Cessna 188 Series Service Manual 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