Inspection of the High Pressure Compressor Rotor Assembly [CFMI]

TASK 72-31-00-290-001-A
Inspection of the High Pressure Compressor Rotor Assembly

FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL

1. Reason for the Job
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 in the compressor stator case, between the 4 and 5 o'clock positions, 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	SOCKET DIA 0,75 IN (19,05 MM) - 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

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2101)	graphite grease
(Material No.CP2619)	Never Seez-Pure Nickel, Special
(Material No.CP8001)	lockwire 0.032 in. (0.8 mm) dia.

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 71-00-00-710-001-A	Dry Motoring Check
TASK 71-00-00-710-006-A	Minimum Idle Check
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 72-00-00-200-005-A	Over-Serviceable-Limit Extensions
TASK 72-31-00-300-001-A	Repair of Broken Borescope Plug
TASK 72-31-00-300-003-A	Blend Repair of High Pressure Compressor (HPC) Rotor Blades, Stages 1-9
TASK 72-63-00-000-004-A	Removal of the Handcranking Drive Cover
TASK 72-63-00-400-004-A	Installation of the Handcranking Drive Cover
TASK 78-30-00-081-041-A	Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-481-041-A	Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-36-00-010-040-A	Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-A	Closing of the Thrust Reverser Doors
TASK 80-11-10-000-001-A	Removal of the Pneumatic Starter
TASK 80-11-10-400-001-A	Installation of the Pneumatic Starter
NTM 720000
Core Rotation Drive Motor Installation
VSV System Connections at the HMU
Borescope Ports of the High-Pressure Compressor
Removal of IGV Borescope Plug (S1)
Compressor Blades Inspection Areas
HPC Rotor Indexing to Zero
Locally Manufactured Alignment Rod
Locally Manufactured Deep Socket Wrench
Stage 1-3 VSV Shroud Rubbing

3. Job Set-up
Subtask 72-31-00-941-051-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 72-31-00-010-051-A ** ON A/C NOT FOR ALL

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 72-31-00-040-050-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041).

Subtask 72-31-00-010-052-A ** ON A/C NOT FOR ALL

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
Subtask 72-31-00-410-051-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.

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 72-63-00-000-004).
2 Install a SOCKET DIA 0,75 IN (19,05 MM) - 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 80-11-10-000-001).
2 Install the 856A1488 MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or 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 the 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 to use 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) Cut and remove the lock wire 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 72-31-00-300-001).
(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 zero degrees. 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 (9).
(d) Remove the fiberscope.
(e) Insert the fiberscope in the borescope plug of the next stage to be inspected and repeat steps (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) and (b) thru 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 stage 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 diameters of the borescope holes are larger than 0.24 in. (6 mm), do the borescope inspection using the 856A1321 FIBERSCOPE SET (856A1321P01 through P03).
(b) If the diameters of the borescope holes are less than 0.24 in. (6 mm), do the following steps:
1 Put a tapered rod in the borescope hole. The rod must be made from 0.37 in. (9.4 mm) diameter aluminum, 18 in. (0.46 m) long, with a 4 in. (101.6 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 72-31-00-290-050-A ** ON A/C NOT FOR ALL

B. Inspect the blades to the limits that follow:

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 the damage limits for HPC blades are the same for different configurations.

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Stage 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. (6.4 mm) in length are serviceable	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
	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 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
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 72-31-00-300-003).
D.Nicks, 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)	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
E.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 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
F.Nicks, dents and tears on the leading and trailing edge in Dim. A	Any number if less than 0.25 in. (6.4 mm) in depth	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
G.Missing material and erosion at the leading and trailing edge tip corners in Dim. A and tip	(1) Individual blades with missing material greater than 0.30 x 0.30 inch (7.6 x 7.6 mm) on both leading and trailing edges are not permitted. (2) Any number of blades for each stage 1 thru 4, up to 0.30 x 0.30 inch (7.6 x 7.6 mm) if the downstream damage is serviceable. (3) For stage 2, a maximum of 4 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm), and 46 blades up to 0.30 x 0.30 inch (7.6 x 7.6mm) for total of 50 blades with missing tip corners. (4) For stage 3, a maximum of 5 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 51 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 56 blades with missing tip corners. (5) For stage 4, maximum of 6 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 57 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 63 blades with missing tip corners.	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003)
H.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
J.Nicks, dents and scratches on the airfoil root radius (does not include the trailing edge root radius of stage 2 and stage 3)	Any number that are 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. Any number of damage is allowed if damage is 0.005 in. (0.13 mm) maximum in depth. Scratches parallel with the platform are not serviceable.
K.Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3	Any amount, if the damage is less than 0.03 in. (0.8 mm) in depth	See limit extensions (Ref. AMM TASK 72-00-00-200-005).
L.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 72-31-00-300-003).
M.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)	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
2.Stage 5-9 compressor blades:
A.Cracks in Dim. A and tip	Up to 20% of the blades of each stage can have radial cracks that are within 0.20 in. (5.1 mm) of 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 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
	Radial cracks more than 0.20 in. (5.1 mm) from the leading or trailing edge are not serviceable
	Up to 20% of the blades of each stage 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 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
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)	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
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 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
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)	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
F.Missing material and erosion at the leading and trailing edge tip corners	Up to 20% of the blades of each stage, up to 0.20 x 0.20 in. (5.1 x 5.1 mm) if downstream damage is serviceable	See limit extensions (Ref. AMM TASK 72-00-00-200-005).
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 72-00-00-200-005).
H.Nicks, dents and scratches on the airfoil root radius	Any number that are 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. Any number of damaged areas are permitted if the damage is 0.005 in. (0.13 mm) maximum in depth. Scratches parallel with the platform are not serviceable.
J.Tears on the leading and trailing edge found in the lower 25% of the airfoil	Not serviceable	See repair (Ref. AMM TASK 72-31-00-300-003).
K.Nicks, dents and missing material on the leading and trailing edge of the lower 25% of the airfoil (but not the root radius)	(1) For stage 6-9 HPC blades: Any amount, if the damage is less than 0.03 in. (0.76 mm) in depth (2) For stage 5 HPC blades: Any amount, if the damage is less than 0.02 in. (0.51 mm) in depth	See limit extensions (Ref. AMM TASK 72-00-00-200-005) or repair (Ref. AMM TASK 72-31-00-300-003).
3.Stage 1-9 compressor blades:
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 airfoil.
B.Nicks and dents on the airfoil center panel	Any number if the damage is not cracked on either 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 stage 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 stage 4-9 blades:
A.Cracks	Any number of cracks on one lock is permitted for each stage	See limit extensions (Ref. AMM TASK 72-00-00-200-005).
B.Looseness	Not serviceable	See limit extensions (Ref. AMM TASK 72-00-00-200-005). NOTE: To examine looseness, use a bent length of heavy gage wire to move the blade lock. Monitor the movement through the borescope.
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.Stage 1 through 3 compressor stator variable vane shrouds
A.Wear caused by rubbing on vanes	Any amount	Stage 1-3 VSV Shroud Rubbing ** ON A/C NOT FOR ALL
8.HPC Inner Shroud Lip for:
A.Wear from rotor-stator contact	Any amount

Subtask 72-31-00-010-053-A ** ON A/C NOT FOR ALL

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. (9.4 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 CP2619Never Seez-Pure Nickel, Special 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 )

.
(d) Wirelock the plugs with CP8001lockwire 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) or CP2619Never Seez-Pure Nickel, Special 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 )

.
(d) Wirelock the borescope plugs. Use CP8001lockwire 0.032 in. (0.8 mm) dia..
(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. (9.4 mm) diameter tapered rod in the borescope port.
(b) Apply graphite grease (Material No.CP2101) or CP2619Never Seez-Pure Nickel, Special to the threads and pressure face of the borescope plugs.
(c) Put the borescope 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 )

.
(g) Wirelock the stage 6, 7 and 8 borescope plugs (S7, S8 and S9) together. Use CP8001lockwire 0.032 in. (0.8 mm) dia..
(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 SOCKET DIA 0,75 IN (19,05 MM) - 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 72-63-00-400-004).
(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 80-11-10-400-001).

5. Close-up
Subtask 72-31-00-410-053-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)
(3) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(4) FOR [1000EM2] (ENGINE-2)
461AL 462AR

Subtask 72-31-00-710-053-A ** ON A/C NOT FOR ALL

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 72-31-00-440-050-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).

Subtask 72-31-00-410-052-A ** ON A/C NOT FOR ALL

D. Close Access
(1) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040)
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 04:03:16 UTC