FAA Advisory Circular 43.13-1B
Acceptable Methods, Techniques, and Practices
Aircraft Inspection and Repair
AC 43.13-1B | 2. Fabric Covering | 1. Practices and Precautions | 2-12. Fasteners
9/27/01
AC 43.13-1B CHG 1
FIGURE 2-12. Fabric attachment spacing
b. When the original lace spacing on the
empennage surfaces and fuselage, is not
known, a maximum spacing of two times the
spacing shown in figure 2-12 for the slipstream
area (prop wash) on the wings may be used.
c. The installations of fabric attach-
ments such as screws, rivets, wire clips, and
rib lacing should be delayed until the fabric is
stabilized and pulled taut with dope. This ac
tion is delayed to avoid pulling wing ribs and
other structures out of alignment or tearing the
fabric at attachment points as the fabric be
comes taut. All lacing should be installed ad
jacent to the structure to which the fabric is
being laced, to avoid tearing the fabric and/or
creating slack in the cord loop when a load is
applied. Where plastic washers were used by
the aircraft manufacturer to provide increased
pull-through resistance, under the heads of riv
ets or screws, the same diameter aluminum
washer may be used as replacement. Alumi
num washers are used because they are not
affected by solvents found in adhesives or
dopes, nor do they become brittle because of
age or cold weather.
2-12. FASTENERS. Several light aircraft
designs employ screws, rivets, or single-wire
metal clips to secure the fabric to the wing.
a. Screws holding the old fabric can be
removed after spinning a small sharpened tube
around each screw or using a razor blade to cut
and peel away the finishing tape. Care must be
taken not to mark or scribe the underlying
metal or wood structure. Blind rivets through
ribs can be removed by drilling in the center to
undercut the head.
b. Single-wire clips may be removed
without damage to the rib by inserting a wide,
thin screwdriver blade under the clip and care
fully twisting. Apply a lifting force at the clip
end to pull it up through the hole.
Par 2-11
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