DOC AIRBUS | AMM A320FCompressor Rotor Blade Erosion Molded Impression Check [CFMB]
TASK 72-31-00-200-011-A
Compressor Rotor Blade Erosion Molded Impression Check
This task gives the instructions to do an engine level molded replication test of the High Pressure Compressor (HPC) stage 1 blade leading edge serviceability after the observation of a stall or ENG STALL message.
When the penetration of the HPC at shop visit is not planned, for the engines with either more than 10,000 cycles since new, or more than 5,000 cycles since the last HPC refurbishment, this procedure should be performed.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 72-31-00-941-063-A ** ON A/C NOT FOR ALL
Subtask 72-31-00-480-057-A ** ON A/C NOT FOR ALL
Subtask 72-31-00-410-074-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:42:13 UTC
Compressor Rotor Blade Erosion Molded Impression Check
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
ZONE: 400
1. Reason for the JobThis task gives the instructions to do an engine level molded replication test of the High Pressure Compressor (HPC) stage 1 blade leading edge serviceability after the observation of a stall or ENG STALL message.
When the penetration of the HPC at shop visit is not planned, for the engines with either more than 10,000 cycles since new, or more than 5,000 cycles since the last HPC refurbishment, this procedure should be performed.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 1M(3 FT) |
| No specific | 1 | BLADE - RAZOR |
| No specific | 1 | BORESCOPE DIA 6 MM (0.236 IN) LENGTH 3 M (9,84 FT) |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 115 and 105 lbf.in (1.30 and 1.19 m.daN )  | |
| 856A3114 | 1 | WRENCH-VBV BALLSCREW ACTUATOR |
| 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 71-13-00-010-040-B | Opening of the Fan Cowl Doors |
| TASK 71-13-00-410-040-B | Closing of the Fan Cowl Doors |
| TASK 72-23-00-000-027-A | Removal of the Fan Duct Panels |
| TASK 72-31-00-290-002-A | Inspection of the High Pressure Compressor Rotor Assembly |
| TASK 75-31-60-000-002-A | Removal of the Bleed Valve and Ballscrew Actuator Assembly |
| TASK 75-31-60-400-002-A | Installation of the Bleed Valve and Ballscrew Actuator Assembly |
| TASK 78-30-00-081-041-B | Make the Thrust Reverser Serviceable after Maintenance |
| TASK 78-30-00-481-041-B | Make the Thrust Reverser Unserviceable for Maintenance |
| TASK 78-36-00-010-040-B | Opening of the Thrust Reverser Doors |
| TASK 78-36-00-410-040-B | Closing of the Thrust Reverser Doors |
Borescope ClampSubtask 72-31-00-941-063-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred a sufficient time before you do this procedure. This is to make sure that the engine is sufficiently cool and that the tooling or the repro material will not melt.
(3) On 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) in position to tell persons not to energize FADEC 1(2).
Subtask 72-31-00-010-070-A ** ON A/C NOT FOR ALL (1) On the center pedestal, on ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred a sufficient time before you do this procedure. This is to make sure that the engine is sufficiently cool and that the tooling or the repro material will not melt.
(3) On 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) in position to tell persons not to energize FADEC 1(2).
B. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR.
(2) Put a ACCESS PLATFORM 1M(3 FT) in position.
Subtask 72-31-00-040-057-A ** ON A/C NOT FOR ALL Subtask 72-31-00-010-071-A ** ON A/C NOT FOR ALL (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR.
(2) Put a ACCESS PLATFORM 1M(3 FT) in position.
D. Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.
Subtask 72-31-00-010-072-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.
E. Remove the fan duct panel from the fan frame at the 2:30 o'clock position to gain access to the Variable Bleed Valve (VBV) door (Ref. AMM TASK 72-23-00-000-027).
Subtask 72-31-00-010-073-A ** ON A/C NOT FOR ALL F. Removal of the Bleed Valve and Ballscrew Actuator Assembly:
4. ProcedureCAUTION:
DO NOT ADJUST THE POSITION OF THE VARIABLE BLEED-VALVE DOOR ASSEMBLY. IF YOU DO, DAMAGE TO THE VARIABLE BLEED-VALVE DOOR ASSEMBLY CAN OCCUR.
(1) Remove the bleed valve and ballscrew actuator assembly (Ref. AMM TASK 75-31-60-000-002). Subtask 72-31-00-480-057-A ** ON A/C NOT FOR ALL
A. Attach the borescope clamp to the threaded hole in the case using a 1/4-28 bolt.
(1) The 6 mm (0.24 in.) hole must be positioned near the edge of the VBV opening so that it is not in the way when the impression is attempted.
(2) The borescope clamp (part of the GE-CFMI-628 (J060275)) can be attached to either bolt hole, or oriented with the clamp portion pointing towards or away from the VBV opening, whichever position is easier for the inspector.
Subtask 72-31-00-480-058-A ** ON A/C NOT FOR ALL (1) The 6 mm (0.24 in.) hole must be positioned near the edge of the VBV opening so that it is not in the way when the impression is attempted.
(2) The borescope clamp (part of the GE-CFMI-628 (J060275)) can be attached to either bolt hole, or oriented with the clamp portion pointing towards or away from the VBV opening, whichever position is easier for the inspector.
B. Insert the borescope through the clamp and into the VBV cavity.
(1) The optimum position for the BORESCOPE DIA 6 MM (0.236 IN) LENGTH 3 M (9,84 FT) is against the inner wall of the cavity with the articulation at 90 degrees towards the stage 1 compressor blades.
(2) Once a good image of the leading edge of the stage 1 compressor blades is achieved, tighten the borescope clamp.
(3) Look at the articulation of the BORESCOPE DIA 6 MM (0.236 IN) LENGTH 3 M (9,84 FT) (steer and stay) if your borescope is so equipped.
Subtask 72-31-00-200-050-A ** ON A/C NOT FOR ALL (1) The optimum position for the BORESCOPE DIA 6 MM (0.236 IN) LENGTH 3 M (9,84 FT) is against the inner wall of the cavity with the articulation at 90 degrees towards the stage 1 compressor blades.
(2) Once a good image of the leading edge of the stage 1 compressor blades is achieved, tighten the borescope clamp.
(3) Look at the articulation of the BORESCOPE DIA 6 MM (0.236 IN) LENGTH 3 M (9,84 FT) (steer and stay) if your borescope is so equipped.
C. Do the erosion molded impression test as follows:
(1) Mix equal parts of the two-part fast setting putty (part of the GE-CFMI-628 (J060275)).
(a) Knead both parts together between your fingers until a uniform blue color is achieved.
(b) An amount enough to fill the cup on the application tool (part of the GE-CFMI-628 (J060275)) plus some extra should be mixed. The correct volume is approximately equal to two milliliters.
(2) Generously fill the cup on the application tool with the putty mixture.
(a) Make sure that you press the material into the cup so that any excess is forced through the holes in the side of the cup.
(b) The material that is squeezed through the holes will serve to keep the material firmly in the cup when the application tool is removed from the blade.
(3) After filling the cup, position the cup on the leading edge of the stage 1 compressor blades as quickly as possible.
(a) Press the cup firmly onto the blade using slight handle pressure.
(5) Remove the sample from the cup of the application tool.
(a) It may be necessary to trim material from the holes on the sides of the cup to remove the material.
(b) Mark the sample number on the sample using a felt tip pen.
(6) Rotate the engine core approximately 90 degrees and repeat the process.
(a) Four samples approximately 90 degrees apart need to be taken (Ref. AMM TASK 72-31-00-290-002).
(7) Evaluate the samples by cutting them with a BLADE - RAZOR perpendicular to the impression of the blade edge.
(a) The cross section should be evaluated approximately 0.25 in. (6.3 mm) from the blade tip.
(b) A cross section of each blade leading edge should be evaluated per the blunt leading edge inspection.
1 If a sample is determined as serviceable as shown in the figure, the blade passes.
2 If a sample is determined to be non-serviceable as shown in the figure, the blade fails.
(8) Complete the inspection data sheet for this inspection.
(a) If any one of the four samples fail the blunt leading edge inspection, then refurbish the HPC rotor assembly.
(b) If all of the four samples pass the blunt leading edge inspection, then this procedure is complete.
Subtask 72-31-00-420-066-A ** ON A/C NOT FOR ALL (1) Mix equal parts of the two-part fast setting putty (part of the GE-CFMI-628 (J060275)).
(a) Knead both parts together between your fingers until a uniform blue color is achieved.
(b) An amount enough to fill the cup on the application tool (part of the GE-CFMI-628 (J060275)) plus some extra should be mixed. The correct volume is approximately equal to two milliliters.
(2) Generously fill the cup on the application tool with the putty mixture.
(a) Make sure that you press the material into the cup so that any excess is forced through the holes in the side of the cup.
(b) The material that is squeezed through the holes will serve to keep the material firmly in the cup when the application tool is removed from the blade.
(3) After filling the cup, position the cup on the leading edge of the stage 1 compressor blades as quickly as possible.
(a) Press the cup firmly onto the blade using slight handle pressure.
NOTE: The putty sets in approximately one minute from mixing.
NOTE: It is helpful to have a small amount of extra material from the mix at the workstation to determine when the material is fully cured.
(4) Once the material is cured, remove the tool by gently working the putty free of the blade using a rocking motion of the handle. (5) Remove the sample from the cup of the application tool.
(a) It may be necessary to trim material from the holes on the sides of the cup to remove the material.
(b) Mark the sample number on the sample using a felt tip pen.
(6) Rotate the engine core approximately 90 degrees and repeat the process.
(a) Four samples approximately 90 degrees apart need to be taken (Ref. AMM TASK 72-31-00-290-002).
NOTE: The number of blades in HPC Stage 1 compressor is 38.
1 For a 90 degrees rotation, make sure that you count nine blades. (7) Evaluate the samples by cutting them with a BLADE - RAZOR perpendicular to the impression of the blade edge.
(a) The cross section should be evaluated approximately 0.25 in. (6.3 mm) from the blade tip.
(b) A cross section of each blade leading edge should be evaluated per the blunt leading edge inspection.
1 If a sample is determined as serviceable as shown in the figure, the blade passes.
2 If a sample is determined to be non-serviceable as shown in the figure, the blade fails.
(8) Complete the inspection data sheet for this inspection.
(a) If any one of the four samples fail the blunt leading edge inspection, then refurbish the HPC rotor assembly.
(b) If all of the four samples pass the blunt leading edge inspection, then this procedure is complete.
D. Install the bleed valve and ballscrew actuator assembly as follows (Ref. AMM TASK 75-31-60-400-002):
(1) Make sure that the retaining nuts on the captive bolts are in the correct position.
(a) If not, adjust with 856A3114 WRENCH-VBV BALLSCREW ACTUATOR as follows:
1 When the bolt if fully out, the bolt end must be set back from the hole bottom with the nut against the inner mating surface.
2 When the bolt is fully in, the nut must be set back from the hole bottom.
a Tighten the captive bolts but do not torque them.
4 Align the actuator door in its seat.
a TORQUE the upper bolts and then the lower bolts to between 115 and 105 lbf.in (1.30 and 1.19 m.daN ).
5. Close-up(1) Make sure that the retaining nuts on the captive bolts are in the correct position.
(a) If not, adjust with 856A3114 WRENCH-VBV BALLSCREW ACTUATOR as follows:
1 When the bolt if fully out, the bolt end must be set back from the hole bottom with the nut against the inner mating surface.
2 When the bolt is fully in, the nut must be set back from the hole bottom.
CAUTION:
DO NOT ADJUST THE POSITION OF THE VARIABLE BLEED-VALVE DOOR ASSEMBLY. IF YOU DO, DAMAGE TO THE VARIABLE BLEED-VALVE DOOR ASSEMBLY CAN OCCUR.
CAUTION:
DO NOT COAT THE THREADS OF THE BLEED-VALVE-DOOR CAPTIVE BOLTS FOR INSTALLATION. IF YOU DO, DAMAGE TO THESE PARTS CAN OCCUR.
3 Install the VBV and ballscrew actuator in its recess. a Tighten the captive bolts but do not torque them.
4 Align the actuator door in its seat.
a TORQUE the upper bolts and then the lower bolts to between 115 and 105 lbf.in (1.30 and 1.19 m.daN )
. Subtask 72-31-00-410-074-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 doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.
Subtask 72-31-00-440-058-A ** ON A/C NOT FOR ALL Subtask 72-31-00-410-075-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 doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.