ZENAIR CH2000 SERVICE MANUAL
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SECTION IV
STRUCTURE
GENERAL
Figure 7 identifies the type and thickness of skin used in the construction of the CH2000.
No structural repairs are recommended without contacting the manufacturer, however,
minor repairs such as patching the skin, welding, etc., may be made in accordance with the
regulations. It may be necessary to cut access holes to make skin repairs in some areas of
the aircraft.
Caution: Skin repairs must result in a surface which is as strong as, or stronger than, the
original skin. However, flexibility must be retained so that the surrounding areas will not
receive extra stress.
The rivets used on most parts are of the blind rivet type, Zenair reference #A-4 (1/8” dia.)
or A-5 (5/32” dia.); to be set with the hand tool, Zenair reference #HP-A4-A5. Aircraft
quality aluminum “Cherry” rivets are an approved substitute. Standard MS20470 rivets
may be used where access is possible.
Repair Carbon Fiber and Fiberglass parts with standard / typical Fiberglass type resin and
woven Fiberglass cloth. Using the Aircraft Inspection and Repair manual AC43. 13-1B
Chapter 3 is also acceptable.
When nylon Locknuts are removed, the installation of new Locknuts is highly
recommended.
Bolt torque valves are given in AC-43-13-1B.
NOTE: Modifications to the fuselage are permissible if they do not involve alterations to
its main structure. The manufacturer must be contacted for approval regarding specific
alterations proposed in accordance with approved data.
Following list gives the “primary structural” parts:
- Wing Spars
- Spar box assembly in fuselage
- Stabilator spar and mass balance attachment
- Rudder spar.
Nov-02
4.1
