AIRBUS INDUSTRIE 

PRODUCT SUPPORT DIRECTORATE 

1 Rond Point Naurice BELLONTE @ A320 

31707 BLAGNAC CEDEX FRANCE 

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 ATA SYSTEM: 53 

T I T L E : FUSELAGE - CENTER FUSELAGE - REINFORCE STRUCTURE OF BELLY 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 RH and 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 RH and 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 TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY 

None 

I 6 DATE: Jun 25/92 

REVISION NO: 2 - SEPTOl/g4 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 1 of 3 

Printed in France 
@ A320 

SERVICE BULLETIN 

SUMMARY 

REFERENCES/REPERCUSSIONS 

TFU: None LIFE LIMIT: None 

OEB: None LINE MAINTENANCE AFFECTED: No 

AOT: None 

SIL: None 

NATURE OF THE 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 

MATERIAL INFORMATION 

Aircraft Data 

Angles, profile segments and associated hardware. 

Equipment Data 

None 

APPENDICES 

None 

IDATE: Jun 25192 

I REVISION NO: 2 - SEPT01/94 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 2 of 3 

Printed in France 
SERVICE BULLETIN 

SUMMARY 

BEFORE 1 STA1753lFR40 

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: 3 of 3 

Printed in France 
AIRBUS INDUSTRIE 

PRODUCT SUPPORT DIRECTORATE 

1 Rond Point Maurice BELLONTE GA320 

31707 BLAGNAC CEDEX FRANCE 

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

Telex: AIRBU 530526 F 

SERVICE BULLETIN 

MODIFICATION NO: 20535K0588, 21519K1630 ATA SYSTEM: 53 

T I T L E : FUSELAGE - CENTER FUSELAGE - REINFORCE STRUCTURE OF BELLX FAIRING 

1. PLANNING INFORMATION 

A. EFFECTIVITY 

(1) Aircraft Models: 320-111, 320-211, 320-231 

(2) Aircraft 

Customer and 

Fleet No. 

MSN Qty of Kits 

531014 

A01 A02 

AAA 001-008 

ACA 201-204 

ADR 001 

AFR 001 

002, 004-007, 

031-033 

BAW 001 

002-006, 

007 

CYP 001-004 

DLH 001-007 

HP 620-622, 

624-634 

IAC 001-012, 014-016 

\ ITF 001-003, 

005-010 

NWA 301-306 

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 MSN 002, 003, 004, 

007 and subsequent. 

Modification 21519K1630 is embodied, prick to delivery, on A/C MSN 002, 093, and 

subsequent. 

I 6 DATE: Jun 25/92 SERVICE BULLETIN NO: A320-53-1014 

REVISION NO: 2 - SEPTOV94 PAGE: 1 of 26 

PLUS SUPPLEMENTARY PAGE 7A 

Printed in France 
@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 RH and 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 RH and 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 a doubLe 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 in France 
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 FRANCE CDGAC). 

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 - COST AND AVAILABILITY 

(11 Material 

Operators with aircraft Listed under paragraph l.A.C2) shouLd 

submit a purchase order quoting this Service Bulletin to: 

I DATE: Jun 25192 

REVISION NO: 2 - SEPT01/94 

AIRBUS INDUSTRIE 

AIRSPARES 

MATERIAL SUPPORT CENTER 

WEG BEIM JAEGER 150 

22335 HAMBURG 

GERMANY 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 3 

Printed in France 
6 A320 

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. WEIGHT AND BALANCE 

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 

I DATE: Jun 25192 SERVICE BULLETIN NO: A320-53-1014 

REVISION NO: 1 - MAY 26/93 PAGE: 4 

Printed in France 
@A320 

SERVICE BULLETIN 

2. ACCOMPLISHMENT INSTRUCTIONS 

A. GENERAL 

I 

Cl) Preparation 

WARNING: OBEY THE HYDRAULIC SAFETY PRECAUTIONS. 

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES 

ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE THE HYDRAULIC 

SYSTEM. MAKE SURE THAT THE LANDING GEAR SAFETY-LOCKS AND THE 

WHEEL CHOCKS ARE IN POSITION. 

PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION 

BEFORE YOU START A TASK ON OR NEAR: 

- THE FLIGHT CONTROLS 

- THE FLIGHT CONTROL SURFACES 

- THE LANDING GEAR AND THE RELATED DOORS 

- ANY COMPONENT THAT MOVES. 

MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU 

START WORK ON THE PNEUMATIC SYSTEM. 

MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT 

AVAILABLE BEFORE YOU START ANY TASK ON THE FUEL SYSTEM. 

OBEY THE FUEL SAFETY PROCEDURES. 

To accompLish this Service BuLletin it is necessary to: 

(a) ELectricaLLy ground the aircraft (Ref. AMM 12-34-24, P. BLock 201). 

(b) De-energite the aircraft electricaL circuits (Ref. AMM 24-41-00). 

(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 COND Overhead ControL Panel 30VU to teLL 

persons not to push in the APU BLEED pushbutton switch, 

- on the HP ground connector to tell persons not to pressurize the 

pneumatic system. 

AppLicabLe to A/C MSN 005 and 006 onLy: 

Ce) Remove the paneLs 191KB, 195AB, 19588, 192KB, 19688 and 196AB. 

I DATE: Jun 25/92 

REVISION NO: 1 - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 5 

Printed in France 
QA320 

SERVICE BULLETIN 

I (f) Open, safety and tag these circuit breakers: 

_____-_------------------------------------------------------------------------ 

PANEL SERVICE IDENT. LOCATION 

---------------------------- --------------------_________________^__----------- 

121vu HYDRAULIC/HYD POWER/B/WARN AND CTL 27026 J N31 

121vu HYDRAULIC/HYD POWER/Y 38036X N30 

123VU B HYD/ELEC/PUMP 270165 AB09 

123VU Y HYD/ELEC/PUMP 3802GX AB06 

123Vu Y HYD/ELEC PUMP NORM 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 TEMP CTL 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 FEED VALVE/BAT 2HV 221 

122vu AIR BLEED/X FEED VALVE/NORM 1HV 220 

(g) Depressurite the BLue hydrauLic system (Ref. AMM 29-10-00, 

P. BLock 201). 

(h) Depressurize the reservoir of the BLue hydrauLic system 

(Ref. AMM 29-13-00, P. BLock 201). 

(i) Depressurize the YeLLow hydraulic system (Ref. AMM 29-10-00, 

P. BLock 201). 

Cj) Depressurite the reservoir of the YeLLow hydraulic system 

(Ref. AMM 29-14-00, 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. AMM 29-23-00, P. Block 212). 

I DATE: Jun 25192 

REVISION NO: 1 - MAY 26/g3 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 6 

Printed in France 
~22 A320 

SERVICE BULLETIN 

I 

Applicable to all A/C, except A/C MSN 005 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 PUMP ENGl/CTL IfO?GK N35 

121vu HYDRAULIC/HYD/PUMP ENGl/MONG 1702GK R34 

(g) Depressirize the Green hydraulic system (Ref. AMM 29-10-00, 

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. AMM 29-23-00, 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: OBEY THE MAINUFACTIJRER'S INSTRUCTIONS WHEN YOU USE CLEANING 

AGENTS (MAT. NO. 11-003 OR 11-004). THE CLEANING AGENTS (MAT. NO. 

II-003 AND 11-004) ARE DANGEROUS. 

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 SRM 51-44-00 for the hole sizes of Hi-Lok fasteners. 

WARNING: SEALANTS ARE DANGEROUS. 

Cf) Wet instalL the HI-LOK pins with the sealant (Mat. No. 09-013) 

(Ref. SRM 51-76-11). 

I DATE: Jun 25/92 

REVISION NO: 1 - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 7 

Printed in France 
SERVICE BULLETIN 

Cg) Apply the sealant <Mat. No. 09-016) to the mating surfaces before you 

install new structural items (Ref. SRM 51-76-11). 

<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. SRM 51-76-11). 

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. SRM 51-76-11). 

(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 AMM 06-31-53, 

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 AMM 20-21-12. 

(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. 

I DATE: Jun 25192 

REVISION NO: 1 - WY Z/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 7A 

Printed in France 
SERVICE BULLETIN 

Applicable to A/C MSN 005 and 006 only: 

Cc) Remove these hydraulic components: 

- the Electric Pump C3075GX) of the Yellow hydraulic system 

(Ref. AMM 29-24-51, P. Block 4011, 

- the Yellow Power Accumulator (3070GM) (Ref. AMM 29-13-42, 

P. Block 4011, 

- the Blue Power Accumulator C2070GM) (Ref. AMM 29-12-42, 

P. Block 401), 

- the Pulsation Dampener C2092GM) of the Blue hydraulic system 

(Ref. AMM 29-12-46, P. Block 4011, 

(d) Between FR40 and FR41 remove the APU bleed-air duct. 

Refer To Figure 1 

CAUTION: TAKE CARE NOT TO DAMAGE THE SENSING ELEMENTS. 

1 Disconnect the Overheat Sensing Element 60HF (Ref. AMM 36-22-18, 

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 - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 8 

Printed in France 
SERVICE 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 in France 
@ 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. AMM 21-51-41, P. Block 401, Workstep 3.S.) 

2 Disconnect the electrical connector from the air outlet fLapactuator 9HH (Ref. AMM 21-61-52, P. Block 401, Workstep 3.A.). 

3 Support the ram air outlet and remove: 

9 screws, item 4, 

9 washers, item 5, 

1 bolt, item 6, 

1 washer, item 7, 

1 nut, item 8, 

12 bolts, item 9, 

12 washers, item 10. 

4 Remove the ram air outlet, item 1, and the rubber seal, item 3. 

I DATE: Jun 25/92 

REVISION NO: 1 - wy 26/9x 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: IO 

Printed in France 
@ A320 

SERVICE BULLETIN 

RemovaL/InstaLLation of the Left Ram Air Outlet 

DATE: JTJN 25/92 

Figure 2 

REVISION NO: 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 11 

Printed in France 
SERVICE 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. SRM 51-76-11). 

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: 

45 HI-LOK pins 

3 HI-LOK pins 

48 coLLars 

22 HI-LOK pins 

28 HI-LOK pins 

6 HI-LOK pins 

2 HI-LOK pins 

58 coLLars 

I DATE: Jun 25/92 

REVISION NO: 1 - MAY 26/93 

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 in France 

@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 1 of 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 2 of 2 

NOTE: The new structural components, which you instaLl have 

pilot holes. 

Match drill and instaLL Hi-Lok fasteners in accordance with 

SRM 51-44-00. 

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 in France 
@A320 

SERVICE BULLETIN 

3 Install 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. 

4 Install the traverse D5337150800200, item 42, with the screws, 

item 34, and the washers, item 35. 

I DATE: Jun 25/92 

REVISION NO: i - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 16 

Printed in France 


@A320 

SERVICE BULLETIN 

C. INSTALLATION OF CGMPONENTS AND TEST (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 MSN 005 and 006 only: 

cc) Install these hydraulic components: 

- the Pulsation Dampener (2092GM) of the Blue Hydraulic System 

(Ref. AMM 29-12-46, P. Block 4011, 

- the Blue Power Accumulator (2070GM) (Ref. ANN 29-12-42, 

P. Block 4011, 

- the Yellow Power Accumulator C3070GM) (Ref. ARM 29-13-42, 

P. Block 401), 

- the Electric Pump (30756X) of the Yellow hydraulic system 

(Ref. AMM 29-54-51, P. Block 4011, 

Cd) Between FR40 and FR41 install the APU bleed-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. AMM 36-22-18, 

P. Block 401, Para. 4.E. thru J .I. 

I DATE: Jun 25/92 

REVISION NO: 1 - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 21 

Printed in France 
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, 

1 washer, item 7, 

1 nut, item 8. 

2 - Connect the electricaL connector to the air outLet flap-actuator 

9HH (Ref. AMM 21-61-52, P. Block 401, Workstep 3.F.). 

3 Connect the left ram air outlet to the fan plenum chamber 

(Ref. AMM 21-52-41, 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 MSN 005 and 006 only: 

Ca) Energite the aircraft electricaL circuits (Ref. AMM 24-41-00). 

(b) Remove the safety cLips and tags and close these circuit breakers: 

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

PANEL SERVICE IDENT, LOCATION 

----^-------------------------------------------------------------------------- 

123VU Y HYD/ELEC/PUMP 38026X ABO6 

123VU .Y HY.D/ELEC PUMP NORM 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 TEMP CTL SYS2/1/28VDC 4HH Y19 

122vu AIR COND/PACK TEMP CTL 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 FEED VALVE/BAT 2HV 221 

122vu AIR BLEED/X FEED VALVE/NORM 1HV z20 

I 

(cl Remove the warning notices. 

(d) Do the test of the PuLsation Dampener C2092GM) of the BLue 

hydrauLic system (Ref. AMM 29-12-46, P. Block 401. 

I Ce) Do the test of the BLue Power Accumulator (2070GM) (Ref. AMM29-12-42, 

P. BLock 401). 

I DATE: Jun 25/92 

REVISION NO: 1 - MAY 26193 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 22 
@A320 

SERVICE BULLETIN 

(f) Do the teat of the Yellow Power Accumulator (307OGM) 

(Ref. AMM 29-13-42, 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) Do the test of the Center-Tank External Ventilating-System 

(Ref. AMM 28-13-00, P. Block 501). 

Cj1 Do the operational text of the APU BLeed-Air Supply and 

Crossbleed System (Ref. AMM 36-12-00, P. Block 501). 

Ck) Do the operational test of the Overheat Detection System 

(Ref. AMM 36-22-00, P. Block 501). 

(1) Do the operational test of the Air-Conditioning Pack-Temperature 

Control-System (Ref. AMM 21-61-00, P. BLock 501). 

ApplicabLe to aLL A/C, except A/C MSN 005 and 006: 

(a) Energize the aircraft electrical circuits (Ref. AMM 24-41-00). 

(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. AMM 29-10-00, 

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. AMM 28-13-00, 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. AMM 12-12-29, P. Block 301). 

I DATE: Jun 25192 SERVICE BULLETIN NO: A320-53-1014 

REVISION NO: I - MAY 26/93 PAGE: 23 

Printed in France 
@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 MSN 005 and 006 only: 

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

AppLicable to all A/C, except A/C MSN 005 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. 

I DATE: Jun 25/92 REVISION NO: I - MAY 26/93 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 24 

Printed in France 
3. MATERIAL INFORMATION 

Basis for the following 

A. LIST OF COMPONENTS 

ITEM NEW P/N 

SERVICE BULLETIN 

material data is per aircraft. 

QTY 

PER KIT 

531014A01 DESIGNATION OLD P/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 

Co1 lar 

HI-LOK Pin 

HI-LOK Pin 

CoLlar 

D533?0601200/201 

D533?0601202/203 

QTY 

‘PER KIT 

ITEM NEW P/N 531014A02 DESIGNATION OLD P/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 33NAS109?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 in France 
SERVICE BULLETIN 

8. LIST OF MATERIALS - OPERATOR SUPPLIED 

REFERENCE 

DESIGNATION CHL QTY PER A/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 

SeaLan t 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. PARTS TO BE REIDENTIFIED BY OPERATOR 

None 

DATE: JuN 25/92 

REVISION NO: 

, 

SERVICE BULLETIN NO: A320-53-1014 

PAGE: 26 

Printed in France 
AIRBUS INDUSTRIE 

PRODUCT SUPPORT DIRECTORATE 

1 Rond Point Maurice BELLONTE GA320 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

Tel: (33) 61-93-33-33 REVISION TRANSMITTAL SHEET 

TeLex: AIRBU 530526 F 

MODIFICATION NO: 20535KO588, 21519K1630 ATA SYSTEM: 53 

TITLE : FUSELAGE - CENTER FUSELAGE - REINFORCE STRUCTURE OF BELLY FAIRING 

Herewith Revision No. 2 of Service BuLLetin A320-53-7014. 

NO ADDITIONAL WORK IS REQUIRED BY THIS 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 1 of 3 Para. REASON - Accomplishment timescale revised. 

Text shift from page 2 of 3 

- Page 2 of 3 Text shift to page 1 of 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 1 of 3 and 2 of 3. 

- Replace Service BuLletin pages 1 of 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: 1 of 1 

Printed in Gance