Cessna 177 SERIES Service Manual

18-38. REPAIRABLE
DAMAGE.
Flap repairs
should 18-50.
RUDDER.
be similar
to aileron
repairs
discussed in
paragraph
18-33. A flap
leading edge repair is shown in figure 18-51.
NEGLIGIBLE DAMAGE. Refer to paragraph
18-9.
18-12.
18-39. DAMAGE NECESSITATING
REPLACEMENT
18-52. REPAIRABLE
DAMAGE.
Skin patches, illus-
OF PARTS. Flap repairs which
require replacement trated in figure 18-4,
may be used to repair skin
of parts should be similar
to aileron repairs
discuss- damage.
If the damaged area would
require a repair
ed in
paragraph 18-34. Since the flap is not con-
which could not be made between adjacent
ribs, see
sidered a movable
control surface, no balancing is the
following paragraph. Following repair, rudder
required.
must be balanced.
Refer to paragraph 18-54 and fig-
ure 18-3 for balancing the rudder.
18-40. WING LEADING EDGE.
18-53. DAMAGE NECESSITATING REPLACEMENT
18-41. NEGLIGIBLE DAMAGE.
Refer to paragraph OF PARTS. If the
damaged area would require a
18-12.
repair which
could not be made between
adjacent ribs,
complete skin panels must be replaced. Ribs and
18-42.
REPAIRABLE DAMAGE.
A typical leading
spars may be
repaired, but replacement
is generally
edge skin repair is shown in figure 18-8.
However, preferable. Where extensive
damage has occurred,
repairs
must not be made to the wing leading edge
replacement of the entire assembly is recommended.
skin inboard of
wing station 40.00 without factory
After repair or replacement, balance rudder
in
approval. Refer to Section
1 for wing station loca- accordance
with paragraph 18-54 and figure 18-3.
tions.
Extra access holes
outlined in figure
18-10
must not
be installed on the cantilever
wing without
18-54. RUDDER
BALANCING. Following
repair,
factory
approval.
replacement or
painting, the rudder must
be balanced.
Complete
instructions for fabricating
balancing fix-
18-43. DAMAGE NECESSITATING
REPLACEMENT tures and
mandrels and their use are given in figure
OF
PARTS. An
entire leading
edge skin may
be re-
18-3.
placed without factory approval.
18-55.
FIN.
18-44. STABILATOR.
18-56.
NEGLIGIBLE DAMAGE.
Refer to paragraph
18-45.
NEGLIGIBLE
DAMAGE.
Refer
to
paragraph
18-12.
18-12.
18-57. REPAIRABLE
DAMAGE. Skin patches
illus-
18-46. REPAIRABLE DAMAGE. Should
damage trated in figure 18-4 may
be used to repair skin
occur to the skin in the
area between the two outboard damage.
Access to the dorsal fin may be gained by
ribs, the entire skin in that area
may be replaced or removing the attaching
screws, then remove the
the skin in any bay may be replaced, depending
on the dorsal fin from the aircraft.
Access to the fin is
extent of damage. Replacement skin must be the best gained by removing skin attaching rivets on one
same gage as the original skin. Repair seams must side of the rear spar and ribs and springing back the
be made to lie along existing structural members, skin. If the damaged area would require a repair
and each
seam must use the same rivet size and
which could not be made between adjacent
ribs, or a
pattern as the
original seam. Should damage occur
repair would be located in an area with compound
to the stabilator tip, replacement of the tip is rec- curves, see the following paragraph.
ommended. Following
repair, the stabilator
must be
balanced. Refer
to paragraph 18-48 and figure 18-3 18-58.
DAMAGE NECESSITATING REPLACEMENT
for balancing the stabilator. OF PARTS. If the damaged area would require a
repair which could not be made between adjacent
18-47. DAMAGE
NECESSITATING REPLACEMENT
ribs or the repair would be located in an area
with
OF PARTS. Repairs
must not be made to the stabila- compound
curves, complete skin panels must be
re-
tor inboard of the area between the two outboard ribs placed. Ribs and spars may be repaired but re-
without factory approval. However, an entire skin, placement is generally preferable. Where damage
spar or rib may be replaced without factory approval, is extensive, replacement of the entire assembly is
Following repair or replacement, the stabilator must recommended.
be balanced. Refer
to paragraph 18-48
and figure
18-3 for balancing the stabilator.
18-59. FUSELAGE.
18-48.
STABILATOR
BALANCING. Following
re-
CAUTION
pair, replacement or painting, the stabilator must be
balanced.
Complete
instructions
for fabricating
bal-
Repairs
must
not be made
to the main
wing
ancing
fixtures and
mandrels and
their use are given
spar carry-thru
section of the
cantilever
in figure 18-3.
wing
without factory approval.
18-49. STABILATOR TRIM TAB. Repairs must not 18-60. DESCRIPTION. The fuselage is of semi-
be made to the stabilator trim tab
without factory monocoque construction
consisting of formed bulk-
approval. heads, longitudinal stringers, reinforcing channels
18-4

Cessna 177 SERIES Specifications

General

Manufacturer	Cessna
Engine Type	Piston
Wingspan	35 ft 6 in (10.82 m)
Seating Capacity	4
Number Built	4, 295
Engine	Lycoming O-360
Horsepower	180 hp
Maximum Takeoff Weight	2, 500 lb (1, 134 kg)