-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-912-004 Electrical Bonding of Components With Conductive
Bolts and Screws and Bonding Straps in the Fuselage
and in the Wings (this does not include the tanks)-
52-22-00-010-001 Opening of the Emergency Exit Doors from the
Passenger Compartment
52-22-00-410-001 Closing of the Emergency Exit Doors from the
Passenger Compartment
52-22-00-614-002 Charging of the Door Damper and Emergency Operation
Cylinders (1600WM, 1601WM, 1602WM, 1603WM) at the
Emergency Exit Doors
52-22-00-860-003 Special Precaution before Maintenance on the Door
Damper and Emergency Operation Cylinder
52-22-00-860-004 Special Precaution after Maintenance on the Door
Damper and Emergency Operation Cylinder
52-22-11-400-001 Installation of the Emergency Exit Doors
52-22-14-400-001 Installation of the Door Damper and Emergency
Operation Cylinder
52-22-12-991-001 Fig. 401
3. Job Set-up__________
Subtask 52-22-12-860-054
A. Aircraft Maintenance Configuration
(1)
Make sure that the applicable emergency exit door (referred to as door) is opened as required (Ref. TASK 52-22-00-010-001).
(2)
Make sure that the special precaution on the door damper and emergency operation cylinder is completed (Ref. TASK 52-22-00-860-003).
(3)
Make sure that the access platform is in position below the partly opened door.
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B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
121VU EIS/SLIDES/ARM AND WARN/FLT 15WN P11 121VU EIS/SLIDES/ARM AND WARN/GND 13WN P10 121VU EIS/SDAC1 AND 2/DOOR/DET/PAX 48WV P05
4. Procedure
_________ Subtask 52-22-12-910-050
A. Preparation for Installation
(1)
Make sure that the parts retained from the removed component are clean and in the correct condition.
(2)
Do an inspection of the component interface and/or the adjacent area.
(3)
Examine the spacers (6) and (15) and the bushings (2) and (5) for surface damage.
(4)
Lubricate the bolts (3) and (13) with COMMON GREASE (Material No. 04-004).
Subtask 52-22-12-420-050
B. Installation of the Support Arm
(Ref. Fig. 401/TASK 52-22-12-991-001)
(1)
Install the spacers (6) and (15) and the bushings (2) and (5) to the related hinge fittings.
(2)
Put the support arm (1) into the position at the attachment fittings of the fuselagre frame and attach it as follows:
(a)
Put the bolt (3) with the washer (4) into the upper hinge fitting.
(b)
Assemble the stop (7) and the nut (8) on the bolt (3).
(c)
Tighten the nut (8) and safety it with the new cotter pin (9).
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(3)
Install the lower bolt (13) as follows:
(a)
Put the bolt (13) together with the lockwasher (14) into the lower hinge fitting.
(b)
Assemble the washers (16) and (19) and the nut (17) on the bolt (13).
(c)
Tighten the nut (17) and safety it with the new cotter pin (18).
(4)
Make sure that the support arm (1) moves easily.
