NOTE: For rigging, ensure control tube measures 120.5 inches from center of end fitting bearing to center of rod end bearing.
9. Riggingthe Elevator ControlSystem(Figure501)
NOTE: Mostadjustmentsto system are made with cable tumbuckles. Pushrodsand tube are a specified length from rod end to rod end bearing center, and can only be used for minor small adjustments. If whole system must be rigged,follow instructions as given. Otherwise,follow instructions for specific areasonly, using other instructionsas a check.
(a)Togain access to existing systems, proceed as follows:
(1.) To gain access to forward control sectors,removepilot seat and surrounding access panels.
(2.) To gain access to aft elevator controlsconsistingof hardware controllingelevatorfrom aft sector,removelast large accesspanelson either side of fuselage, tail cone, and bullet assembly.
(b)
Before rigging any part of elevator control system, set elevator in neutral position (± 1 °) and install rigging tool (P/N 72046) and rigging pins in aft fuselage sector, below fin and sector, under pilot seat (Figure 502). Install rigging too on left hand stabilizer.
(c)
Rig control cables to specifications in Figure 501, or following step, if autopilot is installed. Ensure both rigging pins are in place without carrying a load and clamp sectors or block cables.
EFFECTIVITY: 040-999
Jan 10/90 27-30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Elevatorand Tab (continued)
9. Riggingthe Elevator ControlSystem(continued)
(d) Since autopilot bridles affect primarycable tension, do not readjustprimary elevator cable tensions.Proceedas follows:
(1.) Set tension to 55 ± 5 pounds. Hookupbridle. (2.) Tensionautopilotbridle cables using manufacturerservicemanuals.Primaryelevator cable tension increases downstreamofbridle and decreasesupstream.(3.) Record tension upstreamand downstream of autopilot bridlecable hookup for later verification. (4.) During verification,ensuretensionupstreamand downstream of autopilot bridlecable hookupsare within ± 5 pounds of previously recordedvalues.
(e)Adjustpushrodin fin to bring elevatorto neutral 1 °.
(f) Removerigging pins from sectorsandadjust stops (Figure 503) at elevator to obtain values specifiedin Figure 501.
NOTE:All travels are taken fromtailing edge of control surface.
(g)Adjustpushrod going from front sector to control columnfor 1.50 ± 0.12 inch clearance betweencolumnand instrument panel when column is full forward.
(h)
Checksystem travel for smooth operation.
(i)
Adjust trim wheel in cockpit for neutral with elevator tabin neutral.
(j)
With elevator in neutral, rotatetrim control wheel in cockpit to obtain up and down tab travels andminimumtrimcable tension specified in Figure 501.
(k)
Removeriggingtool. Install accesscovers.
10. ElevatorControlSystemFrictionCheck
CAUTION: DO NOT EXCEED60 POUNDS DURINGTHE FOLLOWING PROCESS.IF SCALE READINGAPPROACHESTHIS VALUE, STOP AND CHECK SYSTEMFOR BINDING.ENSUREALL RIGGING PINS ARE REMOVED.
(a)
Attachspringscale to inboardtrailingedge of elevator (Figure601).
(b)
With spring scale attached, positionelevatortrailingedge 2 inches down from neutral position.
NOTE: To obtain effective readingon spring scale, rotate elevator with firm and steady movement,recordingforcereadingas elevator passes thru neutral position. Do not stop rotation while taking reading orexceed 60 pounds of force for any measurement.
(c)
Raise elevator with attached scale from its down position to 2 inches above neutral and record force required to raise elevator.
(d)
Lower elevator with attached scale from 2 inch up position to 2 inch down position and record force.
(e)
Repeatsteps (c) and (d) until averageforceis attained.
(f)
Subtracttwo average forcesto verify total friction in system. Total friction in elevator control systemmust not exceed 10 pounds without autopilot systeminstalledor 11 pounds with autopilotsysteminstalled.
EFFECTIVITY:
27-30-00 27-30-00 PAGE
' Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Elevatorand Tab (continued)
Elevator
Elevator System FrictionCheck Figure 601
11. Evevator Trim System
The elevator trim system consists of an adjustable trim tab mounted on the left elevator, a trim tab actuatormountedtothe stabilizer rear spar, a control wheeland drum mountedin the cockpit control pedestal, and accompanying
trimcontrol cable and pulleys.
NOTE: Kit No. 764411L is available for modification of the trim actuator to reduce friction and for installationof an environmental enclosure around trim actuator preventingwaterentry. 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 1(112)
