(2)
 On the overhead panel 23VU, make sure that the FLT CTL/SEC1 pushbutton switch is pushed (the FAULT and OFF legends are off).

 (3)
 On the overhead panel 24VU, make sure that the FLT CTL/SEC2 and FLT CTL/SEC3 pushbutton switches are pushed (the FAULT and OFF legends are off).

 (4)
 On the center pedestal, make sure that the SPEED BRAKE lever is in the RET position.

 (5)
 Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

 (6)
 On the center pedestal, on the ECAM control panel, push the F/CTL pushbutton switch (on the lower ECAM display unit, the F/CTL page comes into view).

 (7)
 Extend the flaps (lever in the FULL position ) (Ref. TASK 27-50-00-866-008).

 Subtask 27-64-00-865-053
 B. Make sure that this(these) circuit breaker(s) is(are) closed:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 121VU FLIGHT CONTROLS/SEC3/SPLY 21CE3 Q19 121VU FLIGHT CONTROLS/SEC2/SPLY 21CE2 Q18
 Subtask 27-64-00-010-055
 C. Get Access
 (1) Put the access platform in position:
 (a) At zone 580 for the spoilers 1,2,3,4,5 left side.
 (b) At zone 680 for the spoilers 1,2,3,4,5 right side. Subtask 27-64-00-480-051
 D. Installation of the Tools
 (1)
 Install the LOCKING TOOL - FLAP/SLAT CONTROL LEVER (98D27803000000) on the flap and slat control lever.

 (2)
 Install the PIN-SIDE STICK LOCKING (98D27903500000) on each side stick controller.

 (3)
 Put the warning notice(s) on the CAPT and F/O side stick and on the SPEED BRAKE control lever to tell persons not to touch them.

 (4) Install the LOAD APPLICATION TOOL - SPOILER (98D27603001000) at the trailing edge of the spoiler, at the level of the servocontrol.
 (5) Install the pointer of the LOAD APPLICATION TOOL - SPOILER (98D27603001000) on the trailing edge of the spoiler.
 (6) Install a corner plate on the adjacent structure.
 (7) Install a graduated scale on the corner plate.
 Subtask 27-64-00-863-051
 E. Pressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-863-001) (Ref. TASK 29-24-00-863-001) (Ref. TASK 29-10-00-863-003).
 4. Procedure_________
 Subtask 27-64-00-220-051
 A. Check of the Spoilers Servo-Controls and Hinge Bearings for Excessive Play (Ref. Fig. 601/TASK 27-64-00-991-005)
 NOTE : The check is only given for one surface.____ Do the same operations for the other surfaces. 
R R R R R  (1) Connect the SPRING SCALE ASSY (97A27902016000) or GAGE ASSY - PUSH-PULL (97A27003000000) or GAGE ASSY - PUSH-PULL (97A27003000001) to the LOAD APPLICATION TOOL - SPOILER (98D27603001000) and apply a force of 30 lbf (13.3446 daN) maximum in the up direction on the trailing edge.
 (2) Write the position of the pointer on the graduated scale.
 (3) Apply a force of 30 lbf (13.3446 daN) maximum in the down direction on the trailing edge.
 (4) Write the position of the pointer on the graduated scale.
 (5) Make sure that the play between the two limit positions is not more than 1.2 mm (0.0472 in.).
 (6) If the measured play is more than the maximum permitted value, repair the bearings which attach the control surface to the structure and the servocontrol bearings (Ref. TASK 27-64-41-200-001) (Ref. TASK 27-64-42-200-001) (Ref. TASK 27-64-43-200-001) (Ref. TASK 27-64-44-200-001) (Ref. TASK 27-64-45-200-001).

 Location of the Tools
 Figure 601/TASK 27-64-00-991-005
 1EFF :  ALL  1  27-64-00 Page 605 
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 5. Close-up________
 Subtask 27-64-00-080-050
 A. Removal of the Tools 
R R R R  (1) Remove the SPRING SCALE ASSY (97A27902016000) or GAGE ASSY - PUSH-PULL (97A27003000000) or GAGE ASSY - PUSH-PULL (97A27003000001) , the graduated scale, the corner plate, the pointer and the LOAD APPLICATION TOOL - SPOILER (98D27603001000).
 (2) Remove the PIN-SIDE STICK LOCKING (98D27903500000) from each side stick and the LOCKING TOOL - FLAP/SLAT CONTROL LEVER (98D27803000000) from the flap and slat control lever.
 (3) Remove the warning notice(s).
 Subtask 27-64-00-860-055
 B. Put the aircraft back to its initial configuration.
 (1) Retract the FLAPS (lever in the 0 position) (Ref. TASK 27-50-00-866-009).
 (2) Depressurise the aircraft hydraulic systems (Ref. TASK 29-23-00-864-001) (Ref. TASK 29-24-00-864-001) (Ref. TASK 29-10-00-864-003).
　
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