MAULE AEROSPACE TECHNOLOGY, INC.
MAINTENANCE MANUAL
FOR
M-7-235C
Rev. D
21/37
SECTION III
MAJOR COMPONENT PARTS
WINGS:
The complete wing is of metal construction (2024-T3 aluminum) with a fiberglass wing tip.
Spar root end strut fittings are made of 2024-T4 aluminum.
LIFT STRUTS:
The lift struts are sealed, streamlined tubes attached to the wing and fuselage by means of
AN standard steel bolts. When inspecting the struts, check for nicks and dents and see that all
bolts are snug (not tight).
In handling the airplane on the ground, care should be taken to prevent damage to the lift
struts by pushing or lifting in the middle of the strut. Frequent inspection of the struts should be
made and any paint loss or minor corrosion should be sanded down to bare metal with fine sand-
paper and metal primer should be applied. After the primer is dried, a finish coat of the desired
color may be added.
WARNING: Any unrepairable dents or punctures are cause for replacement of the strut.
FUSELAGE:
The fuselage is a welded truss type structure having an integral vertical tail fin. Chrome
molybdenum steel (4130) is used for all tube members, control fittings, floor supports and seat
members. Doorframes and other nonstructural parts are made of cold rolled steel (1008 to 1015)
or stainless steel (per customer’s request)
.
If it becomes necessary to replace any fuselage members, sleeve type splices should be
made in accordance with practices outlined in FAA AC 43.13-1, Aircraft Inspection and Repair.
The forward fuselage section is aluminum covered (5052-H34 or 2024-T3). The firewall and
bottom fuselage just aft of the cooling air egress are made of .018 galvanized sheet steel.
The aft fuselage section is covered with Ceconite
fabric and standard dope and paint finish
as per Maule Specification S-17. Later models are finished with polyurethane or acrylic urethane
paint in accordance with Maule Specifications S-40 or S-41, respectively.
This fabric need not be
pulled or punch tested.
