosion initiated at the edge of the countersinks of the 

fasteners. The heads, or part of the heads, of some fasteners are 

recessed into the countersinks. This exposes the top edges of the 

countersinks. If the paint is damaged, the area will not have the 

correct protection from pollutants such as leaking toilet fluids. 

In all the cases reported, with the exception of the A310, the 

corrosion was repaired by local rework (blend-out). The A310 

required extensive external doubler repairs. 

Corrosion in this area, if it is not detected and treated at an 

early stage, can lead to costly and time-consuming repairs. 

(2) Objective/Action 

This Service Bulletin recommends a detailed visual inspection of 

the wing bottom skin, inboard and outboard of the rib 1 lower 

surface splice, between FR40 and FR47. It also recommends check of 

the condition of the protective finish and renewing of protection 

if necessary. After the inspections and/or repairs, it is 

recommended to apply sealant beads along the joints to prevent 

fluids going into this area. 

DATE : Dee 04/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 4 

Printed in France 
SERVICE BULLETIN 

(3) 

(41 

(5) 

Repair of the corrosion damage is by local blend-out and 

spot-facing. If the corrosion damage found is more than the 

permissible limits given in this Service Bulletin, then special 

doubler repairs are necessary and the operators are requested to 

contact Airbus Industrie for advice. 

Once the corrosion is removed, if the corrosion damage exceeds the 

permissible limits, there would be a reduction in the strength 

margins which would lead to cracking from the fastener holes. Non 

Destructive Testing or detailed visual inspections are then 

necessary to detect the presence of cracks around the fastener 

holes. 

A fatigue program inspection has been developed in this Service 

Bulletin to cover this possibility. 

Advantages 

Accomplishment of this Service Bulletin permits detection of the 

corrosion at an early stage in the area of the wing bottom skin. 

This will avoid extensive corrosion damage, resulting in extensive 

rework and/or repairs and possible fatigue cracks in the future. 

Operational/Maintenance Consequences 

This Service Bulletin modifies the corrosion inspection task in the 

A300 MPD, Section 06-07-57, Task No. 578021-0607-I. 

Accomplishment Timescale 

CORROSION INSPECTION 

The corrosion inspection is recommended on aircraft which' have been 

in-service for 5 years of more from the date of delivery. The 

inspection is to be repeated every 5 years. 

Aircraft that have been in-service more than 5 years should be 

inspected within the timescaies given below : 

- Aircraft with more than 5 years but less than 15 years service 

should be inspected not later than 18 months from receipt of this 

Service Bulletin, or at the next C-check, whichever occurs last. 

- Aircraft with more than 15 years but less than 20 years service 

should be inspected not later than 12 months from receipt of this 

Service Bulletin. 

- Aircraft with more than 20 years service since delivery should be 

inspected within 6 months from receipt of this Service Bulletin. 

DATE : Dee 04/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 5 

Printed in France 
32 A300 

SERVICE BULLETIN 

FATIGUE INSPECTION 

The fatigue inspections, if corrosion is found to be outside the 

limits given in this Service Bulletin, depend on the results of the 

corrosion inspection. An outline is included in this Service 

Bulletin (Table B, Figure 4). 

The thresholds and intervals given for the fatigue inspection in 

this Service Bulletin, are established and valid for aircraft 

operating with the following average airborne flight time : 

A300 Bl and 82 models 65 minutes (1.08 FH) 

A300 B4-100 modeLs 80 minutes (1.33 FH) 

A300 84-200, C4, F4 models 125 minutes (2.08 FH) 

Therefore, when aircraft are operating with different flight times, 

. inspection thresholds and intervals are to be adjusted in 

accordance with the instructions given in the A300 SSID Section 4, 

Para. 4.4. 

For the fatigue inspection given in this Service Bulletin, the 

Fatigue Rating (FR) to be applied is FR = 0.28. 

Additional flights flexibility for aircraft close to or over the 

threshold is not applicable to the fatigue inspection in this 

Service Bulletin. 

. This Service Bulletin is rendered mandatory by Airworthiness 

Directive (Consigne de Navigabilite) No. 97-006-210(B). 

(6) Special Information 

Airbus Industrie has issued several modifications to improve the 

resistance of the structure to corrosion. For the area of the wing 

lower root joint, operators are strongly advised to follow the 

recommendations listed below : 

If replacement of fasteners is needed, IVD-coated fasteners are 

preferred to anodised MOS2 coatings. 

After inspection and repair (if repair is necessary) fill all 

countersinks in the area with PR1422B (Hat. No. 09-002). 

Install all fasteners wet with PR1422B (Mat. No. 09-002). 

Any damage to the surface protection should be repaired at the 

earliest opportunity. 

DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 6 

Printed in France 
SERVICE BULLETIN 

Operator's attention is drawn to the recommendations of Service 

Information Letter (SIL) No. 38-013, for prevention of leaks from 

the toilet service panels. 

C. DESCRIPTION 

To accomplish this Service Bulletin, it is necessary to : 

(1) Corrosion Inspection 

On the center wing bottom skin, inboard and outboard areas of rib 1 

between frames 40 and 47, do a detailed visual inspection for 

corrosion around the fasteners and on the surface of panels without 

stripping off paint. 

(a) If no corrosion is detected : 

Check condition of paint finish, touch up if protection is 

missing or damaged. 

(b1 If corrosion is detected : 

Rework corroded areas (if necessary remove the fasteners). 

Check the reworked depth and compare with the permissible 

limits. 

(2) Fatigue Inspection 

Check the reworked depth with respect to the initial thickness of 

the panel and the permissible limit of the reworked depth per area 

previously defined. 

(a) Check if the reworked depth is higher than 5 % of the initial 

thickness of the panel and less or equal to the permissible 

limit of the reworked depth per area. 

(b) Check if the reworked depth is less or equal to 5 % of the 

initial thickness of the panel. 

Cc) Check if the reworked depth is higher than the permissible 

limit of the reworked depth per area. 

DATE : Dee 04/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 7 

Printed in France 
SERVICE BULLETIN 

(3) Replace the fasteners. 

Check if the remaining panel thickness is in the permissible limits 

given for the forward and aft lower surface panels. 

(a) If the remaining minimum panel thickness is in the permissible 

Limits : 

- Install an oversize countersunk head fastener. 

(b) If the remaining minimum panel thickness is not in the 

permissible limits to install an oversize countersunk head 

fastener : 

- Install an oversize protruding head fastener. 

NOTE : The remaining minimum thickness (X1 is the panel thickness 

below the head of the fastener (Refer to Figure 5, Views A 

and B). 

(4) Sealing 

(a) Apply sealant along the external lower surface splice and 

fuselage pick-up angle. 

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 : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 8 

Printed in 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. 

Inspection 

Gain access 0.5 

Inspection 6.0 

Close-up 

TOTAL MANHOURS 

.ELAPSED TIME (HOURS) 

1.0 

7.5 

3.5 

F. MATERIAL - COST AND AVAILABILITY 

None. 

G. TOOLING - PRICE AND AVAILABILITY 

Accomplishment of this Service Bulletin entails use of the following 

tools and equipment. 

(1) Equipment and materials for inspection ; refer to NTM 51-20-13, 

51-31-05 and 51-40-13. 

I (2) Equipment and tools for repair ; refer to SRM 51-30-30, 51-30-40, 

51-30-45 and 51-31-00. 

H, WEIGHT AND BALANCE 

None. 

DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 9 

Printed in France 
SA300 

SERVICE BULLETIN 

I. REFERENCES 

Aircraft Maintenance Manual (AMM) : 12-11-28, 20-31-00, 24-00-00, 

24-41-00, 28-00-00, 28-10-00, 

28-11-14, 28-22-00 

Structural 

I 

Repair Manual (SRM) : 51-30-29, 51-30-30, 51-30-40, 

51-30-45, 51-40-11, 51-31-00, 51-40-12, 51-40-10, 51-40-20, 

51-40-21 

Service Information Letter (SIL) : 38-013 

Non Destructive Testing Manual (NDTM) : 51-20-13, Part 1 

51-31-05, Part 1 

51-40-13, Part 1 

J. PUBLICATIONS AFFECTED 

I Maintenance Planning Document (MPD) : 57-80-21 Task No. 578021-0602-1, 

C57500-01-02 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : IO 

Printed in France 
SERVICE BULLETIN 

2. ACCOMPLISHMENT INSTRUCTIONS 

A. GENERAL 

I WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE 

CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 

Cl) Preparation 

(a) De-energite the aircraft electrical network and connect the 

aircraft to ground (Refer to AWM 24-41-00 and AM\ 24-00-00, 

P. Block 3011. 

(b) Put the access platforms in position. 

(2) Job set-up 

NOTE 1 : Draining of fuel tanks is not necessary to do the 

corrosion inspection. However, if bolt removal is 

necessary, the inner and center fuel tanks must be 

defuelled and drained. 

NOTE 2 : The operations below are necessary only if the fasteners 

are removed (Refer to Para. 2.B.C3)). 

WARNING : BEFORE UNDERTAKING MAINTENANCE WORK ON THE FUEL SYSTEM, 

PERSONNEL MUST RIGOROUSLY OBSERVE THE FOLLOWING SAFETY 

PRECAUTIONS. THE DESCRIPTION OF THESE SAFETY PRECAUTIONS 

SHOULD BE READ AT THE SAME TIME AS THE SPECIAL 

INSTRUCTIONS AND SAFETY MEASURES CONCERNING SPECIFIC 

MAINTENANCE PROCEDURES AND, IN PARTICULAR, THE FOLLOWING 

OPERATIONS : 

(a) Job set-up 

1 General servicing precaution (Refer to AMM 28-00-00, 

P. Block 301). 

2 Tank defueling (Refer to ARM 28-22-00, P. Block 301). 

3 Access to fuel tanks (Refer to AMM 28-10-00, P. Block 301). 

5 Manhole cover removal (Refer to AMH 28-11-14, P. Block 401). 

------------------------------------------------------------------------------ 

MANHOLE COVER REFERENCE LOCATION BETWEEN LOCATION BETWEEN 

L WING R WING RIBS STRINGERS 

-------------------------------- ---------------------------------------------- 

541AB 641AB STA71 (rib 2) and STAl42 (rib 3) 8 and 11 

542CB 642C5 STAfl (rib 2) and STA142 (rib 3) 13 and 16 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 11 

Printed in France 
GA300 

SERVICE BULLETIN 

1. FueL tank working area (Refer to AMM 28-10-00, 

P. Block 301). 

6 Use of fLammabLe gas detection devices (Refer to 

AMM 28-10-00, P. BLock 301). 

1 Fuel tank ventilation (Refer to AMM 28-10-00, P. Block 301). 

(3) Standard procedures 

(a) If paint stripping is required (Refer to SRM 51-41-50). 

(b) To drill and deburr the holes (Refer to SRM 31-30-40). 

(c) Countersinking (Refer to SRM 51-30-45). 

Cd) Data for installation and removal fasteners 

(Refer to SRM 51-30-29 and 51-30-30). 

(e) To torque the standard threaded fasteners 

(Refer to AMM 51-31-00). 

(f) If paint coating is required (Refer to SRM 51-40-10 and 

51-40-12). 

DATE : Dee 04/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 12 

hinted in France 


G A300 

SERVICE BULLETIN 

8. INSPECTION 

An inspection program for fatigue inspection has been established in 

case of corrosion finding for which a visual check or an NDT inspection 

is recommended at different thresholds and flight cycles intervals. 

NOTE : Inspection results must be reported to Airbus Industrie 

(AI/SE-El) after completion, on the recording forms attached. 

- In case of findings, this reporting has to be made in 

accordance with Service Bulletin instructions, that is to say : 

. immediately (maximum within 48 hours) in case of damage which 

exceeds allowable or rework Limits for further action(s) 

before next flight. 

. after completion of the corrective action when damage is 

either within aLLowabLe or rework Limits, or repaired in 

accordance with Service Bulletin instructions. 

- In case of no findings, inspection record has to be sent as 

soon as maintenance check or visit report which involves 

subject Service BuLLetin has been established. 

(9) CORROSION INSPECTION 

On the center wing bottom skin, inboard and outboard areas of rib 1 

between frames 40 and 47, do a detailed visual inspection for 

corrosion around the fasteners and on the surface of panels without 

stripping off paint. 

. (a) If no corrosion is detected : 

Check condition of paint finish, touch up if necessary. 

1 If protection is missing or damaged : 

2 Apply wash primer, Mat. No. 16-020 and primer, 

Mat. No. 16-001. 

b Apply new protective coating (Refer to SRH 51-40-10 and 

51-40-12). 

Next visual inspection for corrosion in 5 years. 

2 If protection is not missing or not damaged : 

Next visual inspection for corrosion in 5 years. 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 17 

Printed in France 
GA300 

SERVICE BULLETIN 

(b) If corrosion is detected : 

For the correspondence of the different reference values used 

in this part of the inspection (W, L, Al, A2, D), refer to the 

evaluation principle of corrosion Fig. 2. These values enable 

to determine the rework conditions and also to check the 

permissible limits. 

w : Rework length in flight direction 

L : Rework length in outboard direction 

Al : Distance between two adjacent rework areas in flight 

direction 

A2 : Distance between two adjacent rework areas in outboard 

direction 

1 Remove the corrosion (Refer to SRH 51-40-11). 

Obey the rework conditions specified below. 

I REWORK CONDITIONS I 

L/2 > 41, ) 

and 1 Refer to Fig. 2 

W/2 > 40 1 I 

NOTE : If you find corrosion around the fasteners, remove 

the fasteners (Refer to SRR 51-30-29 and 51-30-30). 

2 Measure the reworked depth (D), do a Non-Destructive Test 

(NDT) (Refer to NTM 51-20-13, Part 1 or 51-40-13, Part I). 

2 Make sure that the rework is in the permissible limits 

specified below. 

I REWORK PERMISSIBLE LIMITS I 

W < 50 mm (1.968 in.) 

L < 100 mm (3.937 in.) Refer to Fig, 2 

Al > 50 mm (1.968 in.) 

A2 > not limited 

2 If the rework is not in the permissible limits : 

- Contact AIB before the next flight. 

b If the rework is in the permissible limits : 

- Continue the inspection. Refer to Para. 2.B.(2)(a). 

DATE : Dee 04/95 

REVISION No. : 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 18 

PrintedinFrance 
GA300 

SERVICE BULLETIN 

. (2). FATIGUE INSPECTION 

In this part of the inspection, the reference value is the reuorked 

depth (D) (result of corrosion inspection Para. 2.8.(l)). The 

permissible limits (5 X, d) are reference values with respect to 

the initial thickness of the panel (El. 

Permissible limit of reworked depth CD), 5 % of the initial 

thickness of the panels (E) (Refer to Table A, Fig. 3). 

Permissible Limit of reworked depth per area Cd) (Refer to Table A, 

Fig. 3). 

NOTE : According to A/C models and damaged areas, permissible 

Limits of the reworked depth are specified Table A, Fig. 3. 

Check the reworked depth CD1 with respect to the initial thickness 

of the panel (El, and the permissible limit of the reworked depth 

per area Cd) previously defined. 

(a) If the reworked depth CD) is higher than 5 % of the initial 

thickness of the panel (E) and Less or equal to the permissible 

Limit of the reworked depth per area Cd> (Refer to Table A, 

Fig. 31, i.e. : 

I S%<D=d I 

Detect presence of crack around the fasteners and on the 

surface of forward and aft lower surface panels. Do a 

Non-Destructive Test (NDT) for fatigue damage (Refer to 

NTM 51-31-05, Part I). 

1 If crack is detected : 

Contact AIB before the next flight. 

1. If no crack is detected : 

2 Apply wash primer, Mat. No. 16-020 and primer, 

Mat. No. 16-001 on countersunk heads and reworked areas. 

h Apply new protective coating (Refer to SRM 51-40-10 and 

51-40-12). 

NOTE : Replace the fasteners if they have been removed for 

the corrosion inspection (Refer to Para. 2.B.C3)). 

DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 19 

Printed in France 
SERVICE BULLETIN 

2 Inspection program 

- Next visual inspection for corrosion in 5 .years. 

- Next inspection for fatigue damage (Refer to Table B, 

Fig. 4). 

NOTE : According to A/C models and damaged area, the fatigue 

inspection program gives the thresholds and inter'vals 

(FC) applicable to the visual check or the 

Non-Destructive Test (NDT) (Refer to Table 8, 

. Fig. 4). 

(b) If the reworked depth CD) is less or equal to 5 % of the 

initial thickness of the panel (E) (Refer to Table A, Fig. 31, 

i.e. : 

I I 

Apply wash primer, Mat. No. 16-020 and primer, 

Mat. No. 16-001. 

Apply new protective coating (Refer to SRM 51-40-10 

and 51-40-12). 

NOTE : Replace the fasteners if they have been removed for 

the corrosion inspection (Refer to Para. 2.8.(3)). 

Next visual inspection for corrosion in 5 years. 

Cc> If the reworked depth CD) is higher than the permissible limit 

of the reworked depth per area Cd) (Refer to Table A, Fig. 31, 

i.e. : 

I D>d 

Contact AIB before next flight. 

DATE : Dee 04195 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 20 

Printed in France 
GA300 

SERVICE BULLETIN 

(3) Replace the fasteners. 

Replace fasteners of damaged holes when sitting is not correct 

or/and the fasteners have been removed for rework. 

The reference value is the remaining thickness of the panel (X1. 

The permissible remaining thickness varies depending on the 

fastener replacement area. 

Permissible remaining minimum thickness (X1 for the forward lower 

surface panel : 3 mm (0.118 in.). 

. 

Permissible remaining minimum thickness (X1 for the aft lower 

surface panel : 5 mm (0.196 in.). 

NOTE : The remaining minimum thickness (X1 is the panel'thickness 

below the head of the fastener (Refer to Figure 5, Views A 

and 6). 

CAUTION : BEFORE YOU DO THE NEW COUNTERSINK OR THE SPOTFACING FOR 

THE NEW FASTENER (REFER TO FIG. 51, DO A CHECK OF THE 

REMAINING THICKNESS (X) REFER TO NON DESTRUCTIVE TEST 

(NDT) (REFER TO NTM 51-20-13, PART 1 OR 51-40-13, 

PART 1). 

(a) If the remaining minimum panel thickness is in the permissible 

limits : 

- Install an oversize countersunk head fastener. 

(Refer to Fig. 5, View A1 

1 FWD LOWER SURFACE PANEL1 

Do the subsequent steps to 

fastener. 

and /I 

install an oversize countersunk head 

1 Drill and deburr the holes (Refer to SRN 51-30-40). 

1 Do the new countersink for an oversize countersunk head 

fastener (Refer to SRM 51-30-45). 

3 Do wet assembly of all parts and fasteners to be installed 

with Mat. No. 09-025 (Refer to SRN 51-40-20 and 51-40-21). 

5 Torque standard threaded fasteners (Refer to SRH 51-31-00). 

DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 21 

Printed in France 
GA300 

SERVICE BULLETIN 

2 Apply wash primer, Mat. No. 16-020 and primer, 

Mat. No. 16-001 on countersunk heads and reworked areas. 

NOTE : According to A/C models and damaged area, for each 

type of existing fastener to be replaced, refer to 

Figures 6, 7, 8 and 9 and associated tables which 

give the alternative fastener identification 

(1st oversize or 2nd oversize). 

fi Apply sealant Mat. No. 09-002 on the head of the fasteners. 

Make sure that the sealant does not come out of the skin 

(Refer to Fig. 5, View A). 

z Apply new protective coating (Refer to SRN 51-40-10 and 

51-40-121. 

(b> If the remaining minimum panel thickness is not in the 

permissible limits to install an oversize countersunk head 

fastener : 

- Install an oversize protruding head fastener. 

(Refer to Fig. 5, View B) 

Do the subsequent steps to install an oversize protruding head 

fastener. 

1 Drill and deburr the holes (Refer to SRN 51-30-40). 

2 Do a spotfacing to insure a good seating for an oversize 

protruding head fastener. 

2 Do wet assembly of all parts and fasteners to be installed 

with Mat. No. 09-025 (Refer to SRN 51-40-20 and 51-40-21). 

4 Torque standard threaded fasteners (Refer to SRN 51-31-00). 

2 Apply wash primer, Mat. No. 16-020 and primer, 

Mat. No. 16-001 on countersunk heads and reworked areas. 

NOTE : According to A/C models and damaged area, for each 

type of existing fastener to be replaced, refer to 

Figures 6, 7, 8 and 9 and associated tables which 

give the alternative fastener identification 

(1st oversize or 2nd oversize). 

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 

REVISION No. : 01 - Apr 02/99 PAGE : 22 

Printed in France 
GA300 

SERVICE BULLETIN 

6 Apply sealant Mat. No. 09-002 on the head of the fasteners. 

Make sure that the sealant does not come out of the skin 

(Refer to Fig. 5, View B). 

1 Apply new protective coating (Refer to SRM 51-40-10 and 

51-40-12). 

(c) Close-up 

1 Make sure that the work areas are clean and clear of tools 

and other items of equipment. 

2 Install the manhole covers (Refer to AMM 28-11-14, 

P. Block 401). 

3 Fill the fuel tank (Refer to AMM 12-11-28, P. Block 1). 

3 Make an inspection for leaks of the manhole covers. 

(4). Sealing 

(a) Apply a layer of sealant Mat. No. 09-002 along the external 

lower surface splice and fuselage pick-up angle. 

C. TESTS 

None. 

D I_ CLOSE-UP 

(I) Make sure that the work areas are clean and clear of tools and 

other items of equipment. 

(2) Remove the access platforms. 

(3) De-energize the aircraft electrical circuits and disconnect the 

aircraft electrical ground-connection (Refer to AMW 24-41-00 and 

AMM 24-00-00, P. Block 301). 

(4). Write in the applicable aircraft records that you have done all the 

work given in this Service Bulletin. 

DATE : 'oec 04/95 

REVISION No. : 01 - Apr 02199 

Printed in France 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 23 
SERVICE BULLETIN 

0 A 

MANHOLE 

COVER 

/ FWO LhWER 

SURFACE PANEL 

MANHOLE 

COVER 

541~S/641~~ 

AREAS TO INSPECT -A 

EXTERNAL LOWER 

SURFACE SPLICE 

Center Wing Bottom Skin Inboard and Outboard 

Areas to Be Inspected 

Figure 1 

DATE : Dee 04195 SERVICE BULLETIN No. : A300-57-0204 

REVISION Ntq. : PAGE : 24 

Printed in France 
SERVICE BULLETIN 

INBOARD AREA 

i I 

_--_I =/p-%7+++ -I- + 1 

t I \+++p,+ + I + + + + + 

LATTICE FLANGE 45 

---- 

STIFFENER 45.1 _ 

LATTICE FLANG 

STIFFENER 46.1 

---- 

I , 

!IEXTERNAL LOWER 

SURFACE SPLICE 

SECTION AA 

DATE : Dee 04195 

REVISION No. : 

AFT LOWER 

supK 

I REWORK PERMISSIBLE LIMITS I 

LEGEND : 

W: REWORK LENGTH IN FLIGHT DIRECTION 

L: REWORK LENGTH IN OUTBOARD DIRECTION 

Al: DISTANCE BETWEEN TWO ADJACENT 

REWORK AREAS IN FLIGHT DIRECTION 

A2: DISTANCE BETWEEN TWO ADJACENT 

REWORK AREAS IN OUTBOARD DIRECTION 

0: REWORKED DEPTH 

E: INITIAL THICKNESS OF THE PANEL 

Evaluation Principle of Corrosion 

Figure 2 

SERVICE BULLETIN No. : A300-57-0204 

PAGE : 25-26 

Printed in Fra~yc