Installation of the Control Alternator [CFMI]

TASK 73-21-30-400-002-A
Installation of the Control Alternator

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	PLIERS - JAWED, SOFT
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 55 and 45 lbf.in (0.62 and 0.51 m.daN )
No specific	Torque wrench: range to between 70 and 55 lbf.in (0.79 and 0.62 m.daN )
No specific	Torque wrench: range to between 345 and 315 lbf.in (3.90 and 3.56 m.daN )
856A2717	1	ADAPTER-LOCK CORE ENGINE
856A2953	1	GUIDE PINS STATOR ALTERNATOR

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2101)	graphite grease
(Material No.CP2442)	engine oil

C. Work Zones and Access Panels

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

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
120	GASKET	AIPC 73-21-30-01-180
210	O-RING	AIPC 73-21-30-01-200
170	NUT	AIPC 73-21-30-01-210
300	GASKET	AIPC 79-21-10-01-020

E. 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 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
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 72-63-00-400-004-A	Installation of the Handcranking Drive Cover
Control Alternator

3. Job Set-up
Subtask 73-21-30-860-050-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.
(2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

Subtask 73-21-30-010-051-A ** ON A/C NOT FOR ALL

B. Make sure that the fan cowl doors are open: (Ref. AMM TASK 71-13-00-010-040)
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

4. Procedure
Subtask 73-21-30-420-050-A ** ON A/C NOT FOR ALL

A. Install the control alternator as follows:

Control Alternator ** ON A/C NOT FOR ALL

(1) Remove the protective covers from the alternator rotor (140), the handcranking drive pad and the end of the AGB drive shaft.
(2) If you see that the rotor removed, do the steps that follows:
(a) Install the 856A2717 ADAPTER-LOCK CORE ENGINE (856A2717G01) in the handcranking drive pad and safety with the two bolts provided. Tighten with your hand.
(b) Install the alternator rotor (140) on the AGB drive shaft.
(c) Apply engine oil (Material No.CP2442) to the threads of the AGB drive shaft.
(d) Install the new AIPC 73-21-30-01-210 NUT (170).

CAUTION: MAKE SURE YOU APPLY THE CORRECT TORQUE ON THE NUT. INCORRECT INSTALLATION CAN LEAD TO ALTERNATOR ROTOR DISENGAGEMENT.

1 Install and TORQUE the new nut (170) to between 345 and 315 lbf.in (3.90 and 3.56 m.daN )

.
(e) Remove the two bolts and the 856A2717 ADAPTER-LOCK CORE ENGINE (856A2717G01) from the handcranking drive pad.
(f) Install the handcranking drive cover (Ref. AMM TASK 72-63-00-400-004), but do the HJ9 and HJ10 harness connections at the end of this procedure and do not do the test.
(3) Install the control alternator (30) as follows:
(a) Install the 856A2953 GUIDE PINS STATOR ALTERNATOR (856A2953G01) in the three bolt holes in the attachment pad.
(b) Remove the protective covers and closures from the control alternator (30).
(c) Lightly lubricate the new AIPC 73-21-30-01-200 O-RING (210) with engine oil (Material No.CP2442) .
(d) Install the new O-ring (210) in the recess on the attachment pad.
(e) Install the control alternator (30) over the rotor (140) until the alternator seats on the attachment pad.
(f) Remove the guide pins from the attachment pad.
(g) Install the three bolts (180) and three washers (130) through the alternator into the attachment pad.
(h) TORQUE the bolts (180) to between 70 and 55 lbf.in (0.79 and 0.62 m.daN )

Subtask 73-21-30-420-051-A ** ON A/C NOT FOR ALL

B. Install the lube tube (40) and connect the electrical connector.
(1) If you see that the lube tube (40) removed, install the lube tube (40) as follows:
(a) Remove the protective covers and closures from the lube tube (40), AGB and lube module (110).
(b) Lubricate the bolts (70), (90) with graphite grease (Material No.CP2101) .
(c) Install the tube (40) between the fourth port of the lube pump and the FORWARD side of the AGB.
(d) Install two new AIPC 79-21-10-01-020 GASKET (300) and AIPC 73-21-30-01-180 GASKET (120) between the lube module (110) and the tube (40) and between the tube (40) and the AGB.
(e) Attach the tube (40) with the eight bolts (70), (90) and eight washers (80), (200).
(f) TORQUE the bolts (70), (90) to between 55 and 45 lbf.in (0.62 and 0.51 m.daN )

.
(g) Install two clamps (60) on the lube tube (40) and safety with two bolts (50) and two nuts (100).
(2) Remove protective caps from the electrical cables, channel A (10) and channel B (20), and from the control alternator electrical connectors.
(3) Connect the electrical cable connectors, channel A (10) and channel B (20). Tighten the connectors with your hand plus one-eighth of a turn. If necessary, use PLIERS - JAWED, SOFT.

Subtask 73-21-30-861-050-A ** ON A/C NOT FOR ALL

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

Subtask 73-21-30-869-050-A ** ON A/C NOT FOR ALL

D. Do the EIS start procedure (upper and lower ECAM DU's) (Ref. AMM TASK 31-60-00-860-001).

Subtask 73-21-30-710-050-A ** ON A/C NOT FOR ALL

E. Do this test:
(1) Do a minimum idle check (Ref. AMM TASK 71-00-00-710-006).
(2) Do the steps below:
(a) On the MCDU, select the CFDS MENU page.
(b) Push the line key adjacent to SYSTEM REPORT/TEST.
(c) Push the NEXT PAGE mode key: a new SYSTEM REPORT/TEST page comes into view.
(d) Push the line key adjacent to the ENG indication: the SYSTEM REPORT/TEST ENG page comes into view.
(e) Push the line key adjacent to the FADEC 1A(1B) for engine 1.
(f) Push the line key adjacent to the FADEC 2A(2B) for engine 2.
(g) Push the line key adjacent to the LAST LEG REPORT.
(h) Make sure that the message ALT, J9(J10), ECU is not in view.

5. Close-up
Subtask 73-21-30-869-051-A ** ON A/C NOT FOR ALL

A. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).

Subtask 73-21-30-862-050-A ** ON A/C NOT FOR ALL

B. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 73-21-30-410-050-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040)
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:56:05 UTC