(b)
Removerubberbleederfitting cap locatedon landinggearbrakeunit housing.

(c)
Slidepressurehosefrompressurepot over bleedervalve.

(d)
Pressurizethepressurepotto 48 ± 2 psi. Open the bleeder valve.

NOTE: By watching fluidflowinginto the reservoir,determinewhetheranyair has enteredthe system.If air bubbles are evident, continuefillingthe system untilall air is out of the systemanda steady flow offluid is obtained.
(e)Allow at least 2 gallons to flow.
(f)
Simultaneouslydepresspilot'sbrakepedalsapproximately1 inch in successive motions. Returnto neutral forcing any bubbles in the system downstream. Repeatwithcopilot'sbrake pedalsuntilnoair is expelledatreservoir.

(g)
Closebleedportsand depressurize system.

EFFECTIVITY: 040-999 Jan 10/9032-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

B. Brake Assemblies (continued)
Catch Tank (5-Gallon)
Airplane Reservoir
Copilot's Brake
Master Cylinder

Left Right
Pilot'sBrake
MasterCylinder

Bleed Port Dual Parking Brake Valve Bleed Port
(Open)
t Regulator
Brake Bleeder (FillWith MIL-H-5606A) Shop
Air
BleedingBrakes
Figure 601

EFFECTIVITY: 040-999
32-40-00 PAGE23
Jan 10/90

PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

B. Brake Assemblies (continued)
20. BleedingProcedure(continued)
(h)Checkbrakesforproperpedalpressureand operation. NOTE:Ifproperpedalpressureis not attained,repeatprocedure.
(i)
Repeatprocedureonthe other gear. (j). Service brake reservoir (referto 12-10-00).

C.
Tires

Referto Tires, 12-10-00for air replenishingprocedures
Forbalancing tires, usetire balancer (refer to 32-40-00 Figure 1).

9.:
3
2

5
Thefollowinglistof materials areused in making the balancer:
Item No.  Item  Dimensions  MaterialSpecifications  CQuantity 
1 2 3 4  Base Tee Sides Axle  12x 11 2.5 x 2 x 11 14 x 11 0.125 x 10.25  0.1902024T3 clad aluminumalloy 0.190 2024 T4 extrudedaluminumalloy 0.1252024clad T3 aluminumalloy 4130steel, normalized  1 ea. 2 ea. 2 ea. 1 ea. 
5  Nuts  AN365-624  2 ea. 
6 7 8  Spacer Spacer Bushing Bushing Pipe  0.50 x 2.25 0.50x 1.25 1.480 x 1.625x 1.00 2.240 x 1.37x 1.00 0.125x 903  5052-0aluminumtubing 5052-0aluminumtubing Richlight,phenolicor aluminum Richlight,phenolicor aluminum black steel pipe  2 ea. 2 ea. 2 ea. 2 ea. 1 ea. 

Bearings Savetwo of each size worn wheelbearingsfrom previousinspections. 2 ea.
Tire Balancer
Figure 1

EFFECTIVITY: 040-999

PAGE 24 32-40-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

A. Steering
1. FaultIsolation-Steering
NOTE: Placeairplaneon jacksbeforeattemptingfaultisolationof landinggearsystem (referto 7-10-00). CHART 1 FAULTISOLATION(STEERING)
Fault Cause  Remedy
Nosegearfailsto steer Oleocylinderbindingin Lubricatestrut housing. properly. strut housing.
Onebrakedragging.  Determinecauseandcorrect. (referto 32-40-00)
Steeringarm rollersheared Replacedefectiveroller. at top of strut.
Nosegearshimmies Internalwearin shimmy Replaceshimmydampener.
duringfasttaxi,takeoff dampener.
and landing.

Shimmydampeneror Replacenecessarypartsand bracketlooseat mounting. bolts. (referto 32-20-00)
Tireout of balance.  Checkbalanceand replace tire if necessary.
Wornor loosewheelbearings.  Replaceand/ or adjustwheel bearings. (referto 32-40-00)
Worntorquelinkboltsand/ Replaceboltsand/ orbushings. or bushings. (referto 32-20-00)
EFFECTIVITY:

32-50-00 Jan
10/90

PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL

A. Steering (continued)
2. Removalof Nose Gear Steering Assembly (refer to 32-50-00 Figure 401)
(a)Remove pilot's seat and floor panels in front of and behind control column.
(b)Removeaccesspanel on left side of the aircraft's nose.
(c) Removeequipmenton the bulkheads and lower shelf (floor) required to gain access to the steering rod coming through the bulkhead.
NOTE: Do not rotate rod end bearings unless as an adjustmentto the nose gear steering.
(d)Removerequired shelf and floor panels.
(e)Use the following instructionsforremovalof the torque tube attached to the rudder control sector:
(1.) Remove forwardworm screw clamp holding pressureseal bellow to tube. (2.) Unbolt rod end bearings from the sector inside the aircraft and control arm inside access area. (3.) Carefully draw tube forward and up through bellows. If rod end bearing does not fit through bellows, removethe rod end; do not force it.
　
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