53-35-13-991-004-B Fig. 405B
**ON A/C 001-049, 051-099, 101-149, 201-299,
53-35-13-991-005 Fig. 406 R **ON A/C 151-199, 401-499,
53-35-13-991-005-A Fig. 406A
**ON A/C 301-399,
53-35-13-991-005-B Fig. 406B R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
53-35-13-991-006 Fig. 407
**ON A/C 301-399,
53-35-13-991-006-A Fig. 407A
EFF : ALL
53-35-13Page 442
**ON A/C ALL
3. Job Set-up
__________
Subtask 53-35-13-860-053
A. Aircraft Maintenance Configuration WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION
_______
BEFORE YOU START A TASK ON OR NEAR:
-
THE FLIGHT CONTROLS
-
THE FLIGHT CONTROL SURFACES
-
THE LANDING GEAR AND THE RELATED DOORS
-COMPONENTS THAT MOVE.
(1)
Make sure the LOCKING TOOL - FLAP/SLAT CONTROL LEVER (98D27803000000) is installed on the flap/slat control lever, when working near the flaps/slats.
(2)
Make sure the warning notice is put on the slat/flap control lever, to tell persons not to operate the flaps/slats.
(3)
Make sure the adjustable access platform is in the required position.
4. Procedure
_________
Subtask 53-35-13-560-052
A. Preparation for Installation R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 407/TASK 53-35-13-991-006)
**ON A/C 301-399,
(Ref. Fig. 407A/TASK 53-35-13-991-006-A)
**ON A/C ALL
(1)
Clean the component interface and/or the adjacent area.
(2)
Do an inspection of the component interface and/or the adjacent area.
EFF : ALL
53-35-13Page 443
(3)
Examine the adhesive tape (2) and the profile sections (1) for damage. If necessary, replace the tape and/or the profile sections.
(4)
If you have removed the panels 191EB/192EB check the sealant bead on the lower belly fairing structure for correct condition. If the sealant bead is not in the correct condition, continue as follows:
-remove the old sealant bead from the lower side of the belly fairing structure, use a nonmetallic scraper,
-apply SPECIAL MATERIALS (Material No. 05-013A) to the panel in the contact area of the sealant bead,
-install the panels,
-apply a new bead of SEALANTS (Material No. 09-002) (Ref. TASK 51-76-11-300-001).
(5)
Make sure that the work area is clean and clear of tool(s) and other items.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
Subtask 53-35-13-420-051
B. Installation of the quick-release access panels
**ON A/C 001-049, 051-099, 101-149, 201-299,
(Ref. Fig. 405/TASK 53-35-13-991-004)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 405A/TASK 53-35-13-991-004-A)
**ON A/C 001-049, 051-099, 101-149, 201-299,
(Ref. Fig. 406/TASK 53-35-13-991-005)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 406A/TASK 53-35-13-991-005-A)
EFF : ALL
53-35-13Page 444
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 407/TASK 53-35-13-991-006)
(1) Install the following quick-release access panels: 191BB, 191EB, 191HB, 191KB, 192EB, 192FB, 192KB, 195AB, 196AB, 197BB, 198DB and 198BB.
CAUTION : DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE
_______ MADE OF CARBONFIBER REINFORCED PLASTIC.
(2)
On panel 191KB and/or panel 192KB, install the pins (5) and let the panel hang down on the cords (6).
(3)
On the panel 198DB connect the cord.
(4)
Put the panel (4) in position.
(5)
Tighten the studs (3). NOTE : When you tighten the studs, do not TORQUE to more than 0.3
____
m.daN (26.5486 lbf.in).
**ON A/C 301-399,
Subtask 53-35-13-420-051-A
B. Installation of the quick-release access panels (Ref. Fig. 405B/TASK 53-35-13-991-004-B, 406B/TASK 53-35-13-991-005-B, 407A/TASK 53-35-13-991-006-A)
(1) Install the following quick-release access panels: 191BB, 191EB, 191HB, 191KB, 192EB, 192FB, 192KB, 195AB, 196AB, 197KB, 198DB and 198KB.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM FUSELAGE 機(jī)身2(128)
