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R  (b) If you can not install the bolt (14) correctly, adjust the length 
R  of the door actuator (Ref. TASK 52-31-11-820-004). 
R  (c) Install the washer (15) and the nut (16) to the bolt (14). 
R  (d) TORQUE the nut (16) to between 1.0 and 1.35 m.daN (88.49 and 
R  119.46 lbf.in) and safety it with the new cotter pin (17). 
R  (e) Install the bonding jumper (10) with the bolt (12), the washer 
R  (11) and the nut (9) at the actuator attachment fitting (13) 
R  (Ref. TASK 20-28-00-912-004). 
R  (3) If you install bonding jumpers (8) at the cargo door, install them 
R  with the bolts (6) and the washers (7) at the upper door frame of the 
R  fuselage (Ref. TASK 20-28-00-912-004). 
R  NOTE : The bonding jumpers (8) do not have to wear on the door seal____ 
R  (1). 
R  NOTE : If the bonding jumpers (8) are damaged, remove them.____ 
R  You do not have to replace the removed bonding jumpers (8). 
R  (4) Remove the bonding jumpers (8) from the cargo door. 
R  (5) Clean and paint the mating surface of the bonding jumpers (8) at the 
R  cargo door and the fuselage side as required (Ref. TASK 52-32-11-100-
R  001). 
R  (6) Install the bolts (6) and the washers (7) with SEALANTS (Material No. 
R  09-013) into the cargo door and the upper fuselage. 
R  (7) Install the wire harness 4613VB (21) to the door actuator area and 
R  connect the electrical connector (20) to the receptacle (19) 
R  (Ref. TASK 52-32-24-400-001).

 

R  **ON A/C ALL
 Subtask 52-32-18-860-052 
R  C. Preparation of the Inspection
 (1) Pressurize the reservoir of the hydraulics system (Ref. TASK 29-14-00-614-002).
 (2) Pressurize the Yellow hydraulic system (Ref. TASK 29-10-00-863-002).
 (3) Remove the SUPPORT STRUT - CARGO DOORS (98D52307524000) from the cargo door and the fuselage.
 Subtask 52-32-18-865-052 
R  D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1MJ, 3801GX, 3802GX, 3803GX.
 Subtask 52-32-18-210-050 
R  E. Visual Inspection of the Door Seal
 (1) Close the cargo door (Ref. TASK 52-30-00-860-002).
 (2) Examine the door seal from inside of the cargo compartment and make sure that it is compressed around its length.
 5. Close-up________
 Subtask 52-32-18-410-050
 A. Close Access
 (1) Make sure that the cargo door is correctly closed and locked (Ref. TASK 52-30-00-860-002).
 (2) Remove the access platform(s).

 

_____________________
 TASK 52-32-18-300-001
 Repair of the Door Seal
 1. Reason for the Job
__________________
 Self Explanatory
 2. Job Set-up Information
______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific emery cloth
 No specific lint-free cloth
 No specific spatula
 No specific very fine emery cloth
 No specific wooden bonding block

 B. Consumable Materials
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 05-023 USA MIL-I-631 POLYTEREPTHALATE (Ref. 20-31-00) Material No. 05-024 FABRIC (Ref. 20-31-00) R Material No. 08-004 USA MIL-A-25457 ADHESIVE SEALANT (Ref. 20-31-00)
 Material No. 08-026
 ADHESIVE/SEALANT ONE PART,RTV SILICONE RUBBER
 (Ref. 20-31-00)

 Material No. 11-016  USA BOEING BAC 5000 BAC 5504 BAC 5750
 CLEANING SOLVENT (Ref. 20-31-00)

 1EFF : ALL 1 52-32-18Page 801 1 1 Nov 01/99 1 1 1CES 1 C. Referenced Information

 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump 52-30-00-860-002 Close the FWD or AFT Cargo-Compartment Door with the
 Yellow Electric Pump
 52-32-18-000-001 Removal of the Door Seal
 52-32-18-400-001 Installation of the Door Seal
 52-32-18-991-004 Fig. 801
 52-32-18-991-005 Fig. 802
 52-32-18-991-006 Fig. 803
　
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