51-00-00
0 Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. StructuralRepairs (continued) 22
21
1
17
SKIN THICKNESS
NUMBER MATERIAL THICKNESS NUMBER MATERIAL THICKNESS NUMBER MATERIAL THICKNESS
1 Fiberglass 9 2024-T3 .050 17 2024** .040
2 3 2024-T3 2024-T3 .020 .025 10 11 2024-T3 321 STSTL .064 .015 18 19 Polyurethane 2024** .032
4 2024-0* .025 12 2024-T3 .080 20 2024** .050
5 2024-T3 .032 13 2024-T3 .050 21 2024** .020
6 2024-0* .032 14 2024-T3 .090 22 Kevlar
7 2024-T3 .040 15 2024-0* .063 23 2024** .025
8 2024-0* .040 16 2024-T3 .016 24 2024* .063
NOTE:
Left Wing Shown, Right Wing Oppositeand Noted Material Outlines in Dots Used on Right Wing Only.
* Heat Treat to 2024-T4 After Forming.
** Heat Treat to 2024-T42 AfterForming.
MaterialSkinThickness
Figure1 (Sheet 1 of 3)
EFFECTIVITY:
040-999
PAGE 2 51-00-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer) MAINTENANCEMANUAL
B. StructuralRepairs (continued)
Left Shown
Right Opposite
MaterialSkinThickness
Figure1(Sheet2of3)
EFFECTIVITY:
040-999 PAGE351-00-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. Structural Repairs (continued)
19 2 5
2
12
SKINTHICKNESS
NUMBER MATERIAL THICKNESS NUMBER MATERIAL THICKNESS
1 2 Fiberglass 2024-T3 .020 13 14 2024-T3 2024-T3 .050 .090
3 2024-T3 .025 15 2024-0* .063
4 2024-0* .025 16 2024-T3 .016
5 2024-T3 .032 17 2024** .040
6 7 2024-0* 2024-T3 .032 .040 18 19 Polyurethane 2024** .032
8 2024-0* .040 20 2024** .050
9 2024-T3 .050 21 2024** .020
10 2024-T3 .064 22 Kevlar
11 321 ST STL .015 23 2024** .025
12 2024-T3 .080 24 2024** .063
NOTE:
Left Wing Shown,Right Wing OppositeandNoted Material Outlinesin Dots Used on Right Wing Only.
* Heat Treat to 2024-T4 After Forming.
** Heat Treat to 2024-T42 After Forming.
MaterialSkin Thickness
Figure1 (Sheet 3 of 3)
EFFECTIVITY:
040-999
Jan10/9051-00-00
PIPERAIRCRAFT
PA42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. StructuralRepairs(continued)
17318AccessHoleCoverPlate
20372AccessHole ReinforcementPlate 17317 Access Hole Reinforcement Plate
o o o o o 17315AccessHole ReinforcementPlate
I - 17316 Access HoleCoverPlate
o
o I
0 0 o 0 o 615/165/167 o o o o o AN507-8-32R10
TypicalAccessHolesandPanels
Figure2
EFFECTIVITY:
040-999
PAGE5
51-00-00
Jan10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Investigation,Cleanupand Aerodynamic Smoothness
1. PassengerWindowSkin Inspection
This inspection is to be carried out by the eddy-current method of non-destructive testing (NDT)
without stripping any paint from the inspection area. An experienced testing laboratory must be
retained to do the testing. The personnel conducting the test must be certified to American Society
of Nondestructive Testing TC-1A, Level II minimum, and have two years of actual working
experience. All passenger windows must be inspected in the area indicated in Figure 601,
Passenger Window Skin Inspection.
The eddy-current testing instrument must be in the 5 kHz to 500 kHz range with the lowest
possible frequency being preferred. A small-tip (0.130 inch) probe, with frequency matched to the
tester, must be used.
Inspection equipment calibration is unconventional, so a reference standard (Piper P/N 73130-02)
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