TASK

Procedure to use CFDS, the A/C being in the jacking configuration (TASK 31-32-00-869-003)
98D32603000000 (6) SIMULATION PLATE - FLIGHT/GROUND
Take the applicable precautions before you open the LGCIU circuit breakers (Ref. TASK 32-00-00-860-
001). Open C/B (C09, Q35), Install the tool, Close C/B (C09, Q35), after you close the LGCIU circuit
breakers, put the aircraft back to the correct (ground) configuration (Ref. TASK 32-00-00-860-002).
Flight Configuration Precautions with Electrical Power (TASK 32-00-00-860-001)
To prevent damage to the anti-ice heat elements: - when the LGCIU 1/2 circuit breakers are open or -
when the A/C is lifted on jacks.
Set the EXT PWR pushbutton switch to the OFF position. Set the MAINT BUS switch to the OFF
position.
WARNING: OPEN THE PITOT-PROBE HEATER CIRCUIT-BREAKERS 3DA1, 3DA2 AND 3DA3
BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1, 2DA2 AND 2DA3. OPEN THE WINDOW
HEAT CIRCUIT-BREAKERS 4DG1 AND 4DG2, AND THE WINDSHIELD HEATER CIRCUIT-
BREAKERS 1DG1 AND 1DG2, BEFORE YOU OPEN THE WHC CIRCUIT-BREAKERS 5DG1 AND
5DG2. OPEN CIRCUIT BREAKERS 1JH, 2JH1, 2JH2, 3JH1 AND 3JH2 (ENGINE 1 AND 2 IGNITION
SYSTEMS). THEN OPEN CIRCUIT BREAKERS 2KS1 AND 2KS2 (FADEC A AND EIU 1 AND 2) AND
4KS1 (FADEC B AND EIU 1).
Do a reconfiguration of the avionics compartment ventilation system (Ref. TASK 21-26-00-860-001).
Configuration of the Avionics Compartment Ventilation System (TASK 21-26-00-860-001)
To have a good flow of air in the avionics compartment when the aircraft is in flight configuration. This is
to do all the maintenance procedures when the external temperature is more than 12 deg.C.
On the skin air outlet-valve and the skin air inlet-valve, Push the PUSH latch to release the handle.
Pull the handle to engage the mechanism. Fold out the handle. Set the deactivation switch to OFF.
Turn the handle to fully open the main flap. Fold, stow and latch the handle.
On the skin-exchanger isolation valve, outlet bypass-valve and inlet bypass-valve, Disconnect the
connector from the valve. Put blanking caps on the disconnected electrical connectors. Keep the
electrical cable with its connector near the valve and attach them with an adhesive tape. Fully close the
valve with the manual mechanism (F position).
NOTE: Because the horn is not serviceable in flight, BLOWER and EXTRACT pushbutton switches must
be in AUTO configuration (pushed, with the FAULT and the OVRD legends off).
Do an operational test of the avionics ventilation system (Ref. TASK 21-26-00-710-001).
Update of the APU Hours and Cycles in the DMU after APU, ECB or DMU Replacement (TASK 31-
36-00-740-004)
ON A/C 001-099, Push the APU MASTER SW button, Push the MCDU MENU, AIDS, DOCUMENTAT/
PROGRAMMING, PROGRAMMING MENUS, PRINT REPORT, INDIVIDUAL REP PROG, INT
COUNTERS, Enter the digits 13 alphanumeric keys and push the line key (1L) under the REPORT
Indication, Enter the hours of the replacement APU with the alphanumeric keys and push the line key
adjacent to the < APU OPERATING HRS indication, Enter the cycles of the replacement APU with the
alphanumeric keys and push the line key adjacent to the < APU OPERATING CYC indication, Push the
line key adjacent to the PRINT indication, Push the line key adjacent to RETURN indication to memorize
the new values.
ON A/C 201-299, MCDU MENU, AIDS, SPECIAL FUNCTION/ REPROGRAMMING, STATISTIC
COUNTER, Enter the values for the APU hours, Push the LSK adjacent to the numbers and asterix of
the APU HRS indication, Push the arrow down mode key, Enter the values for the APU cycles offset with
the alphanumeric keys. Push the LSK adjacent to the numbers and asterix of the APU CYC indication,
Push the LSK adjacent to the RETURN indication 2 times.
Update of the Engine Hours and Cycles in the DMU after Engine or DMU Replacement
(TASK 31-36-00-740-005)
ON A/C 001-099, push the ENG/FADEC GND PWR/1, 2 buttons, MCDU MENU, AIDS
DOCUMENTAT/ < PROGRAMMING, PROGRAMMING MENUS, PRINT REPORT, INDIVIDUAL REP
PROG, INT COUNTERS, Enter the digit 1 with the alphanumeric keys and push the line key (1L) under
the REPORT indication, NEXT PAGE until EHRS1 ENG1 HRS indication comes into view, Enter the
hours of the replacement engine with the alphanumeric keys and push the line key adjacent to the
EHRS1 ENG1 HRS indication, Push the line key adjacent to RETURN to memorize the new values.
ON A/C 201-299, MCDU MENU, AIDS, SPECIAL FUNCTION/ REPROGRAMMING, STATISTIC
COUNTER, READ ONLY, Enter the values for Engine 1 hours, Push the LSK adjacent to the numbers
and asterix of the Engine-1 FLT HRS indication, Push the arrow down mode key, Enter the values for the
 TASK
Engine 1 cycles offset with the alphanumeric keys. Push the LSK adjacent to the numbers and asterix of
the ENGINE-1 CYCLES indication, Push the LSK adjacent to the RETURN indication 3 times.
Printout of the APU Hours and Cycles (TASK 31-36-00-740-006)
ON A/C 001-099, MCDU MENU, AIDS, CALL-UP PARAM ALPHA, Enter the Alpha Call-up Code
(AHRS) with the alpha-numeric keys, Push the line key 1L to take over the Alpha Call-up Code AHRS,
Enter the Alpha Call-up Code (ACYC) with the alpha-numeric, Push the line key 3L to take over the
Alpha Call-up Code ACYC, Push the line key adjacent to PRINT indication.
Printout of the Engine Hours and Cycles (TASK 31-36-00-740-007)
ON A/C 001-099, MCDU MENU, AIDS, CALL-UP PARAM ALPHA, Enter the Alpha Call-up Code
(EHRS) with the alpha-numeric keys, Push the line key 1L to take over the Alpha Call-up Code AHRS,
Enter the Alpha Call-up Code (ECYC) with the alpha-numeric, Push the line key 3L to take over the
Alpha Call-up Code ACYC, Push the line key adjacent to PRINT indication.
Printout of the Engine / APU Hours and Cycles Stored in the FDIMU (TASK 31-36-00-740-015)
ON A/C 201-299, MCDU, AIDS, SPECIAL FUNCTION REPROGRAMMING, STATISTIC COUNTER,
READ ONLY (The data for Engine and APU flight hours), Push the arrow down mode key (The data for
Engine and APU cycles).
Tire Mixability Precautions (TASK 32-41-00-910-001)
ON A/C 001-007, Post SB 32-1300 For A/C 008-099, Tire Mixing on the MLG Not applicable.
ON A/C 008-099, 201-299, Tire Mixing on the MLG Allowed mixing 46 x 16 - 20 and 46 x 17 R20 may be
mixed without restriction.
ON A/C ALL, Tire mixing on the NLG, The mixing of bias tires with radial tires is not permitted on the
NLG. (1) Radial tires: (a) you can mix these radial tires: Bridgestone P/N APR05140 and P/N APR05145
with Michelin P/N M04201 and P/N M08201 with. Sumitomo P/N SR11261T, P/N SR11262T, P/N
SR11263T. (b) For Goodyear radial tires you can mix only: Goodyear P/N 309Q62-1 with P/N 309Q62-2
(2) Bias tires: You can mix these bias tires: Michelin MATC P/N 039-539-0 and P/N 039-539-1.
Inspection/Check of the Wheels and Tires (TASK 32-41-00-210-002)
THE LIMIT SPEED IS 225 MPH (195 KTS).
A. Visual Inspection of the Wheels: (1) Examine the drive shroud of the tachometer. (2) No cracks on the
wheel rims. (3) No leaks on the valves. (4) If there are paint marks on the wheel/tire assembly, make
sure that the position of the tire related to the wheel is the same.
B. Visual Inspection of the Tires: - make sure that there are no air leaks, - make sure that there is no
damage by friction, - make sure that they are worn equally, - make sure that there are no cuts and flat
spots, - remove the wheel when the tire is worn to the base of any groove in any location or if you can
see any reinforcing material. - Make sure that the tire pressure is in the specified limits. - Remove the
wheel when the tire shows signs of a tread bulge. - If the tread is not worn equally and if it is necessary,
remove the wheel and put it on the opposite axle. - If you find tread wear on the shoulder of the tire,
inflate the tire to the nominal inflation pressure plus 10 per cent.
(MICHELIN) (1) Tread Surface (a) CUTS: the metallic protector is not damaged or you cannot see it.
(Keep the tire). (b) BROKEN AWAY: if the protector ply is in view on more than 6 cm2 (Remove the tire).
(c) CHEVRON CUTTING: if chevron cutting goes to and exposes the protector ply (Remove the tire).
(d) FLAT SPOTS: the flat spot goes to the protector ply (Remove the tire). (e) WEAR: if wear goes to the
bottom of any groove along more than 1/8 of the circumference at a given location (Remove the tire).
(f) TREAD JOINT IS OPENED: as soon as you can see the opening (Remove the tire). (g) GROOVE
CRACKING: if the protector ply is in view on more than 6 mm (continuous) (Remove the tire).
(h) RIB UNDERCUTTING: if undercutting goes more than 5.5 mm below the rib (Remove the tire).
(2) Sidewalls (a) RADIAL or INCLINED CUTS, CRACKS OR SPLITS: if the sidewall cords are in view or
damaged (Remove the tire). (b) SEPARATION/BULGES: none permitted (Remove the tire).
(3) Beads The bead wires are in view, the beads or the bead wires are deformed, the part of the bead
that touches the rim flange is worn, Blisters on the top of the bead above the rim flange (Remove the tire)
(DUNLOP) (a) Superficial cuts in the tread and/or sidewall rubber that do not go into the breakers or the
cords of the casing plies. (b) Cracking or splits in the sidewall if you cannot see the cords of the casing
plies. (c) Unevenly worn tires or tires worn on the shoulder can remain in service until worn to the base of
the tread pattern or to normal wear limits whichever occurs the sooner. (d) Tires which have been
subjected to sideways scrubbing can remain in service until fully worn. (e) Rubber blisters in the lower
sidewall if: - The blisters are not more than two and none of them is more than 25.4 mm in diameter.
- The blisters are not less than 304.8 mm apart when measured circumferentially.
 TASK
(GOODYEAR) (1) Tread Wear: You must remove the tires when the tread has worn to the base of any
groove at any spot. You must remove the tires worn to the fabric in the tread area regardless of the tread
remaining. (2) Uneven Tread Wear: If tread wear is excessive on one side, you can remove the tire and
turn it around, if you cannot see the fabric. (3) Tread Cuts: Follow the removal criteria below: - Any cuts
into the reinforcing material. - Cuts that extend more than half of the width of a rib and deeper than 50%
of the remaining groove depth. (4) Sidewall/Bead Damage: Remove tire from service if weather
checking, cracking, cuts and snags extend down to a carcass ply in the sidewall and bead areas.
(5) Bulges: remove from service immediately. (6) Fabric Fraying/Groove Cracking: You must remove the
tires from service if groove cracking exposes fabric or if cracking undercuts tread ribs. (7) Flat Spots:
Usually, tires need not be removed unless you can see the fabric.
(BRIDGESTONE) (1) Criteria relative to tread wear: (a) NORMAL WEAR: The groove depth is more than
1 mm on the whole tread (Keep the tire), the groove depth is less that 1 mm at any point of the tread
surface (Remove the tire), the aramid protector is in view (Remove the tire). (b) FLAT SPOT ON TREAD
SURFACE: The flat spot goes as far as the aramid cord protector (Remove the tire). (2) Tread surface
(a) CUTS and BROKEN AWAY: The aramid cord protector is not in view or view but not damaged (Keep
the tire). (b) GROOVE CRACKING: The aramid cord protector is not in view (Keep the tire).
(c) RIB UNDER CUTTING: cut depth less than or equal to 1/4 inch (Keep the tire).
(d) OPENED TREAD JOINT: (Remove the tire). (e) Blisters, Bulges: (Remove the tire). (3) Sidewalls
(a) CRACKS OR SPLITS: (Radial cuts) depth less than 2 mm length less than 150 mm (Keep the tire),
(Inclined cuts) Do not go as far as the carcass and length less than 150 mm (Keep the tire),
(b) FABRIC SEPARATION: (Remove the tire). (c) BLISTERS OR BULGES: (Remove the tire).
(4) Beads (a) EXPOSURE OF BEAD WIRES: (Remove the tire). (b) DEFORMATION: (Remove the tire).
(c) CRACKS: Cracks in upper part of bead zone depth of the crack more than 1 mm (Remove the tire).
(d) WEAR: The wear of the tire surface near the upper edge of the rim depth of the worn area more than
2 mm (Remove the tire). (e) BLISTER: Blister in upper part of bead zone length or diameter more than
10 mm (Remove the tire).
Inspection/Check of the Pressure of Tires (TASK 32-41-00-210-003)
Do the check when the tires are cold, if it is necessary to do the check when the tires are hot: The
pressure in the tires will be higher than the nominal value; you must not deflate a hot tire.
The pressure of all the tires must be in the same range.
If all the pressures are approximately the same, and higher than the specified operating pressure, no
other steps are necessary. If the pressure of a hot tire is less than or equal to the pressure specified for a cold
tire, this tire is defective.
REMOVE BOTH
NORMAL REMOVE TIRE
TIRES
A320 NLG 178-187 144-161 0-144
(OLD) MLG 165-174 133-149 0-133
A320 NLG 178-187 144-161 0-144
(NEW) MLG 174-182 139-156 0-139
NLG 168-177 135-151 0-135
A321
MLG 212-223 170-191 0-170

Inspection/Check of the Brake with the Wheel Installed (TASK 32-42-27-210-001)

With the brakes on, make sure that the wear indicators are in the limits.
Measure the wear pin when the brake is cold (Brake temperature less than 60 deg.C).
 TASK
When the end of either wear pin aligns with the machined surface of the piston housing, the heat pack is
fully worn. You must replace the brake unit.
For a new brake, measure the distance between the end of the wear pin and the machined surface of the
piston housing. This distance must be 50mm maximum. If more than the maximum value replace the
brake.
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 on the brake unit.
Inspection of the Fan Case Assembly (TASK 72-32-85-200-010)
Examine the Attrition Linings
(a) Blade tip rubs are acceptable if the maximum depth of
the rubbing is less than 2.54 mm.
(b) Wear, gouge and galling are acceptable if following
limits are not exceeded: (1) The GRC layer is not
damaged. (2) Maximum dimension of the damaged area
is less than 76.2 mm in axial width and 254.0 mm in the
circumferential width. (3) A total of five areas of damage
within 1 and 2 are acceptable, if they are separated by a
distance equal to the maximum dimension of the nearest
damaged area. (4) Any number of damaged areas within
1 whose maximum dimensions are less than 25.4 mm
measured in axial width and 38.1 mm in the
circumferential width are acceptable, if they are
separated by at least 76.2 mm of undamaged lining.
(c) Circumferential scores of the attrition linings are
acceptable if following limits are not exceeded: (1) The
GRC layer is not damaged. (2) Scores of any length are
acceptable, if the lining around them is undamaged.
(d) Damage more than in (a), (b) and (c) is acceptable, if
The GRC layer is not damaged. And the linings will have repair within 100 flight hours or 50 flight cycles.
(e) Damage deeper than GRC layer (1) If damaged area at the GRC layer is less than 20 per cent of
each attrition lining, repair within 50 flight hours or 25 flight cycles.(2) Damage more than in (1), repair
within 10 flight hours or 5 flight cycles.
(f) Any cracks are acceptable.
(g) Unbond on the linings is acceptable, if the limits that follows are not exceeded: (1) The unbond
area(s) are less than 5 percent in the edge of the each attrition lining panel. (2) The unbond area(s) are
less than 5 percent in the each attrition lining panel, except are of step (1). (3) The lining panel will be
repaired within 10 flight hours or 5 flight cycles whichever is the sooner.
(h) Unbond more than (g) is acceptable if: (1) The damaged area is less than 10 percent of the total area
of each attrition lining panel. (2) The lining panel will be repaired within 5 flight hours or 2 flight cycles.
Examine the Acoustic Linings
(1) If there are cracks – repair.
(2) Scores not more than 0.05 mm in depth and less than 25.4 mm in length, are acceptable.
(3) Damage more than in (2) is acceptable if: (a) The depth of the scores does not exceed 0.1 mm. (b)
The linings will be repaired within 500 flight hours or 250 flight cycles.
(4) Smooth dents in the lining are acceptable, if following limits are not exceeded: (a) The dents are less
than 55.0mm in diameter. (b) The bond between the perforated skin and honeycomb is not broken.
(5) Damage more than in (4) is acceptable if: (a) The dents are less than 5.5mm in depth. (b) The bond
between the perforated skin and honeycomb is not broken. (c) The linings will be repaired within 350
flight hours or 400 flight cycles.
(6) Damage more than in (3) or (5) is acceptable if: (a) The linings will be repaired within 250 flight hours
or 125 flight cycles.
(7) Unbond in the linings are acceptable, if the limits that follows are not exceeded: (a) The unbond
area(s) are less than 7 percent in the area at edge of the each acoustic lining panel. (b) The unbond
area(s) are less than 20 percent in the area other than edge of the each acoustic lining panel. (c) The
lining panel will be repaired within 50 flight hours or 25 flight cycles whichever is the sooner.
 TASK
(8) Unbond more than (7) is acceptable if: (a) The damaged area is less than 30 percent of the total area
of each acoustic lining panel. (b) The lining panel will be repaired within 10 flight hours or 5 flight cycles
(9) Missing perforated skin is acceptable if: (a) Not more than one acoustic lining perforated skin is
completely missing. (b) The lining will be repaired within 10 flight hours or 5 flight cycles.
Examine the anti-ice impact panels
(1) Multiple damage marks or indentations provided the GRC skin is not penetrated, are acceptable.
(2) Damage more than in (1) is acceptable if: (a) The panels will have repair within 50 flight hours or 25
flight cycles. (b) The damaged area is less than 20 per cent of each anti-ice impact panel.
Examine the flanges the outer surface and the inner surface
(1) Nicks, scratches, galls or scores, bolt hole burrs in the outer surface and the inner surface - repair.
Examine the blue filler
(1) Erosion of the blue filler between anti-ice impact panel and the acoustic lining that is not more than
5.08 mm in depth, is acceptable.
(2) Damage that is more than in (1) - repair, within 160 flight hours or 80 flight cycles.
Reset of the Wing Tip Brake (WTB) of the Flap System on the Ground (TASK 27-50-00-869-006)
Open C/B (B03, M18); Make sure that the Green, the Yellow and the Blue hydraulic systems are
depressurized, Open the C/B (Q21), MCDU, SFCC 1, NEXT PAGE, TEST/RESET FLP, WTB-RESET,
START WTB RESET. If the reset of the WTB is not performed and no SFCC fault is displayed, do the
steps that follow: open the C/Bs (B07, B06, P20, P19, Q21, R21, S07, S06). wait five seconds. close the
C/Bs. repeat steps again. Close the C/B (Q21), Open the C/B (B07), MCDU, SFCC 2, NEXT PAGE,
TEST/RESET FLP, WTB-RESET, START WTB RESET, Close the C/B (B07), Move the slat and flap
control lever in the flap extension and retraction direction. Check all the flap system torque limiters and
reset as necessary. Do the operational test of the flap system.
Reset of the Wing Tip Brake (WTB) of the Slat System on the Ground (TASK 27-80-00-869-004)
Open C/B (B03, M18); Make sure that the Green, the Yellow and the Blue hydraulic systems are
depressurized, Open the C/B (R21), MCDU, SFCC 1, NEXT PAGE, SLT TEST/RESET, WTB-RESET,
START WTB RESET. Close the C/B (R21), Open the C/B (B06), MCDU, SFCC 2, NEXT PAGE, SLT
TEST/RESET, WTB-RESET, START WTB RESET, Close the C/B (B07), Move the slat and flap control
lever in the flap extension and retraction direction. Check all the slat system torque limiters and reset as
necessary. Do the operational test of the slat system.
Reset of the Torque Limiters of the Flap System on the Ground (TASK 27-50-00-866-010)
Pressurize the Yellow and Green hydraulic system, Open C/B (B06, R21), Put the slat/flap control lever
to the last position that had been set, before the torque limiter(s) operated. Open C/B (B07, P20, Q21,
S07), Push each applicable indicator down so that it aligns with the torque limiter. Do the operational test
of the flap system.
Reset of the Torque Limiters of the Slat System on the Ground (TASK 27-80-00-866-006)
Pressurize the Blue and Green hydraulic system, Open C/B (B07, Q21), Put the slat/flap control lever to
the last position that had been set, before the torque limiter(s) operated. Open C/B (B06, P19, R21, S06),
Push each applicable indicator down so that it aligns with the torque limiter. Do the operational test of the
slat system.
Visually Examine the Mixed Exhaust System (TASK 78-10-00-200-012)
Examine the inner duct and the acoustic panel
(a) Cracks: 2.7 mm wide or less - Reject. Larger than 2.7 mm
wide or less - Reject.
(b) Dents, gouges, nicks, scratches, and disbonds (Ref. TASK 78-
10-00-200-013).
(c) Loose or missing fasteners - Not allowed.
Examine the side support struts
(a) Nicked, scored, and scratched More than 0.51 mm after
burnishing or blending Reject.
(b) Cracked - Reject.
(c) Dents, gouges, nicks, scratches, and disbonds (Ref. TASK 78-
10-00-200-013).
(d) Loose or missing fasteners - Not allowed.
Examine the engine exhaust cone
(a) Cracked flange of engine exhaust cone - Reject.
(b) Dents, gouges, nicks and scratches (Ref. TASK 78-10-00-200-013).
 TASK
(c) Loose or missing fasteners - Not allowed.
Visually Examine the Mixed Exhaust System - Allowable Damage Data (TASK 78-10-00-200-013)
(1) Dent: (inner duct, acoustic panel, exhaust cone) 50.8 mm maximum length, 3.05 mm maximum
depth. 25.4 mm maximum radius, No face sheet thinning, crushed core acceptable. No two within 76.2
mm, 38.1 mm minimum from honeycomb core edge, Inspection interval at operator option.
(2) Scratch: (inner duct, acoustic panel, exhaust cone, support struts) 38.1 mm maximum length, 0.127
mm maximum depth, 1.27 mm maximum width, Surface penetration only. No two within 50.8 mm, 38.1
mm minimum from honeycomb core edge, Inspection interval at operator option.
(3) Gouge: (inner duct, acoustic panel, exhaust cone, support struts) 38.1 mm maximum length.0.254
mm maximum depth, 2.54 mm maximum width, Surface penetration only with radiuses width. No
crushed core permitted. No two within 76.2 mm. 38.1 mm minimum from honeycomb core edge.
(4) Nick: (inner duct, acoustic panel, exhaust cone, support struts) 19.05 mm maximum length, 0.254 mm
maximum depth, 2.54 mm maximum width. No two within 50.8 mm. 38.1 mm minimum from honeycomb
core edge.
Fuel Tank Leak Checks (TASK 28-11-00-280-002)
To find the fuel leak, do the applicable leak test as
follows: NOTE: Only do the applicable leak test
procedure(s) for the fuel tank related to the fuel leak.
It will not be necessary to do the leak test
procedures for all the other fuel tanks. (Ref. TASK
28-11-00-790-001, 002, 003, 004, 005, 006, 007)
Leakage Rate Analysis
There are three types of fuel leakage. These are
related to flight safety and are identified as follows:
(a) Light leakage: Dry the area of the leak. After 10
minutes there is a fuel leak indication that does not
go more than 100mm in any direction.
(b) Heavy leakage: Dry the area of the leak. After 10
minutes there is a fuel leak indication that is
between 100mm and 180mm in any direction.
(c) Continuous leakage: Dry the area of the leak.
After 10 minutes there is a fuel leak indication that is
more than 180mm in any direction.
Leakage Type and Location
The correct procedure for the leakage type and
location is given in the Table that follows:
Check for Air in the Green/Blue/Yellow Hydraulic System (TASK 29-00-00-210-001)
A. Check for Air in the Green Hydraulic System.
Pressurize the Green hydraulic system until the hydraulic pressure is stable. Depressurize the Green
hydraulic system and let the hydraulic reservoir level become stable in 1 minute. Make sure that the
reservoir is pressurized to a minimum of 50 psi. If necessary pressurize it.
Read the gage of the Green reservoir and record the fluid level. Depressurize the reservoir of the Green
hydraulic system. After 5 minutes read the gage of the Green reservoir again and record the fluid level.
Compare the two levels. If the difference between the two levels is more than 2 l, do the related bleeding
procedure. If the difference is not more than 2 l, no bleeding operation is necessary.
B. Check for Air in the Blue Hydraulic System.
If the difference is not more than 1 l, no bleeding operation is necessary.
C. Check for Air in the Yellow Hydraulic System.
If the difference is not more than 1.5 l, no bleeding operation is necessary.
Check of the Green or Yellow Hydraulic System after Operation in a Possible Cavitation Condition
of the Engine Pump (TASK 29-00-00-280-006)
(1) Do the subsequent procedure after a engine pump operation for more than 5 minutes: With a closed
engine-pump fire valve, or With the RSVR LO LVL warning on the upper ECAM DU and the fluid index
below the minimum gageable level on the ECAM HYD system page.
NOTE: There are no time limits if the engine pump is set to OFF (ENG1 (2) PUMP FAULT/OFF
pushbutton on panel 40VU) with: The engine-pump fire valve open and the fluid level of the reservoir
above the low level.
 TASK
(a) Replace the related engine pump. (b) Do the operational test of the related hydraulic system. During
the test, slowly move only one flight control surface at a time. Do this to prevent a pressure decrease to
less than 2800 psi. (c) Do a check for particles in the filter bowl and the filter cartridge of the hydraulic
control unit of the thrust reverser, case-drain filter, HP filter. If you find particles: Replace the filter
cartridge. Flush the related hydraulic system. (d) Do the steps (b) thru (c) again, until all particles are
removed.
(2) Do the subsequent procedure, after a engine pump operation for more than 5 minutes: With the
RSVR LO LVL warning on the upper ECAM DU and the fluid index above the minimum gageable level
on the ECAM HYD system page.
(a) Do a check for particles: In the filter bowl and the filter cartridge of the hydraulic control unit of the
thrust reverser. In the case-drain filter bowl and the filter of the related engine pump. In the HP filter bowl
and the filter of the related system. (b) If you find particles: Do the steps (1) (a) thru (1) (d) of this
procedure. (c) If you find no particles: Do the operational test of the related hydraulic system. During the
test, slowly move only one flight control surface at a time. Make sure that the system pressure is more
than 2800 psi during the test. (d) If the system pressure is less than 2800 psi during the test: Do the
steps (1) (a) thru (1) (d) of this procedure.
Check of the Green, Yellow or Blue Hydraulic System after Operation in an Overheat Condition
(TASK 29-00-00-280-005)
If you operate the aircraft for more than one flight in an overheat condition (OVHT warning on the ECAM
display), do the subsequent work: (a) Do a sample check of the hydraulic fluid of the related hydraulic
system. (b) Make sure that the fluid properties are in the limits.
Replace the hydraulic fluid of the related hydraulic system, if the fluid properties are not in the limits.
Check Fluid Level on Reservoir Indicators (TASK 29-10-00-200-001)
Make sure the aircraft is in this configuration: speed brakes and spoilers retracted, thrust reversers
closed, cargo compartment door closed, all accumulators empty of fluid and pressurized with nitrogen to
the correct pressure, reservoirs pressurized to 50 psig, landing gear extended with the doors closed (one
main door of the main gear can be open), the position of the other hydraulic services is not important.
Look at the contents indicator on each reservoir and make sure that it shows:
- Yellow reservoir (with the brake accumulator empty of fluid and precharged with nitrogen) - 15 l
- Yellow reservoir (with the brake accumulator full of fluid at system working pressure) - 12 l
- Green reservoir (14 l) - Blue reservoir (6 l)
NOTE: These levels are for fluid temperatures between 10 and 20 deg.C (50 and 68 deg.F). If the
temperature is out of these limits, the volume of the fluid changes: - 0.5 l for 10 deg.C in the Green and
Yellow hydraulic systems, - 0.25 l for 10 deg.C in the Blue hydraulic system.
To Close the Spare-Seal Activating-Valve (TASK 32-11-13-860-001)
Examine the shock absorber gland housing for the points of hydraulic oil leakage:
(a) If the leak is from the gland housing and the sliding tube interface, or from the gland housing and the
main fitting interface: Examine the sliding tube for damage: (a) If you found damage, replace the shock
absorber. (b) If you did not find damage, do one of these procedures: - replace the shock absorber gland
seals, or - replace the shock absorber, or - close the spare-seal activating-valve.
NOTE: Hydraulic fluid can continue to show for some time.
Make a note in the aircraft technical log that the MLG spare-seal activating-valve has been closed.
NOTE: It is recommended that ALL gland seals on the applicable MLG are replaced at a subsequent
scheduled maintenance procedure.
Check of the External Leaks of the Hydraulic Components (TASK 29-00-00-790-001)
NOTE: - A leak is the quantity of fluid that comes out of a component that is sufficient to become a drop
or drops, or will possibly become a drop (approximately 20 drops = 1 cc). - A leakage is a quantity of
fluid on the surface of a component that is not sufficient to become a drop. - A stain is an area on the
surface of a component that has a different color. It is usually caused when fluid leakage becomes dry on
the component surface after high temperature operation.
NOTE: Do a check of the dynamic seals of pistons, slide valves and swivel joints with the system
pressurized, but do not operate the components. The dynamic seals move only with a short time interval,
and some cannot easily be monitored when they operate.
NOTE: If it is necessary to do a check of the external leaks of the engine driven pumps, do an engine run
of the applicable engine as follows: (a) Start the engine and let it become stable for 5 minutes. (b)
Operate the engine at 75 percent N1 and let it become stable for 5 minutes. (c) Operate the engine at
minimum idle and let it become stable for 5 minutes. (d) Stop the engine.
 TASK
(1) Operate the component.
(2) Do an inspection of the component for external leaks. If you find leaks, you must compare the
quantity of the leaks with the values given in the

table below:
NOTE: 1. For the elevator and the aileron
servocontrols, two leaks of more than the usual
operation limit are not permitted on the same
flight surface.
NOTE: 2. Make sure that the connection is tight
and the correct torque value is applied.
NOTE: 3. The total leaks from the components
and the connections, that are part of the
alternate brake system, must not be more than 10 drops/min.
NOTE: 4. Obey the subsequent leakage limits for the Yaw Damper Servo-Actuators: - If the leakage rate
is less than 4 drops per minute, no more steps are necessary - If the leakage rate is between 4 and 14
drops per minute, replace the yaw damper servo-actuator(s) before the subsequent 600 flight hours and
- If the leakage rate is between 15 and 30 drops per minute, replace the yaw damper servo-actuator(s)
before the subsequent 100 flight hours - If the leakage rate is more than 30 drops per minute, replace the
yaw damper servo-actuator(s) immediately.
NOTE: 5. A leak rate of 10 drops per minute is permitted, if the temperature is less than -40 deg.C (-
40.00 deg.F).
(3) System leak rate limits
(a) Usual leak rate limits: The total leak rate of the Green, Yellow and Blue systems must not be more
than 50 drops/min. If the temperature at the subsequent airport is less than -20 deg.C (-4.00 deg.F) fill
the applicable reservoir to the maximum level shown on the reservoir. Make sure that the drops of
hydraulic fluid do not fall on electrical equipment.
(b) Dispatch leak rate limits with a system leak rate of between 50 and 100 drops/min. Aircraft dispatch is
permitted if all of these rules are obeyed: The reservoir of the applicable system is full. The component
leak rate is less than the dispatch limit of 100 drops/min. One hydraulic system only has component
leaks of more than 50 drops/min. Do a check of the hydraulic reservoir levels. The drops of hydraulic fluid
do not fall on electrical equipment. Do these checks again before each flight.
(c) The total leak rate for the Green, Blue and Yellow systems must not be more than 100 drops/min.
Removal & Installation of the MLG Wheel (TASK 32-41-11-000-006)
 TASK
Open circuit breaker (L35, L32, M32, M31); Make sure that the PARK BRK control switch is set to ON.
Lift the related axle with a jack (Ref. TASK 07-12-00-582-002); Fully deflate the tire.
- Remove the fan: Remove the debris guard (23), Remove the impeller (19); - Remove the TPIS harness:
Disconnect the connector (30) from the plug (32); Remove the transducer (4). Remove the seals (2);
- Remove the joint and the shroud: Remove the shroud (18). Remove the shroud (18); - Remove the axle
nut (10) with the ADAPTOR MLG (H47682); - Install the PROTECTOR (F46754-1000); - Remove the
wheel (1).
- Install the new seals (2); - Install the transducer (4); - Align the wheel (1) with the driving keys on the
brake rotor and install the wheel; - Remove the PROTECTOR (F46754-1000); - Install the axle nut (10)
on the axle and tighten it with the ADAPTOR MLG (H47682); - set the PARK BRK control switch to OFF;
- Turn the wheel in the direction of the axle nut rotation and TORQUE the axle nut (10) to between
184.36 and 221.23 lbf.ft (2212.32 and 2654.76 lbf.in); - Prevent the rotation of the wheel and loosen the
axle nut (10) to between 36.87 and 73.74 lbf.ft (442.44 and 884.88 lbf.in); - Turn the wheel in the
direction of the axle nut rotation and TORQUE the axle nut (10) to 110.61 lbf.ft (1372.32 lbf.in); - Tighten
the axle nut (10) until the holes in the nut are aligned with the holes in the axle; - Turn the wheel
manually to make sure that it is installed correctly; - Install the joint (16) with the clamp (15) If necessary,
turn the transducer (29) to engage the drive dog (27) in its housing; - NOTE: The locating pin (34) puts
the joint (16) in the correct position. It locks the joint so that it cannot turn on the wheel (1); - Install the
shroud (18); - NOTE: Use the locating pins (17) on the joint (16) to put the shroud (18) in the correct
position; - Connect the connector (30) to the plug (32); - NOTE: The cable (7) must make a curve; -
Install the fan; Install the debris guard; - NOTE: The debris guard has holes of different diameters:
- Large diameter (two): to permit removal of the guard assy without removal of the shroud assy screws
(larger than the screw heads). - Medium diameter (two): to put the locating pins in the correct position.
Same holes on the shroud assy (centering function). - Small diameter (four): to put the four attachment
screws in the correct position; - Inflate the tire to the unloaded pressure; - Lower the aircraft on its
wheels; Make sure that the pressure of the tire is correct; Do the functional test of the tire pressure
indicating system.
ON A321: Remove the PROTECTOR (Q47316); - Install the axle nut (10) on the axle and tighten it with
the TORQUE ADAPTOR (460007230); - set the PARK BRK control switch to OFF; - Turn the wheel in
the direction of the axle nut rotation and TORQUE the axle nut (10) to between 294.98 and 324.48 lbf.ft; -
Prevent the rotation of the wheel and loosen the axle nut (10) to 0 torque; - Turn the wheel in the
direction of the axle nut rotation and TORQUE the axle nut (10) to between 147.49 and 162.24 lbf.ft; -
Tighten the axle nut (10) until the holes in the nut are aligned with the holes in the axle.
 TASK
Removal & Installation of the NLG Wheel (TASK 32-41-12-000-001) ON ALL A/C
Open circuit breaker (M31); Put the wheel chocks in position at the main landing gear; Make sure that
the safety devices are installed on the landing gears; Lift the nose gear (Ref. TASK 07-12-00-582-001);
Deflate the tire completely.
- Release the grommet (16) and remove the hubcap (12); - Disconnect the electrical connector (11) from
the connector (18); - Remove the pressure transducer (4); - Remove the preformed packings (3); -
Remove the axle nut (17) with the ADAPTOR NLG (J47549); - Install the PROTECTOR NLG (J47548); -
Remove the wheel.
Install the new preformed packings (3); - Install the pressure transducer (4); - Install the wheel, with the
valve outboard; - Remove the PROTECTOR NLG (J47548); - Install the axle nut (17); - Turn the wheel in
the direction of the axle nut rotation and TORQUE the axle nut (17) to160.76 lbf.ft (1929.12 lbf.in) with
the ADAPTOR NLG (J47549); - Prevent rotation of the wheel and loosen the axle nut (17); - Turn the
wheel in the direction of the axle nut rotation and TORQUE the axle nut (17) to 80.01 lbf.ft (960.12 lbf.in);
- Tighten the axle nut (17) until the holes for the bolts (10) are aligned; - Turn the wheel and make sure
that the wheel is installed correctly; - connect the electrical connector (11) to the connector (18); - Install
the grommet (16) and put the hubcap (12); - Engage the drive dog (13) in the fork of the rotating
mechanism; - Inflate the tire to the unloaded pressure; - Lower the aircraft on its wheels; Make sure that
the pressure of the tire is correct; Do the functional test of the tire pressure indicating system.

Jacking for Nose Gear Wheel Change (TASK 07-12-00-582-001)

NOTE: You can lift the aircraft at its maximum
weight with the passengers.

Put the hydraulic jack TMH CP 07 or equivalent in

position so that its adapter touches the ball-pad of
the shock absorber. Operate the jack to lift the tire
off the ground. Change the wheel. Do not lower
the aircraft on its wheels suddenly. To prevent
this, operate the control of the hydraulic jack slowly.
Jacking for Main Gear Wheel Change (TASK 07-12-00-582-002)
NOTE: You can lift the aircraft at its maximum weight with the
passengers.

Make sure that the parking brake is on. Installation of the wheel
chocks. Put the hydraulic jack TMH CR 15 or equivalent aft in position
so that its adapter touches the ball-pad of the shock absorber.
Operate the jack to lift the tire off the ground. Change the wheel. Do
 TASK
not lower the aircraft on its wheels suddenly. To prevent this, slowly operate the hydraulic control of the
jack.
Removal of the Torque Link Assy (TASK 32-21-27-000-001)
Make sure that the wheel chocks are in position. Lift the aircraft at the forward
jacking point.
Disconnect the center hinge: Remove the cotter pin (9) from the nut (8).
Remove the nut (8), the washer (7) and the screw (10). Hold the shaft (1) and
remove the nut (6) and the washer (5). Remove the shaft (1) with a plastic
drift. Remove the washers (4), (3) and (2).
Adjustment of the Water Flow-Time of the Water Faucet (TASK 38-12-00-820-001)
NOTE: The manufacturer has pre-adjusted the flow time of the water-faucet to 10 +2-2 s.
NOTE: The water pressure and the temperature effect the flow time of the water faucet; the colder the water, the
longer the flow time.
**ON A/C 001-099,
Set the water-faucet temperature control to the central position before you adjust the water-faucet flow time.
Remove the cover (1). Turn the adjusting screw in the knob (2) clockwise to decrease the flow time. Turn the
adjusting screw counterclockwise to increase the flow time. Operate the push knob (2).
Use a STOPWATCH and make sure that the water flows for between 10 and 18 seconds.
The maximum flow time of the water should not be more than 20 seconds.
**ON A/C 201-299,
Remove the cove (1). Use a WRENCH - HEXAGONAL and loosen the screw (2). Remove the knob (3). Use a
STOPWATCH and make sure that the water flows for between 10 and 18 seconds. The maximum flow time of the
water should not be more than 16 seconds.

Operational Test of a Potable Water Heater (TASK 38-12-00-710-004)

NOTE: The control light on the water heater will only go off when: - the water heater is switched off, - the water
heater is in operation and there is an over-temperature, - the quantity transmitter gives a low water level signal.
Cleaning of the Toilet Waste Lines with Crushed Ice (TASK 38-31-00-100-005)
Put (2 Lit) of crushed ice into the toilet assembly. Put (2 Lit) of pure vinegar (10% acetic acid solution) into the
toilet assembly and flush the toilet.
NOTE: The ice must be crushed, you must not use ice cubes.
Cleaning of the Vacuum Waste Lines with Chemical Cleaning Agent and Crushed Ice (TASK 38-31-00-100-
010)
Do the servicing of the waste holding tank. Make sure that the waste holding tank contains (50 Lit) of clean water.
Make sure that the potable water system contains water and is pressurized.
NOTE: Start the procedure at the most forward lavatory.
Flush the toilet assembly. Put (2 Lit) of crushed ice into the toilet assembly. Put (1 Lit) of CLEANING AGENTS
(Material No. 11-028) (HONEY BEE 60) into the toilet assembly and flush the toilet immediately 2 times. Do the
procedure for all of the toilets; After 30 minutes flush the toilet assemblies 3 times.
Cleaning of the Filter-Element of the Washbasin Drain-Valve Assembly (TASK 38-32-00-100-002)
Push and hold the drain knob (5). Push the plug (1) and turn it clockwise to unlock it and remove
the plug (1). Release the knob (5). Remove the filter (3) from the drain-assembly (4). If necessary
remove and discard the O-ring (2).
Put the filter (3) of the waste water drain-assembly in vinegar for approximately 30 min. Clean the
filter (3) with clean water. Use dry compressed air to fully dry the filter. Examine the filter for
damage; if necessary replace the filter (3).
 TASK
Cleaning of the Waste Water Drain Lines with Compressed Air (TASK 38-32-00-100-001- 01)
- Put a AIR COMPRESSED SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI) - REGULATED,
FILTERED, DRY in position at the drain valve. Install an applicable adaptor into the drain mast;
attached the air source to the adaptor.
- Get access to the blocked sink. Put a CONTAINER (1 Lit) under the drain valve. Loosen the
clamps (2) at the inlet hose (1) and outlet hose (4) of the valve (3).
Examine the drain valve for blockage, If the valve is blocked, clean the valve (Ref. AMM 38-32-00-
100-003). 383030).NOTE: Airbus recommends that you do the cleaning and test procedure of the
drain valve in the shop.
Operate the air compressed source and blow the lines through with 0.4 bar (6.0psi) from the drain
mast in the direction of the drain valve. If necessary clean the waste water drain lines with vinegar
(Ref. TASK 38-32-00-100-001).
**ON A/C 201-299,
Installation of the Washbasin Drain Valve (TASK 38-32-42-400-002)
**ON A/C 001-099,
Adjust the control cable as necessary: (Examples A and B) Put the operating handle (28) in the open position.
Adjust the nut (22) to get a clearance between the nut (22) and the valve body (21) of approximately (5 mm) max.
(Examples E and D) Put the operating handle (28) in the close position. Make sure that the lever (27) contacts the
close stop. Loosen the nut (25) and release the tension from the spring (23). Make sure that the plug (20) is in the
close position. Adjust the nut (25) until there is no clearance between the nut (25) and the lever (24). Make sure that
the spring (23) has no tension.
**ON A/C 201-299,
Pull the lever (1) up until it bottoms. Loosen the lock nut (6) and the stud (5); do not remove them from the block
(4). Push the washbasin drain plug down and tighten the stud (5) and the lock nut (6). Push the lever (1) in and
make sure that the washbasin drain plug opens. Loosen the lock nut (8) and the stud (9); do not remove them from
the block (10). Adjust the rod (11) until it is perpendicular with the rod (7) and tighten the studs (9) and the lock
nut (8). Adjust the stud (2) so that the lever (1) has enough friction to keep it in the pulled position. Tighten the lock
nut (3).
 TASK
Check Pressure at Door Escape-Slide/Slide Raft Pressure Gage (TASK 25-62-00-210-0010)
- Examine the pressure gages (2) at the door escape-slides/slide rafts and in the aft cargo-compartment
- Use an inspection mirror to let you see the gage (2) on the LH inflation reservoir (1).
NOTE: The cursor is sensitive to temperature changes and moves independently of the gage needle. It moves faster
by temperature changes than by gas expansion in the inflation reservoir (1).
- A correct indication is shown when the gage needle is in the green cursor (green GO band). The gage needle is to
the right of the green cursor.
- An incorrect indication is shown when the gage needle is to the left of the green cursor.
- If the gage (2) shows an incorrect indication let temperature conditions become stable, then examine the gage (2)
again. If the gage (2) continues to show an incorrect indication, replace the escape-slide/slide raft pack-assembly
and/or inflation reservoir (1). At the doors, replace the escape-slide/slide raft pack-assembly; in the aft cargo-
compartment, replace the inflation reservoir (1).
A320 A321

On A321: Access to the Inflation Reservoir; Do one of the two applicable steps: Open the door of the overhead
stowage compartment. Or; Push the quick-release fasteners (6) and open the access door (7).
 TASK
Discharging/Charging of the Damper and Emergency Operation Cylinder of the Passenger/Crew Doors
(TASK 52-10-00-614-001)
- Discharging of the Damper and Emergency Operation Cylinder; remove the blanking plug (1) from the filling
valve (2). Slowly loosen the nut (3) to release the pressure. Tighten the nut (3) when the pressure gage shows the
necessary pressure. Install the blanking plug (1) on the filling valve (2).
- Charging of the Damper and Emergency Operation Cylinder; remove the blanking plug (1) of the filling valve (2).
Connect a nitrogen filling system that has a pressure regulated gauge to the filling valve (2). Loosen the nut (3) of
the filling valve (2). Slowly open the filling system valve. Fill to the pressure indicated on the chart for the ambient
temperature.

Visual Inspection of the Rudder Servo Controls for Hydraulic Leakage (TASK 27-24-00-210-001)
Open the access doors 325CL, 325DL, 325CR, 325DR. Do several cycles of the rudder with the CAPT or F/O
pedals. Clean the vent hole (1) and the area around the vent hole of each servocontrol. Do again several cycles of
the rudder with the CAPT or F/O pedals. Do a visual check of the vent hole and the area around the vent hole.
Make sure that you can see no leak.

Check the Indicator of the No-Back Wear Detection-Device of the THS-Actuator (TASK 27-44-51-210-003)
Use a flashlight and examine the detection device (30). If the red pop-out (31) is released, examine the position of
the roller (32) on the detection device (30). If the roller (32) is in the position TRIPPED BY VIBRATION, reset the
red pop-out (31) by pushing the roller (32) with a tool, for example a small screwdriver, in the reset position. If the
roller (32) is in the position TRIPPED BECAUSE OF NO BACK WEAR, replace the THS-Actuator.
 TASK

Check the Oil Level of the Gearbox of the THS-Actuator (TASK 27-44-51-210-004)
- Pressurize the Green and the Yellow hydraulic systems. Turn the pitch-trim control wheel in the flight
compartment and move the THS-actuator a minimum of three times from the fully UP position to the fully
DOWN position. Turn the pitch-trim control wheel in the flight compartment and move the THS-actuator to the
zero position. Depressurize the Green and Yellow hydraulic systems. On the fuselage tail cone, make sure that the
THS is opposite the 0 mark.
- Do a check of the oil level at the oil sight glass (40) at approximately one hour after the last movement of the
THS-actuator. NOTE: The oil sight glass (40) minimum level mark can show a MINI mark or a 90cc mark.
If the oil level is between the minimum mark and the maximum mark, fill the gearbox to the maximum mark. If
the actuator housing temperature is less than 10 deg.C; we recommend that you fill the gearbox to a level of 1.5
mm less than the maximum mark. If the actuator housing temperature is more than 30 deg.C; we recommend
that you fill the gearbox to a level of 1.5 mm more than the maximum mark.
If the oil level is below the minimum mark, do a check for an external oil leak of the gearbox. If you find an
external oil leak, replace the THS-actuator. If you do not find an external oil leak, fill the gearbox to the
maximum level. Measure and record the quantity of oil that you add to the gearbox. If the actuator housing
temperature is less than 10 deg.C; we recommend that you fill the gearbox to a level of 1.5 mm less than the
maximum mark. If the actuator housing temperature is more than 30 deg.C; we recommend that you fill the
gearbox to a level of 1.5 mm more than the maximum mark.
- If the added oil quantity is less than 90 cm3, do a check of the oil level in less than 600FH, or less than
750FC, or less than 100 days. Do the check in the limits that come first.
- If the added oil quantity is more than 440 cm3, replace the THS-actuator.
- If the added oil quantity is more than 90 cm3 but less than 440 cm3; remove the position transducers (Ref.
TASK 27-44-56-000-001). Do a check for signs of oil. If you find oil replace the THS-actuator. If you do
not find oil install the position transducers. Remove the pitch trim actuator (Ref. TASK 27-44-57-000-001).
Do a check for signs of oil. If you find oil replace the THS actuator. If you do not find oil install the pitch
trim actuator. Replace the THS-actuator in less than 600FH, or less than 750FC, or less than 100 days. Do
the replacement in the limits that come first.
- During the time before you replace the THS-actuator, you must do checks of the oil level in the gearbox at
intervals. Refer to the table below for the intervals between the checks for a given quantity of added oil.
 TASK

Inspection of the Magnetic Chip Detector and Boroscope Inspection of the Power Gear of the THS-Actuator
(TASK 27-44-51-200-002)
Disconnect the drain plug (5) from the actuator housing. Examine the magnetic chip detector for metal particles. If
you find metal particles which are larger than 2 mm by 1 mm, do a boroscope inspection as written below. If you do
not find metal particles larger than given above, Clean the magnetic chip detector with a lint-free cloth. Connect the
drain plug (5) to the actuator housing.

Extension-Retraction of the Spoilers for Maintenance (TASK 27-60-00-866-002)

- Extend the slats and flaps. On the battery power center 105VU loosen the two screws and remove the protective
cover. Open C/B (B08, B01, Q19, Q18).
- Extension: Install the SPOILER MAINTENANCE KEY (98D27603002001) (2) on the servocontrol and turn it a
quarter turn counterclockwise. NOTE: If necessary, use a metal rod. to turn the spoiler maintenance key. Move
the spoiler to the extended position by hand. Put the COLLAR-SAFETY, SPOILER (98D27604000000) (3) on
the rod (1) of the servocontrol. Install the two pins of the safety collar (3).
- Retraction: Remove the two pins of the safety collar (3). Remove the safety collar (3) of the servocontrol. Move
the spoiler to the retracted position with your hand. Turn the SPOILER MAINTENANCE KEY
(98D27603002001) (2) a quarter turn clockwise and remove it.
TASK
TASK