Cessna T188C - Page 361

MODEL
188
& T188
SERIES
SERVICE
MANUAL
SECTION
17
STRUCTURAL
REPAIR
Page No.
TABLE OF
CONTENTS
Aerofiche/Manual
REPAIR CRITERIA
....... .. .2F19/17-1
Engine Cowling.
.......... 2G5/17-11
EQUIPMENT AND TOOLS .. .... 2F19/17-1 BONDED FORWARD ACCESS DOORS .. 2G5/17-11
Support Stands . ........ 2F19/17-1 FUSELAGE TUBULAR STRUCTURE .. 2G5/17-11
Alignment Jigs . ..... . .. 2F19/17-1 GENERAL CONSIDERATIONS . .... 2G5/17-11
WING TWIST AND STABILIZER ENGINE MOUNT ........... 2G24/17-30
ANGLE-OF-INCIDENCE ...... 2F19/17-1 General Considerations ..... 2G24/17-30
CONTROL SURFACE BALANCING
. . . 2F22/17-4
Support Cradle Damage
...... 2G24/17-30
REPAIR MATERIALS
. ....... 2F22/17-4
Mounting Lugs and Fittings
.... 2G24/17-30
WING ... ............. 2F22/17-4 BAFFLES .............. 2G24/17-30
Wing Skin ............. F22/17-4 HOPPER .............. 2H8/17-38
Wing Stringers . ......... 2F22/17-4 CATWALK ............. 2H8/17-38
Wing Ribs ......... . 2F22/17-4 REPAIR OF GLASS-FIBER
Wing Spars .....
.. . .2F22/17-4
CONSTRUCTED COMPONENTS
. .. 2H13/17-43
Wing Leading
Edge . ......
. 2G4/17-10 SUBSTITUTING
BLIND RIVETS
FOR
Bonded Leading Edge Repair. . ... 2G4/17-10 SOLID RIVETS . .......... 2H13/17-43
Ailerons. .......... . 2G4/17-10 General Considerations. ... 2H13/17-43
Wing Flaps ...........
2G4/17-10
Blind Rivet Substitution .....
2H13/17-43
ELEVATORS AND RUDDER . ... 2G4/17-10 Determining Quantity of
FIN AND STABILIZER ........ 2G4/17-10 Substitute Blind Rivets ..... 2H13/17-43
FUSELAGE
(Except Tubular Structure)
FASTENER
SUBSTITUTION ......
2H13/17-43
Firewall ........
2G5/17-11
17-1. REPAIR CRITERIA. must NOT be supported from the underside, since the
skin bulkheads
are not
designed for
this purpose.
17-2. Although this section
outlines repair premis-
Adapt support stands to fasten
to the wing attach points
sible on structure of the aircraft, the decision of or landing gear attach points when supporting a fuse-
whether
to repair or replace
a major unit
of structure
lage.
will
be influenced
by such factors
as time and
labor
available, and by a comparison
of labor costs with the
17-6. ALIGNMENT JIGS. Whenever
a repair is to
price of replacement assemblies. Past experience be made which could affect structural alignment,
indicates that replacement
in many cases, is less
suitable jigs should be used to
assure correct align-
costly
than major repair. Certainly,
when the air- ment of
major attach points as shown
in figure 17-1.
craft must be restored to its airworthy condition in a Wing and fuselage jigs are available from the factory.
limited
length of time,
replacement
is preferable.
17-7. WING
TWIST AND
STABILIZER
ANGLE-OF-
17-3.
Restoration
of a damaged
aircraft
to its
orig-
INCIDENCE.
Wing
twist (washout)
and
horizontal
inal
design strength,
shape, and
alignment involves
stabilizer
angle-of-incidence
are shown
in the follow-
careful evaluation
of the damage, followed
by exact- ing chart. Stabilizers
do not have twist. Wings
have
ing workmanship
in performing the repairs.
This no twist from the
root to the lift strut station.
All
section
suggests the
extent of structural
repair prac-
twist in
the wing panel
occurs between
this station
ticable and supplements
Federal Aviation Regulations,
and the tip rib.
See figure 17-2 for wing twist
Part 43. Consult the factory when in doubt about a measurement.
repair
not specifically
mentioned
here.
WING
17-4.
EQUIPMENT
AND
TOOLS.
Twist
(washout)
..........
3
17-5. SUPPORT
STANDS.
Padded, reinforced
saw-
horse or tripod
type support stands,
sturdy enough
to STABILIZER
support
any assembly
placed upon
them, should
be
used to store a removed wing or tailcone. The fuse- Angle-of-incidence . ......... -4* 30'
lage assembly,
from
the tailcone
to the
firewall,
Revision 1 17-1