Cessna 177 SERIES Service Manual

NOTE
tains
SP654890B2
Fuel
Tank Area
Sealant
Kit and
SP654706B2
Access
Door Sealant
Kit.
Normal cur-
Allowable
work life
of EC-1675B/A
sealant
ing time
for SP654890B2
Sealant
Kit is
72 hours.
is
four hours
from
the starting
time
of mix-
Normal
curing time
for SP654706B2
Sealant
Kit is
ing.
Allowable
work
life of EC-1608B/A
24 hours.
These
values are
based
on a Standard
sealant
is
one hour.
These
apply to stand-
condition
of 77
°
Fahrenheit
and 50'o
humidity.
Cur-
ard
conditions
of 77
°
Fahrenheitand
50%
rel-
ing
time may
be accelerated
as shown
in the follow-
ative
humidity.
An
increase
in temperature
ing chart.
or a decrease
in
humidity
will
shorten
the
work
life of
the sealant.
Temperature
of Sealant
'F.
Time
in Hours
d.
Apply fay
surface
sealant
to one
mating
part
and
install
rivets
or fasteners
while
sealant
is still
with-
in its
allowable work
life.
160
3
140
4
NOTE
120 7
During
the
sealing
operation,
sealant
must
be
checked
at various
times
to determine
that
it
NOTE
has
not
exceeded
its
allowable
work
life.
Use
a
small wood
paddle, such
as a tongue
depres-
Temperaturt
shall not
exceed 160°F.
Bay
must
sor, to
gather some
sealant.
Touch
the seal-
be
vented
to relieve
pressure
during
accelerated
ant
to a piece
of clean
sheet
metal. If
the
curing.
sealant
adheres
to
the sheet
metal,
it
is still
within
its allowable
work
life.
If the
sealant
IWARNINGL
does
not adhere
to
the
sheet metal,
it is be-
yond
its allowable
work
life and
must not
be
Access
door
sealant
must
not be
heated
above
used.
90
°
until
sealant
is cured
for 24
hours
based
on a
standard
condition
of 77
°
Fahrenheit
and
e.
Apply
a fillet
seal to
the repaired
area
on the
50% relative
humidity.
Harmful
vapors
are
inside
of the bay.
released
if sealant
is heated
above
90°F.
f. Apply
fay
surface
door
sealant
to access
doors
and fuel
quantity
transmitter
adapter,
if
removed,
12-19.
TESTING
INTEGRAL
FUEL BAY.
and install
the
doors
and adapter.
a. Remove
vent line
from
vent
fitting
and cap
the
g. Allow
the sealant
to cure.
Refer
to paragraph
fitting.
12-18
for curing
time.
b.
Remove
forward
and
aft
fuel lines
from
bay.
h. Clean
stains
from
outside
of bay area.
c.
To one
of the
bay fittings,
attach
a
water ma-
i. Test
fuel bay
for leaks
as described
in
paragraph
nometer
capable
of measuring
20 inches
of water.
12-19.
d.
To the
other bay
fitting,
connect
a well
regula-
ted supply
of air
(1/2 PSI
MAXIMUM
or 13.8
12-17.
SEALING
FUEL
LEAKS.
First
determine
the
INCHES
OF WATER).
Nitrogen
may
be used
where
source of
the fuel
leaks. Fuel
can
flow along
a seam
the
bay might
be exposed
to temperature
changes
or the structure
of
the wing
for several
inches,
mak-
while testing.
ing
the leak
source difficult
to
find. A
stained area
e. Make
sure
filler cap
is installed
and sealed.
is
an indication
of the
leak source.
Fuel leaks
can
be
found
by testing
the
complete
bay
as
described
in
CsAUTION
paragraph
12-19.
Another
method
of detecting
the
source
of
a fuel leak
is to remove
access
doors
and
Do not attempt
to
apply pressure
to
the bay
blow
with an
air nozzle
from the
inside
of the bay
in
without
a good
regulator
and a
positive
shut-
the area
of the
leak while
a soap
bubble solution
is
off in
the supply
line.
Do not inflate
the
fuel
applied
to the outside
of the bay.
After
the leak
bay to more
than 1/2
psi or damage
may
source
has been found,
proceed as follows:
occur.
a.
Remove
existing
sealant
in the
area
of
the leak
as described
in
paragraph
12-16, step
"a."
f.
Apply pressure
slowly
until
1/2 PSI
is obtained.
b. Clean
the area
and apply
a fillet seal.
Press
g. Apply
soap solution
as required.
sealant
into leaking
area
with a small
paddle, being
h. Allow 15
to 30 minutes
for pressure
to stabilize.
sure
to work out
all entrapped
air.
i. If bay holds
for 15
minutes, without
pressure
c. If
a leak occurs
around a
rivet or bolt,
restrike
loss,
bay is acceptable.
the rivet
or torque
the bolt
to the maximum
allowable
j. Reseal
and retest
if any leaks
are found.
torque,
and repair
any damaged
sealant.
d. Apply
fay surface
door sealant
to access
doors
12-20.
FUEL QUANTITY
TRANSMITTERS.
or
fuel quantity
transmitter
adapter,
if
removed,
and
install the
doors and
adapter.
12-21.
DESCRIPTION.
Two fuel
quantity indicators,
e. Test
fuel bay for leaks
as described
in para-
located in
a cluster on the
instrument
panel, are
graph
12-19.
actuated
individually
by an electric
fuel quantity
trans-
mitter installed
on each
aft fuel
spar. The
trans-
12-18.
CURING
TIME.
Service
Kit SK210-56
con-
mitters
consist
of
a float
attached
to a pivoted
rod,
12-11

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)