Removal of the Variable Stator Vane (VSV) Actuators [CFMI]

TASK 75-32-10-000-001-A
Removal of the Variable Stator Vane (VSV) Actuators

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

1. Reason for the Job
Self explanatory
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	CAP - BLANKING
No specific	1	CONTAINER 20 L - SHALLOW
No specific	AR	PLIERS - JAWED, SOFT
No specific	AR	PLUG - BLANKING
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
856A1084	1	CART-STATOR ACTUATOR

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2691)	penetrant
(Material No.CP5066)	fuel system preventative

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 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
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
VSV Actuator (Right Side Shown)
VSV Actuator (Left Side Shown)
Cart-stator Actuator Connections

3. Job Set-up
Subtask 75-32-10-941-051-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 75-32-10-861-050-A ** ON A/C NOT FOR ALL

B. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).

Subtask 75-32-10-865-053-A ** ON A/C NOT FOR ALL

C. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1000EM1 (ENGINE1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
FOR FIN: 1000EM2 (ENGINE2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26

Subtask 75-32-10-010-050-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open 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 the ACCESS PLATFORM 1M(3 FT) in position.

Subtask 75-32-10-040-051-A ** ON A/C NOT FOR ALL

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

Subtask 75-32-10-010-053-A ** ON A/C NOT FOR ALL

F. Open Thrust Reverser Cowl Doors: (Ref. AMM TASK 78-36-00-010-040)
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(a) FOR [1000EM2] (ENGINE-2)
461AL 462AR

4. Procedure
Subtask 75-32-10-820-050-A ** ON A/C NOT FOR ALL

A. Move the piston rod of the VSV actuator to the position that allows for easy removal.
(1) Remove the head-end and rod-end flex-hoses from the hydromechanical unit (HMU).
(2) Install the head-end hose of the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) to the head-end flex-hose that you disconnected from the HMU.

NOTE: If the Stator Actuator Cart is not available, a pressure source of dry, regulated air, nitrogen or argon may be used as an alternative.

(3) Install the rod-end hose of the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) to the rod-end flex-hose that you disconnected from the HMU.
(4) Apply pressure

CAUTION: DO NOT LET THE PRESSURE BE MORE THAN 300PSI (20.68BAR) OR YOU WILL CAUSE DAMAGE TO ENGINE PARTS.

(a) Apply pressure, as necessary (approximately 100 psi (6.9 bar)), to set the piston rod of the VSV actuator to the removal position.
(5) Release the pressure on the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04).

NOTE: The actuator stator cart can stay installed if a replacement actuator is to be installed at the completion of this subtask.

(6) Disconnect the head-end hose of the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) from the head-end flex-hose at the HMU.
(7) Disconnect the rod-end hose of the 856A1084 CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) from the rod-end flex-hose at the HMU.
(8) Install CAP - BLANKING and PLUG - BLANKING on the open ports of the HMU and the open ends of the flex-hoses.

NOTE: Do not connect the flex-hoses to the HMU at this time. You will use them later in the procedure.

Subtask 75-32-10-020-050-A ** ON A/C NOT FOR ALL

B. Remove the VSV actuator as follows:
(1) Disconnect the electrical connector from the actuator. Use PLIERS - JAWED, SOFT if necessary.
(2) Put a CAP - BLANKING on the actuator and a PLUG - BLANKING on the electrical connector.
(3) Put a CONTAINER 20 L - SHALLOW below the shroud drain tubes.
(4) Disconnect

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.

(a) Disconnect the shroud drain tubes and let them drain.
(5) Cut and remove the lockwire from the shroud connectors and move the connectors until you can get to the B-nuts on the nipples (130).
(6) Disconnect the fuel tube coupling nuts at the nipples (130).
(7) Remove and discard the O-rings (150) from the drain shrouds.
(8) Remove and discard the O-rings (140) from the fuel tubes.
(9) Locate the actuator at the 2:00 o'clock position when you stand at the aft and look forward (ALF). Then, remove the lockwire from the actuator drain tube.
(10) Disconnect the actuator drain tube.

NOTE: The actuator at the 8:00 o'clock position has a permanently installed blanking plug. Do not remove the blanking plug at this time.

(11) Remove the bolt (80), bushing (70), washer (60) and nut (50) from the actuator clevis.
(12) Remove the bolt (40), bushing (30), washer (20) and nut (10) from the actuator clevis and bellcrank.
(13) Remove the clevis link (90).

CAUTION: DO NOT TURN BOLT (110) UNTIL THE PENETRANT HAS SOAKED FOR AT LEAST FIVE MINUTES. IF YOU TURN THE BOLT BEFORE THE PENETRANT HAS HAD TIME TO SOAK, SEIZURE BETWEEN THE BOLT AND BELLCRANK ASSEMBLY WILL RESULT.

(14) Apply penetrant (Material No.CP2691) to the inboard and outboard side of bolt (110) at the bellcrank clevis location. Let the penetrant soak for a minimum of five minutes before you remove the bolt.
(15) Remove the bolt (110) and nut (100) that attaches the rod-end of the actuator to the bellcrank assembly.
(16) Remove the bolt (160) and nut (180) that attaches the head-end of the actuator to the bellcrank assembly.
(17) Remove the actuator.
(18) Remove the sleeve (170) from the actuator.
(19) Install PLUG - BLANKING on the open shroud drain tubes, fuel tubes, and actuator drain tube.
(20) Remove the nipples (130) from the actuator as follows:
(a) Remove the nipples (130) from the head-end, rod-end and right actuator drain ports.
(b) Remove and discard the O-rings (120) from the nipples (130).
(c) Remove the drain plug from the actuator drain port on the actuator located at the 8:00 o'clock position (ALF).

Subtask 75-32-10-680-050-A ** ON A/C NOT FOR ALL

C. Drain all of the remaining fuel from the actuator.

Subtask 75-32-10-170-050-A ** ON A/C NOT FOR ALL

D. Flush the actuator as follows:
(1) Flush the actuator with fuel system preventative (Material No.CP5066) .
(2) Install PLUG - BLANKING on the open ports of the actuator.

[Rev.10 from 2021] 2026.04.01 12:54:44 UTC