CESSNA AIRCRAFT
COMPANY
SINGLE ENGINE
STRUCTURAL REPA
IR MANUAL
FLAPS AND AILERONS
1. General
A. Each wing flap assembly is constructed of a spar, ribs, upper and lower skins and leading edge skin.
B. Each aileron assembly is constructed of a single spar, ribs, upper and lower skin. Balance weights
are installed
in the lower inboard leading edge and are retained with screws.
C. Flight control surfaces which have been repaired or replaced must be balanced in accordance with
procedures outlined in Chapter 51, Flight Control Surface Balancing.
2. Damage Criteria
A. Damage to the flaps and ailerons can be divided into three major categories and is detailed in Wing
Damage Classi
fication.
3. Flap and Aileron Repair
A. Skin damage, e
xceeding that considered negligible, that can be repaired with minor patches can be
considered repairable. Flush skin patches are illustrated in Chapter 51, Typical Skin Repairs, Figure
801. A typical rib repair is illustrated in Chapter 51, Control Surface Repair, Figure 801, trailing edge
repair in Cha
pter 51, Control Surface Repair, Figure 802, are typical flap and aileron repairs.
B. Flight control surfaces which have been repaired or replaced must be balanced in accordance with
procedures outlined in Chapter 51, Flight Control Surface Balancing.
57-40-00 Page 801
© Cessna Aircraft Company Jun 1/2005
To Next Page
Loading...
