### DocketNo. FAA-2009-1040 FAACaseNo. 2008NM210020 FAADocketNo.CP09NM0013 /?



### IntheMatterof FRONTIERAIRLINES,INC. JudgeRichardC. Goodwin 

### RESPONDENT'SRESPONSETO COMPLAINANT'S

FIRSTSUPPLEMENTALDISCOVERYREQUEST Pursuant

### to 14 C.F.R. 

### § 13.220,RespondentFrontierAirlines, Inc. ("Frontier"), byand through its counsel, Pillsbury Winthrop Shaw Pittman LLP, hereby responds to the Complainant's First Supplemental DiscoveryRequest filed on February 12, 2010 ("Request"). Subject to and without waiving its objections raised in the Respondent's Objections and Responses to Complainant's Initial Discovery Request filed on February 9, 2010, Frontier is providingtheattacheddocUmentsinresponseto**Co~plainant'** 

### sRequest.

. . 

### Frontierreservestherightto amend, expand, ordelete

### all oranypartoftheseobjections andresponses. Respectfullysubmitted,

Dated: March 19,2010 Kenne P. 

### Quinn Jenni E. Trock PILLSBURYWINTHROP SHAWPITTMANLLP 2300NStreet,N.W. Washington,D.C.20037 Tel: (202)663-8000 Fax: (202) 663-8007 E-mail:kquinn@pillsburylaw.com jtrock@pillsburylaw.com CounselforFrontierAirlines,Inc.

### CERTIF1CATEOFSERVICE I, TimothyC. Gerheim, hereby certify that I havethis, the 19thdayofMarch, 2010, caused a copy oftheforegoing document to be served to the following persons via facsimile and U.S. FirstClassmail:

FederalAviationAdministration Attention:HearingDocketClerk,AGC-430 Wilbur WrightBuilding

- Suite2WIOOO 800IndependenceAvenue, SW Washington,DC20591 FAJ<:202-493-5142 (Originalandonecopy)

ScottR. Morris,Attorney FederalAviationAdministration

.NorthwestMountainRegion,ANM-7

1601 LindAvenueS.W. Renton,WA98057-3356 FAJ<: 425-227-1007

TheHonorableRichardC. Goodwin AdministrativeLawJudge OfficeofHearings,M-20 1200NewJerseyAvenue, S.E. EastBuildingGroundFloor RoomE12-320 Washington,D.C.20590 FAJ<:202-366-7536

# ~(L~ TimothyC. Gerheim PillsburyWinthropShawPittmanLLP 2300N

## st.NW Washington,DC20037

2THIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C.§ 552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-42-27-210-003 Check Heat Pack Wear indicator (Parking Brake Applied) 1. Reason for the Job Refer to theMPD TASK: 324227-01 To do an inspection of the brake unit to make sure that the disc pads are not worn. 2. Job Set-up Information A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION , No specific warning notices B. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-42-00-862-001 De-energize the Ground Service Network Supplied from the External Power 29-10-00-863-002 Pressurize the Yellow Hydraulic System 29-10-00-864-002 Depressurize the Yellow Hydraulic System 32-42-00-040-002 Deactivation of the Normal Braking

- With disconnection of the Green HydrauLic Supply 32-42-27-000-001 Removal of the Brake (2641GM,2642GM,2643GM,2644GM) 32-42-27-400-001 Installation of the Brake (2641GM,2642GM,2643GM,2644GM) 32-42-27-991-002 Fig. 601 

# l 32-42-27 Page 605

# .~'LL Feb 01/08 IFFT F90057 Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMEERCIALOR FINANCIAL INFORMATION EXEMPT FROM61SCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 3. Job Set-up Subtask 32-42-27-860-055 A. Aircraft Maintenance Configuration (1)Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2)In the cockpit, on the triple indicator 60GG on the panel 400VU, make sure that the brake yellow pressure indicator is pressurized (the indicator pointer ;s in the green range).If necessary pressurize the brake accumulator: (a)Pressurize the Yellow hydraulic system (Ref. TASK 29-10-00-863­ 002)• (b)On the triple indicator 60GG on the panel 400VU, make sure that the pressure increase (the indicator pointer is in the green range) (c) Depressurize the Yellow hydraulic system (Ref. TASK 29-10-00-864­ 002)• Subtask 32-42-27-941-056 B. Safety Precautions (1)Put the warning notices in the cockpit, to tell persons not to operate the landing gear or the wheel brakes. (2)Make sure that the wheel chocks are ;n position. (3)Set the parking brake to the OFF position.


# l 32-42-27 ALL Page 606 Feb 01/08

F90058 Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. §552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-27-865-053 C. Make sure that this(these)**cir~uit** breaker(s) is(are) closed:
PANEL DESIGNATION IDENT. LOCATION
**ON AlC 201-299, 801-899, 936-999,
49VU ABCU &/Y BRK/PRESS IND 61GG C10

49VU L/G/Y BRK/PRESS/IND 61GG C10 **ON A/C ALL

121VU HYDRAULIC/PARK BRK/CTL/STBY 71GG N37 121VU HYDRAULIC/PARK BRK/CTL/NORM 70GG N36 4. Procedure (Ref. Fig. 601/TASK 32-42-27-991-002) Subtask 32-42-27-210-056 A. Inspection of the Brake (1)On the panel 110VU, put the parking brake control switch 73GG in the ON position. (2)With the parking brake on, make sure that the wear indicators are in the limits. R NOTE Measure the wear pin when the brake is cold (Brake temperature R less than 60 deg.C). R NOTE When the end of either wear pin touches the machined surface of the piston housing:

- the heat pack is fully worn and you must replace the brake (Ref. TASK 32-42-27-000-001). NOTE For a new brake: 

# 32-42-27 Page 607 

# r Feb 01/08
tFFT F90059 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

WEAR INDICATOR PIN LENGTH PIN BRAKE D ASSEMBLY 2-1526 2152&2 SOmm (1.97in.) 2·152&5 2-1526-3 2-1526-4 2-1572 66mm (2.66in.) 2-159&1 2-1600-1 63mm (2A81n.) 2-1600-2 2-1600-3 50.8mm (2.0In.) 2-1684 53.3mm (2.10in.) 

### I2642GM]

STATOR

ASBY



## ... o

# ~ ttJ I:\i**~ ~**  If)**~** ON NEW BRAKE 

### C
Brake Unit-Wear Indicator Figure 601/TASK 32-42-27-991-002
ALL 

# 1

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# I F90060 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL Measure the distance between the end of the wear pin and the machined surface of the piston housing. this distance must be : 50 mm (1.97 in.) maximum for PIN 2-1526, 2-1526-2 and 2-1526-5 68 mm (2.68 in.) maximum for PIN 2-1526-3, 2-1526-4 and 2-1572 63 mm (2.48 in.) maximum for PIN 2-1598-1 and 2-1600-1

- 50.8 mm (2.0 in.) maximum for PIN 2-1600-2 and 2-1600-3.

- 53.3 mm (2.10 in.) maximum for PIN 2-1684. If more than the maximun value replace the brake (Ref. TASK 32-42-27-000-001) (Ref. TASK 32-42-27-400-001). NOTE The brake units usually have two wear pins. If you find a brake that does not have the two wear pins: -the brake is serviceable if there is one wear pin and the wear pin is in the limits. -you must deactivate the brake if there is no wear pin (Ref. TASK 32-42-00-040-002). R (3) Make sure that there are no leaks on:

- the piston housing,

- the hydraulic lines. 5. Close-up Subtask 32-42-27-860-056 A. Put the aircraft back to its initial configuration. (1)De-energize the Ground Service Network Supplied from the External Power (Ref. TASK 24-42-00-862-001) Subtask 32-42-27-941-057 B. Removal of Equipment (1)Remove the ground support and maintenance equipment, the special and standard tools and alL other items. (2)Remove the warning notice(s). (3)Make sure that the work area is clean and clear of tool(s) and other items.



# 32-42-27 Page 609 EFF ALL Aug 01/07 fFT F90061 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5U.S.C. §552(b)(4). 

### " 

# I$JA3181A3191A320 AIRCRAFT MAINTENANCE MANUAL NORMAL BRAKING

- DEACTIVATION/REACTIVATION TASK 32-42-00-040-003 Deactivation of the Main Wheel Brakes WARNING : MAKE SURE GEAR. THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
WARNING MAKE SURE THAT OPERATE BEFORE THE YOU CONTROLS AGREE WITH PRESSURIZE A**~YDRAULIC** SYSTEM. THE POSITION OF THE ITEMS THEY
1. Reason for the Job Refer to the MMEL TASK: 32-42-01 Normal Braking

- Main Wheel Brakes 2. Job Set-up Information A.**Fi~tures,** Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific temporary placard No specific vinyl hose No specific warning notice(s) No specific wide self-adhesive fabric tape No specific container 5 l (1.3208 USgal) B. Consumable Materials
REFERENCE DESIGNATION
No specific corrosion-resistant steel lockwire dia 0.8 mm R Material No. 02-003 F NSA 307110 TYPE 4 HYDRAULIC FLUID (PHOSPHATE ESTER BASE) (Ref. 20-31-00)

## ~~ 

# 32-42-00 Page 401 Feb 01/05 JFFT Printed in France F90062THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

# f$;A3181A3191A320 AIRCRAFTMAINTENANCEMANUAL C. Referenced Information
REFERENCE DESIGNATION
12-12-29-611-001 Fill the Hydraulic Fluid Reservoir with a Hand Pump 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 29-10-00-864-001 Depressurize the Green Hydraulic System 29-10-00-864-002 Depressurize the Yellow Hydraulic System 29-23-00-863-001 Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump 29-24-00-863-001 Pressurize the Yellow Hydraulic System with the Electric Pump 32-41-11-400-006 Installation of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) 32-42-00-720-002 Functional test of the tachometers 32-42-27-000-001 Removal of the Brake (2641GM,2642GM,2643GM,2644GM) R 32-46-00-740-001 BITE Test of the BSCU 32-42-00-991-001 Fig. 401 32-42-00-991-002 Fig. 402 3. Job Set-up Subtask32-42-00-941-061 A. Safety Precautions (1)Put the warning notice(s) in position to tell persons not to operate the landing gear control lever and the brake pedals. R Subtask 32-42-00-740-057 R B. BITE Test R (1) Do the BITE test of the BSCU (Ref. TASK 32-46-00-740-001) • R If there ;s a fault message, make sure that the fault message is not R related to a tachometer related to a wheel with serviceable brake. 

# l 32-42-00 Page 402 ALL May 01/07

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-00-860-068 R C. Aircraft Maintenance Configuration (1)Depressurize the Green and Yellow hydraulic systems (Ref. TASK 29-10­ 00-864-001) (Ref. TASK 29-10-00-864-002). (2)Make sure that the PARKING BRK control switch is set to OFF before you do the deactivation. NOTE If the brake unit can not move, if the stators, rotors or torque-tubes are damaged:

- remove the brake unit. This causes two deactivations: 

## * Deactivation without removal of the brake, 

## * Deactivation with removal of the brake.

Subtask 32-42-00-040-052 A. Deactivation without Removal of the brake (Ref. Fig. 401/TASK 32-42-00-991-001) (1)Loosen the two knurled sleeves (1) and (4) of the half couplings (2) and (3). Turn and disconnect the half couplings. (2)Clean the sleeves (1) and (4) and apply two or three turns of the wide self-adhesive fabric tape 20 mm (0.7874 in.) to 30 mm (1.1811 in.). (3)Tightly wind three or four turns of the corrosion-resistant steel lockwire dia 0.8 mm around the tape on the sleeves (1) and (4). (4)Twist the lockwire and put it through the nearest locking hole you can get access to in the hexagonal head of the fixed half couplings (2) and (3). Tighten the lockwire and twist it. (5)Remove the two bleed screw plugs (6) from the bleed screw. (6)Connect a vinyl hose to a bleed screw (5) and put the other end in a container that contains HYDRAULIC FLUIDS (Material No. 02-003). (7)Slowly loosen the bleed screw (5) to release hydraulic residual pressure from the brake.

ALL 

# 32-42-00 Page 403 May 01/07 

# F 1 IFFT Printedin France F90064THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

NOTE::rHEYELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHINDTHE LEG GEAR. ·THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

4 :3**-t.....Jt(}...Jm!~ry-"----** SENSOR ELECTRIC CONNECTION LEG GEAR SIDE

BRAKE TEMPERATURE

Deactivation without Brake Removal

Figure 401/TASK 32-42-00-991-001
I 

# l 32-42-00 IEFF ALL Page 404 Feb 01/01 FFT F90065 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHEFREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4). 

# $A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL (8)Tighten the bleed screw. (9)Disconnect the vinyl hose. (10) Install the bleed screw plug (6) on the bleed screw (5). (11) Do the same operations for the other bleed screw. Subtask 32-42-00-910-052 B. Precaution: CAUTION : MAKE SURE THAT THE LOCKWIRE CANNOT WEAR DURING THE OPERATIONS OF THE LANDING GEAR. Subtask 32-42-00-040-053 C. Deactivation with the Brake Removal (Ref. Fig. 402/TASK 32-42-00-991-002) (1)Remove the brake (Ref. TASK 32-42-27-000-001). NOTE Install the nuts (8) and the washers (7) on the brake unit bolts (10) when you remove the brake unit. NOTE When you remove the brake unit, you must use the high-pressure blanking plugs. (2)Clean the sleeves (4)**~nd** (12) and the electrical connector (9) of the brake temperature sensor. Apply two or three turns of the wide self-adhesive fabric tape (20 mm (0.7874 in.) to 30 mm (1.1811 in.):

- around the sleeves (4) and (12),

- around the electrical connector (9) of the brake temperature sensor. (3) Tightly wind two or three turns of the corrosion-resistant steel lockwire dia 0.8 mm:

- around the tape on the sleeves (4) and (12),

- around the tape on the electrical connector (9). (4)Twist the lockwire. Put it through the nearest locking hole you can get access to. NOTE Make sure that the lockwire cannot rub when the landing gear operates. (5) Remove the PROTECTIVE CONE (J47779) from the wheel axle (6). 

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## I 2841GM

## 1-\­

## ~ A

- ......·--5

11 10 9 LEG GEARSIDE THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

NOTE:-THEYELLOWHYDRAULIC CONNECTlONONTHE BIW<E UNITS ISN...WAYS BEHINDTHElEGGEAR. -THEGREEN HYDAAlJUC CONNEC1lONONTHEBIW<E UNITS ISAlWAYS IN FRONTOFTHE LEGGEAR.

WHEB.SIDE

# 12_~ \

8 0 ::i! al al

.... 

### 8**~** N (!') 10 :::Ii z

R Deactivation with Brake Removal Figure 402/TASK 32-42-00-991-002


### ALL 

# 32-42-00 Page 406 R 'EFF May 01/03 FFT F90067 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A32D AIRCRAFT MAINTENANCE MANUAL (6) Install the main landing-gear wheel (Ref. TASK 32-41-11-400-006). Subtask 32-42-00-865-063 D. Make sure that this(these) circuit breaker(s) is(are) closed:
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 Subtask 32-42-00-860-069 E. Aircraft**~aintenance** Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861­ 002)• (2)Pressurize the Yellow hydraulic system with the Yellow electric pump. (Ref. TASK 29-24-00-863-001) (3)On the panel 402VU, make sure that the A/SKID 

### &NOSE WHEEL switch is set to ON. Subtask 32-42-00-710-063 F. Tests (1) Do this test:
ACTION RESULT
1. Fully push in the related brake Make sure that there are no leaks on pedals and hold them in this the Yellow hydraulic-pressure line you position. disconnected. 2. Release the brake pedals. 3.Pressurize the Green hydraulic Make sure that there are no leaks on system from the Yellow hydraulic the Green hydraulic-pressure line you system with the PTU. (Ref. TASK disconnected. 29-23-00-863-001) 

# F ALL 

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## I Printed in France F90068THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DiSCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

## f$;A3181A3191A320 AIRCRAFTMAINTENANCEMANUAL ACTION RESULT FulLy push in the reLated brake pedaLs and hoLd them in this position. 4. ReLease the brake pedals. (2)Do the functional test of the tachometer.(Ref. TASK 32-42-00-720-002) R Subtask 32-42-00-869-057 R G. System Consequences and Cockpit Effects in case of deactivation with the 

### R brake removaL R R This deactivation procedure can cause the WheeL page of the Systems R DispLay to show the message XX at the applicable brake temperature R indication. R 5. Close-up, Subtask 32-42-00-860-070 A. Put the aircraft back to its initial configuration. (1) Depressurize the Green and Yellow hydraulic systems (Ref. TASK 29-10­ 00-864-001) (Ref. TASK 29-10-00-864-002) (2)Make sure that the level of the fluid in the Green and Yellow hydrauLic reservoirs is correct. Add some fLuid if it is necessary. (Ref. TASK 12-12-29-611-001) (3) De-energize the aircraft electrical network (Ref. TASK 24-41-00-862­ 002). (4)Remove the warning notice(s). (5)Remove the ground support and maintenance equipment, the speciaL and standard tooLs and aLL other items. (6)In the cockPit, instalL a temporary pLacard placard to tell the crew:
- that the brake unit No.1 (2, 3, 4) is not operational or is removed.

r--- --:--A-LL------------. 

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FFT F90069 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R **ON AIC ALL
Subtask 32-42-27-640-050 A. Preparation for Installation (1)Clean the axle protective sleeve (5) and the studs (11) with CLEANING AGENTS (Material No. 11-002). (2)Do a visual inspection of the axle protective sleeve (5) to make sure that it is in correct condition. (3)Lightly lubricate the studs (11), the bolts (12) and the nuts (8) with COMMON GREASE (Material No. 04-003). (4)If necessary, install the brake temperature sensor retained at removal of the brake unit (Ref. TASK 32-47-15-400-001). Subtask 32-42-27-420-054 B. Installation of the Brake CAUTION: TO PREVENT DAMAGE TO THE AIRCRAFT, MAKE SURE THAT THE COUPLINGS ARE CORRECTLY LOCKED (FULLY TURN THE COLLAR OF THE BRAKE QUICKRELEASE COUPLING CLOCKWISE UNTIL IT TOUCHES ITS MECHANICAL STOP), (1)Install the brake unit (1) on the wheel axle (6) with HANDLING TOOL (1324A). (2)Install the washers (7) and the nuts (8) on the bolts (12). (3)Make sure that the studs (11) are in the correct position in the axle (6). (4)TORQUE the nuts (8) to between 175 and 180 lbf.ft (23.72 and 24.40 m.daN). With the ADAPTOR

- BRAKE UNIT NUT (98D32403001000) or the ADAPTOR

- BRAKE UNIT NUT (98D32403005000) or with a standard socket and extension you must calculate torque wrench setting (Ref. TASK 20­ 21-11-911-001)• NOTE : The given value is the torque that you must apply to the nut. (5)Remove the blanking plugs from the hydraulic couplings (2) and (14) and the unions (3) and (13).

F ALL 

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# l

Printed inFrance F90070THIS DOCUMENTMAY CONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAfT MAINTENANCE MANUAL (6) Connect the hydraulic couplings (2) and (14) to the unions (3) and (13) NOTE If the union nut is loose, TORQUE it to between 2.5 and 2.8 m.daN (18.43 and 20.64 lbf.ft). (7)Remove the PROTECTIVE CONE (J47779) from the wheel axle. (8)Make sure that the retaining ring (4) of the axle protective sleeve (5) is in the correct position. Subtask 32-42-27-420-055-A C. End of the installation (1)Remove the blanking caps from the electrical connector (9) and the receptacle (10). (2)Connect the electrical connector (9) to the receptacle (10) and fold back the end of the sleeve (15) on the connector (9) to cover it fully. (3) Install the wheel (Ref. TASK 32-41-11-400-006). Subtask 32-42-27-870-050 D. Bleed the brake unit (Ref. TASK 32-42-00-870-001) (Ref. TASK 32-43-00­ 870-002) CAUTION : THE BLEEDING PROCEDURE OF THE BRAKE UNIT CALLS FOR OPERATIONAL TEST OF THE NORMAL AND ALTERNATE BRAKING SYSTEM. DURING THESE TESTS CHECK HYDRAULIC CONNECTIONS AND BRAKE UNIT FOR LEAKAGE. Subtask 32-42-27-865-052 E. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GG, 2GG, 3GG, 4GG, 70GG, 71GG, 1GW



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## IFFT F9QQ71 Printedin FranceTHIS DOCUMENT MAY CONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

# SA3181A3191A320 AIRCRAFTMAINTENANCEMANUAL Subtask 32-42-27-710-050 F. Test (1)As the operational tests of the Normal and Alternate braking system necessary after removal/installation of the brake unit are already done in the bleeding procedure, do only an operational test of the brake temperature system (Ref. TASK 32-47-00-710-001). 5. Close-up Subtask 32-42-27-942-050 A. Put the aircraft back to its initial configuration. (1)Make sure that the work area is clean and clear of tool(s) and other items. (2)Remove the warning notice(s). (3)Remove the ground support and maintenance equipment, the special and standard tools and all other items.



# FALL
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## IFFT Printed in France F90072THIS DOCUMENT MAYCONTAINTRADE SECRETS ANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL**BRAK£_(26~1GM,26~?§M,2643GM,?~44GM)** 

### - REMOVAL/INSTALLATION TASK 32-42-27-000-001 Removal of the Brake (2641GM,2642GM,2643GM,2644GM) WARNING MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. 1. Reason for the Job Self Explanatory

A. Fixtures, Tools, Test and Support £quipment
REFERENCE QTY DESIGNATION
No specific blanking cap No specific blanking plugs No specific circuit breaker(s) safety clip(s) No specific safety barriers No specific standart socket and extension No specific warning notice(s) J47779 PROTECTIVE CONE 1324A HANDLING TOOL 98D32403001000 ADAPTOR

- BRAKE UNIT NUT 98D32403005000 ADAPTOR

- BRAKE UNIT NUT B. Consumable Materials
REFERENCE DESIGNATION
R Material No. 04-022 USA MIL-PRF-81322 SYNTHE.HYDROCARBON GREASE HIGH PRESSURE (Ref. 20-31-00)

Page 401 

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## I F90073 

### IFFT Printed**i~** FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT,S U,S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL C. Referenced Information
REFERENCE DESIGNATION
29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 32-41-11-000-006 Removal of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) 32-47-15-000-001 Removal of the Brake Temperature Sensor (4GW,5GW,6GW,7GW) R **ON A/C 801-807, 901-938,
32-42-27-991-001-A Fig. 401 R **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R 32-42-27-991-001-C Fig. 401A R **ON A/C ALL
3. Job Set-up Subtask 32-42-27-941-060 A. Safety Precautions (1) Put the safety barriers in position. (2) Put the warning notice(s) in position: on the ground service panel to tell persons not to pressurize the Green and Yellow hydraulic systems,

- on the panel 40VU, to tell persons not to pressurize the Green and Yellow hydraulic systems.

r 

# ------------1 

# 32-42-27 IEFF ALL Page 402 

### May 01/07 

# I I IFFT F90074 

# I
Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-27-860-059 B. Aircraft Maintenance Configuration (1)Put the wheel chocks in position for the wheels that are on the ground. (2)Make sure that the Green and Yellow hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001). (3)Remove the applicable wheel (Ref. TASK 32-41-11-000-006). (4) On the panel 110VU, set the PARK BRK control switch to OFF. Subtask 32-42-27-865-050 C. Open, safety and tag this(these) circuit breaker(s):
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 121VU HYDRAULIC/PARK BRK/CTLfSTBY 71GG N37 121VU HYDRAULIC/PARK BRK/CTL/NORM 70GG N36 4. Procedure

......

# _------­ R **ON A/C 801-807, 901-938, (Ref. Fig. 401/TASK 32-42-27-991-001-A) R **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R (Ref. Fig. 401A/TASK 32-42-27-991-001-C)

ALL 

# ---, 32-42-27 Page 403 May 01/07

F90075 

### \ Printed in FranceTHIS DOCUMENT MAYCONTAINTRADESECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U.S.C.§ 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

@j C\I ::: 

### r! 

### "" C\I C\I 

### '"


### "" C\I <') ID ::: z 

# rnl

# ~-2 i

13

546
15

# ¥;:s&(~J,,,L,
Brake Unit Figure 401/TASK 32-42-27-991-001-A 801-807, 901-938, 

# l 32-42-27 Page 404 

### May 01/07

F90076 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

14

13 

### A

# .~ I

12 11 10 9 5 6 8

## ~

# 7~1'f:li'. 8--1Ii.C1

Brake Unit R Figure 401A/TASK 32-42-27-991-001-C R 

# I r;;---------------------------------------------l

EFF: 

# 32-42-27 Page 405 ALL May 01/07 

## I F90077 

## IFFT Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL R **ON Ale ALL
Subtask 32-42-27-020-050 A. RemovaL of the Brake**~AR~!~§** THE BRAKE UNIT WEIGHS APPROXIMATELY 67kg (147lb). BE CAREFUL WHEN YOU MOVE IT TO PREVENT INJURY TO PERSONS OR DAMAGE TO THE WHEEL OR AXLE. (1) InstaLL the PROTECTIVE CONE (J47779) on the wheel axLe (6). NOTE SLightly lubricate the outer circumference of the protective tool with COMMON GREASE (MateriaL No. 04-022). (2) Disconnect the electricaL connector (9). (3) Put abLanking cap on the electrical connector (9). (4) Disconnect the hydrauLic couplings (2) and (14) from the unions (3) and (13). (5)InstaLL the bLanking plugs (6) Remove the nuts (8) with the ADAPTOR

- BRAKE UNIT NUT (98D32403001000)**~r** the ADAPTOR

- BRAKE UNIT NUT (98D32403005000) or with a standartsocket and extension and remove the washers (7). (7)Remove the brake unit (1) with the HANDLING TOOL (1324A). (8) If necessary, remove the brake temperature sensor (Ref. TASK 32-47­ 15-000-001) and retain it for installation on the new brake unit.



# ....-----------------------------, EFF: ALL 

## I 

# 32-42-27 Page 406 

# I May 01/07 IFFT F90078 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4). 

## (1$

# A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-42-27-400-001 InstaLLation of the Brake (2641GM,2642GM,2643GM,2644GM) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. 1. Reason for the Job SeLf Explanatory 2. Job Set-up Information A. Fixtures, TooLs, Test and Support Equipment
REFERENCE aTY DESIGNATION
No specific safety barriers No specific standard socket and extension No specific warning notice(s) No specific Torque Wrench range 50.00 to 260.00 lbf.ft (6.00 to 36.00 m.daN) No specific Torque Wrench : range 0.20 to 3.60 m.daN (2.00 to 26.00 Lbf.ft) 1324A HANDLING TOOL 98D32403001000 ADAPTOR

- BRAKE UNIT NUT 98D32403005000 ADAPTOR

- BRAKE UNIT NUT B. Consumable Materials
REFERENCE DESIGNATION
R Material No. 04-003 USA SAE AMS 2518 GRAPHITED PETROLATUM THREAD COMPOUND (Ref. 20-31-00) Material No. 11-002 USA MIL-PRF-680 DRY CLEANING SOLVENT (VARSOL/WHITE SPIRIT) (Ref. 20-31-00)



# I 

# 32-42-27 Page 407 ALL Feb 01/08 

## IEFF

. FFT F90079 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACTI'5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL C. Referenced Information
REFERENCE DESIGNATION
20-21-11-911-001 Tightening Torques for Standard Threaded Fasteners 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 32-41-11-400-006 Installation of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) 32-42-00-870-001 Bleeding of the Normal Braking at the Brake Units 32-43-00-870-002 Bleeding of the High Pressure Alternate Braking System 32-47-00-710-001 Operational Test of the Brake Temperature System 32-47-15-400-001 Installation of the Brake Temperature Sensor (4GW,5GW,6GW,7GW) R **ON A/C 801-807, 901-938,
32-42-27-991-001-A Fig. 401 R **ON A/C ALL R Post SB 32-1291 For AIC 801-807,901-938, R 32-42-27-991-001-C Fig. 401A R **ON A/C ALL
3. Job**Set-u~** Subtask 32-42-27-941-061 A. Safety Precautions (1)Make sure that the safety barriers are in position. (2)Make sure that the warning notice(s) is (are) in position:

- on the ground service panel to tell persons not to pressurize the Green and Yellow hydraulic systems,

- on the panel 40VU, to tell persons not to pressurize the Green and Yellow hydraulic systems.

/EFF ALL 

# l 32-42-27 Page 408 May 01/07 

# I IFFT Printed in France F90080THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT. 5 U.S.C. §552(b)(4). 

# SA3181A3191A320 AIRCRAFTMAINTENANCEMANUAL Subtask 32-42-27-860-060 B. Aircraft Maintenance Configuration (1)Make sure that the wheel chocks are in position for the wheels that are on the ground. (2)Make sure that the Green and. Yellow hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001). (3)On the panel 110VU, make sure that the PARK BRK control switch is set to OFF. Subtask 32-42-27-865-051 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 121VU HYDRAULIC/PARK BRK/CTL/STBY 71GG N37 121VU HYDRAULIC/PARK BRK/CTL/NORM 70GG N36 4. Procedure R **ON A/C 801-807, 901-938, (Ref. Fig. 401/TASK 32-42-27-991-001-A) R **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R (Ref. Fig. 401A/TASK 32-42-27-991-001-C)

Page 409 May 01/07 

# ----l 32-42-27

F90081 Printed in France

## ---------------

----------- THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U.S.C. §552(b)(4). 

## I$;A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL 

### HYDRAULIC POWER

- SERVICING TASK 12-12-29-611-001 Fill the Hydraulic Fluid Reservoir with a Hand Pump R R R 

### WARNING



## ----­ DO NOT GET THE FLUID

- FLUSH IT AWAY WITH

- GET MEDICAL AID. ON YOUR SKIN CLEAN WATER OR IN YOUR EYES. IF YOU DO:

WARNING



# ----­ MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE AHYDRAULIC SURFACES SYSTEM. ARE
1. Reason for the Job Self Explanatory

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific hydraulic fluid container No specific warning notices No specific access platform 2 m (6 ft. 7 in.) B. Consumable Materials
REFERENCE DESIGNATION
R Material No. 02-003 F NSA 307110 TYPE 4 HYDRAULIC FLUID (Ref. 20-31-00) (PHOSPHATE ESTER BASE) R Material No. 02-003A F NSA 307110 TYPE 4
R Material No. 02-003B HYDRAULIC FLUID (Ref. 20-31-00) F NSA 307-110 (PHOSPHATE TYPE 4 ESTER BASE)

Material No. 02-003C HYDRAULIC FLUID (Ref. 20-31-00) F NSA 307-110 (PHOSPHATE ESTER TYPE IV BASE)
HYDRAULIC FLUID (Ref. 20-31-00) (PHOSPHATE ESTER BASE)

r---­ 

### IEFF ALL 

# l 12-12-29 Page 301 

### Feb 01105 

## IFFT F90082 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).



### REFERENCE
Material No. 02-003D

R R 

### Material No. 02-003E

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### DESIGNATION
F NSA 307-110 TYPE IV HYDRAULIC FLUID (PHOSPHATE ESTER BASE) (Ref. 20-31-00) F NSA 307-110 HYDRAULIC FLUID (Ref. 20-31-00) C. Referenced Information
REFERENCE
12-14-29-614-001 24-41-00-861-002 24-41-00-862-002 29-00-00-864-001 29-00-00-870-003 29-00-00-870-007 29-00-00-870-008 29-00-00-870-009 29-00-00-910-002 29-10-00-680-001 29-10-00-680-002 29-10-00-680-003 29-14-00-614-002 29-24-00-863-001 29-24-00-864-001 32-12-00-010-001 32-12-00-410-001 32-44-11-200-001**12~12-29-991-001** 

### DESIGNATION
Fill the Hydraulic Power Accumulators 1070GM/2070GM/3070GM with Nitrogen Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Bleeding Procedure of the Green Hydraulic System Downstream of the Engine Pump Bleeding Procedure of the Yellow Hydraulic System Downstream of the Engine Pump Bleeding Procedure of the Blue Hydraulic System Upstream of the Blue E-Pump Bleeding Procedure of the Blue Hydraulic System Downstream of the Blue E-Pump Safety Procedures of the Hydraulic System Drainage of the Reservoir of the Green Hydraulic System Drainage of the Reservoir of the Yellow Hydraulic System Drainage of the Reservoir of the Blue Hydraulic System Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurize the Yellow Hydraulic System with the Electric Pump Depressurize the Yellow Hydraulic System Open the Main Gear Doors for Access Close the Main Gear Doors after Access Check Nitrogen Charge Pressure On Parking/Emergency Accumulator By Reading Gauge Fig. 301 

# 12-12-29 Page 302 ALL 

# ----I May 01/07 F90083 Printed in France

## ---- THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL ORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

# f!$JA3181 A3191 A320 AIRCRAFT MAINTENANCE MANUAL

Subtask 12-12-29-860-051 A. Aircraft Maintenance Configuration WARNING : OBEY THE HYDRAULIC SAFETY PROCEDURES. (1)Obey the hydraulic safety procedures (Ref. TASK 29-00-00-910-002). (2)Make**su~e** that the aircraft is in this configuration:

- the speed brakes and the spoilers are retracted,

- the thrust reversers are stowed (closed),

- the Landing gear is extended and the Landing gear doors are closed, R

- the FWD and aft cargo-compartment doors 825 and 826 are closed,

- all the other hydraulicaLly controlled systems are in the normal position. (3)Make sure that the hydraulic systems are depressurized and put them in the maintenance configuration. (Ref. TASK 29-00-00-864-001). NOTE: Do not depressurize the system reservoirs. (4) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861­ 002)

. Subtask 12-12-29-010-054 B. Get Access R (1) Open the Left Main Landing Gear (MLG) door (Ref. TASK 32-12-00-010­ 001). (2)Open the access panels 197CB, 198CB. (3)Put the access platform in position.



# r--------------------------­

# I 12-12-29 JEFF: ALL Page 303 

# I Aug 01/08 /FFT F90084 Printed in FranceTHISDOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 12-12-29-210-052 C. Inspection of the Pressure Values (1)Make sure that the nitrogen fill pressure of the brake accumulator 2582GM is correct (Ref. TASK 32-44-11-200-001). (2)Make sure that the hydraulic accumulators 1070GM, 2070GM and 3070GM have a nitrogen pressure of 130 bar (1885.4901 psi) at 20 DEG.C (68.00 DEG. F). If necessary, adjust the nitrogen pressure (Ref. TASK 12-14-29-614­ 001)• (3)Make sure that the pressure on the indicator of the related reservoir is 3.5 +0.3 -0 bar (50.7631 +4.3511 -0.0000 psi). If necessary, pressurize the reservoir (Ref. TASK 29-14-00-614-002). Subtask 12-12-29-863-050 D. Pressurize the Auxiliary Braking System. (1)Pressurize the Yellow hydraulic system with the Yellow E-pump (Ref. TASK 29-24-00-863-001) to pressurize the brake accumulator system to 206 bar (2987.7766 psi). (2)On the panel 110VU, put the parking brake control switch 73GG to the ON position. (3)Make sure that the pressure on the triple indicator 60GG shows the left and right pressure values. (4)Depressurize the Yellow hydraulic system (Ref. TASK 29-24-00-864­ 001)• NOTE : Do not depressurize the alternate braking system. (5)Close the left MLG door (Ref. TASK 32-12-00-410-001). (6)Put the warning notices on the panel 40VU in the cockpit to tell persons not to pressurize the hydraulic systems.



# I 

# r;;;------ EFF: 

# 12-12-29 Page 304 ALL Feb 01/01 

## I F90085 IFFT Printed in France

## -------- THIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 4. Procedure (Ref. Fig. 301/TASK 12-12-29-991-001) Subtask 12-12-29-611-052 R A. Fill the Hydraulic Reservoirs (Refer to the Table) (1)Remove the hand pump lever 3270GM from the service panel of the Yellow hydraulic system. (2)On the service paneL of the Green hydraulic system, connect the hand pump lever 3270GM to the**~haft** of the hand pump**1009GM~** (3) Remove the flexible hose 1699GM from the service panel compartment of the Green hydraulic system. (4) Remove the blanking cap and connect the flexible hose to the fill valve 1698GM. Put the other end in the hydraulic fluid container with one of these hydraulic fluids:

- HYDRAULIC FLUIDS (Material No. 02-003)

- HYDRAULIC FLUIDS (MateriaL No. 02-003A)

- HYDRAULIC FLUIDS (Material No. 02-0038)

- HYDRAULIC FLUIDS (Material No. 02-003C)

- HYDRAULIC FLUIDS (Material No. 02-003D)

- HYDRAULIC FLUIDS (Material No. 02-003E). R (5) Turn the selector 1134GQ to the position that is correct for the R system you will fill. R (6) Make sure that, on the quantity indicator 1834GQ, the colored light R of the related system comes on. (7) Fill the hydraulic reservoir:**CA~I!Q~** MAKE SURE THAT YOU DO NOT PUT TOO MUCH FLUID IN THE RESERVOIR. IF THE RESERVOIR IS TOO FULL, YOU CANNOT PRESSURIZE IT SUFFICIENTLY. LOW AIR PRESSURE CAN CAUSE THE MESSAGE "RSVR LO AIR PR" TO SHOW IN FLIGHT ON THE UPPER AND LOWER ECAM DISPLAY UNITS. (a)Operate the hand pump 1009GM.



## r-------------------------------, JEFF: ALL ) 

# 12-12-29 Page 305 May 01/08 

# I 

# I FFT F90086 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

RESERVOIR FILLSYSTEM SELECTOR VALVE 1134GQ RESERVOIR FILLSYSTEM HAND PUMP FILLVALVE 1698GM QUANTITY INDICATOR 1834GO

o o o o o

RESERVOIR FILLSYSTEM HAND PUMP 1009GM GROUND SUPPLY RESERVOIR FILL CONNECTION 1007GM**~.** o :2**~** M I1l N 

### ... N 

# -

Ground Service Panel of the Green Hydraulic System Figure 301/TASK 12-12-29-991-001



# --------- ._-------------------, 

# 12-12-29 Page 306 ALL 

### Feb 01/01 F90087 Printed in France

# -------------------------------- THIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (b) Monitor the increase of the fLuid LeveL of the related system on the quantity indicator and do these steps: 1 Stop the flow of the hydrauLic fluid when the pointer is almost to the fill level given in the table. 2 Slowly continue to fill again, until the pointer shows aLmost to the fill Level given in the table. NOTE The hydrauLic fLuid volume in the**reservoi~s** can change with the temperature. For each 10 DEG.C scale Celcius (which is each 18 DEG.F on the scale Fahrenheit) change in outside air temperature:

- The volume in the reservoir of the Green hydrauLic system can change by 0.5 l (0.1320 USgal)

- The volume in the reservoir of the Yellow hydraulic system can change by 0.5 L (0.1320 USgal) The volume in the reservoir of the Blue hydraulic system can change by 0.25 l (0.0660 USgal). NOTE If the temperature is above 20 DEG.C (68.00 DEG. F) the quantity indicator pointer must be in the top half of the related scale range. HYDRAULIC RESERVOIR CAPACITIES
R SYSTEM/RESERVOIR 

# 1 QUANTITY 

# 1 REMARKS R 

## 1-------------------------1 R 

## I 1 LITERS 

## 1 US GAL 

## 1 1 R 

## 1-------------------------1------------1------------1-------------------------1 R I GREEN SYSTEM 1 1 1 I R 1 1 1 1 I R 

## 1TotaL Capacity 

## 1 23 

## 1 6.1 

## 1 1 R 1 Max. Capacity shown on 1 1 1 1 R 

## I the Gage 

## 1 18 

## 1 4.8 

## 1 1 R 1 FiLL Level 1 14 I 3.7 I At 20 DEG.C (68 DEG.F) 1 R 1 Low Level Warning 1 3 1 0.8 1 1 

### R 

# 1-------------------------1------------1------------1-------------------------1 R 1 BLUE SYSTEM 1 I 1 1 R 1 I I I 1 R 

### I Total Capacity 

### I 10 

### I 2.6 

### I 1 R I Max. Capacity shown on I I 1 1 R 

### I the Gage 

### 1 8 

### I 2.1 

### I I

EFF: ALL 

# 1 12-12-29 Page 307 Aug 

### 01/08 FFT 

# E

F9008B Printed in France

# ------------------------------------------------------------------------------- THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

## ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL 

## I SYSTEM/RESERVOIR 

## 1 QUANTITY 

## I REMARKS 

### I 

## 1-------------------------1 I 1 

### LITERS I 

### US GAL I 1 

## 1-------------------------1------------1------------1-------------------------1 R 1 

### FiLL LeveL 1 

### 6 1 

### 1.6 1 

### AT 20 DEG.C (68 DEG.F) 1 

### R I 

### Low LeveL Warning 1 

### 2 I 

### 0.5 1 1 

### R 

## 1-------------------------1------------1------------1-------------------------1 R 

### I YELLOW SYSTEM , 

### I I , R 

## 1 1 I' 1 R I 

### TotaLCapacity I 

### 20 I 

### 5.3 I 1 

### R 

### I Max. Capacity shown on 

### 1 I I I R 

## 1the Gage 

## 1 18 

## 1 4.8 

## I 1 R 

### I FiLL LeveL 

### I 12 

### 1 3.2 

### I At 20 DEG.C (68 DEG.F) 

### I R , 

### 'I 1with the normal nitrogenl R 

## 1 I 1 1precharging pressure in 

## 1 R I I' 1 

### the brake accumuLator 1 

### R 

## 1 1 1 12582GM and the auxiLiary' R 

## 1 1 1 1brake system pressurizedl R 

### I Low LeveL Warning 

### I 3 

### I 0.8 

### I 1 (8)If a reservoir is filled too much, drain the unwanted hydraulic fluid:

- For the reservoir of the Green hydraulic system (Ref. TASK 29-10­ 00-680-001)

- For the reservoir of the YeLLow hydraulic system (Ref. TASK 29-10­ 00-680-002)

- For the reservoir of the BLue hydrauLic system (Ref. TASK 29-10-00­ 680-003)

. (9)Turn the selector 1134GQ to the NEUTRAL position. (10)Make sure that the colored light on the quantity indicator 1834GQ goes off. (11)Remove the flexible hose and instaLL the blanking cap on the pump. (12)Put the fLexible hose back in position in the service panel compartment of the Green hydraulic system. (13)Remove the hand pump lever 3270GM from the hand pump 1009GM. Then put the hand pump lever in position on the service paneL of the Yellow hydrauLic system. 

# l 12-12-29 Page 308 ALL Aug 01/08 F90089 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL (14) If you filled the hydraulic reservoir after:

- Maintenance Removal/installation of hydrauLic components Hydraulic fluid low Level (Loss of the hydraulic system) High loss of hydrauLic fluid, (a)Use the related bLeeding procedure as folLows:

- For the reservoir of the Green hydraulic system (Ref. TASK 29­ 00-00-870-003)

- For the reservoir of the YeLLow hydrauLic system (Ref. TASK 29­ 00-00-870-007)

- For the reservoir of the BLue hydrauLic system (Ref. TASK 29­ 00-00-870-008) and (Ref. TASK 29-00-00-870-009).

Subtask 12-12-29-410-054 A. CLose Access (1)Make sure that the work area is cLean and cLear of tooL(s) and other items. (2) Close the access panels 197CB, 198CB and if necessary 197EB. Subtask 12-12-29-860-050 B. Put the aircraft back to its initiaL configuration. (1) De-energize the aircraft eLectrical circuits (Ref. TASK 24-41-00-862­ 002)• (2) Remove the warning notice{s). (3) Remove the access platform{s).



## r---------·--------------------_____, 

# .1 EFF, ALL 

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### Aug 01/08 

## IFFT 

## I F90090 Printed in France

## -----

------------------- THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### AC EXTERNAL POWER CONTROL (GPCU OR GAPCU)

-**MA!~TENANC~** 

### PRA£!.ICES TASK 24-41-00-861-002 Energize the Aircraft ELectrical Circuits from the External Power WARNING MAKE SURE THAT THE AIRCRAFT IS GROUNDED. WARNIN§ MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. CAUTION DO NOT USE AGROUND POWER UNIT WITH ACAPACITY LESS THAN 90 KVA. IF YOU USE ALESS POWERFUL UNIT:

- AN OVERLOAD OF THE GROUND POWER UNIT COULD OCCUR

- IT COULD BE NECESSARY TO RESET MANY COMPUTERS ON THE AIRCRAFT. 1. Reason for the Job NOTE There are alternative methods for this procedure. This task gives one of the methods. For the other methods, refer to the other tasks in this page block.

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
98A24403000000 1 CABLE HOLDING STRAP B. Referenced Information
REFERENCE DESIGNATION
12-31-31-660-001 Cold Weather Maintenance

- Indicating/Recording systems and Navigation 12-34-24-869-002 Aircraft Grounding for the Maintenance Operations 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure R ESPM 20-55-10 24-41-51-000-001 Removal of the External Power Receptacle (20XG) (for corrective action)


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### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL REFERENCE DESIGNATION
24-41-51-400-001 Installation of the ExternaL Power ReceptacLe (20XG) (for corrective action) 24-41-00-991-001 Fig. 201
(Ref. Fig. 201/TASK 24-41-00-991-001) Subtask 24-41-00-860-050 A. Aircraft Maintenance Configuration NOTE In the avionics compartment, if the temperature is below -15 deg.C (+5.00 deg.F), do the coLd-weather maintenance procedure (Ref. TASK 12-31-31-660-001). NOTE When you do maintenance work on the electrical circuits, not possibLe to suppLy electrical power to the aircraft. it can be (1) The aircraft must be grounded (Ref. TASK 12-34-24-869-002). Subtask 24-41-00-010-050 B. Get Access (1)Open the access door 121AL to get access to the externaL power receptacle and the panel 108VU. Subtask 24-41-00-480-050 C. Install the cable holding strap (1)Attach the CABLE HOLDING STRAP (98A24403000000) to the feeder cable. (2)Connect the snap hook of the cabLe holding strap to the fitting on the aircraft structure.



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

External Power Receptacle

- Location Figure 201/TASK 24-41-00-991-001 

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-00-420-050 D. Connect the connector**~ARNING** BEFORE YOU CONNECT THE GROUND POWER UNIT TO THE EXTERNAL POWER RECEPTACLE OF THE AIRCRAFT, MAKE SURE THAT THE EXTERNAL ELECTRICAL POWER SUPPLY IS NOT ENERGIZED. IF IT IS ENERGIZED, DANGEROUS ARCING CAN OCCUR. CAUTION MAKE SURE THAT THE CABLE STRAP SUPPORTS ALL THE WEIGHT OF THE CABLE WHEN THE CONNECTOR IS CONNECTED. THIS PREVENTS DAMAGE TO THE EXTERNAL POWER RECEPTACLE. R**£~~rION** BEFORE YOU CONNECT THE GROUND POWER UNIT TO THE AIRCRAFT, MAKE R SURE THAT THERE ARE NO FOREIGN OBJECTS OR FLUID IN THE EXTERNAL R POWER RECEPTACLE OR THE GPU CONNECTOR. FOREIGN OBJECTS AND R FLUID CAN CAUSE AN OVERHEAT AND/OR DAMAGE TO EQUIPMENT. NOTE Examine the external power-suppLy cabLe and the external power receptacle before you do the connection. If you find corrosion, clean the externaL power receptacLe or the GPU connector (Ref. ESPM 20-55-10). If you find damage or if the pins are not aligned correctly, replace the external power receptacle (Ref. TASK 24-41-51-000-001) and (Ref. TASK 24-41-51-400-001). (1) Connect the connector of the ground power unit to the external receptacLe of the aircraft. 4. Procedure Subtask 24-41-00-861-051 A. Energize the aircraft electrical circuit from the external power (1)On the ELEC panel 35VU, make sure that:

- the GEN1, GEN2, APU GEN, BUS TIE and AC ESS FEED pushbutton switches are pushed,

- aLL the other pushbutton switches are reLeased. (2)On the overhead CTL and IND panel 22VU, make sure that:

- the BLOWER and EXTRACT pushbutton switches are pushed. (3)Obey the instructions given with the ground power unit and start the ground power unit. (4) Ifthe protection circuits operate correctly:

- on the panel 108VU, the PWR/AVAIL caution light EXT PWR/NOT come on, IN USE indicator light and EXT

- on.the panel 35VU, sWltch comes on. the AVAIL Legend on the EXT PWR pushbutton



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (5)On the paneL 35VU, push the EXT PWR pushbutton switch:

- the AVAIL Legend goes off. (6) If the eLectricaL power suppLy of the aircraft circuits is correct, on the paneL 35VU, these Legends come on:

- the ON Legend of the EXT PWR pushbutton switch,

- the FAULT Legend of the GEN1 and GEN2 pushbutton switches,

- the OFF Legend of the BA1"1 and BAT2 pushbutton switches,

- the OFF Legend of the GALY 

### &CAB pushbutton switch. (7)On the paneL 22VU, make sure that the FAULT Legend of the BLOWEW and EXTRACT pushbutton switches is off. NOTE That means the eLectronics rack ventiLation operates correctly. (8)On the paneL 35VU, push the BAT1 and BAT2 pushbutton switches:

- the OFF Legends go off. (9)Do the EIS start procedure (Upper ECAM DU and Lower ECAM DU onLy) (Ref. TASK 31-60-00-860-001) (a)On the ECAM controL paneL, push the ELEC key (on the Lower ECAM DU, the ELEC page comes into view). (b)On the ELEC page, make sure that these EXT PWR parameters are correct:

- AC V = 115 + or - 5V,

- FRQ HZ 

# =400 + or - 10HZ. (10) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 24-41-00-862-002 De-energize the Aircraft ELectricaL Circuits SuppLied from the External Power

SeLf ExpLanatory

A. Referenced Information
REFERENCE DESIGNATION
24-41-00-991-001 Fig. 201

Subtask 24-41-00-869-067 A. Not AppLicabLe 4. Procedure Subtask 24-41-00-862-051 A. De-energize the aircraft eLectricaL circuits from the externaL power (1)On the ELEe paneL 35VU, push and release the BAT1 and BAT2 pushbutton switches:

- the OFF Legends come on. (2)On the paneL 35VU, push the EXT PWR pushbutton switch:

- the ON Legend goes off,

- the AVAIL Legend comes on. (3)The aircraft electricaL circuits are correctLy de-energized if: (a)On the paneL 35VU, these Legends go off:

- the FAULT Legend of the GEN1 and GEN2 pushbutton switches,

- the OFF Legend of the BAT1 and BAT2 pushbutton switches,

- the OFF Legend of the GALY and CAB pushbutton switch. (b)On the paneL 108VU, the EXT PWR/NOT IN USE indicator light comes on.

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## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### (Ref. Fig. 201/TASK 24-41-00-991-001) Subtask**24-41-00-080~051** 

### A. Obey the instructions given with the ground power unit and stop the ground power unit.

- On the paneL 35VU, aLL the pushbutton switch legends are off.

- On the paneL 108VU, all the Lights are off. Subtask 24-41-00-020-050 B. Disconnect the connector WARNING DE-ENERGIZE THE ELECTRICAL POWER SUPPLY BEFORE YOU DISCONNECT THE CONNECTOR OF THE GROUND POWER UNIT. IF NOT DANGEROUS ARCING CAN OCCUR. (1)Disconnect the connector of the ground power unit from the external power receptacle. Subtask 24-41-00-080-050 C. Remove the ground support and maintenance equipment, the special and standard tools and all other items. (1)Disconnect the snap hook from the fitting on the aircraft structure. (2) Dieconnect the aircraft electrical ground connector. Subtask 24-41-00-410-051 D. CLose Access (1) CLose the access door 121AL.



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 24-42-00-862-001 De-energize the Ground Service Network Supplied from the ExternaL Power 1. Reason for the Job Self Explanatory

Not Applicable

Subtask 24-42-00-869-058 A. Not Applicable 4. Procedure Subtask 24-42-00-862-054 A. De-energize the ground service network (1)On the front circuit breaker panel 2000VU which is in the middle of the cabin ceiling at the level of the FWD passenger/crew door, put the MAINT BUS switch in the OFF position. (2)On the panel 108VU, the EXT PWR/NOT IN USE indicator light comes on. This shows that the ground service network. is de-energized**correctly~**
Subtask 24-42-00-080-050 A. Obey the instructions given with the ground power and stop the ground power unit:

- on the panel 35VU, the legends of all the pushbutton switches are off,

- on the panel 108VU, all the lights are off. Subtask 24-42-00-020-050 B. Put the aircraft back to its initial configuration.**~AR~!~§** DE-ENERGIZE THE ELECTRICAL POWER SUPPLY BEFORE YOU DISCONNECT THE CONNECTOR OF THE GROUND POWER UNIT. IF NOT DANGEROUS ARCING CAN OCCUR.

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (1) Disconnect the snap hook from connector the suppoof the ground power unit and release the rt. Subtask 24-42-00-410-052 C. Close Access (1) Close the access door 121AL.

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 1. Reason for the Job Self Explanatory

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific circuit breaker(s) safety clip(s) No specific warning notices B. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure 3.**Job_~et-!:!2** Subtask 29-00-00-861-058 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### Subtask 29-00-00-869-073 B. The following panel gives the circuit breakers for all hydraulic systems:

- for the Green hydraulic system use the circuit breakers 1701GK, 1702GK, 3701GD, 3801GX, 3802GX and 3803GX.

- for the Blue hydraulic system use the circuit breakers 2701GJ and 2702GJ,

- for the Yellow hydraulic system use the circuit breakers 3701GD, 3801GX, 3802GX and 3803GX. Subtask 29-00-00-865-066 C. Open, safety and tag this{these)c;rcuit breaker(s):**------~-----------------------------------------------------------------~-----** 

### PANEL DESIGNATION IDENT. LOCATION 49VU HYD/HYD PWR/B WARN/& CTL 2702GJ C12 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 121VU HYDRAULIC/Y HYD/PUMP ENG2/CTL 3701GD Q36 121VU HYDRAULIC/G HYD/PUMP ENG1/CTL 1701GK R35 121VU HYDRAULIC/G HYD/PUMP ENG1/MONG 1702GK R34 123VU B HYD/ELEC PUMP 2701GJ AB09 123VU YHYD/ELEC/PUMP 3802GX AB06 123VU YHYD/ELEC/ELEC PUMP/NORM 3801GX AB03 Subtask 29-00-00-860-050 D. Aircraft Maintenance Configuration (1) For the Green and Yellow hydraulic systems:

- on the overhead panel 40VU, set the PTU pushbutton switch in the OFF position and make sure that the OFF legend comes on. (2)Do the EIS start procedure (Upper ECAM DU and lower ECAM DU onLy) (Ref. TASK 31-60-00-860-001). (3)On the ECAM control panel, puah the HYD key (on the SD, the HYD page comes into view).**~----** 

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## ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL 4. Procedure Subtask**29-00-00~864-058** A. Check of the Depressurization of the Related Hydraulic System (1)Make sure that there is no hydraulic supply from a ground power cart. (2)On the SD, on the HYD page make sure that the pressure of the related hydraulic system shows 0 PSI. Subtask 29-00-00-941-051 B. Installation of the Warning Notices (1 ) Open the access door of the ground service panel related to the hydraulic system:

- the access door 197CB for the Green system,

- the access door 197EB for the Blue system,

- the access door 198CB for the Yellow system. (2)Put the warning notices in position to tell persons not to pressurize the related hydraulic system:

- on the panel 40VU in the cockpit,

- on the ground service panel of the related hydraulic system.

Subtask 29-00-00-865-068 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):**~QTE** : You must do this close-up only when you have completed the work. (1) For the Green hydraulic system 1701GK, 1702GK, 3701GD, 3801GX, 3802GX, 3803GX. (2) For the Blue hydraulic system 2701GJ, 2702GJ. (3) For the Yellow hydraulic system 3701GD, 3801GX, 3802GX, 3803GX.



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# (/$)A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL Subtask 29-00-00-410-064 

### B. CLose Access (1) Remove the warning notice(s). (2) CLose the access door of the reLated ground service paneL:

- for the Green hydraulic system 197CB,

- for the Blue hydraulic system 197EB,

- for the Yellow hydraulic system 198CB. Subtask 29-00-00-860-051 C. Put the aircraft back to the serviceable condition. (1) For the Green and Yellow hydraulic systems:

- on panel 40VU, set the PTU pushbutton switch to the AUTO position and make sure that the OFF legend goes off. (2)Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3)De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862­ 002)•



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## f$JA3181 

# A3191 A320 AIRCRAFT MAINTENANCE MANUAL TASK 29-10-00-863-002 Pressurize the Yellow Hydraulic System**WARNI~§** OBEY THE HYDRAULIC SAFETY PROCEDURES.**~~~NING** MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE AHYDRAULIC SYSTEM. WARNING PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT. CAUTION DO NOT CONNECT GROUND POWER SUPPLIES TO THE GREEN AND YELLOW HYDRAULIC SYSTEMS AT THE SAME TIME. THIS COULD CAUSE:

- THE PTU TO OPERATE TOO FAST

- DAMAGE TO THE PTU IF ONE GROUND POWER SUPPLY IS IN OPERATION AND THE OTHER IS IN THE BY-PASS MODE. 1. Reason for the Job To pressurize the Yellow hydrauLic system (with a ground power supply) for maintenance. NOTE The procedure to pressurize the YeLLow hydrauLic system with the eLectric pump is given in 29-24-00.

A. Referenced Information**--------------------------------------------~----------------------------------** REFERENCE DESIGNATION
12-12-29-611-001 FiLL the HydrauLic FLuid Reservoir with a Hand Pump 12-12-29-611-002 FiLL the HydrauLic Fluid Reservoir with a HydrauLic Service Cart 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power R 29-10-00-864-002 29-14-00-614-001 29-14-00-614-002 Depressurize the Yellow Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### REFERENCE DESIGNATION
29'-23-00-860-001 Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) 29-23-00-860-002 Connection of the Isolation Coupling of the Power Transfer Unit (PTU) 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure 3. Job Set-uf!. Subtask 29-10-00-010-051 A. Open the access door 198CB. Subtask 29-10-00-860-080 B. Aircraft Maintenance Configuration**£~~!!Q~** 

### DO NOT START OR DRY MOTOR THE ENGINES WITH AHYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE ENGINE PUMPS. (1)Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2)Do the EIS start procedure (Upper ECAM DU and Lower ECAM DU only) (Ref. TASK 31-60-00-860-001). (3)On the ECAM control paneL on the center pedestal, push the HYD pushbutton switch (P/BSW). Make sure that the lower (system) dispLay shows the HYD page. R (4) Make sure that the ECAM does not show these warnings: R

- Low air pressure in the Yellow reservoir R

- Low fluid level in the YeLlow reservoir. (5)Obey the subsequent caution: CAUTION : DO NOT CONNECT GROUND POWER SUPPLIES TO THE GREEN AND YELLOW HYDRAULIC SYSTEMS AT THE SAME TIME. THIS COULD CAUSE:

- THE PTU TO OPERATE TOO FAST

- DAMAGE TO THE PTU IF ONE GROUND POWER SUPPLY IS IN OPERATION AND THE OTHER IS IN THE BY-PASS MODE.



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R (6) If you wiLL pressurize the Green hydrauLic system at the same time R with the Yellow hydraulic system through the PTU, the ECAM must not R show these warnings: R

- Low air pressure in the Green reservoir R

- Low fLuid LeveL in the Green reservoir. (7) If necessary, pressurize the reservoirs (Ref. TASK 29-14-00-614-002). (8) If necessary, add fLuid to the applicabLe reservoir (Ref. TASK 12-12­ 29-611-001) or (Ref. TASK 12-12-29-611-002). R R (9) If it is not necessary to pressurize the Green system at the same R time with the YeLLow system: R NOTE Usually the PTU automatically pressurizes the Yellow hydraulic R system at the same time with the Green hydraulic system. If R you pressurize the Yellow system only, then it is necessary to R stop the operation of the PTU. R R (a) On section 40VU of the overhead panel, push the PTU pushbutton R switch. Make sure that the OFF legend comes on. R R (b) Disconnect the PTU isolation coupling (Ref. TASK 29-23-00-860­ 001). R (10) Depressurize the reservoir of the Yellow hydraulic**syst~m** (Ref. TASK R 29-14-00-614-001). R (11) Connect the suction and delivery lines of the hydraulic ground R power-supply to the aircraft ground connectors: R

- 3006GM suction

- 3008GM delivery. R (12) Pressurize the reservoir of the Yellow hydraulic system (Ref. TASK R 29-14-00-614-002).



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## f$;A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL 4. Procedure Subtask 29-10-00-863-051 A. Pressurization with the Hydraulic Ground Power Supply (1) Start the hydraulic ground power supply and pressurize the Yellow system to 3000 psi (206 bar). NOTE If the PTU is not isolated obey the subsequent precautions to prevent damage to the PTU:

- make sure that the air pressure in the Yellow and the Green reservoirs does not fall beLow 3 bar (43.5113 psi)

- Limit the fLow of the ground hydrauLic supply to max 119 l.min (31.4362 USgaL.mn). (2)Refer to the ECAM indication of the YELLOW system pressure and make sure it shows 3000 psi. NOTE If the PTU is not isolated, it pressurizes the Green system at the same time. Usually, the PTU pressurizes the system to a nominal pressure of 3000 psi, but if no consumers operate, the pressure is not constant. The PTU operates in a cycle which keeps the pressure in the Green system between 2400 and 3100 psi.

Subtask 29-10-00-860-055 A. Putthe aircraft back to the serviceable condition. (1) Depressurize the Yellow hydraulic system (Ref. TASK 29-10-00-864­ 002). R (2) Disconnect the hydraulic ground power-suppLy. R (3) On section 40VU of the overhead panel, push the PTU pushbutton R switch. Make sure that the OFF legend goes off. (4) Connect the PTU isolation coupling**(Ref~** TASK 29-23-00-860-002). R (5) Make sure that the fluid leveL in the reservoir of the Yellow R hydraulic system is correct. Add fluid as necessary (Ref. TASK 12-12­ R 29-611-001) or (Ref. TASK 12-12-29,..611-002).



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### ~A318/A319/A320 AIRCRAFTMAINTENANCEMANUAL R (6) If necessary, pressurize the reservoir of the Yellow hydraulic system R (Ref. TASK 29-14-00-614-002). R (7)Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). R (8) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 29-10-00-410-051 B. Close theaccess door 198CB.



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## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL**~~IN HY~RAULI£_~OWER**  - MAINTENANCE PRACTICES TASK 29-10-00-864-001 Depressurize the Green Hydraulic System WARNING OBEY THE HYDRAULIC SAFETY PROCEDURES. WARNING MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE AHYDRAULIC SYSTEM.

To make sure that the Green hydraulic system is depressurized before wofk is done on the system. 2.**l~~~~t-uE** Information A. Referenced Information
REFERENCE DESIGNATION
29-23-00-860-001 Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) 29-23-00-860-002 Connection of the Isolation Coupling of the Power Transfer Unit (PTU) 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure 32-12-00-010-001 Open the Main Gear Doors for Access 32-12-00-410-001 Close the Main Gear Doors after Access 3. Job**~et-!:!E** Subtask 29-10-00-860-050 A. Aircraft Maintenance Configuration (1)Stop any supply of hydraulic power to the Green and Yellow hydraulic systems through the ground connections. (2)Open one of the main**doo~s** of the main landing gear (Ref. TASK 32-12­ 00-010-001). NOTE You can open anyone of the two doors, but access is better from the right side.



# r=--------------------------------­ 

# 29-10-00 Page 201 

### IEFF: ALL Feb 01/01 F90109 FFT Printed in FranceTHIS DOCUMENT MAY CONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (3) Disconnect the PTU isolation coupling (Ref. TASK 29-23-00-860-001). NOTE If necessary, you can now pressurize the Yellow hydraulic system. (4) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001). (5) On the ECAM control panel pushbutton switch (P/BSW) shows the HYD page. on the

. Make center pedestal, push the HYD sure that the lower (system) display
4. Procedure Subtask 29-10-00-864-051-A A. Depressurization NOTE When the hydraulic pressure supply stops, the pressure decreases quickly to approximately 700 psi I 50 bar. From this value the R pressure decreases very slowly to zer6 (approximately 15 minutes). (1)Refer to the ECAM indication of the GREEN system pressure and make sure that it shows O.**WARNI~!** MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND

### lOR DAMAGE. (2)If the ECAM indication of the GREEN system pressure does not show 0, operate the rudder to reduce the pressure to zero.

Subtask 29-10-00-860-051 A. Putthe aircraft back to the serviceable condition. (1)Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2)Connect the PTU isolation coupling (Ref. TASK 29-23-00-860-002). (3)Close the main door of the main landing gear (Ref. TASK 32-12-00-410­ 001).

## F;-;--~~~-------------l 

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# I May 01102 IFFT F90110 Printed in France

## ---------- THIS DOCUMENTMAYCONTAIN TRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATION ACT, 5 U.S.C. § 552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAl TASK 29-10-00-864-002 Depressurize the Yellow Hydraulic System**~~~~!~~** OBEY THE HYDRAULIC SAFETY PROCEDURES. WARNING



## ----­ MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE AHYDRAULIC SYSTEM. 1. Reason for the Job To make sure that the Yellow hydraulic system is depressurized before work is done on the system.

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTYDESIGNATION
No specific circuit breaker(s) safety clip(s) B. Referenced Information
REFERENCE DESIGNATION
29-23-00-860-001 Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) 29-23-00-860-002 Connection of the IsoLation CoupLing of the Power Transfer Unit (PTU) 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure 32-12-00-010-001 Open the Main Gear Doors for Access 32-12-00-410-001 CLose the Main Gear Doors after Access

1 

# 29-10-00 Page 203 

# F ALL Feb 01/01 F90111 \FFT Printed in France

# ------------------------------------------------------------------------------- THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIALCOMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

Subtask 29-10-00-860-052 A. Aircraft Maintenance Configuration (1)Stop any supply of hydraulic power to the Yellow and Green hydraulic systems through the ground connections. (2) If the Yellow electric pump is in operation:

- in the flight compartment (on section 40VU of the overhead panel) push and release the YELLOW ELEC PUMP pushbutton switch. (3)Make sure that the ON legend goes off. (4) Open one of the main doors of the main landing gear (Ref. TASK 32-12­ 00-010-001). NOTE You can open anyone of the two doors, but access is better from the right side. (5) Disconnect the PTU isolation coupling (Ref. TASK 29-23-00-860-001). NOTE If necessary, you can now pressurize the Green hydraulic system. (6)Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001). (7)On the ECAM control panel on the center pedestal, push the HYD pushbutton switch (P/BSW) • Make sure that the lower (system) display shows the HYD page. Subtask 29-10-00-865-053 B. Open, safety and tag this(these) circuit breaker(s):
PANEL DESIGNATION !DENT. LOCATION 

# -----------------------------------------------------------.-------------------­ R 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 123VU YHYD/ELEC/PUMP 3802GX AB06 123VU YHYD/ELEC/ELEC PUMP/NORM 3801GX AB03



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### ALL 

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### Hay 01/01 

## I FFT F90112 Printed in France

## ---

----- THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

# f$pA3181 A3191 A320 AIRCRAFT MAINTENANCE MANUAL



### R **ON A/C 201-299, 801-899, 936-999,
Subtask 29-10-00-864-050-8 A. Depressurization**l!!~RNING** 

### MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS

.AND/OR DAMAGE. (1)Refer to the ECAM indication of the YELLOW system pressure and make sure that it shows O. (2) If the ECAM indication of the YELLOW system pressure does not show 0, operate the rudder to reduce the pressure to zero. (3)If you wiLL work on the auxiLiary/parking brake systems: WARNING MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. (a) Set the Anti-Skid and Nose WheeL switch to OFF. (b) Operate the manuaL depressurization button on the brake relief valve 3067GM to reLease the pressure. (c) Set the PARKING BRK switch to ON. (d) Make sure that the tripLe gage shows indicators. zero pressure on aLL three
**ON A/C 901-935,
Subtask 29-10-00-864-050-A A. Depressurization NOTE When the hydraulic pressure suppLy stops, the pressure decreases quickly to approximateLy 700 psi / 50 bar. From this value the pressure decreases very sLowLy to zero (approximateLy 15 minutes). (1) Refer to the ECAM indication of the YELLOW system pressure and make sure it shows O. WARNING MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR**DAMAGE~ ~---------------------**  

# 29-10-00 Page 205 IEFF: ALL Nov 01/07 

# I F90113 

### \FFT Printedin France

## ------ THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (2) If the ECAM indication of the YELLOW system pressure does not show 0, operate the rudder to reduce the pressure to zero. WARNING MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. (3)If you wiLL work on the auxiLiary/parking brake systems: (a)Operate the manuaL depressurization button on the brake relief vaLve 3067GM to reLease the pressure. (b)On paneL 110VU of the center pedestaL, operate the PARKING BRK switch and refer to the triple gage on paneL 400VU. (c)Set the PARKING BRK switch to ON. (d)Make sure that the triple gage shows zero pressure on aLL three indicators. **ON A/C ALL
5. Close-u,2 Subtask 29-10-00-865-050 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 3801GX, 3802GX, 3803GX. Subtask 29-10-00-860-053 B. Put the aircraft back to the serviceable condition. (1)Connect the PTU isolation coupling (Ref. TASK 29-23-00-860-002). (2) Close the main door of the main landing gear (Ref. TASK 32-12-00-410­ 001). (3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).



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F90114 Printed in France

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## -----

-----

-----



# ------------- THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATION ACT, 5 U.S.C.§ 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL POWER TRANSFER

- MAINTENANCE PRACTICES TASK 29-23-00-863-001 Pressurize the Green Hydraulic System from the YeLlow Hydraulic System through the PTU with the ELectric Pump WARNING MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE AHYDRAULIC SYSTEM. WARNING PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT. CAUTION DO NOT OPERATE THE ELECTRIC PUMP OR THE PTU IF THE SUPPLY OF HYDRAULIC FLUID IS NOT SUFFICIENT. MAKE SURE THAT THE RESERVOIRS HAVE SUFFICIENT AIR PRESSURE BEFORE YOU OPERATE THE PUMP/PTU. 1. Reason for the Job Self Explanatory 

### 2. Job Set-ue**Infor~~~iQ~** A. Referenced Information
REFERENCE DESIGNATION
12-12-29-611-001 Fill the Hydraulic Fluid Reservoir with a Hand Pump 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 29-00-00-910-002 Safety Procedures of the HydrauLic System 29-14-00-614-002 Pressurization of the Hydraulic Reservoirs through the Ground Connector 31-60-00-860-001 EIS Start Procedure 32-12-00-010-001 Open the Main Gear Doors for Access 29-23-00-991-001 Fig. 201

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# 29-23-00 Page 201 

## IEFF ALL Feb 01/01 

## I F90115 \FFT Printed in France

## ----- THIS DOCUMENT MAY CONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 3. Job Set-u2 Subtask 29-23-00-860-053 A. Aircraft Maintenance Configuration WARNING : OBEY THE HYDRAULIC SAFETY PROCEDURES. (1)Obey the hydraulic safety procedures (Ref. TASK 29-00-00-910-002). (2)Open the main doors of the main Landing gear (Ref. TASK 32-12-00-010­ 001). (3)Make sure that the isoLation coupLing of the Power Transfer Unit (PTU) is connected. (4)Energize the electricaL circuits (Ref. TASK 24-41-00-861-002). (5) Do the EIS start procedure (Upper ECAM DU and Lower ECAM DU onLy) (Ref. TASK 31-60-00-860-001). (6)On the ECAM control paneL on the center pedestaL, press the HYD pushbutton switch (P/BSW). Make sure that the HYD page is shown on the ECAM Lower DU. (7)Make sure that the ECAM does not show any of these conditions:

- Green or Yellow reservoir, low air pressure,

- Green or Yellow reservoir, low fluid contents. (8) If necessary, pressurize the reservoir (Ref. TASK 29-14-00-614-002). (9) If necessary, add fluid to the reservoir (Ref. TASK 12-12-29-611­ 001)

. (10)On the panel 400VU make sure that the landing gear lever is in the DOWN position. (11) On the panel 40VU make sure that the PTU P/BSW is set to AUTO. 

# l 29-23-00 Page 202 

### Feb 01/01

F90116 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### Subtask 29-23-00-865-050 B. Make sure that this(these) circuit breaker(s) is(are) cLosed:
PANEL DESIGNATION IDENT. LOCATION R 

### 121VU HYDRAULIC/HYD POWER/Y 123VU YHYD/ELEC/PUMP 123VU YHYD/ELEC/ELEC PUMP/NORM 3803GX 3802GX 3801GX N30 AB06 AB03 R


### (Ref. Fig. 201/TASK 29-23-00-991-001) Subtask 29-23-00-863-052 A. Pressurization of the Green Hydraulic System from the YeLlow Hydraulic System through the PTU with the ELectric Pump (1)On the paneL 40VU push the YELLOW ELEC PUMP P/BSW. (2)Make sure that the ECAM lower DU shows:

- the correct operation of the PTU,

- that the pressure of the YeLLow hydrauLic system is 3000 psi approximately,

- the pressure of the Green**hydra~lic** 

### system is 3000 psi approximateLy. NOTE The PTU pressurizes the system to a nominaL pressure of 3000 psi, but if no consumers are operated the pressure is not constant. The PTU operates in a cycLe which keeps the pressure in the Green hydrauLic system between 2100 and 3150 psi.



# l 29-23-00 Page 203 ALL May 01/01
F90117 

## I Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL ORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

HYO SYSTEM IDENTIFICATION-+-+--GREEN BLUE

## ~ PSI

ELEC.....-+-+-PTUSTATUS ACTUALSYSTEM PRESSURE

### -+-+-- 3000 PSI ISO PSI INCREMENTSI PTU 

# ,..,..--I I AUXILIARY (ELEel PUMP /tISTATUS

G.W.60300KG C.G.21I.1%

SYSTEM DISPLAY
EXPLANATIONOF PTU STATUSSYMBOLS

### ~- I_.-'1 PTU [> 

# I {GREEN-PTU PIB SWAUTOAND PrU NOTSUPPLYING**~** AMBER-PTU PtsSW OFF 

### .1_ I-­

__ ..**I--~** PTU**~ ~**  {GREEN)-PTUSUPPLIES GREEN HYDRAULICSYSTEM h!2I§.; THISSYMBOLALSOAPPEARS ON THE GROUNDWHEN THE 

### . I---... 

### -J 

# 1--_..--.....,..-.... PrU......-, GREEN SYSTEMONLI( ISSUPPLIED FROMA GROUND SUPPLI( ANDTHE PTU IS SETTO AUTO (GREEN)
- PruSUPPLIESYELLOW HYDRAULICSYSTEM

ECAM Lower DU during Power Transfer

Figure 201/TASK 29-23-00-991-001 

# -------,**r;;-:---~LL** 

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### feb 01/01 

### /FFT J 

# I F90118 Printed in France

## ----



# ---- THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. §552(b)(4). 

# f!;A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL 

### YELLOW**~~XILIARY** 

### HYDRAULIC POWER (§.!:.§.£lRIC/HAND**P~MPS)-=-.!!~!.NTENANCE** 

### PRACTICES TASK 29-24-00-863-001 Pressurize the YeLLow HydrauLic System with the ELectric Pump WARNING MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE AHYDRAULIC SYSTEM. WARNING PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT.

To pressurize the YeLLow hydrauLic system with the YeLlow electric pump, for maintenance procedures. 

### 2.**~ob Set-~nformation**  

### A. Referenced Information**---------------------------------------------~-------- ------------------------**  

### REFERENCE DESIGNATION
12-12-29-611-001 Fill the HydrauLic Fluid Reservoir with a Hand Pump 24-41-00-861-002 Energize the Aircraft ElectricaL Circuits from the External Power 29-14-00-614-002 Pressurization of the HydrauLic Reservoirs through the Ground Connector 29-23-00-860-001 Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) 31-60-00-860-001 EIS Start Procedure 29-24-00-991-001 Fig. 201

Subtask 29-24-00-860-052 A. Aircraft Maintenance**Configu~ation** 

### (1) Energize the aircraft eLectrical circuits (Ref. TASK 24-41-00-861­ 002)• (2)

### Set the Electronic CentraLized Aircraft Monitor (ECAM) to on (Ref. TASK 31-60-00-860-001).



### r 

# ---, 29-24-00 Page 201 IEFF ALL Feb 01/01 F90119 \ 

### IFFT Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT. 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (3) On the ECAM control panel on the center pedestal, push the HYD pushbutton switch (P/BSW). Make sure that the ECAM lower Display Unit (DU) shows the HYD page. (4)Make sure that the ECAM does not show any of these conditions:

- Low air pressure in the Yellow reservoir,

- Low fluid level in the reservoirs. (5) In addition, if you will operate the PTU, make sure that these conditions are also not shown on the ECAM:

- Low air pressure in the Green reservoir,

- Low fluid level in the Green reservoir. (6) If necessary, pressurize the reservoir(s) (Ref. TASK 29-14-00-614­ 002)• (7) If necessary, add fluid to the reservoir(s) (Ref. TASK 12-12-29-611­ 001). Subtask 29-24-00-865-050 B. Make sure that this(these) circuit breaker(s) is(are) closed:
PANEL DESIGNATION IDENT. LOCAnON R 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 123VU YHYD/ELEC/PUMP 3802GX AB06 123vu YHYD/ELEC/ELEC PUMP/NORM 3801GX AB03



## r------------------------

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# 1

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### 01/01 

## IFFT 

# I

F90120 Printed in France

# -

-------- THIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL
4. Procedure (Ref. Fig. 201/TASK 29-24-00-991-001) Subtask 29-24-00-863-050 A. Pressurization with the ELectric Pump (1) If it is necessary to use the Yellow hydraulic system only, continue as follows: NOTE Usually the PTU automatically pressurizes the Green hydraulic system together with the YelLow hydraulic system. If you pressurize the YelLow system only,then it is necessary to stop the operation of the PTU. (a) Disconnect the isolation coupLing of the Power Transfer Unit (PTU) (Ref. TASK**29-23-00-860~001)** NOTE Disconnection of the isoLation coupLing is onLy necessary if the system on the opposite side is disconnected for maintenance. (b) Press and reLease the PTU/AUTO pushbutton switch 1802GL on the overhead panel 40VU. (c)Make sure that the OFF legend comes on. (2)On the overhead panel 40VU, push and reLease the YELLOW ELEC PUMP pushbutton switch 3804GX. (3) Make sure that the ON legend comes on. (4)Make sure that the Yellow eLectric pump starts. (5) On the Lower DU of the ECAM, make sure that the YELLOW hydrauLic system has a pressure of approximateLy 3000 psi. NOTE If the ECAM system is not availabLe, you can check the pressure of 3000 +1-100 psi on the Yellow power accumuLator (3070GM)•



# 29-24-00 Page 203 ALL Feb 01/01 

# 1 F90121 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL

OIl!IH (l)

It V 0 RATMANON 

# [j NGIPUMI'

OFF OVERHEAD PANEL

HYD CReeN II.UI

<j\ <j\ SYSTEM 0000 PSI 0000 PRESSURE

RATI> nle 2

TAT +I"e G.W.S0300KG SAT<18"C Utile CoG. 28 I" 8

SYSTEM DISPLAY-HYDRAULIC PAGE SHOWN WITH PTU ISOLATED 

# (
PUSHBUTTON PUSHBUTTON

SWITCH SWITCH 1802GL 3804GX

YILI.OW

<j\ PIli 3000

TAT••aoc SAT+111"1;

SYSTEM DISPLAY-HYDRAULICPAGE SHOWN WITH PTU CONNECTED
Indications and Controls of the Yellow Hydraulic System Figure 201/TASK 29-24-00-991-001
ALL 

# 29-24-00 Page 204 Feb 01/01

F90122 Printed in FranceTHIS DOCUMENTMAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFTMAINTENANCEMANUAL NOTE To prevent a possibLe overheating of the hydraulic fLuid, operate the electric pump onLy as long as it is necessary to do your maintenance procedure.



### r----­ 

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## IEFF ALL 

# I Feb 01/01 F90123 

## IFFT \ Printed in France

# ------------ THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL**WHEE~~~~649§~L2650GML2651GM,~~~2GM)** - REMOVAL/INSTALLATION TASK 32-41-11-000-006 Removal of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) CAUTION MAKE SURE THAT THE ITEMS IN THE "FIXTURES, TOOLS, TEST AND SUPPORT EQUIPMENT" PARAGRAPH ARE APPLICABLE TO YOUR AIRCRAFT (THIS LIST IS NOT CUSTOMIZED). REFER TO THE APPLICABLE SUBTASKS. 1. Reason for the Job SeLf Explanatory 2. Job Set-up Information A. Fixtures, TooLs, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific safety barriers R No specific standard wheel R

### &I dolly No specific warning notice F46754-1000 PROTECTOR R H47682 ADAPTOR-MLG B. Consumable Materials
REFERENCE DESIGNATION
Material No. 04-004A INFORMATION TRANSFERRED TO 04-022 (Ref. 20-31-00) C. Referenced Information
REFERENCE DESIGNATION
07-12-00-582-002 Jacking for Main Gear WheeL Change 29-10-00-863-002 Pressurize the YeLlow Hydraulic System 32-41-00-210-003 Inspection/Check of the Pressure of Tires 32-41-11-991-010 F;g.401

IEFF ALL I 

# , 

# 32-41-11 Page 401 

## I Aug 01/07 

# IFFT 

# I
F90124 Printed in France

## ----- THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

## f$)A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL 3. Job Set-up Subtask 32-41-11-941-076 A. Safety Precautions (1) Put the safety barriers in position. (2)Put the warning notice in the cockpit to tell persons not to operate the landing gear. (3)Make sure that the wheel chocks are in position. Subtask 32-41-11-860-085 B. Aircraft Maintenance Configuration (1)Make sure that the PARK BRK control switch is set to ON. NOTE On the panel 400VU, make sure that the brake pressure indication on the Yellow brake-pressure triple indicator is correct. If necessary, pressurize the brake accumulator with the Yellow pump (Ref. TASK 29-10-00-863-002). R (2) Jacking for main gear wheel change. R WARNING MAKE SURE THAT THE AIRCRAFT IS STABLE AND DOES NOT MOVE R DURING JACKING OPERATIONS. R IF THE AIRCRAFT MOVES (GATE**DOCKING~** PASSENGER/FREIGHT R LOADING, ETC) THERE IS ARISK OF INJURY TO PERSONNEL AND/OR R DAMAGE TO THE AIRCRAFT. R**£~UTIO~** DURING REFUELING OR DEFUELING PROCEDURES, DO NOT DO THIS R JACKING FOR WHEEL CHANGE PROCEDURE. IF THE AIRCRAFT IS ON R JACKS AND IF A FIRE OR IMPORTANT FUEL SP1LLAGE OCCURS, IT R WILL NOT BE POSSIBLE TO MOVE THE AIRCRAFT. R (a) Lift the related axle with a jack (Ref. TASK 07-12-00-582-002). (3) FuLly deflate the tire. NOTE If you must remove the wheel for access or inspections, it is not necessary to deflate the tire if:

- The tire is in the correct condition

- The tire pressure is in the normal operating range (Ref. TASK 32-41-00-210-003).

r---­ 

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## IEFF ALL Aug 01/07 

## I F90125 

### \ \FFT Printed in France

## ----

----**---------~------.--------.** THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL If you have not these two conditions, you must deflate the tire. 4. Procedure (Ref. Fig. 401/TASK 32-41-11-991-010) Subtask 32-41-11-020-061 A. Preparation of the Wheel Before Removal (1)Loosen the screw (9) and remove the clamp (12). (2)Remove the hubcap (11). NOTE Remove the hubcap aLong the centerLine of the wheeL axle to prevent damage to the tachometer drive shaft. Subtask 32-41-11-020-068 B. Removal of the WheeL WARNING BE CAREFUL WHEN YOU REMOVE/INSTALL THE WHEEL AND TIRE ASSEMBLY TO PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE WHEEL, AXLE OR OTHER EQUIPMENT. THE ASSEMBLY IS VERY HEAVY (BETWEEN 130 KG AND 200 KG (290 LBS AND 440 LBS». CAUTION MAKE SliRE THAT THE AXLE THREAD PROTECTOR IS CORRECTLY INSTALLED ON THE AXLE. YOU CAN CAUSE DAMAGE TO THE AXLE SLEEVE WHEN YOU REMOVE/INSTALL AWHEEL IF THE AXLE THREAD PROTECTOR IS: -NOT USED. -NOT FULLY ENGAGED ON THE AXLE. (1)Remove and discard the cotter pin (4). (2) Remove the nuts (5), the washers (6) and the boLts (8). R (3) Remove the axle nut (1) with the ADAPTOR-MLG (H41682). (4)Install the PROTECTOR (F46154-1000). (5)Apply a thin layer of COMMON GREASE (Material No. 04-004A) on the axle protector. R (6) Put a standard wheeL R

### &I dolly below the wheeL.



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE

### MANUAL

0 0 0 :::iE**~** '01' .,... .,... ':t 14 C\I C'l U') ::! Z 11 10 Main Gear Wheel Figure 401/TASK 32-41-11-991-010 

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Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R (7) Remove the wheel (1).



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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-41-11-400-006 Installation of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) WARNING YOU MUST NOT PUT TOO MUCH GREASE ON THE AXLE SLEEVE. AVERY HOT BRAKE CAN CAUSE THE GREASE TO BURN AND CAUSE AFIRE.**£~~TION** MAKE SURE THAT THE ITEMS IN THE "FIXTURES, TOOLS, TEST AND SUPPORT EQUIPMENT" PARAGRAPH ARE APPLICABLE TO YOUR AIRCRAFT (THIS LIST IS NOT CUSTOMIZED). REFER TO THE APPLICABLE SUBTASKS.

Self Explanatory 2.**Jo~Set~nformation** A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION**-----------------------------------------------~------------------------------** R

R No specific No specific No specific No specific H47682 standard wheeL Torque Wrench Torque Wrench Torque Wrench ADAPTOR-MLG R

### &I doLLy range range range 0.00 to 1.20 m.daN (0.00 to 9.00 Lbf.ft) 6.00 to 36.00 m.daN (50.00 to 260.00 lbf.ft) 15.00 to 82.00 m.daN (120.00 to 600.00 lbf.ft)

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## I F90129 IFFT Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL B. Consumable Materials
REFERENCE
R Material No. 04-003 Material No. 04-004
MateriaL No. 04-022
MateriaL No. 04-035 MateriaL No. 11-002

C. Expendable Parts
FIG.ITEM 

### IDESIGNATION

4 cotter pins DESIGNATION
USA SAE AMS 2518 GRAPHITED PETROLATUM THREAD COMPOUND (Ref. 20-31-00) USA MIL-PRF-23827 TYPE SYNTH.ESTER BASED GREASE (Ref. 20-31-00) USA MIL-PRF-81322 SYNTHE.HYDROCARBON GREASE (Ref. 20-31-00) I HIGH PRESSURE

HIGH PRESSURE
SYNTHETIC WHEEL BEARING GREASE (Ref. 20-31-00) USA MIL-PRF-680 DRY CLEANING SOLVENT (VARSOL/WHITE SPIRIT) (Ref. 20-31-00)

IIPC-CSN
32-11-13 01E-200 D. Referehced Information
REFERENCE
07-12-00-582-002 12-14-32-614-001 29-10-00-863-002 32-41-00-210-003 32-41-00-910-001 32-42-27-000-001 32-42-27-210-006 32-42-27-400-001 32-41-11-991-010 DESIGNATION Jacking for Main Gear WheeL Change Nitrogen Filling of the Tires Pressurize the YelLow HydrauLic System Inspection/Check of the Pressure of Tires Tire MixabiLity Precautions Removal of the Brake (2641GM,2642GM,2643GM,2644GM) Inspection/Check of the Brake with the Wheel Removed InstaLLation of the Brake (2641GM,2642GM,2643GM,2644GM) Fig. 401



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## I 

# I Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 3. !l.ob**~et-!:!2** Subtask 32-41-11-941-077 A. Safety Precautions (1)Make sure that the safety barriers are in position. (2)Make sure that the warning notice is in position in the cockpit to teLL persons not to operate the landing gear. (3)Make sure that the wheeL chocks are in position. Subtask**32-41-11~860-086** B. Aircraft Maintenance Configuration (1)Make sure that the PARK BRK control switch is set to ON. NOTE On the panel 400VU, make sure that the brake pressure indication on the Yellow brake-pressure triple indicator is correct. If necessary pressurize the brake accumulator with the YeLlow pump (Ref. TASK 29-10-00-863-002). (2)Make sure that the related axle is lifted with a jack (Ref. TASK 07­ 12-00-582-002).
(Ref. Fig. 401/TASK 32-41-11-991-010) NOTE If the wheeL has a pressure-sensor seal cap, make sure that the seal cap is correctly instaLled and safetied with a nut and a cotter pin. Subtask 32-41-11-210-054 A. Tires of Different Type (1) Obey the tire mixability precautions (Ref. TASK 32-41-00-910-001).

## f;-;---~LL------------------' 

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## I 

# I F90131 

## IFFT 

## I Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-41-11-560-060 B. Preparation of the WheeL before InstalLation CAUIION MAKE SURE THAT THE GREASE USED FOR THE AXLE SLEEVE IS THE SAME AS THE GREASE USED FOR THE BEARINGS (CONE AND CAGE). IF YOU USE ADIFFERENT GREASE, YOU CAN CAUSE DAMAGE TO THE BEARINGS. (1)Make sure that the wheeL for installation has the same type of tire (radial or cross-pLy) as the other wheeL on the MLG. (2)Make sure that the parts retained from the removed component are cLean and in the correct condition. (3) CLean the component interface and/or the adjacent area. (4) Do an inspection of the component interface and/or the adjacent area. (5)Remove brake dust. (6)Do an inspection of the brake with the wheeL removed (Ref. TASK 32­ 42-27-210-006). NOTE If the brake is unserviceabLe you must replace it (Ref. TASK 32-42-27-000-001) and (Ref. TASK 32-42-27-400-001). (7)Make sure that the driving keys on the brake rotors are correctly aligned. (8)Make sure that the spLines of the tachometer drive shaft (13) and the splines (10) of the hubcap (11) are in the correct condition. NOTE: Ifyou find wear, replace the related parts. (9)Clean the axle sleeve (2) with CLEANING AGENTS (MateriaL No. 11-002) and dry it with fiLtered compressed air. (10) Do a visual inspection of the axLe protective sleeve to make sure that it is in the correct condition. (11)Make sure that the retaining ring (3) of the axle sleeve (2) is in the correct position. The ring must be correctly engaged in its groove. If not, the axle sLeeve is not installed correctLy and you can damage it when you instaLL the axle nut. (12)CLean the splines (11) of the tachometer hubcap (10) and the spLines of the tachometer drive shaft (13) with CLEANING AGENTS (Material No. 11-002) and dry with filtered compressed air. (13)Apply a thin Layer of COMMON GREASE (Material No. 04-003) on the spLines (10) and on the spLines of the tachometer drive shaft (13).



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# IFFT F90132 Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R (14) Apply a thin layer of COMMON GREASE (Material No. 04-004) or COMMON R GREASE (Material No. 04-022) or COMMON GREASE (Material No. 04-035) R to the axle sleeve (2).**~~R~ING** YOU MUST NOT PUT TOO MUCH GREASE ON THE AXLE SLEEVE. AVERY HOT BRAKE CAN CAUSE THE GREASE TO BURN AND CAUSE A FIRE. R NOTE You can use Material No. 04-004 as an alternative to Material R No. 04-022 or to Material No. 04-035. It ;s not permitted to R mix Material No. 04-004 with Material No. 04-022 or with R Material No. 04-035. It ;s necessary to clean and degrease the R parts before you use an alternative grease. R R (15) Apply COMMON GREASE (Material No. 04-004) or COMMON GREASE (Material R No. 04-022) or COMMON GREASE (Material No. 04-035) to the threads of R the axle. R R NOTE You can use MateriaL No. 04-004 as an aLternative to Material R No. 04-022 or to MateriaL No. 04-035. It is not permitted to R mix Material No. 04-004 with Material No. 04-022 or with R MateriaL No. 04-035. It is necessary to cLean and degrease the R parts before you use an aLternative grease. (16) Clean the inner surface of the wheel bearings (surface that touches the axLe). Do not apply grease on these surfaces. Subtask 32-41-11-420-061 C. InstaLLation of the WheeL WARNIN§BE CAREFUL WHEN YOU REMOVE/INSTALL THE WHEEL AND TIRE ASSEMBLY TO PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE WHEEL, AXLE OR OTHER EQUIPMENT. THE ASSEMBLY IS VERY HEAVY (BETWEEN 130 KG AND 200 KG (290 LBS AND 440 LBS». CAUTION MAKE SURE THAT THE AXLE THREAD PROTECTOR IS CORRECTLY INSTALLED 

### ---.----­ ON THE AXLE. YOU CAN CAUSE DAMAGE TO THE AXLE SLEEVE WHEN YOU REMOVE/INSTALL AWHEEL IF THE AXLE THREAD PROTECTOR IS: -NOT USED. -NOT FULLY ENGAGED ON THE AXLE. (1)Use the standard wheeL R

### &I doLly to align the wheeL (1) with the driving keys on the brake rotors. (2) Push the wheeL (1) fully on the axle. (3)Remove the PROTECTOR (F46754-1000).
r-­ 

# 32-41-11 Page 410 [EFF ALL Nov 01/07 [ F90133 

## \FFT Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C.§ 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R (4) Install the axle nut (7) on the axle and tighten it with the ADAPTORR MLG (H47682). R (5) In the cockpit, set the PARK BRK control switch to OFF. R (6) Turn the wheel in the direction of the axle nut rotation and TORQUE the axle nut (7) to 40.7 m.daN (300.14 lbf.ft). R (7) Prevent the rotation of the wheel and loosen the axle nut (7) to zero torque. R (8) Turn the wheel in the direction of the axle nut rotation and TORQUE the axle nut (7) to 20.3 m.daN (149.70 lbf.ft). R (9) Tighten the axle nut (7) until the holes in the nut are aligned with the holes in the axle. R (10) Install the bolts (8), the washers (6) and the nuts (5). NOTE: Install the heads of the bolts (8) in the axle. R (11) TORQUE the nuts (5) to between 0.4 and 0.45 m.daN (35.39 and 39.82 lbf.in). R (12) InstalL the new cotter pins (4). R (13) Turn the wheel manually to make sure that it is installed correctly. Subtask 32-41-11-420-062 D. Installation of the Hubcap (1)Install the hubcap (11) carefully in the tachometer drive shaft (13). NOTE Use the locating pin (14) to put the hubcap (11) in the correct position. This locks the shroud so that it cannot turn on the wheel. (2)Install the clamp (12). (3)TORQUE the screw (9) to between 0.28 and 0.34 m.daN (24.77 and 30.08 lbf.in).



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## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

Subtask 32-41-11-860-087 A. Aircraft Maintenance Configuration (1)If applicable inflate the tire to the unloaded pressure (Ref. TASK 12-14-32-614-001). (2) Lower the aircraft on its wheeLs (Ref. TASK 07-12-00-582-002). (3) Do a check of the pressure of the tire (Ref. TASK 32-41-00-210-003). (4)Make sure that the work area is cLean and cLear of**tooL(~)** and other items.



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F90135 

# IFFT 

# I Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4). 

## f!;A318f A319f 

# A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-42-00-040-002 Deactivation of the Normal Supply Braking

- With disconnection of the Green Hydraulic
1. Reason for the Job



## ---------­ Refer to the MMEL TASK: 32-42-02 Normal Braking

- Green Brake System

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNAlION
No specifi c self-adhesive fabric tape No specific temporary placard No specific vinyl hose No specifi c warning notice(s) No specific container 5 l (1.3208 USgaL) B. Consumable MateriaLs
REFERENCE DESIGNATION

R No specific Material No. 02-003 corrosion resistant steeL Lockwire dia 0.8 F NSA 307110 TYPE 4 HYDRAULIC FLUID (PHOSPHATE ESTER BASE) (Ref. 20-31-00) mm

I 

# ------, 32-42-00 R IEFF ALL Page 412 Feb 01/05

F90136 FFT 

# I Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSANDCONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U,S.C. §552(b)(4). 

# f$)A3181A3191A320 AIRCRAFT MAINTENANCE·MANUAL C. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-002 Energize the Aircraft ELectricaL Circuits from the ExternaL Power 24-41-00-862-002 De-energize the Aircraft ELectricaL Circuits SuppLied from the ExternaL Power 29-10-00-864-001 Depressurize the Green HydrauLic System 29-23-00-863-001 Pressurize the Green HydrauLic System from the YeLLow HydrauLic System through the PTU with**th~** ELectric Pump 32-42-00-991-004 Fig. 403

Subtask 32-42-00-941-056 A. SafetyPrecautions (1)Put the warning notice(s) in position to teLL persons not to operate the Landing gear controL Lever and the brake pedaLs. Subtask 32-42-00-860-074 B. Aircraft Maintenance Configuration (1)Depressurize the Green hydrauLic system (Ref. TASK 29-10-00-864-001). (2)Make sure that the PARKING BRK controL-switch is set to OFF before you do this procedure. CAUTION : MAKE SURE THAT ALL THE PISTONS OF THE BRAKE ARE IN THE RELEASED POSITION. (3)Energize the aircraft eLectricaL circuits (Ref. TASK 24-41-00-861­ 002)•



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# f$)A3181 A3191 A320 AIRCRAFT MAINTENANCE MANUAL

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# I F90138 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHEFREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

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R**~-----------------** 

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F90140 

# IFFT I Printed in FranceTHIS DOCUMENTMAY CONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALORFINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### Subtask 32-42-00-865-057 C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 4. Procedure (Ref. Fig. 403/TASK 32-42-00-991-004) Subtask 32-42-00-040-054 A. Deactivation with isolation of the Green hydraulic supply (1)Loosen the knurled sleeve (2) of the Green half-coupling (1). Turn and disconnect the coupling. (2)Clean the knurled sleeve (2). Apply 2 or 3 turns of the self-adhesive fabric tape (20 mm (0.7874 in.) to 30 mm (1.1811 in.» to the sleeve (1)• 

### (3)Tightly wind 3 or 4 turns of the corrosion resistant steel lockwire dia 0.8 mm around the middle of the sleeve (2) with the tape. (4)Twist the lockwire and put it through the nearest locking hole you can get access to in the hexagonal head of the fixed half-coupling (1). Tighten the lockwire and twist it. (5) Remove the bleed screw plug (4) from the bleed screw (3). (6)Connect a vinyl hose to the related bleed screw and put the other end in a container that contains HYDRAULIC FLUIDS (Material No. 02-003). (7)Slowly loosen the bleed screw (3) to release hydraulic residual pressure from the brake. (8)Tighten**~he** 

### bleed screw (3). (9) Disconnect the vinyl hose. (10) Install the bleed screw plug (4) on the bleed screw.

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# f$)A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL

NOTE: THE GREEN HYDRAUUC CONNECTION ONTHE BRAKE UNR'S ISA1.WAYS IN FRONTOFTHE LEG GEAR.



## 1 2842GM

## 1-,....",'""IIo..JiIP

....I"""IL

WHEELSIDE
---YEU.OWPRESSURE

GREEN PRESSURE
LEG GEARSIDE

BRAKETEMPERATURE**l.-=":":-~--** SENSOR ELEC'IRIC CONNECTION

2

Normal Brake Deactivation Figure 403/TASK 32-42-00-991-004 

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## ---- THIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C.§552(b)(4). 

# f$JA3181A3191A320 AIRCRAFT MAINTENANCE MANUAL Subtask**32-42-00~910-053** B. Precaution CAUTION MAKE SURE THAT THE LOCKWIRE CANNOT WEAR DURING THE OPERATIONS OF THE LANDING GEAR. Subtask 32-42-00-860-073 C. Aircraft Maintenance Configuration (1)Pressurize the Green hydraulic system**fro~** the Yellow hydraulic system through the PTU with the electric pump (Ref. TASK 29-23-00­ (2) 863-001). On the panel 402VU, set to ON. make sure that the A/SKID 

### &NOSE WHEEL switch is
Subtask 32-42-00-710-058 D. Test (1) Do this test:
ACTION RESULT
1. Push in fully the related b pedals and hold them pushedrake in. Make sure that there are the hydraulic-pressure l disconnected. no leaks ine you on

2. Release the brake pedals.

Subtask 32-42-00-860-075 A. Put the aircraft back to its initial configuration. (1) Depressurize the Green hydraulic system (Ref. TASK 29-10-00-864-001). (2)Make sure that the level of the hydraulic fluid is correct in the Green hydraulic**reservoir~** Add some hydraulic fluid if it is necessary.



### r 

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### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL (3) De-erergize the aircraft electrical circuits (Ref. TASK 24-41-00-862­ 002)• (4)Remove the warning not;ce(s). (5)Remove the ground support and maintenance equipment, the special and standard tools and all other items. (6)In the cockpit, install a temporary placard to telL the crew that the normal braking on the wheeL 1 (2, 3, 4) ;s not operational.**r;-;~--A~~--------------------'** 

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F90144 R

# IFFT Printed in FranceTHIS DOCUMENTMAY CONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT,S U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-42-00-720-002 R Functional Test of the Tachometers 1. Reason for the**~~~** R R R R R R R R To make sure that:

- the two tachometers of a MLG operate correctly after their removal/installation

- the anti-skid function operates correctly. If you replace one tachometer only, you can do the functional tachometers with AIDS (Ref. AMM TASK 32-42-00-720-00300). test of the

A. Fixtures, Tools, Test and Support Equipment**-----------------------------~------------------------------------------------** REFERENCE QTY DESIGNATION

R R 355M03190000 1 MLG WHEEL TACHOMETER DRIVING TOOL R 98D32403003000 1 DRIVING ADAPTOR B. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 27-96-00-740-001 BITE Test of the EFCS (Ground Scanning) 29-10-00-864-001 Depressurize the Green Hydraulic System 29-23-00-863-001 Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump 34-10-00-860-004 IR Alignment Procedure 34-10-00-860-005 ADIRS Stop Procedure

## r;;;-~--~LL 

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# I F90145 

### FFT Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 3 . .:!,ob Set-up Subtask 32-42-00-860-059 A. Aircraft Maintenance Configuration R (1) Make sure that the wheel chocks are in position. R (2) If necessary, remove the hubcaps or the debris guards (if brake fans R are installed). R (3) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861­ 002). R (4) Pressurize the Green hydraulic system (Ref. TASK 29-23-00-863-001). R (5) On the panel 402VU, make sure that the ANTI SKID selector switch is in the ON position. R (6) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). R (7) Put the parking brake control switch ;n the OFF position. R Subtask 32-42-00-865-056 B. Make sure that this(these) circuit breaker(s) is(are) cLosed:
PANEL DESIGNATION IDENT. LOCATION
**ON A/C 201-299, 801-899, 936-999,
49VU ABCU &/Y BRK/PRESS IND 61GG C10 **ON A/C 901-935,
49VU L/G/Y BRK/PRESS/IND 61GG C10 **ON A/C ALL

121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35



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------------------------------------------------------------------------------- THIS DOCUMENTMAYCONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

### B

UNDERTHE FREEDOMOF INFORMATIONACT, 5U.S.C. §552(b){4). 

# f!)A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL 

### PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 121VU HYDRAULIC/SOL VALVES/G/Y/PTU 1S01GL N34

R Subtask 32-42-00-4S0-050 R A. Installation of the Driving Tool/Adaptor R R R NOTE If the MLG WHEEL TACHOMETER DRIVING TOOL is not available, alternative, you can use a standard drilling machine and a ADAPTOR (9SD32403003000). as an DRIVING
R R R (1) Install the MLG WHEEL TACHOMETER DRIVING TOOL (355M03190000) on the wheel that has the tachometer for which it is necessary to do the test. R R R R R R R 

### NOTE If the MLG WHEEL TACHOMETER DRIVING TOOL (355M03190000) is not available:

- Install a DRIVING ADAPTOR (9SD32403003000) on a standard drilling machine.

- Connect the DRIVING ADAPTOR (9SD32403003000) to the drive shaft of the tachometer for which it is necessary to do the test. R R R R 

### (2) Install ADAPTOR another a MLG WHEEL TACHOMETER DRIVING TOOL (355M03190000) or DRIVING (9SD32403003000) on the drive shaft of the tachometer of MLG wheel (see the table that follows).


### R

------------------------------------------------------------------------------­ R 

### Wheel with tachometer for which Wheel on which you must install R 

### it is necessary to do the test the other DRIVING TOOL/ADAPTOR R R 1 

### 3 or 4 R R 2 3 

### or 4 R R 3 1 

### or 2 R
------------------------------------------------------------------------------­ R 4 1 

### or 2 

### R

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

### r~;;~--~LL 

# -------------------, 

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## I I F90147 

## IFFT 

# I Printed in FranceTHIS DOCUMENT MAY CONTAIN TRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-00-720-050 R B. Test R R (1) Test of the Tachometers on the Left MLG (wheeLs 1 and 2)

ACTION RESULT
R 1. On the Captain or First Officer R side: R R
- push the brake pedaLs. R R R R R 2. On the two DRIVING R TOOLS/ADAPTORS: R R

- set a wheel speed of between R 900 and 1100 rpm. R R R R R R R 3. On the DRIVING TOOL/ADAPTOR R connected to the left MLG wheel: R R

- decrease the speed to zero. R R R R 4. Release the brake pedals. R R 5. On the DRIVING TOOL/ADAPTOR R connected to the wheel of the R opposite landing gear (right R side): On the Left MLG, all the brakes are applied:

- the brake pistons extend,

- the wear pins move in relation to the pistons,

- the piston housings move in the opposite direction. On the left MLG wheel without the DRIVING TOOL/ADAPTOR, the brake is released:

- the brake pistons retract (gap between the head of the pistons and the pressure pLate),

- the wear pins move in relation to the pistons,

- the piston housings move in the opposite direction. On this wheel, the brake is released:

- the brake pistons retract,

- the wear pins move in relation to the pistons,

- the piston housings move in the opposite direction. On the left MLG:

- all the brakes are released.



### rALL Page 521 

# I 32-42-00 IEFF Aug 01/08 

## I F90148 IFFT 

# I Printed in FranceTHIS DOCUMENTMAY CONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 

### ACTION RESULT R

- decrease the speed to zero. R R R R R 

### NOTE the reference speed in the computer is zero 20 seconds after the end of the test.

R R R R R 

### 6. Do the steps 1 to 6 with the DRIVING TOOL/ADAPTOR connected to the other tachometer on the Left MLG.

R 

### Subtask 32-42-00-720-055 R 

### C. Test R R 

### (1) Test of the Tachometers on the Right MLG (wheeLs 3 and 4)

R R 

### ACTION RESULT R 

### R 1. On the Captain or First officer On the right MLG, all the brakes are R side: appLied: R - push the brake pedals.

- the brake pistons extend, R 

### - the wear pins move in relation to the R 

### pistons, R 

### - the piston housings move in the R 

### opposite direction. R 2. On the two DRIVING On the right MLG wheeL without the R TOOLS/ADAPTORS: DRIVING TOOL/ADAPTOR, the brakes is R - set a wheel speed of between released: R 900 and 1100 rpm. - the brake pistons retract (gap R 

### between the head of the pistons and R 

### the pressure plate), R 

### - the wear pins move in reLation to the R 

### pistons, R 

### - the piston housings move in the R 

### opposite direction. 

# ----'--l 32-42-00 Page 522 ALL Aug 01/08 F90149 \ Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL ACTION RESULT R 3. On the DRIVING TOOL/ADAPTOR R connected to the right MLG wheeL: R

- decrease the speed to zero. On this wheeL, the brake is released: R

- the brake pistons retract, R

- the wear pins move in relation to the R pistons, R

- the piston housings move in the R opposite direction. R 4. Release the brake pedals. On the right MLG: R

- aLL the brakes are released. R 5. On the DRIVING TOOL/ADAPTOR R connected to the wheel of the R opposite landing gear <left R side): R

- decrease the speed to zero. R NOTE the re·ference speed in the R computer is zero 20 R seconds after the end of R the test. R 6. Do the steps 1 to 6 with the R DRIVING TOOL/ADAPTOR connected to R the other tachometer on the right 

### R MLG. R Subtask 32-42-00-740-052 R D. Reset of the Related SEC(s) R (1) Do a reset of the related SEC(s). R R R (a) For the tachometer(s) (wheel 4): 19GG and/or 22GG (wheel 1) and/or 22GG

- on the overhead panel 23VU, release the FLT CTL SEC 3 pushbutton switch, then push it.

- on the overhead panel 24VU, release the FLT CTL SEC 2 pushbutton switch, then push it.



# r:-----------------------------------------­ IEFF: ALL 

# I 

# 32-42-00 Page 523 

## I I Aug 01/08 

## IFFT I F9015D 

### Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U,S.C. § 552(b)(4). 

# f$JA3181A3191A320 AIRCRAFT MAINTENANCE MANUAL R (b) For the tachometer(s) 20GG and/or 21GG (wheel 3) and/or 21GG R (wheel 2):

- on the overhead panel 23VU, release the FLT CTL SEC 1 pushbutton switch, then push it. R (2) Do the BITE test of the EFCS computers (Ref. TASK 27-96-00-740-001). R (3)Make sure that the MCDU shows no maintenance message related to the tachometer. R Subtask 32-42-00-860-060 R E. Aircraft Maintenance Configuration (1) Depressurize the Green hydraulic system (Ref. TASK 29-10-00-864-001). (2)Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862­ 002)• R (4) Remove the MLG WHEEL TACHOMETER DRIVING TOOL (355M03190000) or the R DRIVING ADAPTOR (98D32403003000) and the drilling machines. 

### 5. f.lose-ue Subtask 32-42-00-942-055 A. Removal of Equipment (1)Make sure that the work area is clean and clear of tool(s) and other items.



## r--------------------------­ 

# 32-42-00 Page 524 

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## I F90151 

## IFFT Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

NOTE:THE YELLOW HYDRAUUC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. ·THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

I2642GMI

5 5

1----2

LEG GEAR SIDE C\I 0 0 :2**~** BRAKE TEMPERATURE '<t**~":":~'-:"""---SENSOR** ELECTRIC CONNECTION 0 0 C\I '<t C\I C') 4 3 LO :;; Z Deactivation without Brake Removal Figure 401/TASK 32-42-00-991-001 

# r;;---------­ 

# 32-42-00 Page 404 IEFF: 

### ALL Feb 01/01 

## I 

# 1 F90152 

## IFFT 

## I Printed in FranceTHIS DOCUMENT MAYCONTAINTRADESECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

NOTE:-THEYB..LOW HYDRAUUC CONNECTION ONTHE BRAKE UNITS ISN..WAYS BEHINDTHE LEG GEAR. -THE GREEN HYDRAUUC CONNECTION ON THEBRAKE UNITS IS N..WAYS INFRONTOFTHELEGGEAR.

8 0 ::E ell ell

.... 0 0 C\I

.... C\I CO) l() :2 z WHEELSIDE 

### A

# I~ !2644GM]

11 10 9 LEG GEARSIDE 6

Deactivation with Brake RemovaL Figure 402/TASK 32-42-00-991-002 R 

# R**[EFF-~~-------------------------------~** 

# 32-42-00 Page 406 May 01/03

F90153 IFFT \ Printed in France

## ----------



# ------------------------------ THIS DOCUMENT MAYCONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL TASK 32-42-27-400-001 InstaLLation of the Brake (2641GM,2642GM,2643GM,2644GM) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. 1. Reason for the Job Self ExpLanatory

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specifi c safety barriers No specific standard socket and extension No specific warning notice(s) No specific Torque Wrench range 50.00 to 260.00 lbf.ft (6.00 to 36.00 m.daN) No specific Torque Wrench range 0.20 to 3.60 m.daN (2.00 to 26.00 lbf.ft) 1324A HANDLING TOOL 98D32403001000 ADAPTOR

- BRAKE UNIT NUT 98D32403005000 ADAPTOR

- BRAKE UNIT NUT B. Consumable**Materi~Ls** REFERENCE DESIGNATION
R Material No. 04-003 USA SAE AMS 2518 GRAPHITED PETROLATUM THREAD COMPOUND (Ref. 20-31-00) Material No. 11-002 USA MIL-PRF-680 DRY CLEANING SOLVENT (VARSOL/WHITE SPIRIT) (Ref. 20-31-00)

EFF: ALL 

# 32-42-27 Page 407 

# r Feb 01/08 

# I FFT 

# )
F90154 Printed in FranceTHIS DOCUMENTMAY CONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL C. Referenced Information
REFERENC.E DESIGNATION
20-21-11-911-001 29-00-00-864-001 32-41-11-400-006 32-42-00-870-001 32-43-00-870-002 32-47-00-710-001 32-47-15-400-001 Tightening Torques for Standard Threaded Fasteners Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Installation of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) Bleeding of the Normal Braking at the Brake Units Bleeding of the High Pressure Alternate Braking System Operational Test of the Brake Temperature System Installation of the Brake Temperature Sensor (4GW,5GW,6GW,7GW) R **ON A/C 801-807, 901-938,
32-42-27-991-001-A Fig. 401 R **ON A/C ALL R Post SB 32-1291 For 

### A/C 801-807,901-938, R**32-42-27-991-001~C** Fig. 401A R **ON 

### A/C ALL

Subtask 32-42-27-941-061 A. Safety Precautions (1)Make sure that the safety barriers are in position. (2)Make sure that the warning notice(s) is (are) in position:

- on the ground service panel to tell persons not to pressurize the Green and Yellow hydraulic systems,

- on the panel 40VU, to tell persons not to pressurize the Green and Yellow hydraulic systems.



## -----------------------, 

# 32-42-27 Page 408

### IEFF-~----~ZL . May 01/07 

# I F90155 \FFT Printed in France

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# ----------------- THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-27-860-060 B. Aircraft Maintenance Configuration (1)Make sure that the wheel chocks are in position for the wheels that are on the ground. (2)Make sure that the Green and Yellow hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001). (3)On the panel 110VU, make sure that the PARK BRK control switch is set to OFF. Subtask 32-42-27-865-051 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 121VU HYDRAULIC/PARK BRK/CTL/STBY 71GG N37 121VU HYDRAULIC/PARK BRK/CTL/NORM 70GG N36 4. Procedure R **ON A/C 801-807, 901-938, (Ref. Fig. 401/TASK 32-42-27-991-001-A) R **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R (Ref. Fig. 401A/TASK 32-42-27-991-001-C)

EFF: ALL 

# -----l 

# 32-42 -27 Page 409 

# I May 

### 01/07 

# f I FFT F90156 Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U,S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL R **ON AIC ALL
Subtask 32-42-27-640-050 A. Preparation for InstaLLation (1)Clean the axLe protective sleeve (5) and the studs (11) with CLEANING AGENTS (Material No. 11-002). (2)Do a visuaL inspection of the axLe protective sLeeve (5) to make sure that it is in correct condition. (3) Lightly lubricate the studs (11), the boLts (12) and the nuts (8) with COMMON GREASE (MateriaL No. 04-003). (4)If necessary, instalL the brake temperature sensor retained at removal of the brake unit (Ref. TASK 32-47-15-400-001). Subtask**32-42-27~420-054** B. InstaLLation of the Brake CAU!.ION TO PREVENT DAMAGE TO THE AIRCRAFT, MAKE SURE THAT THE COUPLINGS ARE CORRECTLY LOCKED (FULLY TURN THE COLLAR OF THE BRAKE QUICK-

. RELEASE COUPLING CLOCKWISE UNTIL IT TOUCHES ITS MECHANICAL STOP). (1)InstaLL the brake unit (1) on the wheeL axLe (6) with HANDLING TOOL (1324A). (2) InstaLL the washers (7) and the nuts (8) on the bolts (12). (3)Make sure that the studs (11) are in the correct position in the axLe (6). (4)TORQUE the nuts (8) to between 175 and 180 Lbf.ft (23.72 and 24.40 m.daN). With the ADAPTOR

- BRAKE UNIT NUT (98D32403001000) or the ADAPTOR

- BRAKE UNIT NUT (98D32403005000) or with a standard socket and extension you must calculate torque wrench setting (Ref. TASK 20­ 21-11-911-001)• NOTE : The given vaLue is the torque that you must appLy to the nut. (5)Remove the bLanking pLugs from the hydrauLic couplings (2) and (14) and the unions (3) and (13).



# r;;--:--**AL~-------------------l** 

# 32-42-27 Page 410 May 01/07

F90157 FFT 

## I Printed in France

## --- THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL (6) Connect the hydrauLic coupLings (2) and (14) to the unions (3) and (13) NOTE If the union nut is Loose, TORQUE it to between 2.5 and 2.8 m.daN (18.43 and 20.64 Lbf.ft). (7) Remove the PROTECTIVE CONE (J47779) from the wheel axle. (8)Make sure that the retaining ring (4) of the axLe protective sleeve (5) is in the correct position. Subtask 32-42-27-420-055-A C. End of the instaLlation (1)Remove the blanking caps from the eLectrical connector (9) and the receptacLe (10). (2)Connect the electricaL connector (9) to the receptacLe (10) and foLd back the end of the sleeve (15) on the connector (9) to cover it fuLly. (3) InstaLL the wheel (Ref. TASK 32-41-11-400-006). Subtask 32-42-27-870-050 D. Bleed the brake unit (Ref. TASK 32-42-00-870-001) (Ref. TASK 32-43-00­ 870-002) CAUTION THE BLEEDING PROCEDURE OF THE BRAKE UNIT CALLS FOR OPERATIONAL TEST OF THE NORMAL AND ALTERNATE BRAKING SYSTEM. DURING THESE TESTS CHECK HYDRAULIC CONNECTIONS AND BRAKE UNIT FOR LEAKAGE. Subtask 32-42-27-865-052 E. Remove the safety clip(s) and the tag{s) and cLose this{these) circuit breaker(s): 1GG, 2GG, 3GG, 4GG, 70GG, 71GG, 1GW



## r------------------­ 

# -----1 32·42·27

EFF: ALL Page 411 May 01/07

F90158 

## IFFT 

# I Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL Subtask 32-42-27-710-050 F. Test (1)As the operational tests of the Normal and Alternate braking system necessary after removal/installation of the brake unit are already done in the bleeding procedure, do only an**~perational** test of the brake temperature system (Ref. TASK 32-47-00-710-001).

Subtask 32-42-27-942-050 A. Put the aircraft back to its initial configuration.· (1)Make sure that the work area is clean and clear of tool(s) and other items. (2)Remove the warning notice(s). (3)Remove the ground support and maintenance equipment, the special and standard tools and all other items.



# l 32-42-27 Page 412 

### ALL May 01/07 F90159 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIAL ORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAIN"rENANCE MANUAL

13 /2641GMr-t 

# ZA 

# JJ A [2643GM

## I 

# ti-2 i

546

# $;;s~sJ's,Js,
Brake Unit Figure 401/TASK 32-42-27-991-001-A
R

## f;;~----;~-80;:-;01-93~----------1 

# 32-42-27

IFFT 

# I

Printed in France Page 404 May 01/07

F90160THI3 DOCUMENT MAYCONTAINTRADESECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

R Brake Unit R Figure 401A/TASK 32-42-27-991-001-C


### ALL Page 405 

# l 32-42-27 14

13 12 11 10 9 5 6 .7

May 01/07 F90161 Printed in FranceTHIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATION ACT. 5U.S.C. § 552(b)(4). 

# f$)A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL

WEAR INDICATOR PIN LENGTH PIN BRAKE D ASSEMBLY 2-1526 2-15262 SOmm (1.97in.) 2-1526-5 2-1526-3 2-1528-4 2-1572 88mm (2.68in.)
2-1598-1 2-1600-1 63mm (2.48in.) 2-1600-2 2-1600-3 50.8mm (2.0In.) 2-1684 53.3mm (2.10In.) I2642GMi-c

STATOR

ASSY 

# I

,... Q o :;j; u.. <: <.0 

### ,... (\j**~ ~**  

# <::4-- A**12641GMI~** I2644GMI \

## ~- A

Brake Unit-Wear Indicator Figure 601/TASK 32-42-27-991-002

### ~ ON NEW BRAKE

## C



## r;;F ALL 

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## I R 

## IFFT F90162 

# 1 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIAL ORFINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C.§552(b)(4).

## ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL**BRAKE~ AN!_~!EERI~§_=~ITE**  

### - ADJUS!MENT/TEST TASK 32-46-00-740-001 

### BITE Test of the BSCU

Self Explanatory

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific warning notice B. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-002 

### Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 

### De-energize the Aircraft ElectricaL Circuits SuppLied from the External Power 31-32-00-860-009 

### Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page 31-60-00-860-001 

### EIS Start Procedure 31-60-00-860-002 

### EIS Stop Procedure R 34-10-00-860-004 

### IR Alignment Procedure R 34-10-00-860-005 

### ADIRS Stop Procedure

Page 501 

# ---I 32·46·00 ALL May 01/03
F90163 \ Printed ;n France

### ------------------------

---- .. THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALORFINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 3. JOQ Set-uE! R **ON A/C**201-299~** 801-899, 925-999,
Subtask 32-46-00-860-052-A A. Aircraft Maintenance Configuration (1)Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861­ 002)• (2)On the panel 400VU, make sure that the Landing Gear control-lever is set to DOWN. (3)On the panel 402VU, make sure that the A/SKID 

### &N/W STRG switch is at ON. (4)Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001). (5)Do the IR alignment procedure. (Ref. TASK 34-10-00-860-004) (6)On one MCDU, get the SYSTEM REPORT/TEST/L/G Page (Ref. TASK 31-32-00­ 860-009). nON A/C 901-924,
Subtask 32-46-00-860-052 A. Aircraft Maintenance Configuration (1)Energize the aircraft electricaL circuits (Ref. TASK 24-41-00-861­ 002)• (2)On the panel 400VU, make sure that the Landing Gear control-lever is set to DOWN. (3)On the paneL 402VU, make sure that the A/SKID 

### &N/W STRG switch is at ON. (4)Do the IR alignment procedure. (Ref. TASK 34-10-00-860-004) (5)On one MCDU, get the SYSTEM REPORT/TEST/L/G Page (Ref. TASK 31-32-00­ 860-009)

.

IEFF ALL 

# 32-46-00 Page 502 Nov 01/07 

# I J 

## I FFT 

## I F90164 Printed in France

## ----- THIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL **ON A/C ALL
Subtask 32-46-00-941-054 B. Safety Precautions (1)On the panel 400VU, put a warning notice on the Landing Gear control-lever to tell persons not to move it. Subtask 32-46-00-865-050 C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG M34 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 4. Procedure R**~*ON** A/C 201-202, 801-899, 925-999,
Subtask 32-46-00-740-050-A A. Do this test: NOTE This test is for channel 1. For channel 2, use the indications between parentheses.
ACTION RESULT
1 • On the MCDU, push the line key

- the BSCU CHAN 1(2) page comes into adjacent to the BSCU 1(2) view. indication. 2. Push the Line key adjacent to the

- the BSCU CHAN 1(2)/SYSTEM TESTS page SYSTEM TESTS indication. comes into view. 

# l 32-46-00 ALL Page 503 Aug 01/08

F90165 Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALORFINANCIALINFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4). 

# rs;A3181A3191A320 AIRCRAFT MAINTENANCE MANUAL ACTION 3.Push the line key adjacent to the LRU WIRING 

### &BSCU TEST indication. 4. Do a check of these initial conditions:

- on the ECAM controL paneL, push the ELEC key

- on the paneL 402VU, make sure that**th~** A/SKID 

### &N/W STRG switch is at ON. 5. Push the line key adjacent to the START TEST indication. NOTE If the IN PROGRESS 4S indication stays in view, push the Line key adjacent to the RETURN indication. Do a check of aLL the initial conditions and do the test again. RESULT

- the BSCU CHAN 1(2)/LRU WIRING 

### &BSCU TEST page comes into view with INITIAL CONDITIONS

On the lower ECAM DU, the ELEC page comes into view. On the ELEC page: the TR1(2) energizes the DC1(2) busbar.

On the BSCU CHAN 1(2) page: the IN PROGRESS 4S indication is shown

- then the NO fAULT DETECTED and PRESS RETURN indications come into view when the system is serviceable. If the system is not serviceable: - a list of fault messages comes into view. NOTE The prompt 

### ">" to the right of the CLass number show that there are TSD pages reLated to this fault. Push the Line key adjacent to the prompt to get access to these pages.

- or if one or more of the initial conditions is not satisfactory, these indications come into view: • TEST NOT PERfORMED • the initial condition(s) that ;s (are) not satisfactory.

- or the TEST TIME OUT indication comes into view when the test is not


# 32-46-00 Page 504 R 

## I rEFF 201-202, 801-899, 925-999, Aug 01/08 F90166 FFT



# • Printed in FranceTHIS DOCUMENTMAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL ACTION

R **ON A/C 203-299, 901-924,
Subtask 32-46-00-740-050 A. Do this test:
ACTION
1.On the MCDU, push the line key adjacent to the BSCU 1 indication. 2.Push the line key adjacent to the TEST indication. 3.Obey the instructions shown on the screen. Wait 5 seconds then push the line adjacent to the TEST indication.

4.Push the line key adjacent to the RETURN indication to get**~he** SYSTEM REPORT/TEST/L/G page. 5.Push the line key adjacent to the BSCU 2 indication. 6. Do the same actions as in Para. 2. and 3. RESULT completed in the time limit. Push the line key adjacent to the RETURN indication and do the test again.

RESULT

- the BSCU SYS 1 page comes into view.

- the BSCU SYS 1/TEST page comes into view and gives instructions. The test starts and continues for 45 seconds. If the test finds no faults:

- the NO FAILURE indication comes into view. If the test results are incorrect: - a list of fault messages comes into view.

- the SYSTEM REPORT/TEST/L/G page comes into view.

- the BSCU SYS 2 page comes into view.

- same results as for the BSCU SYS 1.


# -------1 32-46-00 Page 505 ALL Aug 01/08 

## I F90167 

## I Printed in FranceTHIS DOCUMENT MAYCONTAIN TRADE SECRETS AND CONFIDENTIALCOMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL **ON A/C ALL

R **ON A/C 201-299, 801-899, 925-999,
Subtask 32-46-00-860-051-A A. Put the aircraft back to its initial configuration. (1)On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do the AIDR stop procedure (Ref. TASK 34-10-00-860-005). (3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (4) Remove the warning notice(s). (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). **ON A/C 901-924,
Subtask 32-46-00-860-051 A. Put the aircraft back to its initial configuration. (1)On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do the AIDR stop procedure (Ref. TASK 34-10-00-860-005). (3)Remove the warning notice(s). (4)De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).



## ------, ALL 

# 32-46-00 Page 506 

# I Nov 01/07 F90168 Printed in France

## ----------- THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE

. UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4). 

# f$JA3181A3191A320 AIRCRAFT MAINTENANCE MANUAL SENSOR

- BRAKE TEMPERATURE (4GW,5GW,6GW,7GW)

-**RE~OVAbLINSTAbbATION** TASK 32-47-15-000-001 RemovaL of the Brake Temperature Sensor (4GW,5GW,6GW,7GW) 1. Reason for the Job SeLf Explanatory

A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific blanking cap No specific circuit breaker(s) safety clip(s) No specific warning notice B. Referenced InformatiOn
REFERENCE DESIGNATION
R**32~47-15-991-001-B** Fig. 401

Subtask 32-47-15-865-050 A. Open, safety and tag this(these) circuit breaker(s):
PANEL DESIGNATION !DENT. LOCATION

121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 Subtask 32-47-15-941-052 B. Safety Precautions (1) Put the warning notice in the cockpit to tell persons not to operate the landing gears.



## r---------------­ Page 401 

# ---1 32-47-15 IEFF ALL Aug 01/06 \ F90169 IFFT Printed in France

## ------ THIS DOCUMENT MAY CONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL 4. Procedure R (Ref. Fig. 401/TASK 32-47-15-991-001-B) R Subtask 32-47-15-020-050-A A. Removal of the Brake Temperature Sensor (1) Fold back the rubber sleeve (4) untiL you can disconnect the connector (3). (2) Disconnect the connector (3) from the temperature sensor (1). (3) Put a bLanking cap on the connector (3). (4) Cut and remove the Lockwire from the screw (2). (5) Remove the screw (2). (6) ReLease the temperature sensor (1) from its housing along its axis. (7) Put a bLanking cap in the temperature sensor housing.



# r-:**--;:~-L**

# -------------------1 32·47·15 Page 402 Aug 01/06

F90170 Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIALCOMMERCIALOR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A31B/A319/A320 AIRCRAFT MAINTENANCE MANUAL

60W

4GW

7GW sow

R Brake Temperature Sensor R Figure 401/TASK 32-47-15-991-001-B 

# IEFF ALL 

# 32-47-15 Page 403 Aug 01/06 

# I F90171 IFFT Printed in FranceTHIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL BRAKE (2641GM,2642GM,2643GM,2644GM)

- REMOVAL/INSTALLATION TASK 32-42-27-000-001 RemovaL of the Brake (2641GM,2642GM,2643GM,2644GM) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. 1. Reason for the Job SeLf ExpLanatory 2. Job Set-up Information A. Fixtures, TooLs, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific blanking cap No specific bLanking plugs No specific circuit breaker(s) safety clip(s) No specific safety barriers No specifi.c standart socket and extension No specific warning notice(s) J47779 1 PROTECTIVE CONE 1324A 1 HANDLING TOOL 98D32403001000 1 ADAPTOR

- BRAKE UNIT NUT 98D32403005000 1 ADAPTOR

- BRAKE UNIT NUT B. Consumable MateriaLs
REFERENCE DESIGNATION
R MateriaL No. 04-022 USA MIL-PRF-81322 SYNTHE.HYDROCARBON GREASE HIGH PRESSURE (Ref. 20-31-00) 

# l 32-42-27 ALL Page 401 Nov 01/05

Printed in France F90172THIS DOCUMENT MAYCONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOMOF INFORMATIONACT, 5 U.S.C.§ 552(b)(4). 

# f$)A3181A3191A320 AIRCRAFTMAINTENANCE MANUAL C. Referenced Information
REFERENCE DESIGNAnON**---------------------------------------------------------------------------~--** 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 32-41-11-000-006 Removal of the MLG Wheel (2649GM,2650GM,2651GM,2652GM) 32-47-15-000-001 Removal of the Brake Temperature Sensor (4GW,5GW,6GW,7GW) R 

### **ON AIC 801-807, 901-938,
32-42-27-991-001-A Fig. 401 R 

### **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R 32-42-27-991-001-C Fig. 401A R uON A/C ALL
3. Job Set-up Subtask 32-42-27-941-060 A. Safety Precautions (1)Put the safety barriers in position. (2)Put the warning notice(s) in position:

- on the ground service panel to tell persons not to pressurize the Green and Yellow hydraulic systems,

- on the panel 40VU, to tell persons not to pressurize the Green and YeLLow hydrauLic systems. 

# l 32-42-27 Page 402 ALL May 01/07

F90173 Printed;n France

# ------------------------------------------------------------------------------- THIS DOCUMENT MAYCONTAIN TRADE SECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF.INFORMATIONACT, 5U.S.C. §552(b)(4). 

# I$JA3181A3191A320 AIRCRAFTMAINTENANCEMANUAL Subtask 32-42-27-860-059 B. Aircraft Maintenance Configuration (1)Put the wheel chocks in position for the wheels that are on the ground. (2)Make sure that the Green and Yellow hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001). (3)Remove the applicable wheel (Ref. TASK 32-41-11-000-006). (4) On the panel 110VU, set the PARK BRKcontrol switch to OFF. Subtask 32-42-27-865-050 C. Open, safety and tag this(these) circuit breaker(s): " PANEL DESIGNATION IDENT. LOCATION

121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/CTL 3GG M35 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/CTL 1GG "134 121VU HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY 2GG M33 121VU HYDRAULIC/PARK BRK/CTL/STBY 71GG N37 121VU HYDRAULIC/PARK BRK/CTl/NORM 70GG N36 4. Procedure R **ON A/C 801-807, 901-938, (Ref. Fig. 401/TASK 32-42-27-991-001-A) R **ON A/C ALL R Post SB 32-1291 For A/C 801-807,901-938, R (Ref. Fig. 401A/TASK 32-42-27-991-001-C)

EFF ALL 

# ---l 32-42-27 Page 403 May 01/07 

# f

HT Printed in France F90174THIS DOCUMENT MAY CONTAINTRADE SECRETSANDCONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL



# [!J

# ~-2 I

6

13

Brake Unit Figure 401/TASK 32-42-27-991-001-A 801-807, 901-938, 

# 32·42·27

Printed in France g C\I ::l! 

### ca 

# ..**~** CII 

# .. C\I (') II) ::l! z 

# RF Page 404 May 01/07 [FFT F90175THIS DOCUMENT MAYCONTAINTRADESECRETSAND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. § 552(b)(4).

### ~A318/A319/A320 AIRCRAFT MAINTENANCE MANUAL

!:5 

# !**~** I'­ 14

13 12 12S44GMI

6

11 10 9 5**"'<L.~** 

## 7-Fn.. N 5 4 6**8--~** 

# i**$;~~~'s,;,l,,)**
R Brake Unit R Figure 401A/TASK 32-42-27-991-001-C 

# FALL 32-42-27 Page 405 May 01/07 

## )FFT Printed in France F90176THIS DOCUMENT MAYCONTAINTRADE SECRETSAND CONFIDENTIAL COMMERCIALOR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE UNDERTHE FREEDOM OF INFORMATIONACT, 5 U.S.C. §552(b)(4).

### ~A318/A319/A320 AIRCRAFTMAINTENANCE MANUAL R **ON Ale ALL
Subtask 32-42-27-020-050 A. Removal of the Brake WARNING THE BRAKE UNIT WEIGHS APPROXIMATELY 67kg (147lb). BE CAREFUL WHEN YOU MOVE IT TO PREVENT INJURY TO PERSONS OR DAMAGE TO THE WHEEL OR AXLE. (1)Install the PRo'rECTIVE CONE (J47779) on the wheel axle (6). NOTE: Slightly lubricate the outer circumference of the protective

---- tool with COMMON GREASE (Material No. 04-022). (2)Disconnect the electrical connector (9). (3) Put ablanking cap on the electrical connector (9). (4) Disconnect the hydraulic couplings (2) and (14) from the unions (3) and (13). (5)Install the blanking plugs (6)Remove the nuts (8) with the ADAPTOR

- BRAKE UNIT NUT (98D32403001000) or the ADAPTOR

- BRAKE UNIT NUT (98D32403005000) or with a standart socket and extension and remove the washers (7). (7)Remove the brake unit (1) with the HANDLING TOOL (1324A). (8) If necessary, remove the brake temperature sensor (Ref. TASK 32-47­ 15-000-001) and retain it for installation on the new brake unit.



# 1m ALL Page 406 

# l 32·42·27 May 01/07 

## IFFT 

# I

F90177 Printed in France