CESSNA AIRCRAFT COMPANY
SINGLE ENGINE
STRUCTURAL REPAIR MANUAL
WINGS - GENERAL
1.
General
A.
Description of Wing Assemblies:
(1)
The wing assemblies are a semicantilever type, employing semimonocoque type of structure.
(2)
The internal structure consists of a built-up front spar, a formed inboard front fuel spar, a rear
spar, and a formed auxiliary spar assembly in the aileron attach area.
(3)
Ribs are formed sheet metal, and consist of nose, intermediate and trailing edge assemblies.
(4)
On the 172 series airplanes, stressed skin is riveted to the rib and spar assemblies to complete
the rigid structure. On 182 and 206 series airplanes, the skin is bonded to the leading edge ribs
and riveted at other locations.
(5)
The inboard section of the wing is sealed to form an integral fuel cell. The sealed area runs from
the wing root outboard toward the strut attach; and from the front fuel spar to the rear spar.
NOTE:
On the 172 series airplanes, the fuel closeout rib is located approximately 7 inches
outboard from the wing root.
(6)
Access openings (hand holes with removable cover plates) are located in the wing These
openings afford access to
fl
ap and aileron bellcranks and control systems, the
fl
ap actuator
in the left hand wing, electrical wiring and wiring disconnect points, the wing portion of the
ventilation system, strut attach
fi
ttings, and the inside of the fuel cell.
B.
Refer to applicable Maintenance Manual, Chapter 6, Dimensions and Areas, for wing station
diagrams.
C.
If questions arise concerning approved repairs, or for repairs not shown in this section, contact Cessna
Propeller Aircraft Product Support, Box 7706, Wichita, KS 67277. (316) 517-5800, Facsimile (316)
942-9006.
2.
Tools, Equipment and Materials
A.
Refer to Figure 1 for an illustration of wing and fuselage support stands which may by fabricated locally
and used during structural repair.
3.
Installation of Access Holes
NOTE:
In some instances, it may be advantageous to create access holes in the wing skin to facilitate
wing repair. Refer to the following steps and Figure 2 for an illustration of access holes.
WARNING: The following procedures are not applicable to the integral fuel cell
skins.
A.
Precautions and Notes.
(1)
Add the minimum number of access holes necessary.
(2)
Any circular or rectangular access hole which is used with approved optional equipment
installations may be added in lieu of the access hole illustrated.
(3)
Do not add access holes at outboard end of wing: remove wing tip instead.
(4)
Locate new access holes near the center of a bay (spanwise).
(5)
Locate new access holes forward of the front spars as close to the front spar as practical.
(6)
Locate new access holes aft of the front spar between the
fi
rst and second stringers aft of the
spar. When installing the doubler, rotate it so the two straight edges are closest to the stringers.
(7)
Alternate bays, with new access holes staggered forward and aft of the front spar, are preferable.
(8)
A maximum of
fi
ve new access holes in each wing is permissible. If more are required, contact
Cessna Propeller Aircraft Product Support.
B.
Access Hole Installation. (Refer to Figure 2)
(1)
Establish exact location for inspection cover and inscribe centerlines.
(2)
Determine position of doubler on wing skin and center over centerlines. Mark the ten rivet hole
locations and drill to size shown.
57-00-00
Page 1
© Cessna Aircraft Company
Jun 1/2005
Содержание 172 Skyhawk SERIES
Страница 11: ...CHAPTER STANDARD PRACTICES STRUCTURES ...
Страница 68: ...CHAPTER 52 DOORS ...
Страница 74: ...CHAPTER 53 FUSELAGE ...
Страница 97: ...CHAPTER 55 STABILIZERS ...
Страница 106: ...CHAPTER 56 WINDOWS ...
Страница 115: ...CHAPTER 57 WINGS ...
Страница 158: ...CHAPTER 71 POWER PLANT ...
