35-10-00Page 509

 C. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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 31-60-00-860-001 EIS Start Procedure 35-10-00-991-001 Fig. 501 35-10-00-991-004 Fig. 503
 3. Job Set-up
__________ Subtask 35-10-00-010-056
 A. Get Access
 (1)
 Put the access platform in position at the access door 812.

 (2)
 Open the access door 812.

 (3)
 In the avionics compartment, open the cover of the oxygen compartment.

 (4) Close the valve of the oxygen storage cylinder (5750HM). Subtask 35-10-00-865-051
 B. Make sure that this(these) circuit breaker(s) is(are) closed:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU OXYGEN/CREW/OXY/SPLY 1HT HA01
 Subtask 35-10-00-860-053
 C. Aircraft Maintenance Configuration
 (Ref. Fig. 501/TASK 35-10-00-991-001)

 (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
 EFF : ALL

35-10-00Page 510

 (2)
 Do the EIS start procedure (EWD DU, SD DU only)
 (Ref. TASK 31-60-00-860-001).

 (3)
 Make sure that the avionics equipment ventilation operates correctly.

 (4)
 Make sure that the oxygen cylinder source is bled correctly, 1850 psi (127.5530 bar) at 21 deg.C (69.80 deg.F).

 (5)
 Bleed the oxygen system:

 (a)
 On the panel 21VU, release the OXYGEN/CREW SUPPLY pushbutton switch (the OFF legend comes on).

 (b)
 On one of the oxygen-masks: Push the PRESS TO TEST AND RESET control button a sufficient number of times.

 Subtask 35-10-00-480-051
 D. Preparation of the Test Installation
 (Ref. Fig. 503/TASK 35-10-00-991-004)

 (1)
 Remove the blanking cap of the test port 5755HM.

 (2)
 Install a pressure gage that can read pressure from 0 psi (0.0000 bar) to 150 psi (10.3421 bar) on the test port 5755HT.

 (3)
 Fully open the valve of the oxygen cylinder valve assembly.

 (4)
 Check that the pressure read on the pressure gage is between 78 psi (5.3779 bar) and 94 psi (6.4810 bar).

 4. Procedure
_________ Subtask 35-10-00-860-054
 A. Test of the LP Oxygen
 (1)
 On the panel 21VU, push the OXYGEN/CREW SUPPLY pushbutton switch (the OFF legend goes off).

 (2)
 Let the pressure become stable.

 (3)
 Close the valve of oxygen cylinder valve assembly.

 (4)
 Measure on the pressure gage the initial pressure "PO" in the LP system (between 70 psi (4.8263 bar) and 94 psi (6.4810 bar).

 EFF : ALL

35-10-00Page 511

 Flight Crew Oxygen System - Schematic
 Figure 503/TASK 35-10-00-991-004
 EFF :  ALL  35-10-00 Page 512 
Feb 01/98
 CES 

R R  (5) Measure the Outside Air Temperature (OAT) and the cockpit temperature on the ECAM SD "page COND".
R  (6) Calculate the initial temperature To = OAT+COCKPIT TEMP ----------------
2
 (7) Let the pressure become stable during 1 hour then measure on the pressure gage the final pressure "P". 
R R R (8) Measure the OAT and the cockpit temperature on the ECAM SD "page COND". 
R  (9) Calculate the final temperature T = OAT+COCKPIT TEMP ----------------
2
 NOTE : The two values initial pressure/final pressure must be equal____ with a tolerance of 2 psi (0.1378 bar).
R R R  NOTE : If the temperature has changed, do the pressure correction as____ follows: (T+273) P = Po --------(To+273) Po=initial pressure P=final pressure To=initial temperature in deg.C T=final temperature in deg.C
 Subtask 35-10-00-614-053
 B. Disconnect the Test Installation (Ref. Fig. 501/TASK 35-10-00-991-001)
 (1) Put the blanking cap on the test port 5755HM.
 (2) After the test, make sure that the pressure read on the pressure gage (corrected in function of the temperature) is stable with a tolerance of 2 psi (0.1378 bar).
　
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 OXYGEN 氧氣(25)