AIRBUS INDUSTRIE

PRODUCTSUPPORTDIRECTORATE 1 Rond Point Naurice BELLONTE 

# @A320 31707 BLAGNACCEDEXFRANCE TeL: (33) 61-93-33-33 TeLex: AIRBU 530526 F SERVICE BULLETIN SUMMARY
This summary is for information onLy and is not approved for modification of the aircraft MODIFICATION NO: 20535KO588, 21519K1630 ATASYSTEM: 53 T I TL E: FUSELAGE- CENTERFUSELAGE- REINFORCE STRUCTUREOFBELLY FAIRING
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The test program carried out on the A320 fatigue test modeL reveaLed the folLowin in the area of the keelbeam:

- At the angle attachment between the keeLbeam and the RHand LH beLLy fairingsupport frames , rivet heads sheared off after 6000 simulated fLights and cracks were found in the angLes after 33000 simulated fLights.

- At the shear pLates between the keelbeam and the RHand LH beLLy fairing support frames at Sta x 18552.4 cracks were found in the angLe attachment after 14000 simuLated flights. This Service BuLLetin is issued as a result of those tests. It makes the foLLowin reinforcements mandatory:

- Where the beLLy fairing support frames are attached to the keelbeam, the extruded angLe brackets are to be replaced with titanium angLe brackets and fastened with HI-LOK pins and coLLars.

- Redesigned shear pLates are instaLLed with a double row riveting using HI-LOK pins and coLLars. Embodiment of this modification wilL increase the structuraL integrity of the affected components. I This modification is rendered mandatory and must be embodied before 12000 flights. EFFECTIVITY This Service BuLLetin is appLicable to these operators: AA& ACA, ADR, AFR, BAW, HP, CYP, DLH, IAC, ITF, NWA,RJA and XP. SERVICE BULLETIN/MODIFICATION TOBEACCOMPLISHED PREVIOUSLY ORSIMULTANEOUSLY None 

# I 6 DATE: Jun 25/92 REVISION NO: 2- SEPTOl/g4 SERVICE BULLETIN NO: A320-53-1014 PAGE: 1of 3

Printed inFrance

# @A320 SERVICE BULLETIN SUMMARY
REFERENCES/REPERCUSSIONS TFU: None 

### LIFELIMIT: None OEB: None 

### LINEMAINTENANCE AFFECTED: No AOT: None 

### SIL: None NATUREOFTHE

### MODIFICATION AIRCRAFT: YES EQUIPMENT: NO COMPLIANCE

I This Service Bulletin is rendered mandatory in accordance with Airworthiness Directive (Consigne de Navaigability) No. 92-201-0308.

. MANPOWER Manhours/aircraft Kit No. 531014 A01 A02 Total manhours: 288.00 48.00 ELapsed time (hours): 72.OO 24-00 

### MATERIALINFORMATION Aircraft Data 

### Angles, profile segments and associated hardware. Equipment Data None 

### APPENDICES None

IDATE: Jun 25192 

# IREVISIONNO:

### 2- SEPT01/94 SERVICEBULLETINNO:A320-53-1014 PAGE: 2of 3

Printed inFranceSERVICE BULLETIN SUMMARY



# BEFORE 1STA1753lFR40



# pJc$ AFTER TYPICAL

EXISTING ANGLE REPLACED WITH ANGLE MADE FROM TITANIUM, INSTALLED WITH HI-LOK RIVETS.

DATE: JUN 25/92 REVISION NO: SERVICE BULLETIN NO: A320-53-1014 PAGE: 

### 3of 

### 3 Printed inFranceAIRBUS 

### INDUSTRIE

PRODUCTSUPPORTDIRECTORATE 1Rond Point Maurice BELLONTE 

# GA320 31707 BLAGNACCEDEXFRANCE Tel: (33) 61-93-33-33 

### Telex: AIRBU 530526 F SERVICE BULLETIN



### MODIFICATIONNO: 

### 20535K0588,21519K1630 ATASYSTEM: 53 T I T L E: FUSELAGE- CENTERFUSELAGE- REINFORCE STRUCTUREOFBELLX 

### FAIRING 1.PLANNINGINFORMATION A. EFFECTIVITY (1) Aircraft 

### Models: 320-111, 320-211, 320-231 (2) Aircraft
Customer and 

### Fleet No. MSN Qty of Kits 531014 A01 A02 AAA001-008 ACA201-204 ADR001 AFR 001 002, 004-007, 031-033 BAW001 002-006, 007 CYP001-004 DLH 001-007 HP 620-622, 624-634 

### IAC001-012, 014-016 \ 

### ITF 001-003,

005-010 NWA301-306 RJA 001, 002 XP 001 022, 023, 024, 025, 026, 027, 029, 030 059, 068, 073, 084 043 005 007, 014, 019, 020, 021 061, 062, 063 006 008, 011, 017, 018, 039, 042 028, 035, 037, 038 069, 070, 071, 072, 078, 083, 086 052, 053, 054, 055, 064, 065, 066, 067, 076, 077, 081, 082, 091, 092 045, 046, 047, 048, 049, 050, 051, 056, 057, 058, 074, 075, 080, 089, 090 QIO, 012, 013, 016, 033,

. 036, 044, 004, 003 031, 032, 034, 040, 041, 060, 087, 088 085 8 4 1 1’ 1 8 1 1 6 4 7 14
15
9 6 2 1 Modification 20535K0588 is embodied, prior to delivery, on A/C MSN002, 003, 004, 007 and subsequent. Modification 21519K1630 is embodied, prick 

### todelivery, on A/C MSN002, 093, and subsequent. 

# I 6 DATE: Jun 25/92 

### SERVICEBULLETIN NO: A320-53-1014 

### REVISIONNO:2 - SEPTOV94 PAGE: 1of 26 PLUSSUPPLEMENTARYPAGE7A

Printed inFrance

# @A320 SERVICE BULLETIN (3) Spares None B. REASON Cl) History The test program carried out on the A320 fatigue 

### test model revealed the 

### following in the area of 

### the keelbeam:

- At 

### the angle attachment between the keeLbeam and the RHand LH beLLy fairing-support frames , rivet heads sheared off after 6000 simulated flights and cracks were found in the angLes after 33000 

### simulated flights.

- At the shear plates between the keelbeam and the RHand LH 

### beLly fairing support frames at Sta x 18552.4 , cracks were found in the angLe attachment after 14000 simulated flights. (2) Objective/Action This Service BulLetin is issued 

### as a result of those tests. 

### It makes the 

### following reinforcements mandatory:

- Where the beLLy fairing support frames are attached to the keelbeam, the extruded 

### angle brackets are to be replaced with titanium angLe brackets and fastened with 

### HI-LOK pins and 

### collars.

- Redesigned shear plates are 

### instalked with adoubLe row riveting using 

### HI-LOK pins and coLL,ars. (3) Advantages Embodiment of this modification wiLL increase the structuraL integrity of the affected components. (4) Accomplishment Timescale

I This modification is rendered mandatory and must be embodied before

12000 flights. 

### C. DESCRIPTION AccompLishment of this Service BuLLetin consists of: (I) Removing the hydrauLic components, fuel drain pipes and bleed air ducts as necessary to gain access to the modification area. 

# I DATE: Jun 25/92 REVISION NO: 2- SEPT01/94 

### SERVICE BULLETIN NO: A320-53-1014 PAGE: 2

Printed inFrance

# GA320 SERVICE BULLETIN (2) RepLacing the affected 

### angles and shear plates. (3) 

### Installing the removed components. (4) Testing the associated systems of the reinstaLled components. D

. APPROVAL

I This Service BulLetin is approved by the Direction GeneraLe de L’Aviation

Civiie FRANCECDGAC). E

. MANPOWER This Service BuLLetin may be accompiished in the foLLowing approximate manhours and 

### elapsed time: Manhours/aircraft Kit No. 531014 A01 A02 Gain access 120.00 18.00 Modification 32.00 8.00 Test 16.00 4.00 CLose-Up 120.00 18.00 

### Total manhours 288.00 48.00 ELapsed time (hours) 72.00 24.00 NOTE: This Service BuLLetin assumes that the aircraft has been placed in a maintenance status. The manhours/elapsed time estimates do not incLude preparation for the modification, nonproductive eLapsed time or administrative functions. F. MATERIAL 

### - COSTAND

### AVAILABILITY (11 Material Operators with aircraft Listed under paragraph l.A.C2) shouLd submit a purchase order quoting this Service Bulletin to:



# IDATE: Jun 25192 

### REVISION NO: 2- SEPT01/94 

### AIRBUS INDUSTRIE AIRSPARES MATERIAL SUPPORTCENTER WEG

### BEIM JAEGER 150 22335 HAMBURG GERMANY



### SERVICE BULLETIN NO: A320-53-1014 PAGE: 3
Printed inFrance

# 6A320 SERVICE BULLETIN (2) Cost and 

### Availability Kit cost (US Dollars) 

### Availability * ’
531014AOl 1045 210 531014A02 938 210 

### * Calendar days from receipt of order. NOTE: 

### Sales terms stated (cost and 

### availability) are evaluated with respect to economic conditions at the issue date of this Service 

### Bulletin. G. TOOLING - PRICE AND

### AVAILABILITY None 

### H. WEIGHTANDBALANCE Not affected 

# I I. REFERENCES

Aircraft Maintenance 

### ManualCAMM) 06-31-53, 12-12-29, 12-34-24, 20-21-12, 21-51-41, 21-52-41, 21-61-00, 21-61-52, 24-41-00, 28-13-00, 29-10-00, 29-12-42, 29-12-46, 29-13-00, 29-13-42, 29-14-00, 29-23-00, 29-24-51, 36-12-00,.36-22-00, 

# I 36-22-18 

### Consumable Materials List CCML) 

# I Structural Repair Manual CSRM) 51-42-11, 51-44-00, 51-76-11 

# I J. PUBLICATIONS AFFECTED

None



# IDATE: Jun 25192 SERVICE BULLETIN NO: A320-53-1014 

### REVISION NO: 

### 1- MAY26/93 PAGE: 4

Printed inFrance

# @A320 SERVICE BULLETIN
2. ACCOMPLISHMENT 

### INSTRUCTIONS A. GENERAL



# I Cl) Preparation

WARNING: OBEYTHEHYDRAULIC SAFETY PRECAUTIONS.

MAKESURETHATTHETRAVEL RANGESOFTHEFLIGHT CONTROLSURFACES ARECLEARBEFOREYOUPRESSURIZE/DEPRESSURIZE THE HYDRAULIC SYSTEM. MAKESURETHATTHE LANDING GEARSAFETY-LOCKS ANDTHE WHEELCHOCKSARE

### INPOSITION. PUTTHESAFETY DEVICES ANDTHEWARNING

### NOTICESINPOSITION BEFOREYOUSTARTATASKONORNEAR:
- THE

### FLIGHTCONTROLS
- THE FLIGHT CONTROLSURFACES
- THE LANDING GEARANDTHE RELATED DOORS
- ANYCOMPONENTTHATMOVES. MAKESURETHAT THEPNEUMATIC SYSTEM

### IS DEPRESSURIZED BEFOREYOU STARTWORKONTHEPNEUMATIC SYSTEM. MAKESURETHAT YOUHAVETHECORRECTFIRE 

### FIGHTINGEQUIPMENT AVAILABLE BEFOREYOUSTART ANYTASKONTHE FUEL SYSTEM. OBEYTHE FUEL SAFETYPROCEDURES. To accompLish this Service BuLletin it is necessary to: (a) ELectricaLLy ground the aircraft (Ref. AMM12-34-24, P. BLock 201). (b) De-energite the aircraft electricaL circuits (Ref. AMM24-41-00). (c) Put an access platform at the aft belly fairing, Left and right side. (d) Put the warning notices in position:

- in the cockpit on the Engine Control Panel 115VU to teLL persons not to start the engine(s),
- in the cockpit on the AIR CONDOverhead ControL Panel 30VU to teLL persons not to push in the APUBLEED pushbutton switch,
- on the HPground connector to tell persons not to pressurize the pneumatic system. AppLicabLe to A/C MSN005 and 006 onLy: Ce) Remove the paneLs 191KB, 195AB, 19588, 192KB, 19688 and 196AB.



# IDATE: Jun 25/92 REVISION NO: 1- MAY26/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 5
Printed inFrance

# QA320 SERVICE BULLETIN 

# I (f) Open, safety and tag these circuit breakers:
_____-_------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ---------------------------- --------------------_________________^__----------- 121vu HYDRAULIC/HYD POWER/B/WARNANDCTL 27026 J N31 121vu HYDRAULIC/HYD POWER/Y 38036X N30 123VU BHYD/ELEC/PUMP 270165 AB09 123VU YHYD/ELEC/PUMP 3802GX AB06 123Vu YHYD/ELEC PUMPNORM 3801GX AB03 122vu AIR COND/PACK TE#P/CTL SYS1/1/115VAC 1HH x22 122vu AIR COND/PACK TEMP/CTL SYS1/1/28VDC 3HH x21 122vu AIR COND/PACK TEMPCTL SYS2/1/28VDC 4HH Y19 122vu AIR COND/PACK fEMP CTL SYS2/1/115VAC 2HH Y18 49vu AIR BLEED/ENG l/CTL 3HAl D12 49vu AIR BLEED/ENG l/MONG 2HAl Dll 122vu AIR BLEED/ENG 2/CTL 3HA2 223 122vu AIR BLEED/ENG 2/MONG 2HA2 222 122vu AIR BLEED/X FEEDVALVE/BAT 2HV 221 122vu AIR BLEED/X FEEDVALVE/NORM 1HV 220

(g) Depressurite the BLue hydrauLic system (Ref. AMM29-10-00, P. BLock 201). (h) Depressurize the reservoir of the BLue hydrauLic system (Ref. AMM29-13-00, P. BLock 201). (i) Depressurize the YeLLow hydraulic system (Ref. AMM29-10-00, P. BLock 201). Cj) Depressurite the reservoir of the YeLLow hydraulic system (Ref. AMM29-14-00, P. Block 201). (k) Put the warning notices in position to teLL persons not to pressurize the BLue and the YeLLow hydrauLic systems:

- in the cockpit on the hydraulic section 40VU of the overhead paneL,
- in the ground service paneL of the Blue and YeLLow hydraulic systems. CL) Disconnect the isoLation coupLing of the Green/YeLLow Power Transfer Unit (PTU) 1088GM (Ref. AMM29-23-00, P. Block 212).



# IDATE: Jun 25192 REVISION NO: 1- MAY26/g3 SERVICE BULLETIN NO: A320-53-1014 PAGE: 6

Printed inFrance

# ~22 A320 SERVICE BULLETIN



# I Applicable to all A/C, except A/C MSN005 and 006:



### Ce) Remove the 

### panels 195AB, 196AB, 19158, 14i'AB, 147BB and 148DB. (f) Open, safety and tag these circuit breakers: ^_--_____-_____----_----------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------_------------------------------------------------------------------ 121vu HYDRAULIC/SOL VALVES/G/Y/PTU 1801GL N34 12lVU HYDRAULIC/HYD PUMPENGl/CTL IfO?GK N35 121vu HYDRAULIC/HYD/PUMP ENGl/MONG 1702GK R34

(g) Depressirize the Green hydraulic system (Ref. AMM29-10-00, P. 

### Block 201). 

### Ch)Put the warning notices in position 

### to tell persons not to pressurize the Green hydraulic system:

- in the cockpit on the hydraulic section 40VU of the overhead panel,
- in the ground service 

### .panel of the 

### Blue and 

### Yellow hydraulic systems. ci) Disconnect the isoLation 

### coupling of the 

### Green/Yellow Power Transfer Unit CPTU) 1088GM (Ref. AMM29-23-00, P. BLock 212). (2) Standard Procedures (a) You must refer 

### to the 

### Consumable Materials List CCML) for specification of the materials (Mat. No.) that this Service 

### Bulletin gives. Cb) The rivet 

### hole tolerance is +0.1 mm

### C+0.004 in.) 

### unless the text gives other information. WARNING: OBEYTHEMAINUFACTIJRER'S INSTRUCTIONS WHENYOUUSECLEANING

AGENTS(MAT. NO. 11-003 OR11-004). THECLEANING AGENTS(MAT. NO. II-003 AND 11-004) AREDANGEROUS. 

### Cc) Clean all mating surfaces and 

### drilled holes with the cleaning agent (Mat. No. 11-003 or 11-004). Cd) After you 

### drill the 

### holes, remove the burrs and 

### apply the wash primer (Mat. No. 16-020) and the polyurethane primer (Mat. No. 16-001). (e) Refer to SRM51-44-00 for the 

### hole sizes of Hi-Lok fasteners. WARNING: SEALANTS AREDANGEROUS. Cf) Wet instalL the HI-LOK pins with the sealant (Mat. No. 09-013) (Ref. SRM51-76-11). 

# I DATE: Jun 25/92 REVISION NO: 1- MAY26/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 7
Printed inFranceSERVICE BULLETIN Cg) Apply the sealant <Mat. No. 09-016) to the mating surfaces before you 

### install new 

### structural items (Ref. SRM51-76-11). <h1 Apply the 

### sealant (Mat. No. 09-025) to 

### all structure surfaces where you install components. (i) Apply the zinc chromate putty (Mat. No. 05-002) to the threaded fasteners before 

### you install them (Ref. SRM51-76-11). Cj> After 

### you install the rivets, you must 

### apply the polyurethane primer (Mat. No. 16-001) and the polyurethane top coat (Mat. No. 16-002) (Ref. SRM51-76-11). (k) Tag the parts you want to keep and make a note of their locations. This 

### will make the installation easier. 

### Cl) For Station/Frame (STA/FR) identification refer to AMM06-31-53, P. Block 001. 

### (m) InstaLl the hydraulic tubes with the hydraulic fLuid (Mat. No. 02-003) 

### as a lubricant. (n) Mark each torque-tightened connection with the polyurethane top coat (Mat. No. 16-002). 

### (01 Apply the sealant (Mat. No. 09-025) to aLL structure surfaces where hydraulic components 

### are installed. Cp) Put containers beLow the hydrauLic connections to 

### collect the hydrauLic fluid. (q) Put bianking covers on the open ends of the tubes. (r) For the torque 

### values refer to AMM20-21-12. (3) Removal of Components (for access only) NOTE: Keep 

### all components for the 

### installation in Para. C. 

### Cal Remove the 

### hydraulic tubes as necessary to gain access to the modification area. Cb) Disconnect and remove the tubes of the center-tank 

### external ventilating-system as necessary.



# IDATE: Jun 25192 

### REVISION NO: 1- WY Z/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 7A

Printed inFranceSERVICE BULLETIN Applicable to A/C MSN005 and 006 only: Cc) Remove these hydraulic components:

- the Electric Pump C3075GX) of the 

### Yellow hydraulic system (Ref. AMM29-24-51, P. 

### Block 4011,
- the 

### Yellow Power Accumulator (3070GM) (Ref. AMM29-13-42, P. 

### Block 4011,


### - the 

### Blue Power Accumulator C2070GM) (Ref. AMM29-12-42, P. Block 401),
- the Pulsation Dampener C2092GM) of the Blue hydraulic system (Ref. AMM29-12-46, P. Block 4011, (d) Between FR40 and FR41 remove the APUbleed-air duct. Refer To Figure 1 CAUTION: TAKECARENOTTODAMAGETHESENSING ELEMENTS. 1 Disconnect the Overheat Sensing Element 60HF (Ref. AMM36-22-18, P. Block 401, Worksteps 3.A. thru G). 2 Unlock the safety catch 

### at the 

### clamp, item 16, and remove 

### the clamp. 3 Remove the insulation muff, item 11. 4 Remove the bolts, item 12, the washers, item 13, and the nuts, item 14. 

### 2 Remove the 

### bleed air duct, item 15. *NOTE: 

### If you remove the air 

### seal O-rings, make a note of their positions. 6 Put caps on the open duct ends.



# I DATE: Jun 25/92 REVISION NO: 1- MAY26/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 8

Printed inFranceSERVICE BULLETIN

I STAl669/FR38



## w I‘f -*

Removal/Installation of Bleed Air Duct between FR40 and FR41 Figure 1 DATE: JUN 25/92 SERVICE BULLETIN NO: A320-53-1014 REVISION NO: PAGE: 9 Printed inFrance

# @A320 SERVICE BULLETIN (e) Remove the 

### left ram air 

### outlet. Refer to Figure 2 1 Disconnect the Left ram air 

### outlet from the fan plenum chamber (Ref. AMM21-51-41, P. 

### Block 401, Workstep 3.S.) 2 Disconnect 

### the electrical connector from the air outlet fLapactuator 9HH (Ref. AMM21-61-52, P. 

### Block 401, Workstep 3.A.). 3 Support the ram air 

### outlet and remove: 

### 9 screws, item 4, 9washers, item 5, 1

### bolt, item 6, 1washer, item 7, 

### 1nut, item 8, 

### 12 bolts, item 9, 12 washers, item 10. 4 Remove the ram air outlet, item 1, and the rubber 

### seal, item 3.



# IDATE: Jun 25/92 REVISION NO: 1- wy 26/9x 

### SERVICE BULLETIN NO: A320-53-1014 PAGE: IO

Printed inFrance@

# A320
SERVICE BULLETIN

RemovaL/InstaLLation of the Left RamAir Outlet DATE: JTJN25/92 Figure 2 REVISION NO: SERVICE BULLETIN NO: A320-53-1014 PAGE: 11 PrintedinFranceSERVICE BULLETIN 

# -I B. MODIFICATION NOTE: The item numbers in brackets refer to the parts which you do not use again. 

### All other parts are kept. AppLicabLe to Kit 531014 A01 Refer to Figure 3 (11 Make the connection stronger between the keeLbeam and the traverse webs at STA1782 and STA1855. (a) Remove the connecting angles between the keeLbeam and the traverse webs at STA1782 and STA1855. 1 Remove the rivets from the angles, items Cl81 and (19). 2 Discard 

### the angles, items (18) and (19). 2 Retain the bracket, item 30. <b) InstaLL the new angLes (Ref. SRM51-76-11). 1 Transfer drill the rivet hoLes from the keelbeam and the traverse web to the new angles, items 18 and 19. 

### 2 InstaLL the new angLes D5337060121295, item 18, and D5337060121495, item 19, and the retained bracket, item 30, with: 

### 45HI-LOKpins 

### 3HI-LOKpins 48 coLLars 

### 22HI-LOKpins 28 HI-LOK pins 6 HI-LOK pins 

### 2

### HI-LOKpins 58 coLLars



# IDATE: Jun 

### 25/92 

### REVISIONNO:1- MAY26/93 DANS-6-3, item 23, DANS-6-4, item 24, NSA5075-6, item 17, DANS-6-5, item 25, DANS-6-6, item 26, DANS-6-8, item 28, DANS-6-9, item 29, HL79-6, item 22.

SERVICE BULLETIN NO: 

### A320-53-1014 PAGE: 12

Printed inFrance

# @A320 SERVICE BULLETIN Applicable to Kit 531014AO2 (2) Make the connection stronger between the structurak box below the 

### keelbeam and the traverse web at 

### STA1855. Refer to Figure 4, Sheet 1of 2 Ca) Remove the shear 

### plates between the structural box below the keelbeam and the traverse.web at STA1855. 1 Remove the rivets, item (33). 1 Remove and keep the screws, item 34, and the washers, item 35. 3 Remove the traverse, item (421, the shear 

### plates, item (311 and (321, and the 

### angles, item (44). Cb) 

### InstalL the new 

### shear plates. Refer to Figure 4, Sheet 2of 2 NOTE: The 

### newstructural components, which you 

### instaLl have pilot 

### holes. Match 

### drill and instaLL Hi-Lok fasteners in accordance with SRM51-44-00. 

### Install the anchor nuts MS21059L3, item 41, with the rivets DIN65399-2404CF, 

### item 40, at the shear plates. 

### Install 14 rivets NAS1097AD5-4, item 33. AppLicabLe to the rivets 

### only (6 per side), which you install at the. keelbeam: These rivets are for 

### closing the Last rivet row onLy and do not fuLfiLL any stress requirements. To prevent any contact with the shear 

### plates, item 31 and item 32, and the 

### angles, item 44, instaLL the rivets as doubLe countersunk rivets. Countersink the rivet holes on the inboard face of the 

### keelbeam in accordance with standard procedures. Countersink the 

### rivet holes on the outboard face of the 

### keelbeam in accordance with the standard procedures. 

### InstaLL the rivets from the inboard face of the keeLbeam and microshave the rivet heads 

### flush with the keeLbeam surface. ‘.

. Put the Left shear 

### plate D5337150820200, item 32, and the right shear 

### plate D5337150820400, item 31, in position. Transfer drill the rivet 

### holes from the shear 

### plates, items 31 and 32, to 

### the structural box-traverses. 

# I DATE: 

### Jun 25/92 REVISION NO: 2-‘SEPT01/94 

### SERVICE BULLETIN NO\ A320-53-1014 PAGE: 15
Printed inFrance

# @A320 SERVICE BULLETIN 

### 3Install the Left shear 

### plate, item 32, and the right shear 

### plate, item 31, with the 

### angle D5337150820600, item 44, with: these HI-LOK pins: DANS-6-2, item 37, DANS-6-3, item 36, DANS-6-4, item 38, and the 

### collars NSA5075-6, item 39. 

### 4Install the traverse D5337150800200, item 42, with the screws, item 34, and the washers, item 35.



# IDATE: Jun 25/92 REVISION NO: i - MAY26/93 

### SERVICEBULLETINNO:A320-53-1014 PAGE: 16

Printed inFrance

# @A320 SERVICE BULLETIN
C. INSTALLATION OFCGMPONENTSANDTEST (removed for access only] Cl) Install the components that you removed to gain access to the modification area. (a) Install the hydrauLic tubes in the position that you noted before removal. Cb) Install the tubes of the center-tank external ventilating system. Applicable to A/C MSN005 and 006 only: cc) Install these hydraulic components:

- the Pulsation Dampener (2092GM) of the Blue Hydraulic System (Ref. AMM29-12-46, P. Block 4011,

- the Blue Power Accumulator (2070GM) (Ref. ANN29-12-42, P. Block 4011,

- the Yellow Power Accumulator C3070GM) (Ref. ARM29-13-42, P. Block 401),

- the Electric Pump (30756X) of the Yellow hydraulic system (Ref. AMM29-54-51, P. Block 4011, Cd) Between FR40 and FR41 install the APUbleed-air duct. to Figure 1 Remove the caps from the duct ends. Put the bleed air duct, item 15, in position. NOTE: If the air seal O-rings are dry, apply grease (Mat. No. 04-017). InstaLl the bolts, item 12, the washers, item 13, and the nuts, item 14. InstaLl the insulation muff, item 11. Install the clamp, item 16, and secure it with the safety catch. Connect the Overheat Sensing Element 60HF (Ref. AMM36-22-18, P. Block 401, Para. 4.E. thru J.I. 

# IDATE: Jun 25/92 REVISION NO: 1- MAY26/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 21

Printed inFrance

# 9A320 SERVICE BULLETIN (e) Install the Left ram air outlet. Refer to Figure 2 1 Support the Left ram air outlet, item 1, and instaLL the rubber seaL, item 3, with: 12 washers, item 10, 12 bolts, item 9, 9 washers, item 5, 9 screws, item 4, 1 bolt, item 6, 1washer, item 7, 1 nut, item 8. 

### 2 Connect the 

### electricaL connector to the air outLet 

### flap-actuator - 9HH (Ref. AMM21-61-52, P. Block 401, Workstep 3.F.). 3 Connect 

### the left ram air 

### outlet to the fan plenum chamber (Ref. AMM21-52-41, P. BLock 401, Paras 3.N. and P-1. (21 Do a test of the components which you installed and the reLated systems. 

# I Applicable to A/C MSN005 and 006 

### only:

Ca) Energite the aircraft electricaL circuits (Ref. AMM24-41-00). (b) Remove the safety cLips and tags and close these circuit breakers:

------------------------------------------------------------------------------- PANEL SERVICE IDENT, LOCATION ----^-------------------------------------------------------------------------- 123VU YHYD/ELEC/PUMP 38026X ABO6 123VU .YHY.D/ELEC PUMPNORM 3801GX AB03 122vu 

### AIR COND/PACK TEMP/CTL SYS1/1/115VAC lHH x22 122vu 

### AIR COND/PACK TEMP/CTL SYS1/1/28VDC 3HH x21 122vu 

### AIR COND/PACK TEMPCTL SYS2/1/28VDC 4HH Y19 122vu AIR COND/PACK TEMPCTL SYS2/1/115VAC 2HH Y18 49vu AIR BLEED/ENG l/CTL 3HAl 012 49vu 

### AIR BLEED/ENG l/MONG 2HA1 Dll 122vu AIR BLEEDlENt 2/CTL 3HA2 223 122vu AIR BLEED/ENG 2/MONG 2HA2 z22 122vu AIR BLEED/X FEEDVALVE/BAT 2HV 221 122vu AIR BLEED/X FEEDVALVE/NORM 1HV z20

I (cl Remove the warning notices.

(d) Do the test of the PuLsation Dampener C2092GM) of the BLue hydrauLic system (Ref. AMM29-12-46, P. Block 401. I Ce) Dothe test of the BLue Power Accumulator (2070GM) (Ref. AMM29-12-42,

P. BLock 401). 

# I DATE: Jun 25/92 REVISION NO: 1- MAY26193 SERVICE BULLETIN NO: A320-53-1014 PAGE: 22

# @A320 SERVICE BULLETIN (f) Do the teat of the 

### Yellow Power Accumulator (307OGM) (Ref. AMM29-13-42, P. Block 401). (g) Do the test of the Electric Pump (30756X) of the Yellow hydraulic system (Ref. AMM

### 29-24-51, P. 

### Block 401). Ch) Look at the connections of the hydraulic tubes that you installed. Make sure that there are no 

### leaks. Ci) Dothe test of the Center-Tank 

### External Ventilating-System (Ref. AMM28-13-00, P. Block 501). 

### Cj1 Dothe 

### operational text of the APUBLeed-Air 

### Supply and 

### Crossbleed System (Ref. AMM36-12-00, P. 

### Block 501). Ck) Dothe 

### operational test of the Overheat Detection System (Ref. AMM36-22-00, P. 

### Block 501). 

### (1) Do the operational test of the Air-Conditioning Pack-Temperature Control-System (Ref. AMM21-61-00, P. BLock 501). ApplicabLe to aLL A/C, except A/C MSN005 and 006: (a) Energize the aircraft electrical circuits (Ref. AMM24-41-00). 

### (b) Remove the safety clips and tags and 

### close these circuit breakers:

------------------------------------------------------------------------------- PANEL 

### SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 121vu HYDRAULIC/SOL VALVES/G/Y/PTU 

### 1801Gi N34 121vu HYDRAULIC/G HYD/PUMP ENGl/CTL 1701GK R35 121vu HYDRAULIC/G HYD/PUMP ENGI/MONG 1702GK R34

cc) Remove the warning notices. Cd1 Pressurize the Green hydraulic system (Ref. AMM29-10-00, P. BLock 201). (e) Look at the connections of the hydraulic tubes that you 

### installed. Make sure that there are no 

### leaks. Cf) Do the test of the Center-Tank External Ventilating-System (Ref. AMM28-13-00, P. Block 501). D

. CLOSE-UP (I) Make sure that the 

### fluid LeveLs in the reservoirs of the Green and 

### Yellow hydraulic systems are correct. Add fluid as necessary (Ref. AMM12-12-29, P. 

### Block 301). 

# I DATE: Jun 25192 

### SERVICE BULLETIN NO: A320-53-1014 

### REVISION NO: 

### I - MAY26/93 PAGE: 23

Printed inFrance

# @A320 SERVICE BULLETIN (2) Remove the containers from 

### below the hydraulic connections. (3) Make sure that the work area is 

### clean and clear of 

### tools and other items. AppLicable to A/C MSN005 and 006 only: 

### (4) Install the panels 19IKB, 195AB, 19588, 192KB, 196BB and 196AB. AppLicable to 

### all A/C, except A/C MSN005 and 006: 

### (4) InstalL the panels 195AB, 196AB, 19lJB, 147AB, 14788 and 148DB. AppLi 

### cable to all A/C: 

### (5) Remove 

### the access 

### platforms. E. DOCUMENTATION Record the accomplishment of this Service Bulletin in the relevant aircraft technical records.



# IDATE: Jun 25/92 REVISION NO: I - MAY26/93 SERVICE BULLETIN NO: A320-53-1014 PAGE: 24
Printed inFrance3. MATERIAL INFORMATION

Basis for the following A. LIST OFCOMPONENTS

ITEM NEWP/N SERVICE BULLETIN

material data is per aircraft.

QTY PERKIT 531014A01 DESIGNATION OLDP/N REMARKS ______--__-------------------------- 18 (18) D5337060121295 2 19 (19) D5337060121495 2 23 DAN5-6-3 45 24 DANS-6-4 3 25 DANS-6-5 22 26 DAN5-6-6 28 17 NSAS0?5-6 48 28 DANS-6-8 6 29 DAN5-6-9 2 22 HL?9-6 58 Angle Angle Hi-Lok Pin Hi-Lok Pin HI-LOK Pin HI-LOK Pin Co1lar HI-LOK Pin HI-LOK Pin CoLlar D533?0601200/201

D533?0601202/203

QTY ‘PERKIT ITEM NEWP/N 531014A02 DESIGNATION OLDP/N REMARKS --^---------------------- -----------------------------------------------------~--- 32 (32) D5337150820200 1 Shear Plate D5337152120000 31 (31) D5337150820400 1 Shear PLate D5337152120200 44 (44) D5337150820600 2 AngLe D5337168620000 42 (42) D5337150800200 1 Traverse D5337152800000 37 DANS-6-2 41 HI-LOK Pin 36 DAN+6-3 17 HI-LOK Pin 38 DAN5-6-4 3 HI-LOK Pin I 40 33 NAS109?ADS-4

DIN65399-2404CF 14 8 Rivet 41 MS21059L3 4 Anchor Nut 39 NSASO?S-6 63 Collar



# I DATE: Jun 25192 SERVICE BULLETIN NO: A320-53-1014 REVISION NO: 2-SEPT01/94 PAGE: 25

Printed inFranceSERVICE BULLETIN

8. LIST OFMATERIALS - OPERATORSUPPLIED REFERENCE DESIGNATION CHL QTYPERA/C ---------------------------- ------------------------------------------- Hydraulic Fluid Mat. No. 02-003 As required Grease High Temperature Mat. No. 94-017 As required Zinc Chromate Putty Mat. No. OS-002 As required Sealant Hat. No. 09-013 As required Sealant Hat. No. 09-016 As required SeaLant Mat. No. 09-025 As required CLeaning Agent Mat. No. 11-003 As required Cleaning Agent Hat. No. 11-004 As required Polyurethane Primer Mat. No. 16-001 As required Pblyurethane Top Coat Mat. Nb

. 16-002 As required Wash Primer Mat; No. 16-020 As required
C. PARTSTOBEREIDENTIFIED BYOPERATOR None

DATE: JuN 25/92 REVISION NO: ,

SERVICE BULLETIN NO: A320-53-1014 PAGE: 26 Printed inFranceAIRBUS INDUSTRIE

PRODUCTSUPPORTDIRECTORATE 1Rond Point Maurice BELLONTE 

# GA320 31707 BLAGNACCEDEXFRANCE SERVICE BULLETIN Tel: (33) 61-93-33-33 REVISION TRANSMITTAL SHEET TeLex: AIRBU 530526 F MODIFICATION NO: 20535KO588, 21519K1630 ATASYSTEM: 53 TITLE : FUSELAGE- CENTERFUSELAGE- REINFORCE STRUCTUREOFBELLY FAIRING Herewith Revision No. 2of Service BuLLetin A320-53-7014. NOADDITIONAL WORKIS REQUIRED BYTHIS REVISION. REASON This Revision is issued to revise para. Modification, concerning Kit 531014A02, and to revise the information given for the compliance and the accomplishment timescale. CHANGES Summary:

- Page 1of 3 Para. REASON- Accomplishment timescale revised. Text shift from page 2 of 3
- Page 2of 3 Text shift to page 1of 3. Para. COMPLIANCE - Statement revised. Service BuLletin:

- Page I of 26 Revision No. updated.
- Page 2 Para. REASON- AccompLishmerit timescaLe revised.
- Page 3 Para. I.D. - ApprovaL statement revised. Para. 1 F. - Address revised.
- Page 15 Para. 2.B.(2)Cb)z - Installation procedure revised.
- Page 19/20 ILlustration - Item 43 deleted.
- Page 25 Para. 3.A. - List of components revised. FILING INSTRUCTIONS

- Replace Summary pages 1of 3 and 2 of 3.
- Replace Service BuLletin pages 1of 26, 2, 3, 15, 19120 and 25.
- FiLe this Revision TransmittaL Sheet in front of this Service Bulletin. REVISION SEQUENCE Original: Jun 25/92 Revision: 1- May 26/93 Revision: 2 - SEpT01194

SERVICE BULLETIN NO: A320-53-1014 PAGE: 1of 1
Printed inGance