Installation of the T5 Sensor [CFMB]

TASK 77-22-10-400-002-A
Installation of the T5 Sensor

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	WARNING NOTICE(S)
No specific	Torque wrench: range to between 10.5 and 9.5 lbf.in (0.12 and 0.11 m.daN )
No specific	Torque wrench: range to between 55 and 50 lbf.in (0.62 and 0.57 m.daN )
No specific	Torque wrench: range to between 110 and 95 lbf.in (1.24 and 1.07 m.daN )
No specific	Torque wrench: range to between 160 and 150 lbf.in (1.81 and 1.70 m.daN )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2101)	graphite grease
(Material No.CP8004)	lockwire 0.6 mm (0.0236 in.) dia
(Material No.CP8005)	lockwire 0.6 mm (0.0236 in.) 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 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 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
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 73-29-00-710-040-B-02	Operational Test of the FADEC on the Ground (with Engine Non motoring)
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
Removal/Installation of the T5 Sensor

3. Job Set-up
Subtask 77-22-10-860-052-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 77-22-10-010-057-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Make sure that the fan cowl doors are open: (Ref. AMM TASK 71-13-00-010-040)
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Make sure that the thrust reverser doors are open: (Ref. AMM TASK 78-36-00-010-040)
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR

Subtask 77-22-10-040-053-A ** ON A/C NOT FOR ALL

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

4. Procedure
Subtask 77-22-10-420-051-A ** ON A/C NOT FOR ALL

A. Installation of the T5 Sensor:

CAUTION: THE DESIGN OF T5 SENSOR ASSEMBLY IS SUCH THAT IT CAN BE EASILY DAMAGED IF YOU HANDLE IT WITHOUT PRECAUTION. DO NOT USE FORCE AND PREVENT CONDITIONS WHICH PUT IT UNDER STRAINS AND STRESSES.

(1) Assemble the bracket (170) to the T5 sensor (10) connector as follows:
(a) Clean the component interfaces and the adjacent area.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Remove the blanking cap from the T5 sensor (10) connector.
(d) Apply a thin layer of graphite grease (Material No.CP2101) to the threads of the 4 screws (120).
(e) Engage the T5 sensor connector through bracket (170). Attach the bracket to the connector with screws (120) and half-plates (160).
(f) TORQUE the screws (120) to between 10.5 and 9.5 lbf.in (0.12 and 0.11 m.daN )

. Safety the screws in pairs with a CP8004lockwire 0.6 mm (0.0236 in.) dia or CP8005lockwire 0.6 mm (0.0236 in.) dia.
(2) Installation of the T5 Sensor Assembly
(a) Lubricate the threads of bolts (110) with graphite grease (Material No.CP2101)
(b) Engage the T5 sensor probe (10) in the recess of turbine frame boss. Install the bolts (110) and nuts (100). Tighten the nuts by hand.
(c) Lubricate the threads of the bolts (20, 60) with graphite grease (Material No.CP2101) .
(d) Attach the T5 sensor (10) to the bracket (40) at flange T with the clamp (30), the bolt (20) and the nut (50). Tighten the nut by hand.
(e) Attach the T5 sensor (10) to the bracket (80) at flange S with the clamp (70), the bolt (60) and the nut (90). Tighten the nut by hand.
(f) Lubricate the threads of bolts (150) with graphite grease (Material No.CP2101)
(g) Attach the bracket (170) and the T5 sensor (10) assembly to the bracket (140), at flange R, with the bolts (150) and the nuts (130). Tighten the nuts by hand.
(h) Make sure the T5 sensor rigid lead is installed stress-free on the engine and, from rear to front:

TORQUE nuts (100) to between 110 and 95 lbf.in (1.24 and 1.07 m.daN )
TORQUE nuts (50, 90) to between 55 and 50 lbf.in (0.62 and 0.57 m.daN )
TORQUE nuts (130) to between 110 and 95 lbf.in (1.24 and 1.07 m.daN ) .

(i) Connect the CJ13 harness connector to the T5 sensor connector.
(j) TORQUE the coupling nut of CJ13 harness connector to between 160 and 150 lbf.in (1.81 and 1.70 m.daN )

. Safety the coupling nut with a CP8004lockwire 0.6 mm (0.0236 in.) dia or CP8005lockwire 0.6 mm (0.0236 in.) dia.

Subtask 77-22-10-861-051-A ** ON A/C NOT FOR ALL

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

Subtask 77-22-10-410-054-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 thrust reverser cowl doors: (Ref. AMM TASK 78-36-00-410-040)
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(3) Remove the WARNING NOTICE(S).

Subtask 77-22-10-440-051-A ** ON A/C NOT FOR ALL

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

Subtask 77-22-10-869-054-A ** ON A/C NOT FOR ALL

E. On the panel 50VU, make sure that the OFF legend of the FADEC GND PWR1(2) pushbutton switch is off.

Subtask 77-22-10-710-051-A ** ON A/C NOT FOR ALL

F. Do an operational test on the FADEC on the ground (with Engine Non Motoring) (Ref. AMM TASK 73-29-00-710-040).

Subtask 77-22-10-869-055-A ** ON A/C NOT FOR ALL

G. Do the EIS start procedure (upper ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).

Subtask 77-22-10-710-052-A ** ON A/C NOT FOR ALL

H. Operational Test:
(1) On the left or right MCDU, get the SYSTEM REPORT/TEST page (Ref. AMM TASK 31-32-00-860-012).
(2) Push the line key adjacent to the FADEC 1A(1B) for engine 1.
(3) Push the line key adjacent to the FADEC 2A(2B) for engine 2.
(4) Make sure that the message "T5 SENS, J13, ECU" is not in view.

Subtask 77-22-10-860-051-A ** ON A/C NOT FOR ALL

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

5. Close-up
Subtask 77-22-10-862-051-A ** ON A/C NOT FOR ALL

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

Subtask 77-22-10-410-055-A ** ON A/C NOT FOR ALL

B. Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040)
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

[Rev.10 from 2021] 2026.04.02 06:37:43 UTC