THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
1-4
Effective: 01/01/08
SUPPLIER FURNISHED COMPONENT MANUALS
COMPONENT MANUAL PART
#
R1340 AN1
Maintenance Manual
118611
R1340 AN1
Parts Manual
N/A
Propeller Owner’s
Manual
N/A
Note:
Should there be a conflict between the information in this manual and that in the
manuals for component parts, the information in the component part manual takes
precedence.
AIRCRAFT STRUCTURE
FUSELAGE
The fuselage is comprised of a welded
tubular steel frame, fiberglass hopper, and
detachable skins. An overturn structure
forms an integral part of the fuselage
frame. The frame structure is fabricated
from 4130 chrome-moly seamless steel
tubing, and the fittings, bushings, brackets,
and so forth are 4130 steel sheet.
As a corrosion preventative, hot linseed oil
is pumped throughout the entire welded
structure. On an average, 12 gallons are
pumped into the frame and 11 to 11 ½
gallons drain out, leaving a residual interior
coating on all members. The exterior of
the frame is sandblasted, etched, and
primed, which is followed by two coats of
polyurethane paint that is resistant to
chemical reaction.
The fuselage is covered with heat treated
Alclad panels attached with camloc
fasteners. Side skins can be removed
using only a screwdriver, thus exposing
the fuselage frame for thorough cleaning
and inspection. All skins are supported
clear of the fuselage tubing to prevent
accumulation of corrosive chemicals.
Each skin panel is etched, primed, and
painted before assembly to ensure
complete coverage. All bottom fuselage
skins around the hopper opening and aft to
the tail post are made of stainless steel.
The skin fasteners in the high corrosion
areas are also stainless steel.
WING
The wing has a constant chord of 90
inches, and is all metal, full cantilever
design. The massive main spar is a
tension field beam structure constructed
from Alclad webs and high strength heat-
treated steel caps. All wing skins, ribs, and
leading edges are constructed from Alclad
heat-treated material. The leading edge
structure is made especially strong to
minimize denting and is riveted with
universal rivets for strength. The fuel
tanks, which are located in the inboard
section of the wing, are an integral part of
the structure. Close pitch riveting of the
seams, substantial reinforcement, and
flexible sealants minimize chances of
rupture in crash conditions. Drain holes
are provided in adjacent bays to prevent
accumulation of fuel in the event of a leak.
The ailerons and flaps are all metal
