Docket No. FAA-2009-1040 

FAA Case No. 2008NM210020 

FAA Docket No. CP09NM0013 

/? 

In the Matter of 


FRONTIER AIRLINES, INC. 


Judge Richard C. Goodwin 

RESPONDENT'S RESPONSE TO COMPLAINANT'S 


FIRST SUPPLEMENTAL DISCOVERY REQUEST 


Pursuant to 14 C.F.R. § 13.220, Respondent Frontier Airlines, Inc. ("Frontier"), by and 

through its counsel, Pillsbury Winthrop Shaw Pittman LLP, hereby responds to the 

Complainant's First Supplemental Discovery Request 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 

providing the attached docUments in response to Co~plainant's Request. 

. . 

Frontier reserves the right to amend, expand, or delete all or any part of these objections 

and responses. 

Respectfully submitted, 

Dated: March 19,2010 

Kenne P. Quinn 

J enni E. Trock 

PILLSBURY WINTHROP 

SHAW PITTMAN LLP 

2300 N Street, N.W. 

Washington, D.C. 20037 

Tel: (202) 663-8000 

Fax: (202) 663-8007 

E-mail: kquinn@pillsburylaw.com 

jtrock@pillsburylaw.com 

Counsel for Frontier Airlines, Inc. 
CERTIF1CATE OF SERVICE 


I, Timothy C. Gerheim, hereby certify that I have this, the 19th day of March, 2010, caused a 

copy of the foregoing document to be served to the following persons via facsimile and U.S. 

First Class mail: 

Federal Aviation Administration 

Attention: Hearing Docket Clerk, AGC-430 

Wilbur Wright Building - Suite 2WIOOO 

800 Independence Avenue, SW 

Washington, DC 20591 

FAJ<:202-493-5142 

(Original and one copy) 

Scott R. Morris, Attorney 


Federal Aviation Administration 


. Northwest Mountain Region, ANM-7 

1601 Lind Avenue S.W. 

Renton, WA 98057-3356 

FAJ<: 425-227-1007 

The Honorable Richard C. Goodwin 


Administrative Law Judge 


Office ofHearings, M-20 


1200 New Jersey Avenue, S.E. 


East Building Ground Floor 


Room E12-320 


Washington, D.C. 20590 


FAJ<:202-366-7536 


Timothy 

~(L~ C. Gerheim 

Pillsbury Winthrop Shaw Pittman LLP 

2300N st. NW 

Washington, DC 20037 

2 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 .~'LL 32-42-27 Page 605 

Feb 01/08 

IFFT 

F90057 Printed in France 
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UNDER THE 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 ALL 	 32-42-27 Page 606 

Feb 	 01/08 

Printed F90058 in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE 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 

t FFT 

Printed F90059 in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 32·42·27 Page 608 

Feb 01/08 

I 

F90060 Printed in France 
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UNDER THE FREEDOM OF INFORMATION ACT, 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. 

EFF ALL 32-42-27 Page 609 

Aug 	 01/07 

fFT 

Printed F90061 in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.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 	 F90062 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$;A3181A3191A320 

AIRCRAFT MAINTENANCE MANUAL 

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 ALL 32-42-00 Page 402 

May 01/07 

Printed in France 	 F90063 
----------------.~~-----------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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 F 	 May 	 01/07

IFFT 1

Printed 	in France F90064 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

NOTE::rHE YELLOW HYDRAULIC 

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. 

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 IEFF ALL 32-42-00 Page 404 

Feb 01/01 

FFT 

F90065 Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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). 

l R~LL 32-42-00 Page 405 

I 	 May 01/07 FFT 

Printed in France 	 F90066 
I 2841GM 1-\­

~ A 

- ......·--5 

11 10 9 

LEG GEAR SIDE 

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

NOTE: -THE YELLOW HYDRAULIC 


CONNECTlON ON THE BIW<E 


UNITS IS N...WAYS 


BEHIND THE lEG GEAR. 


-THE GREEN HYDAAlJUC 


CONNEC1lON ON THE BIW<E 


UNITS IS AlWAYS 


IN FRONT OF THE LEG GEAR. 


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 


R 'EFF ALL 32-42-00 Page 406

May 01/03 

FFT 

F90067 Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE 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 ------l 32-42-00 Page 407 

May 01/07 R 

IFFT I 

Printed in France F90068 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DiSCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$;A3181A3191A320 

AIRCRAFT MAINTENANCE MANUAL 

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------------. 32-42-00 Page 408 EF F May 	 01/07 

FFT 

F90069 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 r	 32-42-27 Page 410 

May 01/07 

IFFT l 

Printed in 	France F90070 
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UNDER THE FREEDOM OF INFORMATION ACT, 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 

32-42-27 Page 411 f ALL 

May 01/07 

IFFT 

F9QQ71 Printed 	in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

SA3181A3191A320 

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 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 -- 32-42·27 Page 412 

May 01/07 

IFFT 

Printed in France F90072 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 l ALL 32-42-27 rEF F Nov 01105 

I 	 F90073 

IFFT 

Printed i~ France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT,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 

IEFF ALL ------------1 32 -42-27

Page 402 

May 01/07 I I 

IFFT I F90074

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

Sub task 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

R Brake Unit 

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

I

r;;---------------------------------------------l 

EFF: 32-42-27 Page 405 ALL May 01/07 

I F90077 IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 a 	bLanking 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL ORFINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 specif ic 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) 


ALL I 32-42-27 Page 	407

Feb 01/08

IEFF 

. FFT 

F90079 Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACTI'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 F90080 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT. 5 U.S.C. § 552(b)(4). 

SA3181A3191A320 

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) 

Page 409 ----l May 01/07

32-42-27 

F90081 Printed in France 
---------------

-----------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.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 A HYDRAULIC 

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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

ALL 12-12-29 Page 302 ----I 
 May 01/07 

F90083 

Printed in France 
----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f!$JA3181A3191A 320 

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--------------------------­

JEFF: ALL 	 I 12-12-29 Page 303 

I 	 Aug 01/08 /FFT F90084 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 	 FFT I F90086 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

RESERVOIR FILL SYSTEM 

SELECTOR VALVE 1134GQ 

RESERVOIR FILL SYSTEM 

HAND PUMP FILLVALVE 1698GM 

QUANTITY INDICATOR 

1834GO 

o 

o 

o 

o 

o 

RESERVOIR FILL SYSTEM 

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 DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 Ye llow 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 1 TotaL 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 E FFT

F9008B 

Printed in France 
-------------------------------------------------------------------------------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 Tota L Capacity I 20 I 5.3 I 1 

R I Max. Capacity shown on 1 I I I 

R 1 the 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 1 with the normal nitrogenl 

R 1 I 1 1 precharging pressure in 1 

R I I' 1 the brake accumuLator 1 

R 1 1 1 1 2582GM and the auxiLiary' 

R 1 1 1 1 brake 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 ALL 12-12-29 Page 308 

Aug 	 01/08 

F90089 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 I 12-12-29 Page 309 

Aug 01/08 

IFFT I F90090 

Printed in France 
-----

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

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 A GROUND POWER UNIT WITH A CAPACITY LESS THAN 90 KVA. IF 

YOU USE A LESS 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) 

EFF 24-41-00 Page 201 : ALL r Feb 01/07 

\ F90091 

IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR fiNANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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. 

r;;--:~------------------l 24-41-00 Page 202 

Feb 	 01/07 

R 1m 	 I F90092 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

External Power Receptacle - Location 


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


r--------­ 24-41-00 Page 203 IEFF: ALL Feb 01/01 

I F90093 

IFFT 

Printed in France 
----

-----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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) If 	the 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 

r-- --­

IEFF ALL ----------] 24·41·00 Page 204 

Aug 01/08 

}FFT I 	 F90094 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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). 

r;;;-~----~~~--------------------------------l 24 -41-00 Page 205 

May 01/08 I 	 I 

R I 	 \ F90095 

IFFT I 


Printed in France 

------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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. 

rFF-~----~LL 24-41-00 Page 210 

Feb 	 01/01 I 

IFFT 

F90096 

Printed in France 
----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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. 

24-41-00 Page 211 ALL Feb 01/01 

F90097 

Printed in France 
--------------

------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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. 

[-~~~----------------l 24·42 ·00 Page 204 

Feb 	 01101 

F90098 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

(1) Disconnect the 

snap hook from 

connector 

the suppo

of the ground power unit and release the 

rt. 

Subtask 24-42-00-410-052 

C. Close Access 

(1) Close the access door 121AL. 

Page 205 

Feb 01/01 [;;;-~---ALL ------, 24-42-00 

F90000 

\FFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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). 

r;;;-~-~~-----------------------, 29-00 -00 


Page 257 

R I I Nov 01/07 

IFFT . I 

F90100 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b}(4). 

~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. 

Sub task 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 Y HYD/ELEC/PUMP 3802GX AB06 

123VU Y HYD/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). 

~----ALL ---------­ Page 258 

Nov 01/07 

R \ 	 F90101 

----, 29-00 -00 

\FFT I

Printed in France 
-----

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UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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. 

r-----------------.--------___, IEFF ALL 29-00-00 Page 259 

R I 	 /) Nov 	01/07

/FFT 

/ 	 F90102 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

(/$)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) • 

ALL 29-00-00 Page 260

Nov 	 01/07 

F90103 

Printed in France 
-----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$JA3181A3191A 320 

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 A HYDRAULIC 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 

r---­

IEFF 	 ALL -1 29-10-00 Page 220 

I 	 May 01/05 I 

IFFT 

F90104 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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 A HYDRAULIC 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. 

----------, 29 -10 -00 ~- ALL Page 221

May 	 01/05 

F90105 \ \ IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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). 

IEFF ALL 

r 	

------, 29 -10 -00 Page 222 I 	 May 	01105 ! IFFT 

F90106 

Printed in France 
------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

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. Put 	the 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). 

r----------­

EFF: ALL 	 29-10-00 Page 223 

May 	 01/05 

F90107 FFT l 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT. 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

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 the 	access door 198CB. 

ALL 29-10-00 Page 224 

May 01/05 

F90108 

Printed in France 
----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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 A HYDRAULIC 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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. Put 	the 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 29·10·00 Page 202 

I 	 May 01102 IF FT F90110 

Printed in France 
----------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF 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 A HYDRAULIC 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 MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 Y HYD/ELEC/PUMP 	 3802GX AB06 

123VU Y HYD/ELEC/ELEC PUMP/NORM 	 3801GX AB03 

r---- ---­ ...., EFF ALL 29-10-00 Page 204 

Hay 	01/01 

IFFT 

F90112 

Printed in France 
---

-----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$pA3181A3191A320 

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 

Printed 	in France 
------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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). 


29-10-00 Page 206 

Feb 	 01/06 

F90114 

Printed in France 
---------- -----

-----

-----

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

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF 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 A HYDRAULIC 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 

r--'----' 29-23-00 Page 201 IEFF 	 ALL 

Feb 01/01 I 

F90115 \FFT 

Printed in France 
-----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 Y HYD/ELEC/PUMP 

123VU Y HYD/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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

HYO 


SYSTEM IDENTIFICATION-+-+--GREEN BLUE 


~ PSI 

ELEC 

.....-+-+-PTU STATUS 

ACTUAL SYSTEM PRESSURE -+-+-- 3000 PSI 

ISO PSI INCREMENTSI 

PTU ,..,..-- I I AUXILIARY (ELEel PUMP 

/tISTATUS 

G.W.60300KG 

C.G.21I.1% 

SYSTEM DISPLAY 

EXPLANATION OF PTU STATUS SYMBOLS 

~-~ I _.-'1 PTU [> I { GREEN-PTU PIB SW AUTO AND PrU NOT SUPPLYING 

AMBER-PTU Pts SW OFF 

.1_ I-­__..I--~ PTU ~ 

~ {GREEN)-PTU SUPPLIES GREEN HYDRAULIC SYSTEM h!2I§.; THIS SYMBOL ALSO APPEARS ON THE GROUND WHEN THE 

. I ---... -J 1--_..--.....,..-.... PrU......-, 

GREEN SYSTEM ONLI( IS SUPPLIED FROM A GROUND SUPPL I( 

AND THE PTU IS SET TO AUTO 

(GREEN) - Pru SUPPLIES YELLOW HYDRAULIC SYSTEM 

ECAM Lower DU during Power Transfer 


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


r;;-:---~LL -------, 29-23-00 Page 204 

feb 01/01 

/FFT J 

I F90118 

Printed in France 
----

----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f!;A 3181A 3191A 320 

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 A HYDRAULIC 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT. 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 	 I DENT. LOCAnON 

R 

121VU HYDRAULIC/HYD POWER/Y 3803GX N30 

123VU Y HYD/ELEC/PUMP 3802GX AB06 

123vu YHYD/ELEC/ELEC PUMP/NORM 3801GX AB03 

r------------------------_____ IEFF: ALL 1 	29-24-00 Page 202 

May 	 01/01 

IFFT I 

F90120 

Printed in France 
-

--------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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) • 

ALL 29-24-00 Page 203 

Feb 	 01/01 

1 	 F90121 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A31B/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

OIl!IH 

(l) 

It 

V 


0 


RAT MAN ON 

[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 

8 SAT < 18"C Utile CoG. 28 I"

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-HYDRAULIC PAGE 

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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

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----­ --, 29-24-00 Page 205 IEFF ALL 

I 	 Feb 01/01 

F90123 IFFT 	 \ 

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

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UNDER THE FREEDOM OF INFORMATION ACT, 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 MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 A RISK 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---­ ---------, 32-41-11 Page 402 IEFF ALL Aug 	 01/07 I 

F90125 \ \FFT 

Printed in France 
----

----

---------~------.--------. 

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

A WHEEL 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. 

r------------------------------_. IEFF 	 ALL 32-41-11 Page 403 I 	 Aug 01/07 

/FFT l F90126

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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 

r----------- ------'-'-----1 32-41-11 Page 404 IEFF ALL Feb 01/01 

F90127 

\FFT I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

R (7) Remove the wheel (1). 

---------, EFF ALL 32-41-11 Page 405 

I Aug 01/07

{ 

FFT 

F90128 

Printed in France 
-

----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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. A VERY HOT BRAKE 

CAN CAUSE THE GREASE TO BURN AND CAUSE A FIRE. 

£~~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) 

r'---' 

IEFF 	 ALL 32-41-11 Page 406 

Aug 01/07 ! 

I 	 F90129 

IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE 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 

r---------------·----------.--­ IEFF ALL 	 -] 32·41·11 Page 407 

Feb 	 01/08 

IFFT 

F90130 

I 	 I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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------------------' 32-41-11 Page 408 

Aug 01/07 

R I 	 I 

F90131 IFFT 	 I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

A DIFFERENT 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: If 	you 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). 

r---­

, 	32-41-11 Page 409 

Nov 01/07 

IEFF 	 ALL 

I 

R IFFT F90132 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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. A VERY 

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 


A WHEEL 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 

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THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 whee l. 

(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). 

r 

EFF ALL 	 --------------1 32 -41-11 

I Page 411 

Aug 01107 

IFFT 

F90134 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~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. 

r;;;--:-~LL-----,;..-----------l 32·41·11 Page 412 

Aug 	 01/07 

F90135 IFFT 	 I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f!;A318fA319fA320 

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 spec ifi c self-adhesive fabric tape 

No specific temporary placard 

No specific vinyl hose 

No spec ifi 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 

R 

I 

IEFF ALL ------, 32 -42-00 Page 412 

Feb 01/05 

F90136 FFT I 


Printed in France 

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U,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. 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. 

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) • 

r----	-'---------------1 32-42-00 Page 413 R IEFF ALL Feb 	 01/05 

F90137 

IFFT 

Printed in France 
--- ----------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$)A3181A3191A320 

AIRCRAFT MAINTENANCE MANUAL 

INTENTIONALLY BLANK 


l 32·42·00 Page 414 

May 01/03

I F90138 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

INTENTIONALLY BLANK 


Page 415 

Feb 01/05 

I 32·42·00 

I F90139 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

INTENTIONALLY BLANK 


R ~----------------- --, 32 -42 -00 Page 416 

Feb 01/05 

F90140 IFFT I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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. 

-1 32·42·00 Page 417 ALL 

Nov 	 01/02 

F90141 

\ 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U,S,C, § 552(b)(4). 

f$)A3181A 3191A320 

AIRCRAFT MAINTENANCE MANUAL 

NOTE: THE GREEN HYDRAUUC 

CONNECTION ON THE BRAKE 

UNR'S IS A1.WAYS 

IN FRONT OF THE LEG GEAR. 

12842GM 1-,....", '""IIo..JiIP....I"""IL 

WHEEL SIDE 

---YEU.OW PRESSURE 

GREEN 

PRESSURE 

LEG GEAR SIDE 

BRAKE TEMPERATURE l.-=":":-~-- SENSOR ELEC'IRIC CONNECTION 

2 

Normal Brake Deactivation 

Figure 403/TASK 32-42-00-991-004 

I

r;----------------------

EF F: ALL 32-42-00 Page 418 

R I Nov 01/02 

JFFT ) 

F90142 

Printed in France 
----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 pushed 

rake 

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 	

EFF ALL ----------------1 32-42-00 Page 419 

Nov 01/02 

R 

F90143 IFFT 

Printed in FranCe 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 5S2(b)(4). 

~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~~--------------------' 32-42-00 Page 420 

Nov 	 01/02 

F90144 R IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT,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------------------1 32-42-00 Page 518 

Aug 01/08 

I F90145 FFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

3 . .:!,ob Set-up 


Sub task 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 

r--------------------------__ )EFF: ALL --'1 32-42-00 Page 519 

Aug 01/08 

IFFT I 

F90146 

Printed in France 
--------------------------------------------------------------------------------

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

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

B 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.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 Sub task 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-------------------, 32-42 -00 Page 520 

Aug 01/0S I I 

F90147 IFFT I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 I 32-42-00 Page 521 IEFF Aug 01/08 

I F90148 IFFT I 

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UNDER THE FREEDOM OF INFORMATION ACT, 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: appL ied: 


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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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--------------------------­ IEFF ALL 32-42-00 Page 524 

Aug 	 01/08

I 

F90151 IFFT 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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. 

I 2642GMI 

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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDERTHE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

NOTE: -THE YB..LOW HYDRAUUC 

CONNECTION ON THE BRAKE 

UNITS IS N..WAYS 

BEHIND THE LEG GEAR. 

-THE GREEN HYDRAUUC 

CONNECTION ON THE BRAKE 

UNITS IS N..WAYS 

IN FRONT OF THE LEG GEAR. 

8 

0 

::E 

ell 

ell 

.... 

0 

0 

C\I 

.... 

C\I 

CO) 

l() 

:2 

z 

WHEEL SIDE 

A 

!2644GM] 

I~ 

11 10 9 

LEG GEAR SIDE 

6 

Deactivation with Brake RemovaL 


R Figure 402/TASK 32-42-00-991-002


R[EFF-~~-------------------------------~ 32-42-00 Page 406 

May 01/03 

F90153 

IFFT \ 

Printed in France 
----------

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

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 spec if i 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 IFFT 	 ) F90154 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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. 

-----------------------, IEFF-~----~ZL . 32-42-27 Page 408 

May 	 01/07 I 	 F90155 

\FFT 

Printed in France 
------

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

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 	 f May 01/07

IFFT 

F90156 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

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 MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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------------------­

EFF: ALL -----1 32·42·27 Page 411 

May 01/07 

F90158 IFFT 	 I 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAIN"rENANCE MANUAL 

13 

/2641GMr-t 

ZA 

JJ A [2643GMI

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 

F90160 
THI3 DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT. 5 U.S.C. § 552(b)(4). 

f$)A3181A 3191A 320 

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 32-42-27 Page 608 

Feb 01/08 I 

R IFFT F90162 1 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

ALL ---I 32·46 ·00 Page 501

May 01/03 

F90163 

\ 

Printed ;n France 
---------------------------- .. 

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 IFFT I 	 F90164 

Printed in France 
-----

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 ALL 	 32-46-00 Page 503 

Aug 	 01/08 

F90165 

Printed in France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIALINFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 

R I 32-46-00 Page 504 

r 

EFF 201-202, 801-899, 925-999, 

Aug 01/08 

F90166 FFT 

• 

Printed in France 
THIS DOCUMENT MAY CONTAINTRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 AI DR 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 MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPTFROM DISCLOSURE 

. UNDER THE FREEDOM OF INFORMATION ACT, 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 IEFF ALL 32-47-15

Aug 01/06 

\ F90169 

IFFT 

Printed in France 
------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 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 France 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 ALL 	 32-42-27 Page 401 

Nov 01/05 

Printed in France 	 F90172 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

f$)A3181A3191A320 

AIRCRAFT MAINTENANCE MANUAL 

C. Referenced Information 

REFERENCE 	 DESIGNA nON 

---------------------------------------------------------------------------~--

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 ALL 32-42-27 Page 402

May 01/07 

F90173 Printed;n France 
-------------------------------------------------------------------------------

THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF .INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

I$JA3181A3191A320 


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 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 

fHT 

Printed in France F90174 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 

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May 01/07 

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F90175 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE MANUAL 

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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 F90176 
THIS DOCUMENT MAY CONTAIN TRADE SECRETS AND CONFIDENTIAL COMMERCIAL OR FINANCIAL INFORMATION EXEMPT FROM DISCLOSURE 

UNDER THE FREEDOM OF INFORMATION ACT, 5 U.S.C. § 552(b)(4). 

~A318/A319/A320 

AIRCRAFT MAINTENANCE 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 a 	blanking 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 	 l 32·42·27 Page 406 

May 	 01/07 

IFFT 	 I 

F90177 Printed in France