(5)
 Remove the access platform(s).

 (6)
 In the cockpit on the CAPT jack panel, disconnect and remove the 600 ohm headset.

 Subtask 21-31-51-862-050
 B. De-energize the aircraft electrical circuits
 (Ref. TASK 24-41-00-862-002).

R 1EFF : 001-049, 051-099, 101-105, 1 21-31-51Page 455 1 1 May 01/05 1 1 1CES 1 **ON A/C ALL

 TASK 21-31-51-000-002 Removal of the Outflow Valve (10HL) - Electronics Module 10HL-1 (10HL-2) 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 electronics modules 1 and 2,
____
 ELECTRONIC MODULE1 is 10HL-1, ELECTRONIC MODULE 2 is 10HL-2.

 1.
 Reason for the Job

__________________
 Self Explanatory

 2.
 Job Set-up Information

______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------
REFERENCE  QTY DESIGNATION
 -------------------------------------------------------------------------------
No specific blanking caps
 No specific circuit breaker(s) safety clip(s)
 No specific access platform 2 m (6 ft. 7 in.)

 B. Referenced Information
 -------------------------------------------------------------------------------
REFERENCE  DESIGNATION
 -------------------------------------------------------------------------------
24-41-00-861-002  Energize the Aircraft Electrical Circuits from the External Power
 25-55-12-000-003  Removal of the Sidewall Panels in the AFT Cargo
 Compartment - FR59/FR65

 52-30-00-860-001  Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

R **ON A/C 001-049, 051-099, 101-105,
 21-31-51-991-005  Fig. 403

 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R  **ON A/C 106-149, 151-199, 201-299, 301-399, 401-499,
 21-31-51-991-005-A  Fig. 403A
 **ON A/C ALL
 3. Job Set-up__________
 Subtask 21-31-51-861-053
 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
 Subtask 21-31-51-865-064
 B. Open, safety and tag this(these) circuit breaker(s):
R  -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AIR COND/CAB/PRESS/CTL1 1HL D09 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399, 
R  122VU AIR COND/AFT CARGO VENT/FAN  30HN  S22 
R  **ON A/C ALL 
R R R  122VU AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/SPLY 122VU AIR COND/CAB PRESS/CTL/MAN 122VU AIR COND/CAB PRESS/CTL/2  6HU 3HL 2HL  U19 Y23 Y22

 **ON A/C 001-049, 051-061, 101-102,
 Subtask 21-31-51-010-051
 C. Get Access
 (Ref. Fig. 403/TASK 21-31-51-991-005)

 WARNING : DO NOT OPEN OR GO NEAR PRESSURE-SEALED DOORS WHEN THE AIRCRAFT
_______ IS PRESSURIZED. A PRESSURE-SEALED DOOR THAT OPENS WHEN THE AIRCRAFT IS PRESSURIZED.
 -WILL CAUSE EXPLOSIVE DECOMPRESSION.
 -CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAUSE DAMAGE TO THE AIRCRAFT/EQUIPMENT.
 WARNING : OPEN THE ACCESS DOOR AND MAKE SURE IT STAYS OPEN.
_______ ATTACH A WARNING NOTICE TO THE ACCESS DOOR TO TELL PERSONS NOT TO CLOSE IT. THIS IS TO PREVENT ACCIDENTAL PRESSURIZATION OF THE AIRCRAFT BY THE AIR CONDITIONING SYSTEM IF ALL THE OTHER CABIN OPENINGS ARE CLOSED. PRESSURIZATION OF THE AIRCRAFT CAN BE DANGEROUS. IT CAN CAUSE A DOOR TO OPEN WITH EXPLOSIVE FORCE WHICH CAN CAUSE INJURY AND/OR DAMAGE.
 (1)
 Open the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-001).

 (2)
 Put the access platform in position at the AFT cargo-compartment door

 826.

 (3)
 Remove the access panel 162CW (Ref. TASK 25-55-12-000-003).

R **ON A/C 062-099, 103-149, 151-199, 201-299, 301-399, 401-499,
 Subtask 21-31-51-010-051-A
 C. Get Access
 **ON A/C 062-099, 103-105,
 (Ref. Fig. 403/TASK 21-31-51-991-005)
R 1EFF : ALL 1 21-31-51Page 458 1 1 Aug 01/05 1 1 1CES 1

 Electronics Module 10HL-1 (10HL-2) - Component Location
　
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