W DOC AIRBUS | AMM A320F

Removal of the Air Inlet

TASK 21-61-51-000-002-A
Removal of the Air Inlet

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.
FIN: 20HM
FIN: 21HM
FIN: 28HH
FIN: 8HH
1. Reason for the Job
NOTE: A minimum of two persons are necessary to do this task.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
CAP - BLANKING
No specific
AR
PLUG - BLANKING
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
191BB, 191KB, 192FB, 192KB
 C. Referenced Information
REFERENCE
DESIGNATION
TASK 24-41-00-861-002-A
Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01
Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02
Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 53-35-13-000-002-A
Removal of the Quick-Release Access Panels from the Belly Fairing Structure
F Air Inlet - Access Panel Location ** ON A/C NOT FOR ALL
F Air Inlet - Access Panel Location ** ON A/C NOT FOR ALL
F Air Inlet - Component Location ** ON A/C NOT FOR ALL
F Air Inlet - Component Location ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 21-61-51-861-052-A
A. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 21-61-51-865-053-A
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUAIR COND/TEMP CTL/SYS 1 CHAN B/28VDC52HHD08
** ON A/C NOT FOR ALL
122VUAIR COND/PACK TEMP/CTL SYS1/2/115VAC21HHW22
122VUAIR COND/PACK TEMP/CTL SYS1/2/28VDC23HHW21
122VUAIR COND/PACK TEMP/CTL SYS1/1/115VAC1HHX22
122VUAIR COND/PACK TEMP/CTL SYS1/1/28VDC3HHX21
122VUAIR COND/PACK TEMP CTL SYS2/2/28VDC24HHY21
122VUAIR COND/PACK TEMP CTL SYS2/2/115VAC22HHY20
122VUAIR COND/PACK TEMP CTL SYS2/1/28VDC4HHY19
122VUAIR COND/PACK TEMP CTL SYS2/1/115VAC2HHY18
** ON A/C NOT FOR ALL
122VUAIR COND/TEMP CTL SYS 2/CHAN A/115VAC53HHW22
122VUAIR COND/TEMP CTL SYS 2/CHAN A/28VDC55HHW21
122VUAIR COND/TEMP CTL SYS 1/CHAN A/115VAC49HHX22
122VUAIR COND/TEMP CTL SYS 1/CHAN A/28VDC51HHX21
122VUAIR COND/TEMP CTL SYS 2/CHAN B/28VDC56HHY21
122VUAIR COND/TEMP CTL SYS 2/CHAN B/115VAC54HHY20
122VUAIR COND/TEMP CTL SYS 1/CHAN B/115VAC50HHY18
Subtask 21-61-51-941-053-A
C. Safety Precautions
   (1) On the panel 30VU:
     (a) Make sure that the APU BLEED and the ENG BLEED/1(2) pushbutton switches are released.
     (b) Put a warning notice in position to tell persons not to operate these pushbutton switches.
   (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.
Subtask 21-61-51-010-051-A
D. Get Access
   (1) Remove the access panels (Ref. AMM TASK 53-35-13-000-002).
     (a) For the Left air inlet,
     (b) For the Right air inlet,
4. Procedure
Subtask 21-61-51-020-051-B ** ON A/C NOT FOR ALL
A. Removal of the Air Inlet
   (1) For the Left air inlet,
     (a) Remove the clamp (4) and disconnect the bellows (5).
     (b) Remove the quick-release pins (9) and (22) and the cross beam (7).
     (c) Disconnect the water injector connector (57).
     (d) Put the PLUG-BLANKING in each disconnected line end.
     (e) Disconnect the electrical connector (58).
     (f) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.
     (g) Remove the bolts (30), the washers (31), the clamps (32) and the spacers (33).
     (h) Remove the bolts (34), the washers (31), the clamps (32) and (35) and the spacers (36).
     (i) Remove the nut (13), the washer (14), the clamp (15), the spacer (16) and the screw (17).
     (j) Temporarily attach the disconnected electrical cable (39) to the aircraft structure.
     (k) Disconnect the support rod (38):
       1 Remove the nut (27), the washer (26), the bolt (24) and disconnect the support rod (38).
     (l) Hold the air inlet (3).
     (m) Remove the nut (21), the washer (20), the bolt (18) and disconnect the support rod (19).
     (n) Disconnect the support rods (25) and (29):
       1 Remove the nuts (27), the washers (26), the bolts (24) and disconnect the support rods (25) and (29).
     (o) Remove the screws (2), the washers (1) and the air inlet (3).
     (p) Put protective covers on the open ends of the bellows (5) and the air inlet (3).
   (2) For the Right air inlet
     (a) Remove the clamp (4) and disconnect the bellows (5).
     (b) Remove the quick-release pins (10) and (44) and the cross beam (8).
     (c) Disconnect the water injector connector (57).
     (d) Put the PLUG-BLANKING in each disconnected line end.
     (e) Disconnect the electrical connector (58).
     (f) Put the PLUG-BLANKING in each disconnected line end.
     (g) Remove the bolts (30), the washers (31), the clamps (32) and the spacers (33).
     (h) Remove the bolts (34), the washers (31), the clamps (32) and (35) and the spacers (36).
     (i) Remove the nut (13), the washer (14), the clamp (15), the spacers (16) and the screw (17).
     (j) Temporarily attach the disconnected electrical cable (55) to the aircraft structure.
     (k) Disconnect the support rod (40):
       1 Remove the nut (27), the washer (26), the bolt (24) and disconnect the support rod (40).
     (l) Hold the air inlet (6).
     (m) Disconnect the support rods (41) and (42):
       1 Remove the nuts (27), the washers (26), the bolts (24) and disconnect the support rods (41) and (42).
     (n) Remove the nut (53), the washer (52), the bolt (50) and disconnect the support rods (51) and (54).
     (o) Remove the nut (49), the washer (48), the bolt (46) and disconnect the support rod (47).
     (p) Remove the screws (2), the washers (1) and the air inlet (6).
     (q) Put protective covers on the open ends of the bellows (5) and the air inlet (6).
Subtask 21-61-51-020-051-C ** ON A/C NOT FOR ALL
A. Removal of the Air Inlet
   (1) For the Left air inlet,
     (a) Remove the clamp (4) and disconnect the bellows (5).
     (b) Remove the quick-release pins (9) and (22) and the cross beam (7).
     (c) Disconnect the water injector connector (57).
     (d) Put the PLUG-BLANKING in each disconnected line end.
     (e) Disconnect the electrical connector (58).
     (f) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.
     (g) Remove the bolts (30), the washers (31), the clamps (32) and the spacers (33).
     (h) Remove the bolts (34), the washers (31), the clamps (32) and (35) and the spacers (36).
     (i) Remove the nut (13), the washer (14), the clamp (15), the spacers (16) and the screw (17).
     (j) Temporarily attach the disconnected electrical cable (39) to the aircraft structure.
     (k) Support the IGGS pallet (8YA) with an applicable tool:
WARNING: SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
       1 Carefully install a support tool between the side frame of the IGGS pallet and frame C34/35.7.
NOTE: The IGGS pallet weighs approx. 20.9 kg (46.0766 lb).
Make sure that you support it correctly before you disconnect the bracket (60) in the next work step.
     (l) Disconnect the support rod (38):
       1 Remove the nut (27), the washer (26), the bolt (24) and disconnect the support rod (38) and the bracket (60) with bushing (59).
     (m) Hold the air inlet (3).
     (n) Remove the nut (21), the washer (20), the bolt (18) and disconnect the support rod (19).
     (o) Disconnect the support rods (25) and (29):
       1 Remove the nuts (27), the washers (26), the bolts (24) and disconnect the support rods (25), (29) and the bracket (60) with bushing (59).
     (p) Remove the screws (2), the washers (1) and the air inlet (3).
     (q) Put protective covers on the open ends of the bellows (5) and the air inlet (3).
   (2) For the Right air inlet
     (a) Remove the clamp (4) and disconnect the bellows (5).
     (b) Remove the quick-release pins (10) and (44) and the cross beam (8).
     (c) Disconnect the water injector connector (57).
     (d) Put the PLUG-BLANKING in each disconnected line end.
     (e) Disconnect the electrical connector (58).
     (f) Put the PLUG-BLANKING in each disconnected line end.
     (g) Remove the bolts (30), the washers (31), the clamps (32) and the spacers (33).
     (h) Remove the bolts (34), the washers (31), the clamps (32) and (35) and the spacers (36).
     (i) Remove the nut (13), the washer (14), the clamp (15), the spacers (16) and the screw (17).
     (j) Temporarily attach the disconnected electrical cable (55) to the aircraft structure.
     (k) Disconnect the support rod (40):
       1 Remove the nut (27), the washer (26), the bolt (24) and disconnect the support rod (40).
     (l) Hold the air inlet (6).
     (m) Disconnect the support rods (41) and (42):
       1 Remove the nuts (27), the washers (26), the bolts (24) and disconnect the support rods (41) and (42).
     (n) Remove the nut (53), the washer (52), the bolt (50) and disconnect the support rods (51) and (54).
     (o) Remove the nut (49), the washer (48), the bolt (46) and disconnect the support rod (47).
     (p) Remove the screws (2), the washers (1) and the air inlet (6).
     (q) Put protective covers on the open ends of the bellows (5) and the air inlet (6).
[Rev.10 from 2021] 2026.04.02 06:11:39 UTC
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