夏延飞机维护手册 Cheyenne IIIA PA-42-720 AMM 2(126)

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12.Install new rivets in drag angle on top side of wing.
13.Reinstallforward fillet bulkheadswith new rivets.
14.Draw engine control cables into place.
15.At wing leading edge and butt, connect engineinstrument,fuel,and hydraulic lines. Secure lines and cables with support blocks and clamps.
16.Connectelectrical wire connectors.
17.Throughwing fairing access openingsat underside of fuselage, connectfuel, hydraulic lines, and fuel valve controlcables.
18.Draw flexible drive shaft from flap transmission into fuselage and rig accordingto 27-50-00.
19.Connectbleed air pressurization and deicer lines.
20.Drawaileron control cable and balance cable into wing; connect at aileron bellcrank. Install cable guard pin at pulley near bellcrank and at wing butt. Check rigging and adjustment. (Refer to 27-10-00.) Install cable guard pin at pulley near bellcrank and at wing butt. Check rigging and adjustment(refer to 27-10-00),cable tension, and safety tumbuckles.
21.The following pertainsto installation of the right wing only:
(a)Connecthydrauliclines at station 140.
(b) Draw aileron trim cables into wing, connect tumbuckles,and unblock cables. Install cable guard pin at butt end of wing. Check rigging, adjustment, cable tension, (refer to 27-10-00) and safety turnbuckles.
22.Install engine. (Refer to 71-00-00)
23.Check hydraulic fluid lever (refer to 29-10-00). With airplaneon jacks, operate gear through several retraction and extension cycles to check for hydraulic fluid leaks.
24.Check brake fluid level and bleed brakes. (Refer to 32-40-00.)
25.Check fuel system for leaks and proper flow.
26.At top of wing, screw fillet fairing to wing and fuselage. Apply a bead of sealant (Minnesota Mining and Manufacturing along edge of wing root fillet at fuselage and
Sealant EC750 or equivalent)
wing skins. Start at leading edge and extend aft over top of trailing edge.

27.At fairing between undersideof fuselage and wing, turn three adjustingscrewsto draw fairing against underside of wing butt. Ensure a rub strip exists betweenwing and fairing.
28.Install floor panels.
29. Install tip tanks.
EFFECTIVITY: 040-999

Jan10/9057-10-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

401

Wing Installation
Figure401 (Sheet1 of 3)

EFFECTIVITY:
040-999
57-10-00 PAGE 3

10/90
57-10-00 Jan

PIPER AIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

BOLT -NAS464P7LA10
WASHER -AN960-716 (2 REQ.)
(UNDER HEAD & NUT)
NUT -MS20364-720C
(1 REQ. LEFT & 1 REQ. RIGHT)

BOLT AN4-20A WASHER AN960-416 WASHER AN960-416L NUT MS20365-428C 1 REQ. LEFT 2 REQ. RIGHT
LB

BOLT AN3-6A 
WASHER AN960-10 
NUT MS20365-1032C 
2 REQ. LEFT 
2 REQ. RIGHT 
BOLT -AN3-6A 
WASHER AN960-10 
WASHER AN960-10L 
NUT MS20365-1032C 
2 REQ. LEFT 
2 REQ. RIGHT  SKETCH B  BOLT AN3-5A WASHER AN960-10 
NUT MS20365-1032C 
2 REQ. LEFT 
2 REQ. RIGHT 
Wing Installation 
Figure 401 (Sheet 2 of 3) 
EFFECTIVITY: 
040-999 

Jan 10/9057-10-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

NOTE: Refer to Installation of Wing StepB.7. for torquevalue.
SKETCH C

BOLT-WINGATTACHMENT
LOWER-P/N 59824
BOLT -AN179-16A

WASHER-AN960-916
(2 REQ.) (UNDER HEAD & NUT)
NUT -MS20364-918C
(1 REQ. LEFT & 1 REQ. RIGHT)

TORQUE 480-600 IN.-LB
SKETCHD
Wing Installation
Figure 401 (Sheet 3 of 3)

EFFECTIVITY:
040-999
PAGE
57-10-00
PIPER AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL

A. Ailerons
1. Aileron Balancing Procedure(Figure 501)
(a)
Removeaileronaccording to instructions in 27-10-00.

(b)
Support aileron upside down on knife edges using hinge bolts as fulcrum points.

(c)
Establishhorizontal reference mark which aligns with trailing edge of aileron when held in horizontalposition. (Chordline level.)

(d)
Ensure surface rotates freely with no binding at knife edges.

(e)
Verify unbalance is between limits -17+0 -2 inch-pounds, leading edge heavy.

(f)
If aileron is trailing edge heavy with master test weight installed, determine and correct reason for unbalance.

(g)
If aileron is leading edge heavy, remove material from outboard balance weight to correct imbalance.

(h)
Installbalanced aileron on aircraft.

NOTE: Aileron placed upside down in jig.
　
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