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AIRCRAFT MAINTENANCE MANUAL
of the cylinders.
Master Cylinder Installation
To install the brake master cylinders,
reverse the removal procedures and fill
and bleed brakes as outlined in this
section.
BRAKE BLEEDING
Ref. figure 6-2 and Section 3
To bleed the brakes proceed as follows:
A. Place parking brake control in OFF
position.
B. Prepare a piece of 5/32" clear plastic
(preferred) or rubber (any color) tubing
at least 12 inches long.
bleeder screw dust cap.
end of hose onto bleeder screw.
C. Place free end of hose in a clean glass
receptacle
containing
hydraulic fluid to cover end of hose.
End
of
bleeder
submerged at all times to properly
check for air bubbles and prevent
entry of air into hydraulic system.
D. Apply
brake
pressure
bleeder screw approximately 1/3 to ½
turn, close bleeder screw before
releasing brake pressure to avoid
reentry of air into brake system.
Repeat this procedure until system is
free of air.
E. Tighten bleeder screw, remove rubber
hose and replace dust cap.
F. Repeat
bleeding
opposite brake.
*NOTE*
Keep master cylinder reservoir
full of MIL-H-5606 hydraulic
fluid throughout the bleeding
operation.
TAIL LANDING GEAR
Ref. Figure 6-6
TAIL GEAR REMOVAL
A. Remove fuselage skins as required.
B. Using a suitable Jack.
6-12
Page
THRUSH AIRCRAFT, INC – MODEL S2R-G10
Remove
Install one
enough
hose
must
be
and
open
procedure
for
Jack and
secure tail of aircraft, using jack point.
C. Remove cotter pin and axle castellated
nut, and spacer P/N CA84106-05-2,
and
then
remove
assembly.
D. Disconnect flex control lock cable at
pivot arm and cable hold down clamp.
E. Disconnect centering springs from tail
wheel centering arm assembly by
removing attach bolt.
* NOTE *
Do not alter lock cable or
elevator travel stops. Alteration
of tail gear lock cable or
elevator travel stops will require
re-rigging of tail wheel locking
system.
F. If disassembly of tail gear wheel/tire
assembly is necessary, follow steps
given on page 6-16.
G. Remove main leaf spring assembly by
removing NAS6207-38D bolt (Replace
annually) holding spring to trunnion
assembly.
Remove two-(2) each
NAS6606-54 bolts that holds the lower
spring support block to upper support
block.
Note how many 90056-26
washers were located on each side
between support blocks.
H. Remove
trunnion
fuselage by removing trunnion attach
shaft.
Cleaning, inspection and repair of tail
landing gear
A. Clean all parts with a suitable type
cleaning solvent.
B. Remove, clean, and inspect leaf spring
forward attach P/N NAS6207-38D bolt
every 100 hours.
lubricate bolt and leaf spring hole with
Snap-on™ General Purpose Anti-
seize or equivalent or MIL-G-81322
(Aeroshell 22) grease.
specifications
I/A/W
(figure 2-7).
Replace MS24665-300
cotter pin each inspection.
C. Inspect all bolts holes for elongation.
the
tire/wheel
assembly
from
Upon reassembly
Torque to
Torque
chart
Effective: 03/26/2010
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