pinholes align.
(4.) Insert rigging pins and unclamp cables.

(d)
Install rigging pins in bottom of pilot control column. Adjust pushrod to sector if necessary. Adjust length of vertical pushrod in column as follows (refer to Figure 501).

EFFECTIVITY:

PAGE 12 040-999 Jan 10/9027-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

A. AileronandTab (continued)
18. Riggingof AileronTrim
(a) Toadjustailerontrim, ensurethefollowingisaccomplishedeitherduringinstallationor as a preadjustmentcheck: (1.) Trimcablesareevenlywrapped(centered)on drumsboth belowcontrolpedestaland in
wing and bothcabletumbucklesarelocatedapproximatelyat WingStation90. (2.) Trimdrum in wing is centeredbetweenstopsof trim screw. (3.) The cabletensionis setaccordingto specificationsin Figure502.
(b)
Removeaccessplateson undersideof rightwing at Stations171.0and176.0.

(c)
Withtrim screwheldfromrotating,turntrim drumuntil0.560 inchexistsbetweenforwardscrew stopand drumhousingmeasuredalongscrew. (This is neutralpositionof screw.)

(d)
Withrightwing riggingtool(P/N72159-2)installedand aileronsin neutralposition,rotatetrim wheelin cockpitto specificationsinfigure 27-6as indicatedon riggingtool. Ensurecable tensionmeetsspecificationsin Figure502.

(e)
Ensurerotationof wheelfrom stopto stopis smoothandfree with nobindingorchafing.

(f)
Usingtool (L73035)and a dialtypetorquewrench,checktrim systemfrictionat pedestalby removingtrim wheelandattachingtoolandtorquewrenchto splinedshaft. Frictionmustnot exceed9 inch-poundswhentestedin eitherdirectionat anypointbetweenlimits.

AdjustPush-PullRod 
insidepilotscontrol 
Cover  CopilotControl  columnto positionrod end(andbellcrank)at W.L.-18.00. 
Bellcrank 
TurnbuckleC 
Access  VIE 
Cover 

ControlColumn (Right)
.1.50+ .12
FWD

InstrumentPanel
ControlColumnTravelandLimits
Figure 501

EFFECTIVITY:
040-999
27-10-00 10/90
Jan
10/90

A. Aileronand Tab (continued)
Aileronand Aileron Trim Tab
°
A-18.5 +1 "-0
°
B-18.5 ° +1 -0
C -290 +1 -0"
°

D -15 +1  -0
Cable Tension
Aileron-55 lbs.± 5 lbs.
AileronTrim Tab -14 lbs. ± 2 lbs.

Chord Line Level
PIPER AIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL

CAUTION: MAKESURETO SECURELY CLAMPBELLCRANKS
AT QUADRANT BEFORETIGHTENING
CABLES.
TrimTab travel with
Aileron in neutral position
2° below chord line

Aileron Control Travels and Cable Tension
Figure 502

b

Stop Bolt
-RiggingHole Bellcrank

Stop
Stop Bolt

Locationof Bellcrank Rigging Hole Figure 503
EFFECTIVITY: 040-999

PAGE14 27-10-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

A. Aileron and Tab (continued)
TOOL P/N 72025

Installation of Aileron Rigging Tool Figure 504
19.
AileronControL System FrictionCheck (Figure 601)

Using a spring scaleand pulling from point on aileron shown in Figure 503, take readingsin both up and down directionsas aileron passesthroughneutral position. Record readings,addthem, and ensure total does not exceed 9 pounds without autopilot bridle cables connected,or 10 poundswith autopilot bridlecables connected.

20.
Aileron Trim Tab Free Play

(a)
Positiontrim tab in neutral position.Trailing edge of tab in neutral positionmust be in line with trailing edge of main surface.

(b)
Total free play must not exceed 0.04 inch measuredfrom one extreme to other between outboardend of tab trailing edge and trailing edge of main surface.

(c)
If excessiveplay exists, inspect aileron trim screw and hinge assemblies to determine location of excessive play. Repairor replace wornparts as required.

EFFECTIVITY:

040-999
27-10-00Feb1/98

PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

A. Aileron and Tab (continued)
Flap

Aileron
.50
Measure from here
.50

Aileron Friction Check Figure 601
EFFECTIVITY:
040-999

PAGE
Jan 10/9016 27-10-00
PIPER AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL

A. Rudder and Tab
1. Removal of Forward Rudder Cables (Figure401)
(a)
Removepilot seat and floor panelsunder and in frontof pressure bulkheadat Fuselage Station (F.S.) 57.0.

(b)
Ruddercablepulleysfor forward systemarelocatedat F.S. 77.2 (in front of controlcolumn), 161.35,212.96,248.96,and 281.5. Remove left seats and floorboards in these areas, only wherenecessary.Removeleftsidefloor panels aroundF.S. 303.5 to makeaccessto rudder cableturnbuckles.
　
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