DOC AIRBUS | AMM A320FLubrication of the LPC Bleed Valve Mechanism [IAE]
TASK 72-00-00-600-011-A
Lubrication of the LPC Bleed Valve Mechanism
A. This task is for V2500-A5 engines.
B. This task gives the procedure to lubricate the LPC bleed valve mechanism of the LP compressor/intermediate case module. Lubrication is necessary if friction force of the mechanism is thought to be too large.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 72-00-00-941-111-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-020-065-A ** ON A/C NOT FOR ALL
Pre SBE 72-0155
(1) Remove the 18 screws (11) which attach the rear fairing (12) to the LP compressor bleed duct.
(a) Do not remove the sealant in the hole position No. 6 and 16 in the rear fairing.
(2) Move the rear fairing rearward fully.
Subtask 72-00-00-020-066-A ** ON A/C NOT FOR ALL
SBE 72-0155: A new LPC bleed duct with improved durability features.
(1) Remove the 20 screws (11) which attach the rear fairing (12) to the LP compressor bleed duct.
(2) Move the rear fairing rearward fully.
Subtask 72-00-00-640-055-A ** ON A/C NOT FOR ALL
(1) Put lubricant (Material No.V10-108) in to the GUN - SPRAY.
(2) Install the HOSE LENGTH 1,2 M (3,93 FT) - FLEXIBLE on to the IAE6F10408 EQUIPMENT-BORESCOPE.
(3) Connect the other end of the hose to the spraying gun. Use applicable adapters between the hose and the spraying gun if necessary.
Subtask 72-00-00-640-056-A ** ON A/C NOT FOR ALL
Pre SBE 72-0155
(1) Align the through holes in the rear fairing with the threaded holes in the bleed duct.
(2) Attach the rear fairing to the bleed duct with the 18 screws (11).
(a) Do not install the screws in to the holes No. 6 and 16.
(3) TORQUE the screws to between 45 and 36 lbf.in (0.51 and 0.41 m.daN )
Subtask 72-00-00-420-069-A ** ON A/C NOT FOR ALL
SBE 72-0155: A new LPC bleed duct with improved durability features.
(1) Align the through holes in the rear fairing with the threaded holes in the bleed duct.
(2) Attach the rear fairing to the bleed duct with the 20 screws (11).
(3) TORQUE the screws to between 45 and 36 lbf.in (0.51 and 0.41 m.daN ).
Subtask 72-00-00-020-067-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-410-155-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:44:01 UTC
Lubrication of the LPC Bleed Valve Mechanism
ZONE: 400
1. Reason for the JobA. This task is for V2500-A5 engines.
B. This task gives the procedure to lubricate the LPC bleed valve mechanism of the LP compressor/intermediate case module. Lubrication is necessary if friction force of the mechanism is thought to be too large.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | AR | COVER - SHEET |
| No specific | AR | GUN - SPRAY |
| No specific | AR | HOSE LENGTH 1,2 M (3,93 FT) - FLEXIBLE |
| No specific | 1 | TAPE - ADHESIVE |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 45 and 36 lbf.in (0.51 and 0.41 m.daN ) | |
| IAE6F10408 | 1 | EQUIPMENT-BORESCOPE |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V10-108) | lubricant |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 71-00-00-710-013-C | Test No.11 : High Power Assurance Test |
| TASK 71-13-00-010-010-A | Opening of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-13-00-410-010-A | Closing of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 78-30-00-040-012-A | Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance |
| TASK 78-30-00-440-012-A | Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance |
| TASK 78-32-00-010-010-A | Opening of the Thrust Reverser Halves |
| TASK 78-32-00-410-010-A | Closing of the Thrust Reverser Halves |
Installation of Cover Sheet on the Fan CaseSubtask 72-00-00-941-111-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
Subtask 72-00-00-010-155-A ** ON A/C NOT FOR ALL (1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
B. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010)
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
Subtask 72-00-00-040-084-A ** ON A/C NOT FOR ALL (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010)
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
C. Deactivate the thrust reverser.
Subtask 72-00-00-010-157-A ** ON A/C NOT FOR ALL WARNING:
MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Deactivate the thrust reverser hydraulic control unit (HCU) (Ref. AMM TASK 78-30-00-040-012). D. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
Subtask 72-00-00-941-112-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
E. Put the ACCESS PLATFORM 1M(3 FT) in position to give access to the fan case rear end.
Subtask 72-00-00-420-067-A ** ON A/C NOT FOR ALL F. Install an applicable COVER - SHEET on the ACOC inlet hole in the fan case to prevent unwanted materials that can go in to the ACOC.
4. ProcedureSubtask 72-00-00-020-065-A ** ON A/C NOT FOR ALL
CAUTION:
CAREFULLY REMOVE THE SCREWS NOT TO LET THEM FALL IN THE BLEED AIR PASSAGE IN THE BLEED DUCT. THE SCREWS GO IN TO THE HP COMPRESSOR AND BREAK THE BLADES AND THE VANES. DISASSEMBLE THE ENGINE AND REMOVE THE SCREWS IF THEY FALL IN THE BLEED AIR PASSAGE.
CAUTION:
BE CAREFUL NOT TO LET LOOSE OBJECTS FALL IN THE BLEED AIR PASSAGE. THIS CAN CAUSE FOREIGN OBJECT DAMAGE (FOD) TO THE HP COMPRESSOR.
A. Open the rear fairing Pre SBE 72-0155
(1) Remove the 18 screws (11) which attach the rear fairing (12) to the LP compressor bleed duct.
(a) Do not remove the sealant in the hole position No. 6 and 16 in the rear fairing.
(2) Move the rear fairing rearward fully.
CAUTION:
CAREFULLY REMOVE THE SCREWS NOT TO LET THEM FALL IN THE BLEED AIR PASSAGE IN THE BLEED DUCT. THE SCREWS GO IN TO THE HP COMPRESSOR AND BREAK THE BLADES AND THE VANES. DISASSEMBLE THE ENGINE AND REMOVE THE SCREWS IF THEY FALL IN THE BLEED AIR PASSAGE.
CAUTION:
BE CAREFUL NOT TO LET LOOSE OBJECTS FALL IN THE BLEED AIR PASSAGE. THIS CAN CAUSE FOREIGN OBJECT DAMAGE (FOD) TO THE HP COMPRESSOR.
B. Open the rear fairing SBE 72-0155: A new LPC bleed duct with improved durability features.
(1) Remove the 20 screws (11) which attach the rear fairing (12) to the LP compressor bleed duct.
(2) Move the rear fairing rearward fully.
WARNING:
DO NOT BREATHE GAS FROM TEFLON BASED LUBRICANT. PUT A PROTECTION ON YOUR MOUTH. THE GAS CAN IRRITATE YOU.
C. Set the tools and lubricant for lubrication (1) Put lubricant (Material No.V10-108) in to the GUN - SPRAY.
(2) Install the HOSE LENGTH 1,2 M (3,93 FT) - FLEXIBLE on to the IAE6F10408 EQUIPMENT-BORESCOPE.
NOTE: You can not look directly at the pins which the lubricant is to be applied to. You can access and apply the lubricant to the pins with the borescope and hose which are attached together.
(a) Attach the hose to the borescope. Wind an TAPE - ADHESIVE on them at the position near the ends of the hose and the borescope. (3) Connect the other end of the hose to the spraying gun. Use applicable adapters between the hose and the spraying gun if necessary.
D. Apply the lubricant (Material No.V10-108) to the 10 pins
(b) The 10 angular positions are equally apart. Calculate the remaining eight angular positions with the two positions given in step (a).
(a) Put the borescope and the hose in to the clearance between the 2.5 SV shroud and the support ring at the angular position given in step (1).
(b) Find the pin with the borescope. Move the borescope and hose near the pin.
(c) Apply the lubricant to the pin with the spraying gun and hose.
Subtask 72-00-00-420-068-A ** ON A/C NOT FOR ALL NOTE: You must do the high power assurance test (Ref. Para. "Do the High Power Assurance Test") or next aircraft take-off within four hours after lubrication of the pins. The bleed valve mechanism is driven by the engine run and the mechanism movement makes the lubricant spread fully on the outer diameter faces of the pins. But, the lubricant can dry in four hours and dried lubricant can not spread.
(1) Find the 10 angular positions where you put the borescope. NOTE: You are recommended to put the borescope in to the engine at the angular positions near the 10 pins. You can easily find the pins with the borescope if you put it at the positions. This step makes you know the angular positions.
(a) Find the two actuating rods. Two of the 10 angular positions are at the same position as the actuating rods. (b) The 10 angular positions are equally apart. Calculate the remaining eight angular positions with the two positions given in step (a).
WARNING:
DO NOT BREATHE GAS FROM TEFLON BASED LUBRICANT. PUT A PROTECTION ON YOUR MOUTH. THE GAS CAN IRRITATE YOU.
(2) Lubricate each pin. (a) Put the borescope and the hose in to the clearance between the 2.5 SV shroud and the support ring at the angular position given in step (1).
(b) Find the pin with the borescope. Move the borescope and hose near the pin.
(c) Apply the lubricant to the pin with the spraying gun and hose.
CAUTION:
CAREFULLY INSTALL THE SCREWS NOT TO LET THEM FALL IN THE BLEED AIR PASSAGE IN THE BLEED DUCT. THE SCREWS GO IN TO THE HP COMPRESSOR AND BREAK THE BLADES AND THE VANES. DISASSEMBLE THE ENGINE AND REMOVE THE SCREWS IF THEY FALL IN THE BLEED AIR PASSAGE.
CAUTION:
BE CAREFUL NOT TO LET LOOSE OBJECTS FALL IN THE BLEED AIR PASSAGE. THIS CAN CAUSE FOREIGN OBJECT DAMAGE (FOD) TO THE HP COMPRESSOR.
E. Close the rear fairing Pre SBE 72-0155
(1) Align the through holes in the rear fairing with the threaded holes in the bleed duct.
(2) Attach the rear fairing to the bleed duct with the 18 screws (11).
(a) Do not install the screws in to the holes No. 6 and 16.
(3) TORQUE the screws to between 45 and 36 lbf.in (0.51 and 0.41 m.daN )
CAUTION:
CAREFULLY INSTALL THE SCREWS NOT TO LET THEM FALL IN THE BLEED AIR PASSAGE IN THE BLEED DUCT. THE SCREWS GO IN TO THE HP COMPRESSOR AND BREAK THE BLADES AND THE VANES. DISASSEMBLE THE ENGINE AND REMOVE THE SCREWS IF THEY FALL IN THE BLEED AIR PASSAGE.
CAUTION:
BE CAREFUL NOT TO LET LOOSE OBJECTS FALL IN THE BLEED AIR PASSAGE. THIS CAN CAUSE FOREIGN OBJECT DAMAGE (FOD) TO THE HP COMPRESSOR.
F. Install the rear fairing SBE 72-0155: A new LPC bleed duct with improved durability features.
(1) Align the through holes in the rear fairing with the threaded holes in the bleed duct.
(2) Attach the rear fairing to the bleed duct with the 20 screws (11).
(3) TORQUE the screws to between 45 and 36 lbf.in (0.51 and 0.41 m.daN )
. G. Remove the cover sheet from the fan case
5. Close-upSubtask 72-00-00-410-155-A ** ON A/C NOT FOR ALL
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 72-00-00-440-083-A ** ON A/C NOT FOR ALL Subtask 72-00-00-410-156-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
C. Close Access
(1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
Subtask 72-00-00-710-062-A ** ON A/C NOT FOR ALL (1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
D. Do the high power assurance test (Ref. AMM TASK 71-00-00-710-013)
NOTE: This test is not necessary if the aircraft can take-off within four hours after lubrication of the pins (Ref. Para. "Apply the Teflon based lubricant to the 10 pins").
(1) Increase the N1 speed of the engine, of which LPC bleed valve mechanism was lubricated, equal to or more than the minimum LP rotor speed in accordance with the ambient temperature. NOTE: Excercising of the LPC Bleed Valve Mechanism can also be performed during the next take-off if this take-off is accomplished within 4 hours of completion of the lubrication task.