Inspection of the High Pressure Compressor Rotor Assembly [CFMB]
TASK 72-31-00-290-002-A
Inspection of the High Pressure Compressor Rotor Assembly
Inspection of a High Pressure Compressor Rotor (HPCR) with the stator case installed is limited to those areas that can be seen with a rigid borescope. There are nine borescope ports (S1 through S9) in the compressor stator case, between the 4 and 5 o'clock position, aft looking forward.
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 72-31-00-941-052-A ** ON A/C NOT FOR ALL
Subtask 72-31-00-410-055-A ** ON A/C NOT FOR ALL
Subtask 72-31-00-410-057-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:42:14 UTC
Inspection of the High Pressure Compressor Rotor Assembly
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.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
1. Reason for the JobInspection of a High Pressure Compressor Rotor (HPCR) with the stator case installed is limited to those areas that can be seen with a rigid borescope. There are nine borescope ports (S1 through S9) in the compressor stator case, between the 4 and 5 o'clock position, aft looking forward.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | BAR LENGTH 60 CM (2 FT) BREAKER |
| No specific | 1 | CONTAINER 20 L - SHALLOW |
| No specific | AR | SPEED BRACE 3/4 IN - SQUARE DRIVE |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 20 and 15 lbf.in (0.23 and 0.17 m.daN ) ![]() | |
| No specific | Torque wrench: range to between 63 and 57 lbf.in (0.71 and 0.64 m.daN ) ![]() | |
| No specific | Torque wrench: range to between 85 and 75 lbf.in (0.96 and 0.85 m.daN ) ![]() | |
| No specific | Torque wrench: range to between 300 and 270 lbf.in (3.39 and 3.05 m.daN ) ![]() | |
| No specific | Torque wrench: range to between 550 and 450 lbf.in (6.22 and 5.09 m.daN ) ![]() | |
| 856A1084 | 1 | CART-STATOR ACTUATOR |
| 856A1320 | 1 | BORESCOPE-KIT |
| 856A1321 | 1 | FIBERSCOPE SET |
| 856A1322 | 1 | BORESCOPE-LIGHT SOURCE SET |
| 856A1323 | 1 | MONITOR, RESOLUTION BORESCOPE |
| 856A1488 | 1 | MOTOR, DRIVE - CORE ENGINE ROTATION |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.CP1064) | milk of magnesia |
| (Material No.CP2101) | graphite grease |
| (Material No.CP2619) | Never Seez-Pure Nickel, Special |
| (Material No.CP8001) | lockwire 0.032 in. (0.8 mm) dia. |
| (Material No.CP8002) | lockwire 0.032 in. (0.8 mm) dia |
| (Material No.CP8006) | safety cable 0.032 in. (0.8 mm) dia. |
| 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 71-00-00-710-001-B | Dry Motoring Check |
| TASK 71-00-00-710-006-B | Minimum Idle Check |
| 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 72-00-00-200-025-A | Over-Serviceable-Limit Extensions |
| TASK 72-00-00-200-025-A-01 | Over-Serviceable-Limit Extensions |
| TASK 72-21-00-290-003-A | Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 |
| TASK 72-31-00-300-002-A | Repair of Broken Borescope Plug |
| TASK 72-31-00-300-004-A | Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9 |
| TASK 72-63-00-000-002-A | Removal of the Handcranking Drive Cover |
| TASK 72-63-00-400-002-A | Installation of the Handcranking Drive Cover |
| 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 |
| TASK 80-11-10-000-002-A | Removal of the Pneumatic Starter |
| TASK 80-11-10-400-002-A | Installation of the Pneumatic Starter |
| NTM 720000 | |
Subtask 72-31-00-941-052-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 72-31-00-010-055-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. Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040)
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
Subtask 72-31-00-040-052-A ** ON A/C NOT FOR ALL Subtask 72-31-00-010-056-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
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.
4. Procedure(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
Subtask 72-31-00-410-055-A ** ON A/C NOT FOR ALL
A. Do a borescope installation:
(1) Use the 856A1323 MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure NTM 720000.
(2) Install the tools to turn the core engine.
1 Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter. (Ref. AMM TASK 72-63-00-000-002)
2 Install a SPEED BRACE 3/4 IN - SQUARE DRIVE with a BAR LENGTH 60 CM (2 FT) BREAKER into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward).
1 Remove the starter (Ref. AMM TASK 80-11-10-000-002).
2 Install the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P0/P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines.
4 Tighten the two captive bolts by hand.
5 Install the clamp to secure the drive motor.
6 Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(b) Remove the caps from the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04).
(c) Attach the rod-end and head-end hoses from the cart to rod-end and head-end connectors of the rod-end and head-end hoses you disconnected from the HMU.
(d) Actuate the variable stator system
(e) Disconnect the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04).
2 Disconnect the hoses of the cart from the rod-end and head-end hoses.
3 Install the caps on the cart hoses.
(f) Connect the rod-end and head-end hoses to the HMU.
.
2 TORQUE the rod-end hose to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )
.
(4) Remove the borescope plugs from the stages to be inspected as follows. Tag each borescope plug to identify the stage from which it was removed:
(b) Remove the IGV borescope plug (S1), if necessary, as follows:
1 Remove the two screws (20) that attach the borescope access blanking plate (10) at 5 o'clock, aft looking forward, on the fan frame inner flange.
2 Remove the borescope access blanking plate (10).
3 Remove the IGV borescope plug (S1).
4 Tag the plug to ensure it will be reinstalled in the correct port.
(c) Remove the stage 1 through stage 5 borescope plugs (S2 through S6), as necessary. Tag each plug to ensure it will be reinstalled in the correct port.
(d) Remove the stage 6, 7 and 8 borescope plugs (S7 through S9), as necessary, as follows:
2 Pull the outer borescope plug straight out as far as possible to engage the internal shaft spline.
3 Remove the borescope plug.
4 Tag each plug to ensure it will be reinstalled in the correct port.
5 If the borescope plug is broken or if the inner plug does not come out with the outer plug, remove the broken inner plug with a deep socket wrench (Ref. AMM TASK 72-31-00-300-002).
(5) Connect the fiber light cable to the fiberscope (green or blue band) from the 856A1320 BORESCOPE-KIT (856A1320P04 or P05) and to the port on the 856A1322 BORESCOPE-LIGHT SOURCE SET (856A1322P01 through P07). Turn the light source on.
(6) If you use the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) to turn the core engine, do an inspection of the compressor blades as follows. If you use the breaker bar to turn the core, go to step (7).
(a) Index the core engine to zero as follows:
1 Put the fiberscope into the stage 3 borescope port (S4) and look aft to the stage 4 compressor blade platform.
2 While you look in the fiberscope turn the core clockwise (CW), as seen from the front of the engine, using the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02).
3 Turn the core until you see the first blade slot locking lug.
4 Continue to turn the core until you see the second locking lug. The second locking lug is 2 blades past the first locking lug.
5 Align the leading edge of the first blade past the second locking lug with the leading edge of the nearest stage 4 vane. This is the zero index point and blade number 1.
6 Set the pointer on the protractor to the zero degree mark. The core engine is now set to the zero index point for inspection of all stages of the compressor rotor.
(b) Do an inspection of stage 4 compressor blades while you turn the core engine using the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02).
(c) Use the limits found in step 4.B.
(d) Remove the fiberscope.
(e) Insert the fiberscope in the borescope plug of the next stage to be inspected and repeat step (b) thru (d) for the other stages to be inspected.
(f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope port, do step (8).
(7) If you use the breaker bar to turn the core engine, do an inspection of the compressor blades as follows:
(a) Insert the fiberscope in the borescope port of the stage you want to inspect.
(b) Do an inspection of the compressor blade you see. Use the limits found in the inspection table.
(c) Rotate the core engine so that you can see the next blade. Use the breaker bar to turn the core engine clockwise (CW).
1 Stage 1 : 38 blades
2 Stage 2 : 53 blades
3 Stage 3 : 60 blades
4 Stage 4 : 68 blades
5 Stage 5 : 75 blades
6 Stage 6 : 82 blades
7 Stage 7 : 82 blades
8 Stage 8 : 80 blades
9 Stage 9 : 76 blades
(e) Repeat steps (a) thru (d) for the other stages to be inspected.
(f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope holes (S7 through S9), do step (8).
(8) To inspect the stages 6, 7, 8 and 9 blades when the vane segments have moved to partially cover the borescope holes, use the alternatives that follow:
(b) If the diameter of the borescope holes are less than 0.24 in. (6.01 mm) , do the following steps:
1 Put a tapered rod in the borescope hole. The rod must be made from 0.37 in. (9.40 mm) diameter aluminum, 18 in. (0.46 m) long, with a 4 in. (101.60 mm) taper at one end. The tapered end must be rounded to 0.062 in. (1.57 mm) radius, accurate radius not necessary.
2 Apply a light downward force on the end of the tapered rod to move the vane segments.
(c) If the stage 7 borescope hole (S8) is not fully open, inspect the aft part of the compressor through the stage 8 borescope hole (S9). If the stage 8 borescope hole (S9) is not fully open, try to do the inspection through the stage 6 borescope port (S7).
Subtask 72-31-00-290-051-A ** ON A/C NOT FOR ALL (1) Use the 856A1323 MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure NTM 720000.
(2) Install the tools to turn the core engine.
NOTE: The core engine may be turned using a breaker bar (see step (a)) or with a drive motor (see step (b)).
(a) To turn the core manually with a breaker bar, do the steps that follow: 1 Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter. (Ref. AMM TASK 72-63-00-000-002)
2 Install a SPEED BRACE 3/4 IN - SQUARE DRIVE with a BAR LENGTH 60 CM (2 FT) BREAKER into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward).
NOTE: To turn the core engine CW, the handcranking drive must be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 Remove the starter (Ref. AMM TASK 80-11-10-000-002).
2 Install the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P0/P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines.
NOTE: The tool must be installed in the horizontal position with the air hoses to the rear.
3 Turn the tool until the captive bolts align with the gearbox bolt holes. 4 Tighten the two captive bolts by hand.
5 Install the clamp to secure the drive motor.
6 Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
WARNING:
BE CAREFUL NOT TO GET AIRCRAFT FUEL IN YOUR MOUTH OR IN YOUR EYES.
IF YOU GET FUEL ON YOUR SKIN OR ON YOUR CLOTHES, FLUSH IT IMMEDIATELY WITH WATER.
IF NECESSARY, GET MEDICAL HELP.
AIRCRAFT FUEL IS POISONOUS.
CAUTION:
USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE NIPPLE WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES.
(3) Actuate the VSV system to the full open position as follows: NOTE: Put a CONTAINER 20 L - SHALLOW under the HMU to catch fuel released when fuel lines are disconnected.
NOTE: If the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) is not available, the VSV system may be actuated to the full open position by dry motoring the engine (Ref. AMM TASK 71-00-00-710-001).
(a) Disconnect the VSV rod-end and head-end flex-hoses from the hydromechanical unit (HMU). (b) Remove the caps from the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04).
(c) Attach the rod-end and head-end hoses from the cart to rod-end and head-end connectors of the rod-end and head-end hoses you disconnected from the HMU.
(d) Actuate the variable stator system
CAUTION:
DO NOT LET THE PRESSURE BE MORE THAN 300PSI (20.68BAR) OR YOU WILL CAUSE DAMAGE TO ENGINE PARTS.
1 Pump the actuator until the VSV system is at the open position (actuator rod retracted). (e) Disconnect the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04).
WARNING:
PRESSURE OF UP TO 300 PSI. (20.68 BAR) EXISTS IN THE SUPPLY LINES. RELIEVE PRESSURE TO PREVENT INJURY WHEN DISCONNECTING FITTINGS.
1 Follow the instructions for use of the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) to relieve any static pressure existing in the supply hoses. Gages on the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) should read zero and the selector valve should be in the OFF position. 2 Disconnect the hoses of the cart from the rod-end and head-end hoses.
3 Install the caps on the cart hoses.
(f) Connect the rod-end and head-end hoses to the HMU.
CAUTION:
USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE NIPPLE WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES.
1 TORQUE the head-end hose to between 550 and 450 lbf.in (6.22 and 5.09 m.daN )
. 2 TORQUE the rod-end hose to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )
. (4) Remove the borescope plugs from the stages to be inspected as follows. Tag each borescope plug to identify the stage from which it was removed:
NOTE: The borescope plugs are located along the compressor case between the 4 and 5 o'clock positions, aft looking forward.
(a) Remove the lockwire: WARNING:
USE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
1 Cut and remove the lockwire from the borescope plugs to be removed. (b) Remove the IGV borescope plug (S1), if necessary, as follows:
1 Remove the two screws (20) that attach the borescope access blanking plate (10) at 5 o'clock, aft looking forward, on the fan frame inner flange.
2 Remove the borescope access blanking plate (10).
3 Remove the IGV borescope plug (S1).
4 Tag the plug to ensure it will be reinstalled in the correct port.
(c) Remove the stage 1 through stage 5 borescope plugs (S2 through S6), as necessary. Tag each plug to ensure it will be reinstalled in the correct port.
(d) Remove the stage 6, 7 and 8 borescope plugs (S7 through S9), as necessary, as follows:
CAUTION:
DO NOT APPLY A TORQUE OF MORE THAN 280 lbf.in. (3.164 m.daN) TO THE 6TH, 7TH AND 8TH STAGE BOROSCOPE PLUGS WHEN YOU REMOVE THEM. IF YOU DO NOT OBEY THIS INSTRUCTION, THE INNER PLUG SHAFT CAN BREAK.
1 Loosen the outer borescope plug. 2 Pull the outer borescope plug straight out as far as possible to engage the internal shaft spline.
3 Remove the borescope plug.
4 Tag each plug to ensure it will be reinstalled in the correct port.
5 If the borescope plug is broken or if the inner plug does not come out with the outer plug, remove the broken inner plug with a deep socket wrench (Ref. AMM TASK 72-31-00-300-002).
(5) Connect the fiber light cable to the fiberscope (green or blue band) from the 856A1320 BORESCOPE-KIT (856A1320P04 or P05) and to the port on the 856A1322 BORESCOPE-LIGHT SOURCE SET (856A1322P01 through P07). Turn the light source on.
(6) If you use the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) to turn the core engine, do an inspection of the compressor blades as follows. If you use the breaker bar to turn the core, go to step (7).
(a) Index the core engine to zero as follows:
1 Put the fiberscope into the stage 3 borescope port (S4) and look aft to the stage 4 compressor blade platform.
2 While you look in the fiberscope turn the core clockwise (CW), as seen from the front of the engine, using the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02).
3 Turn the core until you see the first blade slot locking lug.
4 Continue to turn the core until you see the second locking lug. The second locking lug is 2 blades past the first locking lug.
5 Align the leading edge of the first blade past the second locking lug with the leading edge of the nearest stage 4 vane. This is the zero index point and blade number 1.
6 Set the pointer on the protractor to the zero degree mark. The core engine is now set to the zero index point for inspection of all stages of the compressor rotor.
(b) Do an inspection of stage 4 compressor blades while you turn the core engine using the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02).
(c) Use the limits found in step 4.B.
(d) Remove the fiberscope.
(e) Insert the fiberscope in the borescope plug of the next stage to be inspected and repeat step (b) thru (d) for the other stages to be inspected.
(f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope port, do step (8).
(7) If you use the breaker bar to turn the core engine, do an inspection of the compressor blades as follows:
(a) Insert the fiberscope in the borescope port of the stage you want to inspect.
(b) Do an inspection of the compressor blade you see. Use the limits found in the inspection table.
(c) Rotate the core engine so that you can see the next blade. Use the breaker bar to turn the core engine clockwise (CW).
NOTE: To turn the core engine CW, the handcranking drive must be turned counterclockwise (CCW).
(d) Repeat steps (b) and (c) until you have inspected all of the blades in that stage. Count the blades as you inspect them to make sure all of the compressor blades are inspected. The number of blades in each stage is: 1 Stage 1 : 38 blades
2 Stage 2 : 53 blades
3 Stage 3 : 60 blades
4 Stage 4 : 68 blades
5 Stage 5 : 75 blades
6 Stage 6 : 82 blades
7 Stage 7 : 82 blades
8 Stage 8 : 80 blades
9 Stage 9 : 76 blades
(e) Repeat steps (a) thru (d) for the other stages to be inspected.
(f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope holes (S7 through S9), do step (8).
(8) To inspect the stages 6, 7, 8 and 9 blades when the vane segments have moved to partially cover the borescope holes, use the alternatives that follow:
CAUTION:
MAKE SURE THE FLEXIBLE BORESCOPE DOES NOT GET CAUGHT IN THE BLADES WHILE YOU TURN THE CORE.
(a) If the diameter of the borescope holes are larger than 0.24 in. (6.01 mm) , do the borescope inspection using the 856A1321 FIBERSCOPE SET (856A1321P01 through P03). (b) If the diameter of the borescope holes are less than 0.24 in. (6.01 mm) , do the following steps:
1 Put a tapered rod in the borescope hole. The rod must be made from 0.37 in. (9.40 mm) diameter aluminum, 18 in. (0.46 m) long, with a 4 in. (101.60 mm) taper at one end. The tapered end must be rounded to 0.062 in. (1.57 mm) radius, accurate radius not necessary.
2 Apply a light downward force on the end of the tapered rod to move the vane segments.
(c) If the stage 7 borescope hole (S8) is not fully open, inspect the aft part of the compressor through the stage 8 borescope hole (S9). If the stage 8 borescope hole (S9) is not fully open, try to do the inspection through the stage 6 borescope port (S7).
B. Inspect the blades to the limits that follow:
Subtask 72-31-00-010-057-A ** ON A/C NOT FOR ALL NOTE: If you find airfoil damage, we recommend that you do a borescope inspection of the stage 5 booster blades and the abradable (refer to CFM SB 72-0391) (Ref. AMM TASK 72-21-00-290-003).
NOTE: The depth of a defect such as a nick is measured along the axis of the damage unless otherwise noted.
NOTE: Unless otherwise identified, all damage limits for high pressure compressor blades are the same for the different blade configurations.
NOTE: HPC blades with PN P33xPxx (3D Aero) have a 'C' marked on the aft platform. HPC blades with PN P39xPxx (TI) have a 'H' marked on the platform.
| INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Stages 1-4 compressor blades: | | |
| A.Cracks in Dim. A and tip | Any number of radial cracks within 0.30 in. (7.6 mm) of the leading or trailing edge, up to 0.25 in. (6.3 mm) in length are serviceable | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| | Any number of radial cracks more than 0.30 in. (7.6 mm) from the leading or trailing edge, up to 0.10 in. (2.5 mm) in length are serviceable | |
| | Any number of chord-wise cracks, up to 0.30 in. (7.6 mm) from the tip, up to 0.2 in. (5.1 mm) in length are serviceable | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| B.Missing or chipped erosion coating | Any amount | |
| C.Tears on the leading and trailing edge found in Dim. B | Not serviceable | See repair (Ref. AMM TASK 72-31-00-300-004). |
| D.Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, if the HPC blade is not a Tech Insertion Stage 4 blade (PN P394PXX) | Any number if the damage is less than 0.04 in. (1.0 mm) in depth | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| E.Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, if the HPC blade is a Tech Insertion Stage 4 blade (PN P394PXX) | Any number, if the damage is less than 0.030 in. (0.8 mm) in depth | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004) |
| F.Dents on the leading or trailing edge found in Dim. B | Any amount if the damage is less than 0.04 in. (1.0 mm) in depth and up to 0.06 in. (1.5 mm) deflection from the original contour | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| G.Nicks, dents and tears on the leading and trailing edge tip corners in Dim. A | Any number if less than 0.25 in. (6.3 mm) in depth | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| H.Missing material and erosion at the leading and trailing edge tip corners in Dim. A and tip | a) Individual blades with missing material more than 0.30 in. (7.6 mm) x 0.30 in. (7.6 mm) on both leading and trailing edges are not permitted. b) Any number of blades for each stage 1 thru 4, up to 0.30 in. (7.6 mm) x 0.30 in. (7.6 mm) if the downstream damage is serviceable. c) For stage 2, a maximum of 4 blades up to 0.40 in. (10.2 mm) x 0.40 in. (10.2 mm), and 46 blades up to 0.30 in. (7.6 mm) x 0.30 in. (7.6 mm) for total of 50 blades with missing tip corners. d) For stage 3, a maximum of 5 blades up to 0.40 in. (10.2 mm) x 0.40 in. (10.2 mm) and 51 blades up to 0.30 in. (7.6 mm) x 0.30 in. (7.6 mm) for a total of total of 56 blades with missing tip corners. e) For stage 4, maximum of 6 blades up to 0.40 in. (10.2 mm) x 0.40 in. (10.2 mm) and 57 blades up to 0.30 in. (7.6 mm) x 0.30 in. (7.6 mm) for a total of total of 63 blades with missing tip corners | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| J.Curl on the end of the airfoil | Up to 25% of chord, maximum radial length of 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation | |
| K.Nicks, dents and scratches of the airfoil root radius (does not include the trailing edge root radius of stage 2 and stage 3). | Any number if the damage is 0.005 in. (0.13 mm) maximum in depth. Alternatively, any number of elliptical, smooth, and round bottom dents having no sharp edges with a maximum diameter of 0.030 in. (0.76 mm). Dents must not connect or overlap. Scratches parallel to the platform are not serviceable. | |
| L.Nicks, dents and scratches of the trailing edge root radius of stage 2 and stage 3. | Any amount, if less than 0.03 in. (0.8 mm) in depth. | See limit extensions (Ref. AMM TASK 72-00-00-200-025). |
| M.Tears on the leading and trailing edge found in the lower 25% of the airfoil (but not the root radius) | Not serviceable | See repair (Ref. AMM TASK 72-31-00-300-004). |
| N.Nicks, dents and missing material on the leading and trailing edge of the lower 25% of the airfoil (but not the root radius) | Any amount if the damage is less than 0.03 in. (0.8 mm) in depth. | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| Wear or scratches on trailing edge platform of stages 2 and 3 | Any amount, if less than 0.03 in. (0.8 mm) in depth. | See limit extensions (Ref. AMM TASK 72-00-00-200-025). |
| 2.Stages 5-9 compressor blades: | | |
| A.Cracks in Dim. A and tip | Up to 25% of the blades across stages 5 through 9 can have radial cracks that are within 0.20 in. (5.1 mm) from the leading or trailing edge. These cracks can be up to 0.15 in. (3.8 mm) in length. | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| | Radial cracks more than 0.20 in. (5.1 mm) from the leading or trailing edge are not serviceable | |
| | Up to 25% of the blades across stages 5 through 9 can have chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip. These cracks can be up to 0.15 in. (3.8 mm) in length | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| B.Missing or chipped erosion coating | Any amount | |
| C.Nicks, tears, missing material and erosion on the leading and trailing edge found in Dim. B | Any number if the damage is less than 0.04 in. (1.0 mm) in depth | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| D.Dents on the leading and trailing edge found in Dim. B | Any number if the damage is less than 0.04 in. (1.0 mm) in depth and 0.06 in. (1.5 mm) deflection from the original contour | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| E.Nicks, dents and tears on the leading and trailing edge found in Dim. A | Any number is serviceable if the damage is less than 0.15 in. (3.8 mm) in depth | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| F.Missing material and erosion at the leading and trailing edge tip corners | All blades, up to 0.15 in. (3.8 mm) x 0.15 in. (3.8 mm), if downstream damage is serviceable. A maximum of 25 blades across stages 5 through 9 up to 0.2 in. (5.1 mm) x 0.2 in. (5.1 mm). | See limit extensions (Ref. AMM TASK 72-00-00-200-025). |
| G.Curl on the end of the airfoil | Up to 50% of chord maximum radial length 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation | See limit extensions (Ref. AMM TASK 72-00-00-200-025). |
| H.Dents, nicks and scratches on the airfoil root radius | Any number if the damage is 0.005 in. (0.13 mm) maximum in depth. Alternatively, any number of elliptical, smooth, and round bottom dents having no sharp edges with a maximum diameter of 0.030 in. (0.76 mm). Dents must not connect or overlap. Scratches parallel to the platform are not serviceable. | |
| J.Tears on the leading and trailing edge found in the lower 25% of the airfoil (but not the root radius) | Not serviceable | See repair (Ref. AMM TASK 72-31-00-300-004). |
| K.Nicks, dents and missing material on the leading and trailing edge of the lower 25% of the airfoil (but not the root radius) | Any amount if the damage is less than 0.03 in. (0.76 mm) in depth. | See limit extensions (Ref. AMM TASK 72-00-00-200-025) or repair (Ref. AMM TASK 72-31-00-300-004). |
| 3.Stages 1-9 compressor blade: | | |
| A.Tears, nicks, dents, missing material, erosion, bending and burrs in the tip | Any number or amount is serviceable | |
NOTE: The blade tip is the top 0.10 in. (2.5 mm) of the blade. | | |
| B.Nick and dents on the airfoil center panel | Any number if the damage is not cracked on the opposite side of the airfoil | |
| C.Erosion and scratches on the airfoil center panel | Any amount | |
| D.Material on the blade | Any amount | |
| E.Through holes | Not serviceable | |
| 4.Platform of stages 4-9 locking blades. | | |
| A.Clearance between the blade platforms | Serviceable | |
| B.Distortion on the blades | Any amount | |
| C.Cracks | Not serviceable | |
| D.Shingling | Not serviceable | |
| 5.Blade locks for stages 4-9 blades: | | |
| A.Cracks | Any number of cracks on one lock is permitted per stage. | See limit extensions (Ref. AMM TASK 72-00-00-200-025) |
| B.Looseness NOTE: To check for looseness, use a bent length of heavy gage wire to move the blade lock. Monitor the movement through the borescope. | Not serviceable | See limit extensions (Ref. AMM TASK 72-00-00-200-025) lock. |
| 6.Stator flow path: | | |
| A.Missing rub coating | Any amount | |
| B.Cracks which are crazed | Any amount NOTE: The area adjacent to the borescope ports is the only rub coat you can examine. | |
| 7.Stages 1 through 3 compressor stator variable vane shrouds | | |
| A.Wear caused by rubbing on vanes | Any amount | |
| 8.HPC Inner Shroud Lip for: | | |
| A.Wear from rotor-stator contact | Any amount | |
C. Remove the borescope equipment
(1) When inspection is complete, turn the lamp switch off. Keep the main light source blower on until the lamp and housing cools down.
(2) Before you install the borescope plugs, put the 0.37 in. (9.40 mm) diameter tapered rod into the borescope hole. This will make sure the hole is open.
(3) Install the IGV borescope plug (S1) as follows:
(a) Apply graphite grease (Material No.CP2101) orCP2619 Never Seez-Pure Nickel, Special or milk of magnesia (Material No.CP1064) to the threads and pressure face of the borescope plug.
(b) Put the borescope plug in the correct borescope port. Tighten the plug by hand.
(c) TORQUE the plug to between 63 and 57 lbf.in (0.71 and 0.64 m.daN )
.
CP8001 lockwire 0.032 in. (0.8 mm) dia. or CP8002 lockwire 0.032 in. (0.8 mm) dia or CP8006 safety cable 0.032 in. (0.8 mm) dia. .
(e) Install the borescope access blanking plate (10) using the two screws (20).
(4) Install the stage 1 through 5 borescope plugs (S2 through S6) as follows:
(a) Apply graphite grease (Material No.CP2101) orCP2619 Never Seez-Pure Nickel, Special or milk of magnesia (Material No.CP1064) to the threads and pressure face of the borescope plugs.
(b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
(c) TORQUE the borescope plugs to between 63 and 57 lbf.in (0.71 and 0.64 m.daN )
.
CP8001 lockwire 0.032 in. (0.8 mm) dia. or CP8002 lockwire 0.032 in. (0.8 mm) dia or CP8006 safety cable 0.032 in. (0.8 mm) dia. .
(5) Install the stage 6, 7 and 8 borescope plugs (S7, S8 and S9) as follows:
(b) Apply graphite grease (Material No.CP2101) orCP2619 Never Seez-Pure Nickel, Special or milk of magnesia (Material No.CP1064) to the threads and pressure face of the borescope plugs.
(c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug.
(d) TORQUE the inner plug to between 85 and 75 lbf.in (0.96 and 0.85 m.daN )
. Loosen half a turn and RETORQUE to between 20 and 15 lbf.in (0.23 and 0.17 m.daN )
more than the running torque.
(e) Compress the plug spring and tighten the outer plug by hand.
.
CP8001 lockwire 0.032 in. (0.8 mm) dia. or CP8002 lockwire 0.032 in. (0.8 mm) dia or CP8006 safety cable 0.032 in. (0.8 mm) dia. .
(6) Remove the tools used to rotate the core as follows:
(b) Install the handcranking drive pad cover (Ref. AMM TASK 72-63-00-400-002).
(c) Remove the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB.
(d) Install the starter (Ref. AMM TASK 80-11-10-400-002).
5. Close-up(1) When inspection is complete, turn the lamp switch off. Keep the main light source blower on until the lamp and housing cools down.
(2) Before you install the borescope plugs, put the 0.37 in. (9.40 mm) diameter tapered rod into the borescope hole. This will make sure the hole is open.
(3) Install the IGV borescope plug (S1) as follows:
(a) Apply graphite grease (Material No.CP2101) or
(b) Put the borescope plug in the correct borescope port. Tighten the plug by hand.
(c) TORQUE the plug to between 63 and 57 lbf.in (0.71 and 0.64 m.daN )
. WARNING:
USE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(d) Wirelock the plugs with (e) Install the borescope access blanking plate (10) using the two screws (20).
(4) Install the stage 1 through 5 borescope plugs (S2 through S6) as follows:
(a) Apply graphite grease (Material No.CP2101) or
(b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
(c) TORQUE the borescope plugs to between 63 and 57 lbf.in (0.71 and 0.64 m.daN )
. WARNING:
USE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(d) Wirelock the borescope plugs. Use (5) Install the stage 6, 7 and 8 borescope plugs (S7, S8 and S9) as follows:
CAUTION:
MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR.
(a) Make sure the borescope port is open. Insert the 0.37 in. (9.40 mm) diameter tapered rod in the borescope port. (b) Apply graphite grease (Material No.CP2101) or
(c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug.
(d) TORQUE the inner plug to between 85 and 75 lbf.in (0.96 and 0.85 m.daN )
. Loosen half a turn and RETORQUE to between 20 and 15 lbf.in (0.23 and 0.17 m.daN )
more than the running torque. (e) Compress the plug spring and tighten the outer plug by hand.
NOTE: If the inner plug is correctly installed and the threads are not damaged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand, the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e).
(f) TORQUE the outer plug to between 63 and 57 lbf.in (0.71 and 0.64 m.daN )
. WARNING:
USE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(g) Wirelock all 3 outer plugs together with (6) Remove the tools used to rotate the core as follows:
NOTE: If the breaker bar is installed, see steps (a) and (b). If the drive motor is installed, see steps (c) and (d).
(a) Remove the SPEED BRACE 3/4 IN - SQUARE DRIVE and BAR LENGTH 60 CM (2 FT) BREAKER from the handcranking drive pad. (b) Install the handcranking drive pad cover (Ref. AMM TASK 72-63-00-400-002).
(c) Remove the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB.
(d) Install the starter (Ref. AMM TASK 80-11-10-400-002).
Subtask 72-31-00-410-057-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 72-31-00-710-054-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
B. If fuel or oil lines were disconnected, do a minimum idle leak check (Ref. AMM TASK 71-00-00-710-006) and check for leaks.
Subtask 72-31-00-440-052-A ** ON A/C NOT FOR ALL Subtask 72-31-00-410-058-A ** ON A/C NOT FOR ALL
Core Rotation Drive Motor Installation