(2)
Make sure that the LOCKING TOOL - FLAP/SLAT CONTROL LEVER (98D27803000000) is on the slat/flap control lever.
Subtask 36-11-48-865-066
C. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11
122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20
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Wing Bleed Air Ducting - Access Panel Location
Figure 601/TASK 36-11-48-991-022
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Wing Bleed Air Ducting - Location and Detail
Figure 602/TASK 36-11-48-991-023
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Subtask 36-11-48-010-058
D. Get Access
R R (1) Put an access platform, adjustable in position below the wing leading edge panels, zone 510(610).
R R R (2) Remove the applicable access panels (Ref. TASK 53-35-11-000-001), (Ref. TASK 57-41-37-000-004), (Ref. TASK 57-41-37-000-005), (Ref. TASK 57-41-37-000-009): (Ref. Fig. 601/TASK 36-11-48-991-022)
(a) For the LH wing: - remove the access panels 191BT, 521AB, 521BB, 521CB, 521EB, 521BT, 522AB.
(b) For the RH wing: - remove the access panels 192BT, 621AB, 621BB, 621CB, 621EB, 621BT, 622AB.
(c) For the LH engine pylon: - remove the access panels 413DL, 414FR.
(d) For the RH engine pylon: - remove the access panels 423DL, 423FL.
(3) On the bleed air ducting between the wing/fuselage connection, anti-ice valve and the precooler: - remove and discard the braided wire from the insulation muffs.
(4) Remove the insulation muffs.
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4. Procedure
_________
(Ref. Fig. 602/TASK 36-11-48-991-023)
R **ON A/C 001-049, 101-105, 151-199, 201-210,
Subtask 36-11-48-790-055-B
A. Leak Check of the Bleed Air Ducting (Air supplied by the APU)
NOTE : There are two leak check procedures given. One procedure uses air
____ supplied by the APU and the other uses air supplied by the Ground Air Power Cart (GAPC). Use one of the two procedures to leak check the applicable connections.
(1)
Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
(2)
Do the EIS start procedure (ECAM only) (Ref. TASK 31-60-00-860-001).
(3)
On the ECAM control panel 11VU:
-push(in) the BLEED P/BSW
-make sure that the BLEED page is shown on the lower ECAM DU.
(4)
On the panel 25VU:
-
make sure that the ANTI-ICE/WING P/BSW is released (out)
-
make sure that the ANTI-ICE/WING P/BSW ON light is off.
(5)
Start the APU (Ref. TASK 49-00-00-860-008).
(6)
On the AIR COND panel 30VU:
-push (in) the APU BLEED P/BSW
-make sure that the APU BLEED P/BSW ON light comes on (blue) and the bleed air system is pressurized.
(7)
On the ECAM lower DU, make sure that the BLEED page shows:
-
the X BLEED valve is open (green in-line)
-
the APU BLEED valve is open (green in-line).
(8)
On the ECAM control panel:
-push (in) the APU P/BSW
-
make sure that the APU page comes into view on the lower ECAM DU
-
make sure that the APU BLEED pressure is shown.
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(9) Use leak detection solution to do a leak check of the wing bleed air ducting connections. Do the leak check from the wing/fuselage connection, to the wing anti-ice valve and the precooler on:
-all air ducts
-each duct joint
-all flexible connections.
NOTE : Leakage is permitted when a series of bubbles are continuously
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