MM40-107/30-107 COMPONENT MAINTENANCE MANUAL WITH IPL
FOR MAIN WHEEL ASSEMBLY PART NO. 40-107 SERIES AND
MAIN BRAKE ASSEMBLY PART NO. 30-107 SERIES
Page 14
Feb 01/02
6.5
Install retract mechanisms.
6.5.1
Prior to installation, the position of the friction sleeves (10-145, 10-150) on
retract stud assembly (10-135) or friction ring and collar spring retainer
(10-175, 10-180) on retract stud assembly (10-165) must be reset in
accordance with the following procedures.
NOTE:
Laboratory tests show that this reset procedure may be accomplished 8 times
without degradation of the components function. It is recommended that after
8 reset procedures, that the entire retract mechanism be discarded and
replaced. If there is suspicion that the unit is worn prior to accomplishing 8
reset procedures, the retract stud assembly (10-135 or 10-165) must be
checked in accordance with the following procedure:
6.5.1.1
Use a spring tester. Set the friction sleeve on a suitable
fixture having a hole through which the stud (10-140) or
pin (10-170) can pass and apply a load of 215 lbs. to
either end of the stud or pin. If the stud slips, prior to
withstanding a load of 215 lbs.,
r e p l a c e m e n t i f n e c e s s a r y .
6.5.2
Resetting and installing retracts for Brake Assemblies equipped
with retract stud assembly (10-135): (See Figure 5)
6.5.2.1
Using a suitable bench press, reset the friction sleeves
(10-145, 10-150) position on the retract stud
(10-140) to attain a dimension of 0.690 inch.
6.5.2.2
Verify bolt (10-155) torque of 50 to 60 in-lb.
NOTE:
Torquing may require a slight amount of thumb pressure be applied
to the piston face to prohibit piston rotation.
6.5.2.3
After setting the retract mechanism, screw one each
into the back of each piston and tighten with suitable 3/8
inch [0.375] wrench or socket. Final torque stud
assembly (10-135) 30 to 40 in-lb.
6.5.2.4
Install brakes on aircraft. Apply and release parking
brake. Push cylinder inboard to its full extent. Check
retract stud torque to verify adjuster pin has fully
engaged the piston. Inboard force on cylinder may be
required to prohibit piston rotation.
6.5.2.5
Safety wire as required.
6.5.2.6
Return aircraft to service.