Cessna T182 Series User Manual

MODEL
182 &
T182 SERIES
SERVICE
MANUAL
18-42. DAMAGE NECESSITATING
REPLACEMENT elevators
and rudder must be balanced. A flight
OF PARTS. If the damage would require
a repair control surface balancing
fixture kit is available
which could not be made between adjacent
ribs, com- (P/N 5180002-1). See figure
18-3 for procedures
plete skin panels
must be replaced.
Ribs and spars
pertaining
to the use of this kit.
may be repaired, but replacement is generally pre-
ferable.
Where extensive
damage
has occurred,
re-
18-53. FIN
AND STABILIZER.
placement
of
the aileron
assembly is
recommended.
18-54.
NEGLIGIBLE
DAMAGE.
Refer
to paragraph
After repair and/or replacement, balance aileron 18-13
in accordance with paragraph 18-43 and figure 18-3.
18-55.
REPAIRABLE DAMAGE.
Skin patches illus-
18-43 AILERON
BALANCING. Following
repair.
trated in figure 18-4 may
be used to repair skin
dam-
replacement
or painting,
the aileron
must be balanced.
age.
Access to the
dorsal area of
the fin may be
A flight
control surface
balancing
fixture kit
is avail-
gained
by removing
the horizontal
closing
rib at the
able (P/N5180002-1).
See figure
18-3
for procedures
bottom
of the fin.
Access
to the internal
fin
structure
pertaining
to the
use of this
kit.
is best
gained
by removing
skin
attaching
rivets
on
one side of
the rear spar and ribs,
and springing back
18-44. WING FLAPS
the
skin. Access to the stabilizer
structure may
be
gained by removing
skin attaching
rivets on one side
18-45. NEGLIGIBLE
DAMAGE. Refer to
paragraph of the
rear spar and ribs, and
springing back the skin.
18-13.
If the damaged
area would require a repair which
could
not be made between
adjacent ribs, or a
repair
18-46. REPAIRABLE DAMAGE. Flap repairs should would be located in an area with compound curves,
be similar
to aileron repairs discussed
in paragraph see the following
paragraph.
18-41. A flap leading edge repair is shown in figure
18-10.
18-56. DAMAGE NECESSITATING
REPLACEMENT
OF PARTS.
If the damaged
area would require
a
18-47. DAMAGE NECESSITATING REPLACEMENT
repair which could not be made
between adjacent ribs,
OF PARTS. Flap repairs which require replacement or the repair would be located in an area with com-
of parts should
be similar to aileron repairs dis- pound
curves, complete skin panels must be replaced.
cussed in paragraph 18-42.
Since the flap is
not con- Ribs and
spars may be repaired,
but replacement is
sidered a movable control surface,
no balancing is generally preferable.
Where damage is extensive,
required.
replacement
of the entire
assembly is recommended.
18-48.
ELEVATORS AND RUDDER.
18-57. FUSELAGE.
18-49. NEGLIGIBLE
DAMAGE. Refer
to paragraph
18-58. DESCRIPTION.
The fuselage is of
semi-
18-13.
The exception to negligible damage on the
monocoque construction, consisting of
formed bulk-
elevator surfaces is the
front spar, where a
crack heads,
longitudinal stringer, reinforcing
channels,
appearing
in the web at the hinge fittings
or in the and skin panels.
structure which supports the overhanding balance
weight
is not considered negligible. Cracks in the
18-59. NEGLIGIBLE DAMAGE. Refer
to paragraph
overhanging tip rib, in the area at the front
spar 18-13. Mild corrosion appearing
upon alclad sur-
intersection with the web of the rib,
also cannot be faces does not necessarily
indicate incipient failure
considered negligible.
of the base
metal. However, corrosion
of all types
must be carefully
considered, and approved
reme-
18-50.
REPAIRABLE DAMAGE.
Skin patches illus-
dial action taken.
Small cans appear
in the skin
trated in
figure 18-4 may
be used to repair
skin dam-
structure
of all metal aircraft.
It is strongly
rec-
age between
corrugations.
For skin
damage which
ommended
however, that
wrinkles which
appear to
includes
corrugations, see
figure 18-12. Follow-
have originated
from other sources,
or which do
ing repair,
the elevator/rudder
must be balanced.
not follow the general
appearance of the
remainder
See figure
18-3 for balancing procedures. If damage
of the skin panels, be thoroughly
investigated.
requires a repair
which could not be made between Except
in the landing gear bulkhead areas, wrinkles
adjacent
ribs, see paragraph 18-51.
occurring over stringers which disappear
when the
rivet
pattern is
removed,
may be considered
negligi-
18-51.
DAMAGE NECESSITATING
REPLACEMENT
ble.
However, the
stringer rivet holes
may not
OF
PARTS. If the
damaged area
would require
a re- align
perfectly with
the skin holes because
of a per-
pair which
could not be made
between adjacent
ribs,
manent "set"
in the stringer.
If this is apparent,
complete
skin panels
must
be replaced.
Ribs and
replacement
of
the stringer
will usually
restore
the
spars
may be repaired,
but replacement is generally
original
strength characteristics
of the area.
preferable.
Where extensive
damage has occurred,
replacement
of the entire
assembly
is recommended.
NOTE
After
repair
and/or
replacement,
balance
elevators
Wrinkles
occurring
in
the skin
of the
main
and rudder
in accordance
with paragraph
18-52 and
landing
gear
bulkhead
areas must
not
be
figure 18-3.
considered
negligible. The
skin panel must
be opened
sufficiently
to permit
a thorough
18-52.
ELEVATOR
AND
RUDDER
BALANCING.
examination
of
the lower
portion
of the land-
Following
repair,
replacement
or painting, the
ing gear bulkhead
and its tie-in
structure.
18-4

Cessna T182 Series Specifications

General

Engine Type	Lycoming IO-540-AB1A5
Horsepower	230 hp
Seating Capacity	4
Service Ceiling	18, 100 feet
Takeoff Distance	1, 600 feet
Landing Distance	1, 350 ft
Type	Single-engine
Max Takeoff Weight	3, 100 lb
Wingspan	36 ft
Length	29 ft
Height	9 feet 3 inches
Fuel Capacity	92 US gal (348 L)