EngineControls
A. Descriptionand Operation
WARNING: WHEN SERVICING OR INSPECTING VENDOR EQUIPMENT INSTALLED IN PIPER AIRCRAFT, IT IS THE USER'S RESPONSIBILITY TO REFER TO THE APPLICABLE VENDOR PUBLICATION.
This chapter containsprocedures for the installation and adjustmentof the Pratt & Whitney Canada PT6A-61 engine controls. Referto Pratt and Whitney Maintenance Manual,p/n 3034342, Chapter76 for moreinformationon Engine Controls.
1. Both engines are controlled bythree levers:
(a)
The power lever, which controls:
(1.) Enginepower.
(2.) Propeller reversingmechanism.
(b)
The propeller controllever.
(c)
The condition lever, or start control leverusedfor:
(1.) Engine idle
(2.) Fuel shutoff.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Power Lever Control Cable
1. Storage and Handling
CAUTION: BECAUSE THE POWER LEVER CONTROL CABLE CONTAINS CLOSE SPACEDBALL BEARINGS ABOVE AND BELOW A STAINLESS STEEL RIBBONCORE, THEY REQUIRE SPECIAL STORAGE, HANDLING, AND INSTALLATIONPROCEDURESTO PREVENT IRREVERSIBLEDAMAGE.
CAUTION: DO NOT USE PLIERS TO GRIP CONTROL CABLE SURFACES.
CAUTION: USE WRENCH FLATS ON END FITTINGS AND TERMINAL ENDS TO PREVENT TWISTING WHEN TORQUING NUTS OR ATTACHING HARDWARE.
CAUTION: THE BEND RADIUS MUST NEVER BE LESS THAN 7 INCHES. THE PLANE OF BEND CAN BE CHANGED BY ALLOWING THE CONTROL CABLE TO COIL INTO THE NEW PLANE.
CAUTION: NEVER LUBRICATE CONTROL CABLE ASSEMBLIES.
CAUTION: DO NOT TWIST, CRIMP, DENT, APPLY SIDE PRESSURE, OR STAND ON CONTROLCABLE ASSEMBLY.
CAUTION: DO NOT COIL CONTROL CABLE LIKE A ROPE OR FORCE INTO POSITION.
(a) Remove control cable from shipping box very carefully as follows: (Refer to Figure 201.)
(1.) The control cable is shipped in a figure eight configuration. Lift the control cable from the
box. (Refer to Figure 201 Step 1.) (2.) Hold control cable upright with both hands. (Refer to Figure 201 Step 2.) (3.) Remove shipping wire. (Refer to Figure 201 Step 3.) (4.) Start with the nearest end fitting and play out the loops of the control, one at a time.
(Refer to Figure 201 Step 4.) (5.) To straighten the control cable, establish a hump and gently carry it through from one end to the other as shown in Figure 201.
EFFECTIVITY:
040-999 Page1
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Jan 10/90
PIPERAIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Power Lever Control Cable (continued)
1. Storage and Handling (continued)
See View A
Step 1 Step 2 Step3 Step4
6.50+ STROKE
.34 DIA TYP
.44 DIA TYP
.5625-18UNF-3A
WingCableConnection
View A
PowerLeverControlCable Handling
Figure 201
EFFECTIVITY:
040-999 Jan 10/90 76-10-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Power Lever Control Cable (continued)
2. Removal of Power Lever Control Cable
Thereare two power lever control cable sections: one from the cockpit power control lever to wing leading edge between W.S. 10.0 and W.S. 20.0; the second from this point to the engine.
(a)
Remove control pedestal access covers.
(b)
Removeappropriate cockpit floor panel section between forward pressure bulkhead and crew seat tracks.
(c)
Remove leading edge wing-to-fuselage fairing.
CAUTION: DURING REMOVAL, FAILURE TO SUPPORT THE INBOARD LEADING EDGE UNTILWING PNEUMATIC DEICE HOSE CONNECTION IS DISCONNECTED MAY RESULT IN DAMAGE TO THE HOSE OR ITS CONNECTION.
(d)
Support inboard wing leading edge. Remove attachment screws.
(e)
Carefully separate leading edge from wing far enough to gain access to pneumatic deice hose. Disconnect deice hose and remove leading edge.
(f)
Remove wing leading edge fairing on inboard side of nacelle.
(g)
Removenacelle access covers aft of engine firewall.
(h)
Removeupper engine cowling.
(i)
Before disconnecting cable from power lever or engine:
(1.) Set power lever to idle. (Cam follower pin on propeller reverse cam must be in idle
detent.)
(2.) Insert cam rigging pin. Do not disturb engine rigging. See Figure 401.
(j) If necessary, removecable section between wing connection and engine. (Refer to Figure 402).
(1.) Using calibers, measure and record distanceX between seal nut and reverse power stop.
(2.) Back off seal nut.
(3.) Measure distance Y from end of cable housing threads to support bracket.
(4.) Loosen pivot end jam nut. Remove control pivot end and jam nut, without disconnecting
rod end. (5.) Remove special bolt, reverse power stop, and jam nut as an assembly. (6.) Remove seal nut. (7.) Remove jam nut on front side of support bracket. (8.) Pull cable through bracket. Remove rear bracket jam nut. (9.) Disconnect cable connector in wing leading edge. (10.)Removecableclampsalong wing leading edge. (11.)Note routing and attachment points. Remove cable section. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：夏延飞机维护手册 Cheyenne IIIA PA-42-720 AMM 2(145)
