Page 8 - Aeronca 11AC Interactive Service Manual

LIMITATIONS DATA

CENTER OF GRAVITY LIMITATIONS
Datum line wing leading edge
M.A.C. 58.87 inches
Leading Edge M.A.C. plus .28 inches
Center of gravity range plus 14.91, (24.97% M.A.C.) most forward, plus 22.40 inches (37.59% M.A.C.)
most rearward

AIRSPEED LIMITATIONS

Do not exceed 129 M.P.H. true indicated airspeed at any time. This figure is derived from stress analysis
and flight testing at the factory and has been established with a reasonable margin of safety.

PROPELLER LIMITS
Static RPM at full throttle setting not more than 2265 RPM, not less than 2040 RPM.

DIAMETER
Not more than 72 inches.
Not less than 70 inches.

WING FRAME

The wing frame consists of laminated spruce spars reinforced at the butt and strut attachments with three
ply spruce pads. All ribs are one piece hydro-formed aluminum reinforced at the spar openings bottom,
with spot welded aluminum gussets. The butt and inner aileron bay ribs are .040 – 52 S ½ H. aluminum
alloy, and the main, tip and aileron bay ribs are .020 – 52 S ½ H. aluminum alloy.

Spar butt attachment and strut attachment fittings holes are reinforced with micarta bushings pressed and
glued into the spar blank. Kem wood primer is applied to the spar as a protective coating, and should be
reapplied to any exposed wood after splicing or repairs. Methods of splicing and repair are covered in Civil
Aeronautics Manual 18.

Spar butt fittings are X4130 steel, clevis type. Damaged or worn spar butt fittings should never be welded
or bushed but should be replaced complete and may be ordered by giving the number shown on the
accompanying drawing.

The wings are attached to the fuselage with AN6-24 bolt, AN310-6 nut, rear spar, and AN5-14 bolt,
AN310-5 nut, front spar.

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