Engine 2 Differential Pressure Transducer Measurement Failure

TASK 36-11-00-810-A21-A
Engine 2 Differential Pressure Transducer Measurement Failure

1. Possible Causes

XDCR-BLEED DIFFERENTIAL PRESS, ENG2 [18HA2]
sense line

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
AMM 36-11-18-000-801	Removal of the Bleed Differential Pressure-Transducer
AMM 36-11-18-400-801	Installation of the Bleed Differential Pressure-Transducer
AMM 36-11-49-000-826	Removal of the Sense Line between the Bleed-Air Precooler Exchanger (Upstream) and the Bleed Differential Pressure-Transducer
AMM 36-11-49-400-826	Installation of the Sense Line between the Bleed-Air Precooler Exchanger (Upstream) and the Bleed Differential Pressure-Transducer
AMM 36-22-00-790-802	Leak Check on all the Bleed Air Ducts and Packs Components

3. Fault Confirmation
Subtask 36-11-00-740-115-A ** ON A/C NOT FOR ALL

A. Test
(1) Not Applicable

4. Fault Isolation
Subtask 36-11-00-810-467-A ** ON A/C NOT FOR ALL

A. If the test gives the maintenance message:
DIFF-PRESS XDCR (18HA2)/ SENSE LINE
(1) Replace the XDCR-BLEED DIFFERENTIAL PRESS, ENG2 [18HA2] AMM 36-11-18-000-801 and AMM 36-11-18-400-801.

Subtask 36-11-00-810-468-A ** ON A/C NOT FOR ALL

B. If the fault continues:
(1) Replace the sense line of the bleed differential pressure-transducer AMM 36-11-49-000-826 and AMM 36-11-49-400-826.
(2) Do a leak check of the sense line AMM 36-22-00-790-802.

Subtask 36-11-00-710-651-A ** ON A/C NOT FOR ALL

C. Test
(1) After the subsequent flight, make sure that the fault does not continue.

[Rev.8 from Aug 2018] 2026.04.04 04:33:57 UTC