Cessna 177 SERIES Service Manual

15-3. INSTRUMENT
PANEL. (Refer
to figure 15-1.)
NOTE
15-4. DESCRIPTION.
The instrument panel
assem- All
instruments (gages
and indicators), re-
bly consists
of shock-mounted and
stationary panels.
quiring a thread
seal or lubricant, shall
be
The stationary
panel contains fuel and engine instru-
installed using teflon tape on male fittings
ments,
which are NOT sensitive
to vibration. The
only.
This tape is available
through Cessna
shock-mounted
panel contains major flight instru-
Service Parts Center.
ments such as horizontal and directional gyros which
ARE affected by
vibration. Most of the
instruments When
replacing an electrical
gage in an instrument
are screw-mounted
on the panel backs.
The stabila-
cluster assembly,
avoid bending pointer
or dial
tor
trim wheel is also secured
to the instrument
panel. plate. Distortion
of dial or back plate
could change
calibration of gages.
15-5. REMOVAL AND INSTALLATION. The sta-
tionary panel
is secured
to engine
mount stringers
15-10.
PITOT AND
STATIC
SYSTEMS.
(Refer to
and a
forward fuselage
bulkhead and
ordinarily is
not figure
15-2.)
considered
removable. The shock-mounted
panel is
secured to
the main stationary
panel with
rubber
15-11. DESCRIPTION.
The
pitot system conveys
shock-mounted
assemblies.
Beginning with
1969
ram air pressure
to the airspeed
indicator.
The
Models
the main
panel may
be removed
for access
static system
vents vertical
speed
indicator,
alti-
after
disconnecting
plumbing,
wiring,
removing
meter
and airspeed
indicator
to atmospheric
pres-
decorative
cover and nuts
securing panel
to mounting
sure through
plastic tubing
connected to static
ports.
studs. To remove
shock-mounted panel
proceed as A
static line sump is installed
at source button
to
follows:
collect
condensation
in static system.
An alternate
a. Prior
to 1972
models,
remove
decorative
panel
static source
may
be installed
and is
used only
in
covers
by unscrewing
threaded
buttons. On 1972
and emergencies.
When
used as a static
source, cabin
1973
models the covers
are held on
with Velcro fast-
pressure
is substituted
for atmospheric
pressure,
eners
and can be
removed by
pulling gently
on cover.
causing
instrument
readings
to vary from
normal.
1974 models
utilize
a guide pin
and rubber
grommet
Refer
to Owner's
Manual for
flight operation
using
arrangement and
can be removed
by pulling evenly
alternate
static source
pressure.
A pitot tube heater
on the cover.
Reinstall by
reversing procedure.
may be installed.
The heating
element is controlled
b. Remove
nuts from shock-mounts, tag and dis-
by a switch at the instrument panel and
is powered
connect
instrument
wiring
and plumbing
and pull
panel by
the electrical
system.
Beginning
with aircraft
straight
back.
17702108,
an encoding
altimeter
and a standby
al-
c. Reverse
preceding
steps for installation.
En-
timeter
may be installed.
The encoding
altimeter
sure
ground
strap is
properly
installed.
supplies
an altitude
reading
to the
optional
300 or
400 transponder
for signal
transmission. The
15-6.
SHOCK MOUNTS.
Service
life
of instruments
standby
altimeter
is connected
to the
static system
is
directly
related to
adequate
shock-mounting
of
by
a tube
to the vertical
speed
indicator.
panel.
If removal of panel
is necessary,
check
mounts
for deterioration.
15-12. MAINTENANCE. Proper maintenance of
pitot and static system is essential for proper opera-
15-7. INSTRUMENTS.
(Refer
to figure 15-1.)
tion of altimeter,
vertical speed and airspeed
indi-
cators. Leaks, moisture and obstructions in the
15-8. REMOVAL.
Most instruments are
secured pitot
system will result in false
airspeed indications,
to panel with screws
inserted through panel face.
while static
system malfunctions
will affect readings
To remove an
instrument, remove
decorative cover,
of all three instruments.
Under instrument
flight
disconnect wiring
or plumbing to instrument,
re- conditions,
these instrument
errors could be hazar-
move mounting screws
and take instrument
out from dous.
Cleanliness and security
are the principal
behind, or in
some cases, from front
of panel. In-
rules for system maintenance.
The pitot tube
and
strument
clusters are installed
as units and are
static ports MUST
be kept clean and unobstructed.
secured by a screw
at each end. A cluster
must be
removed
from panel to replace
an individual gage.
In
all cases
when an instrument is removed, disconnect-
15-13. STATIC PRESSURE SYSTEM
INSPECTION
ed lines or wires should be protected. Cap
open AND LEAKAGE TEST. The
following procedure
lines and cover pressure connections on instrument outlines inspection and testing of static pressure
to prevent thread damage and entrance of foreign system, assuming altimeter has been tested and in-
matter. Wire terminals should be insulated
or tied spected in accordance with current
Federal Aviation
up so accidental grounding
or short-circuiting will
Regulations.
not occur. a. Ensure static system is free from entrapped
moisture and
restrictions.
15-9. INSTALLATION. Generally, installation pro- b. Ensure no alterations or deformations of air-
cedure is the reverse of removal procedure.
Ensure frame surface have been made
which would affect
mounting
screw nuts are tightened firmly, but do not
the relationship between air pressure in
static pres-
over-tighten, particularly
on instruments
having sure
system and true ambient
static air pressure for
plastic cases. The same rule applies to connecting any flight configuration. If dual static ports are used,
plumbing
and wiring.
seal one opening with tape (air tight),
then close
Change 4 15-3

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)