(2)
 Do an inspection of the component interface and/or the adjacent area.

 (3)
 Make sure that the parts retained from the removed component are clean and in the correct condition.

 (4)
 Lubricate the new O-rings (1), (3), (5) and (6), and the back-up rings (2) and (4), with HYDRAULIC FLUIDS (Material No. 02-003).

 (5)
 Remove the blanking plugs from the solenoid valve (7) and the interface of the wing tip brake.

 Subtask 27-81-51-420-051
 B. Installation of the Solenoid Valve to the Slat Wing-Tip Brake (WTB)
 (1)
 Install the new O-ring (5) and the new O-ring (6) on the solenoid valve (7).

 (2)
 Install the new back-up ring (4) and the new O-ring (3) on the solenoid valve (7). Make sure that the curve on the face of the back-up ring (4) is against the O-ring (3).

 (3)
 Install the new back-up ring (2) and the new O-ring (1) on the solenoid valve (7). Make sure that the curve on the face of the back-up ring (2) is against the O-ring (1).

 1EFF : ALL 1 27-81-51Page 425 1 1 May 01/98R 1 1 1CES 1

 (4)
 Install the solenoid valve (7) on the wing tip brake. NOTE : Solenoid valves 903A0000-01 removed from the PCU valve block

____ (Ref. 27-54-53 and 27-84-53) must not be installed on the wing-tip brake.

 (5)
 Install the screws (9).

 (6)
 TORQUE the screws (9) to between 0.25 and 0.27 m.daN (22.12 and 23.89 lbf.in).

 Subtask 27-81-51-860-056
 C. Aircraft Maintenance Configuration
 (1)
 Fill the Blue and the Green hydraulic reservoirs (Ref. TASK 12-12-29-611-001) or (Ref. TASK 12-12-29-611-002).

 (2)
 Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER from the flap/slat control lever on panel 114VU.

 Subtask 27-81-51-865-055
 D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 9CV, 11CV.
 Subtask 27-81-51-420-056
 E. Install the Safety Collar
 (1) Install the safety collar on the circuit breakers 9CV and 11CV. Subtask 27-81-51-863-051
 F. Pressurize the Hydraulic Systems WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES
_______ ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
 WARNING : MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE
_______ ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM.
 (1) Pressurize the Blue and the Green hydraulic systems (Ref. TASK 29-10-00-863-003) and (Ref. TASK 29-10-00-863-001).

 Subtask 27-81-51-790-052
 G. Test
 (1)
 Examine the solenoid valve (7) and the interface of the solenoid valve (7) and the wing tip brake, for leaks.

 (2)
 Do an operational test of the slats wing-tip brake (Ref. TASK 27-81-00-710-001).

 (3)
 Do the leak check again.

 5. Close-up
________
 (Ref. Fig. 402/TASK 27-81-51-991-002) Subtask 27-81-51-410-051
 A. Close Access
 (1)
 Make sure that the work area is clean and clear of tool(s) and other items.

 (2)
 Install the applicable access panel:

 -for the solenoid valve (7) on 35CV install 522SB
 -for the solenoid valve (7) on 36CV install 622SB. Subtask 27-81-51-942-051
 B. Removal of Equipment
 (1)
 Remove the safety barriers.

 (2)
 Remove the warning notice(s).

 (3)
 Remove the access platform(s).

 (4)
 Remove the ground support and maintenance equipment, the special and standard tools and all other items.

 SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION - DESCRIPTION AND OPERATION
____________________________________________________________________________
 1. General
_______
 A hydromechanical Power Control Unit (PCU) in the aircraft fuselage supplies mechanical power to the slat transmission system. The PCU has two hydraulic motors. Each motor has a Pressure-Off Brake (POB) and a valve block, which is electrically controlled.
 Torque shafts and gearboxes in the fuselage and the wings transmit the
 mechanical power from the slat PCU to the actuators, which move the slats.
 There are two actuators for each slat. The actuators are installed on the
 aircraft structure.
 Torque limiters in the transmission system and in the actuators make sure
 that the load applied to the structure is not too high.
 Wing tip brakes give asymmetry and runaway protection (Ref. 27-81-00).
 2. Component Location
　
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