(4)
 Let the air outlet flap move to the fully open position and make sure that:

 (a)
 The air outlet flap is not cracked or damaged.

 (b)
 When you move the air outlet flap it does not cause damage to the aircraft structure or to itself.

R 1EFF : 001-003, 051-054, 1 21-61-52Page 603 1 1 May 01/05 1 1 1CES 1

 Air Outlet Flap - Component Location
 Figure 601/TASK 21-61-52-991-012

R 1EFF : 001-003, 051-054, 1 21-61-52Page 604 1 1 May 01/05 1 1 1CES 1

 (5)
 If the air outlet flap is cracked or damaged you must:

 (a) Replace the air outlet flap (Ref. TASK 21-61-52-000-002) and (Ref. TASK 21-61-52-400-002).

 (6)
 Put the lever (6) in position on the actuator (3) and install the bush (5), the bolt (4) and the nut (7).

 (7)
 Remove the blanking caps and connect the electrical connector (2).

 5. Close-up
________
 Subtask 21-61-52-865-064

 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 9HH 1HH, 2HH, 3HH, 4HH. FOR 29HH 21HH, 22HH, 23HH, 24HH.
 Subtask 21-61-52-410-057
 B. Close Access
 (1) Make sure that the work area is clean and clear of tool(s) and other items.
 (2) Close the access panel/s (Ref. TASK 53-35-13-400-002). R (a) FOR 9HH
 -191KB R (b) FOR 29HH
 -192KB
 (3) Remove the warning notice(s).
 Subtask 21-61-52-862-053

 C. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
R 1EFF : 001-003, 051-054, 1 21-61-52Page 605 1 1 May 01/05 1 1 1CES 1

 TASK 21-61-52-200-002 Ram-Air Outlet Flap - In-Service Wear Limits
 1.
 Reason for the Job

__________________
 Self Explanatory

 2.
 Job Set-up Information

______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
21-61-00-300-001 Attachment and Linkage Components -
Repair/Replacement 21-61-52-000-001 Removal of the Air-Outlet Flap Actuator 9HH (29HH) 21-61-52-000-003 Removal of the Ram-Air Outlet 21-61-52-400-003 Installation of the Ram-Air Outlet CMM 215312 21-61-52-991-009 Fig. 602
 3. Job Set-up
__________ Subtask 21-61-52-860-056
 A. Aircraft Maintenance Configuration
 (1) Make sure that the applicable components are disassembled to do the inspection procedure.
 4. Procedure
_________ (Ref. Fig. 602/TASK 21-61-52-991-009) Subtask 21-61-52-210-052
 A. Visual Inspection of the Spherical Bearings NOTE : The tolerance for radial play in a spherical bearing is 0.05 mm
____ (0.0019 in.). The tolerance for axial play in a spherical bearing is 0.2 mm (0.0078 in.).
R 1EFF : 001-003, 051-054, 1 21-61-52Page 606 1 1 May 01/05 1 1 1CES 1 (1) Use an applicable measurement method and:

 (a)
 Do a check for radial and axial play at the spherical bearing (1):

 -if you find radial and/or axial play more than the tolerances then you must replace the eye-end in the air-outlet flap actuator (Ref. CMM 215312).

 (b)
 Do a check for radial and axial play at the spherical bearings

 (6) and (12):
 -if you find radial and/or axial play more than the tolerances then you must replace the ram air outlet (Ref. TASK 21-61-52-000-003) and (Ref. TASK 21-61-52-400-003).
 Subtask 21-61-52-220-052
 B. In-Service Wear Limits
 (1) Use applicable measurement equipment and measure the outside diameter (OD) of the bolt (7) and the inside diameter (ID) of the bushings (2).
 NOTE : If any of the components are 'out of limits' then you must
____
 replace them.

 -for item (2) (Ref. CMM 215312).
 -------------------------------------------------------------------------------| FIG. | ORIGINAL MANUFACTURING LIMITS | IN-SERVICE WEAR LIMITS | | DETAIL |---------------------------------------|----------------------------| | AND | DIMENSION | ASSEMBLY CLEARANCE| DIMENSION LIMITS | MAX. | | ITEM | MM (IN.) | MM (IN.) | MM (IN.) | ALLOW. | | NO. |-------------------|-------------------|---------|---------| CLEAR. | | | MIN. | MAX. | MIN. | MAX. | MIN. | MAX. |MM (IN.)| |--------|---------|---------|---------|---------|---------|---------|--------| | AA | 6.325 | 6.335 | | | 6.318 | | | | OD 7 |(0.2490) |(0.2494) | | |(0.2487) | | | | | | | 0.023 | 0.055 | | | 0.069 | | | | | (0.0009)| (0.0021)| | |(0.0027)| | AA | 6.358 | 6.380 | | | | 6.387 | | | ID 2 |(0.2503) |(0.2511) | | | |(0.2514) | | -------------------------------------------------------------------------------
　
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