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时间:2011-02-24 09:55来源:蓝天飞行翻译 作者:admin
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 3. Job Set-up
__________ Subtask 21-61-12-861-050
 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 21-61-12Page 401 1201-299, 301-399, 1Aug 01/05 1 1 1CES 1


 Subtask 21-61-12-865-050
 B. Open, safety and tag this(these) circuit breaker(s):
R  -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------FOR 15HH 122VU AIR COND/PACK TEMP/CTL SYS1/1/115VAC 1HH X22 122VU AIR COND/PACK TEMP/CTL SYS1/1/28VDC 3HH X21 
R  **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302, 
R  122VU AIR COND/PACK TEMP CTL SYS2/1/28VDC  4HH  Y19 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399, 
R  122VU AIR COND/PACK TEMP CTL SYS2/1/115VAC  2HH  Y18 
R  **ON A/C 106-149, 303-399, 
R  122VU  4HH  Y19 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
 FOR 35HH 122VU AIR COND/PACK TEMP/CTL SYS1/2/115VAC 122VU AIR COND/PACK TEMP/CTL SYS1/2/28VDC 122VU AIR COND/PACK TEMP CTL SYS2/2/28VDC 122VU AIR COND/PACK TEMP CTL SYS2/2/115VAC  21HH 23HH 24HH 22HH  W22W21Y21Y20
 Subtask 21-61-12-010-050
 C. Get Access
 (1) Remove the access panel/s (Ref. TASK 53-35-13-000-002). 
R  (a) FOR 15HH - 191KB. 
R  (b) FOR 35HH - 192KB. 

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 4. Procedure
_________
 (Ref. Fig. 401/TASK 21-61-12-991-001) Subtask 21-61-12-020-050
 A. Removal of the Compressor Overheat-Temperature Sensor
 (1)
 Disconnect the electrical connector (2).

 (2)
 Put blanking caps on the disconnected electrical connectors.

 (3)
 Remove and discard the lockwire.

 (4)
 Remove the compressor overheat-temperature sensor (1) and the packing (3).

 (5)
 Remove the packing (3) from the compressor overheat-temperature sensor (1).

 (6)
 Put blanking plugs on the disconnected line ends.


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 Compressor Overheat - Temperature Sensor
 Figure 401/TASK 21-61-12-991-001

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 TASK 21-61-12-400-001 Installation of the Compressor Overheat - Temperature Sensor 15HH (35HH) WARNING : MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM
_______ FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
 NOTE : The procedure is the same for the compressor overheat temperature
____ sensors 15HH and 35HH.
 1.
 Reason for the Job

__________________
 Self Explanatory


 2.
 Job Set-up Information


______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific  Torque Wrench : range 0.00 to 1.20 m.daN
 (0.00 to 9.00 lbf.ft)
 B. Consumable Materials
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-012  USA VV-P-236 PURE MINERALVASELINE OR PETRO- LATUM (Ref. 20-31-00)
 Material No. 19-009  USA AMS 5687 LOCKWIRE STAINLESS STEEL ANNEALED 0.5MM DIA (Ref. 20-31-00)
 C. Expendable Parts
 -------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
3 packing 21-61-03 08 -050 3 packing 21-61-03 08 -050A
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 D. Referenced Information
 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
21-61-00-710-001 Operational Test of the Pack Temperature-Control System 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 53-35-13-000-002 Removal of the Quick-Release Access Panels from the Belly Fairing Structure 53-35-13-400-002 Installation of the Quick-Release Access Panels on the Belly Fairing Structure 21-61-12-991-001 Fig. 401
 
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