• 热门标签

当前位置: 主页 > 航空资料 > 机务资料 >

时间:2011-03-26 23:52来源:蓝天飞行翻译 作者:admin
曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

 52-21-11-991-004-A Fig. 407A R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 3. Job Set-up
__________
 Subtask 52-21-11-010-054

 A. Get Access
 (1)
 Remove the emergency exit hatch (referred to as hatch) (Ref. TASK 52-21-11-000-001).

 (2)
 If necessary, remove the lining from the applicable hatch (Ref. TASK 25-23-47-000-001).


R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 52-21-11Page 430 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1


 4. Procedure
_________
 Subtask 52-21-11-020-051

 A. Removal of the Slide Release Mechanism
 **ON A/C 001-049, 051-099, 101-149, 201-299,

 (Ref. Fig. 407/TASK 52-21-11-991-004) R **ON A/C 151-199, 401-499,
 (Ref. Fig. 407A/TASK 52-21-11-991-004-A) R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 (1)
 Remove the nuts (24) and the bolts (23) from the edge curve of the hatch structure.

 (2)
 Remove the slide release mechanism (25) from the hatch structure.

 (3)
 If necessary, remove and discard the spring pin (26) from the guide fitting (22).

 (4)
 Remove the latch pin (20) and the spring (21) from the guide fitting (22).


R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 52-21-11Page 431 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1


 Slide Release Mechanism
 Figure 407/TASK 52-21-11-991-004

R 1EFF : 001-049, 051-099, 101-149, 201-299, 1 52-21-11Page 432 1 1 Aug 01/05 1 1 1CES 1


 Slide Release Mechanism Figure 407A/TASK 52-21-11-991-004-A
R 1EFF : 151-199, 401-499, 1 52-21-11Page 433 1 1 Aug 01/05 1 1 1CES 1 TASK 52-21-11-400-003


 Installation of the Slide Release Mechanism
 1. Reason for the Job
__________________
 Self Explanatory
 2. Job Set-up Information
______________________
 A. Consumable Materials
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-004  USA MIL-PRF-23827 TYPE I SYNTH.ESTER BASED GREASE HIGH PRESSURE (Ref. 20-31-00)
 Material No. 09-018  USA AMS 3267/3 CORROSION INHIBITING LOW ADHESION SEALANT (Ref. 20-31-00)
 B. Expendable Parts
 -------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
spring pin  52-21-11 35 -100
 C. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
25-23-47-400-001  Installation of the Lining on the Emergency Exit Hatches
 52-21-00-200-001  Detailed Visual Inspection of the Emergency Exits, Internal Structure and Load Transmitting Profile LH/RH
 52-21-00-720-001 Functional Test of the Automatic and the Manual Slide Release Signal 52-21-11-400-001 Installation of the Emergency Exit Hatch
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 52-21-11Page 434 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------


**ON A/C 001-049, 051-099, 101-149, 201-299,
 52-21-11-991-004 Fig. 407 R **ON A/C 151-199, 401-499,
 52-21-11-991-004-A Fig. 407A R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 3. Job Set-up
__________
 Subtask 52-21-11-100-050

 A. Preparation for the Installation
 (1)
 Make sure that the parts retained from the removed component are clean and in the correct condition.

 (2)
 Clean the component interface and/or the adjacent area.

 (3)
 For the opposide installation, remove the self-adhesive cover from the inner edge curve of the emergebcy exit hatch (referred to as hatch).


 NOTE : In this case, you must also install the opposite guide fitting
____
 (22).

 (4)
 Make sure that the new installation area is clean and in the correct condition.

 (5)
 Apply SEALANTS (Material No. 09-018) to the mating area of the guide fitting (22), the bolts (23) and the new spring pin (26).

 (6)
 Apply COMMON GREASE (Material No. 04-004) to the latch pin (20).


R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 52-21-11Page 435 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
 
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址:A320飞机维护手册 AMM DOORS 舱门3(36)