CESSNA AIRCRAFT
COMPANY
SINGLE ENGINE
STRUCTURAL REPA
IR MANUAL
VERTICAL STABILIZER
1. General
A. The vertical stabilizer is of conventional aluminum construction utilizing spars, ribs, and skins.
2. Vertical Stab
ilizer and Dorsal
A. The vertical stabilizer and dorsal are constructed jointly to form a single unit.
3. Negligible Da
mage
A. The same criteria which is used to define "negligible damage" to the fuselage may be applied to the
vertical stabilizer. Refer to Chapter 53, Fuselage Damage Classification for a complete description of
negligible da
mage.
4. Repairable Damage
A. Skin damage ex
ceeding that considered negligible that can be repaired as illustrated in Chapter 51,
Typical Skin Repairs, Figure 801. For skin damage which includes corrugations, Refer to Chapter
51, Typical Skin Repairs, Figure 802. Access to the internal fin structure is best gained by removing
skin attachin
g rivets on one side of the rear spar and ribs, and springing back the skin. Access to the
stabilizer may be gained by removing skin attaching rivets on one side and springing back the skin. If
the damaged area would require a repair which could not be made between adjacent ribs, or a repair
would be loca
ted in an area with compound curves, replacement of parts is recommended.
5. Replacement Damage
A. Hinge bracke
ts and small ribs should be replaced rather than repaired. In general, where parts are
available, the easiest and most satisfactory repairs can be accomplished by replacing the damaged
parts.
B. If the damage
d area would require a repair which would not be made between adjacent ribs, or the
repair would be located in an area with compound curves, complete skin panels must be replaced.
Ribs and spars may be repaired, but replacement is generally preferable. Where damage is extensive,
replacemen
t of the entire assembly is recommended.
55-30-00 Page 801
© Cessna Aircraft Company Jun 1/2005
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