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Cessna 402C - Page 25

Cessna 402C
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SECTION
2
G'~J,
402C
LIMITATIONS
MODEL
MISCELLANEOUS
INSTRUMENT
MARKINGS
Instrument
Vacuum:
a.
Red
Line:
4.75
Inches
Hg.
b. Green Arc:
4.75
to
5.25
Inches
Hg.
Oxygen
Pressure:
a.
Yellow Arc: 0
to
300
PSI
b. Green Arc: 1550
to
1850
PSI
c.
Red
Line:
2000
PSI
d.
The
Cubic Foot
Capacity
of
the
80ttle
Installed
Will
Be
Indicated
On
The
Face
of the
Gage.
WEIGHT
LIMITS
Maximum
Ramp
Weight:
6885
Pounds
Maximum
Takeoff
Weight: 6850 Pounds
Maximum
Landing
Weight:
6850
Pounds
Maximum
Zero
Fuel
Weight:
6515
Pounds
Maximum
Weights
in
Baggage
Compartments
(Passenger Configuration):
a.
Left
and
R;
ght
Wi
ng
lockers
- 200 pounds
each.
'11
,;,..;;;
b.
Avionics
Bay
-
250
pounds
less
installed
optional
equipment.
/'~.
c.
Nose
Bay
- 350
pounds
less
installed
optional equipment.]:\-1 :.cc"
d.
Aft
Cabin (Bay
A)
- 400 pounds (200 Pounds
Per
Side).
If
I
"'.'
e.
Aft
Cabin (Bay
B)
- 100 pounds (50 Pounds
Per
Side).
'is.,
Maximum
Weights
in
Baggage
Compartments
(Cargo
Configuration):
a.
Left
and
Right
Wing
Lockers - 200 pounds
each.
b. Avionics
Bay
- 250 pounds
less
installed
optional
equipment.
c.
Nose
Bay
- 350 pounds
less
installed
optional
equipment.
~1~-!;c
d.
Maximum
cargo load
aft
of
the
front
spar
is
not
to
exceed 2000 pounds.
e.
The
total
cabin load
including
optional
equipment
aft
of
Station
238.1
is
not
to
exceed 600
pounds.·-
-
_';,',
".,_.
<.
f.
Maximum
cargo load in any
22.5
inch
length
Of
cabin
floor
is
500 pounds.
The
maximum
load
for
the
lower
aft
cabin
shelf
(.Bay
A)
is
400 pounds,
for
the
upper
aft
cabin
shelf
(Bay
B)
is
100 pounds.
Center
of
Gravity
Limits
(Gear
Extended):
a.
Aft
Limit:
160.67
inches
aft
of
reference
datum (34.0%
MAC)
at
6850
pounds
or
less.
b.
Forward
Limit:
151.58
inches
aft
of
reference
datum (19.6%
MAC)
at
6850
pounds and
14g.08
inches
aft
of
reference
datum (15.5%
MAC)
at
5800 pounds
or
less
with
straight
line
variation
between
these
points.
c.
See Weight
and
Balance Data in
Section
6
for
loading
schedule.
The
I
reference
datum
line
is
100 inches forward
of
the
aft
face
of
the
fuselage
bulkhead forward
of
the
rudder
pedals.
The
mean
aerodynamic
chord
(MAC)
is
62.65
inches
in
length.
The
leading
edge
of
the
MAC
is
139.37 inches
aft
of
the
reference
datum
line.
FAA
Approved
1 November 1979
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