TRANSDUCER - BLEED TRANSFERRED PRESSURE (7HA1,7HA2) - ADJUSTMENT/TEST
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TASK 36-11-15-720-001
Functional Test of the Bleed Transferred Pressure Transducer (7HA1,7HA2)
1. Reason for the Job
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Self Explanatory
2. Job Set-up Information
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A. Fixtures, Tools, Test and Support Equipment
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REFERENCE QTY DESIGNATION
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No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)
R 98D36003000000 1 TEST SET - ENGINE BLEED SYSTEM
R 98F36003002000 1 TEST SET - ENGINE BLEED SYSTEM
B. Consumable Materials
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REFERENCE DESIGNATION
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Material No. 19-018 USA AMS 5687
LOCKWIRE 0.6 MM (Ref. 20-31-00)
C. Referenced Information
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REFERENCE DESIGNATION
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24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
36-11-00-740-001 BITE Test of the BMC 1(2)
36-11-15-991-002 Fig. 501
3. Job Set-up
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Subtask 36-11-15-861-051
A. Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
Subtask 36-11-15-941-051
B. Safety Precautions
(1)
Make sure that the engine 1(2) is shut down for at least 5 minutes.
(2)
On the AIR COND panel 30VU:
-make sure that the ENG 1(2) BLEED pushbutton switch is released
(OFF legend is on), R - make sure that the APU BLEED pushbutton switch is released (ON R legend is off),
-put a warning notice to tell persons not to operate the pneumatic system.
(3)
On the ENG panel 115VU:
-put a warning notice to tell the persons not to start the engine 1(2).
(4)
On the HP ground connector:
-Put a warning notice to tell persons not to pressurize the pneumatic system.
(5)
On the MAINTENANCE panel 50VU:
-make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off,
-put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 36-11-15-010-052
C. Get Access
(1)
Put the access platform in position at the pylon access.
(2)
Open these access doors :
FOR 7HA1
415AL, 415AR
FOR 7HA2
425AL, 425AR
Subtask 36-11-15-860-051-A
D. Aircraft Maintenance Configuration
R R (1) Disconnect the electrical connector 7HA1-A(7HA2-A) from the bleed transferred pressure-transducer 7HA1(2).
(2) Disconnect the electrical connector 8HA1-A(8HA2-A) from the bleed regulated pressure-transducer 8HA1(2).
(3) Put a blanking cap on the wiring side of the electrical connector 7HA1-A(7HA2-A).
R R (4) Use the cable bundle from the TEST SET - ENGINE BLEED SYSTEM (98F36003002000) or TEST SET - ENGINE BLEED SYSTEM (98D36003000000) to connect the electrical connector 8HA1-A(8HA2-A) on the bleed transferred pressure-transducer 7HA1(2).
(5) Remove and discard the lockwire from the sense line.
(6) Disconnect the sense line from the bleed transferred pressure-transducer 7HA1(2).
(7) Put a blanking plug on the disconnected line end.
4. Procedure_________
(Ref. Fig. 501/TASK 36-11-15-991-002)
Subtask 36-11-15-720-050
A. Functional Test of the Bleed Transferred Pressure-Transducer
(1) Connect the TEST SET - ENGINE BLEED SYSTEM (98F36003002000) or TEST SET - ENGINE BLEED SYSTEM (98D36003000000) as on the diagram of the given figure.
Test of the Bleed Transferred Pressure Transducer (7HA1,7HA2) Figure 501/TASK 36-11-15-991-002 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護手冊 AMM PNEUMATIC 氣源 1(74)
