Removal of the Transient Bleed Valve [CFMB]

TASK 75-26-10-000-001-A
Removal of the Transient Bleed Valve

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.

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

1. Reason for the Job
This task is applicable for /P, /3 and /3 PIP engines.
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	AR	CAP - PROTECTION
No specific	AR	CONTAINER 5 L (1.32 USGAL)
No specific	AR	PLIERS - JAWED, SOFT
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)

B. 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

C. 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-B	Opening of the Fan Cowl Doors
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
Transient Bleed Valve - Removal/Installation

3. Job Set-up
Subtask 75-26-10-941-050-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).
(4) On the overhead panel 20VU, make sure that the ENG1(2) FIRE pushbutton switch is released.

Subtask 75-26-10-861-050-A ** ON A/C NOT FOR ALL

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

Subtask 75-26-10-865-050-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
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08

Subtask 75-26-10-010-050-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the 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 75-26-10-040-050-A ** ON A/C NOT FOR ALL

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

Subtask 75-26-10-010-051-A ** ON A/C NOT FOR ALL

F. Open the thrust-reverser cowl 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 75-26-10-020-050-A ** ON A/C NOT FOR ALL

A. Remove the Transient Bleed Valve (TBV).

NOTE: Procedure to remove the TBV is the same for Engines Pre and post CFM 72-0255 Configuration.

(1) Disconnect the electrical connectors as follows:
(a) Disconnect the electrical connectors (130) and (140) from the TBV (10). Use PLIERS - JAWED, SOFT if necessary.
(b) Install CAP - BLANKING on the open ends of the electrical connectors (130) and (140) and on the electrical connectors on the TBV (10).
(2) Remove the TBV air outlet and inlet tubes as follows:
(a) Loosen the V retainer coupling (110) that attaches the TBV air outlet tube (2) to the outlet port of the TBV (10).
(b) Remove the TBV air outlet tube (2) from the outlet port of the TBV (10).
(c) Remove and discard the seal (170) from the TBV air outlet tube (2) and the outlet port of the TBV (10).
(d) Loosen the V retainer coupling (100) that attaches the TBV air inlet tube (3) to the inlet port of the TBV (10).
(e) Remove the TBV air inlet tube (3) from the inlet port of the TBV (10).
(f) Remove and discard the seal (160) from the TBV air inlet tube (3) and the inlet port of the TBV (10).
(g) Install CAP - BLANKING on the open ends of the inlet tube and air outlet tube and on the inlet and outlet ports of the TBV.
(3) Remove the fuel manifold as follows:

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) Put a CONTAINER 5 L (1.32 USGAL) below the area of the fuel manifold (40) of the TBV (10).
(b) Remove the four bolts (25) and (26) on the fuel manifold (40).
(c) Carefully move aside the CJ13 harness bracket (31) installed over the fuel manifold (40) to allow the TBV removal.
(d) Remove and inspect the seal gasket (50) from between the fuel manifold (40) and the TBV (10).
(4) Remove the TBV as follows:

WARNING: PROVIDE SUPPORT FOR THE TBV AS YOU REMOVE THE BOLTS TO AVOID POSSIBLE DAMAGE TO EQUIPMENT AND PERSONNEL INJURY. THE TBV WEIGHS APPROXIMATELY 7 LB (3 KG).

(a) Remove the bolts (80) that attach the TBV (10) to the bracket (70) on the core engine.
(b) Remove the bolts (60) that attach the TBV (10) to the forward bracket.
(c) Remove the TBV (10).
(d) Install CAP - PROTECTION on the fuel inlet and fuel drain ports of the TBV and on the outlet of the fuel manifold.

[Rev.10 from 2021] 2026.04.01 03:10:21 UTC