6-6 Change 3
Table 6-5. Center of Gravity Limits (Landing Gear down) Restricted Category
FORWARD CG LIMIT
AFT CG LIMIT
16,200 LBS (MAXIMUM TAKE-OFF)
15,400 LBS (MAXIMUM LANDING)
13,100 LBS (MAXIMUM ZERO FUEL)
12,600 LBS OR LESS
The moment/100 for retraction of the landing gear is 61.6. Loadings based on wheels-down condition which fall
within the limiting moments in the table, will be satisfactory for flight with landing gear retracted.
CENTER OF GRAVITY
6-11. CENTER OF GRAVITY LIMITATIONS.
When the mission gear is removed, the forward
center of gravity limit is easily exceeded.
Center of gravity limitations are expressed in ARM
inches which refers to a positive measurement from the
aircrafts reference datum. The forward CG limit at
12,600 lbs., or less, is 179.0 ARM inches. The forward-
sloping CG limit line is a straight line from 12,600 lbs. to
16,200 lbs, ending at fuselage station 188.0. At 16,200
lbs., or less, the aft CG limit is 195.1 ARM inches. The
Center of Gravity Loading Diagram (fig. 6-3) is designed
to establish forward and aft CG limitations. When the
mission gear is removed, it may be necessary to add re-
movable ballast or baggage in the aft baggage compart-
6-12. LOAD PLANNING.
The basic factors to be considered in any loading situ-
ation are as follows:
a. Cargo shall be arranged to permit access to all
emergency equipment and exits during flight.
b. Floorboard structural capacity shall be considered
in the loading of heavy or sharp-edged containers and
equipment. Shorings shall be used to distribute highly
condensed weights evenly over the cargo areas. Use of
the floor seat tracks to support loads is encouraged
c. All cargo shall be adequately secured to prevent
damage to the aircraft, other cargo, or the item itself.
6-13. LOADING PROCEDURE.
The cabin airstair door is weight limited to a max-
imum of 300 pounds to prevent possible struc-
Loading of cargo is accomplished through the cabin
door (21.5 in. X 50.0 in.) or the cargo door.
6-14. SECURING LOADS.
All cargo shall be secured with restraints strong
enough to withstand the maximum force exerted in any
direction. The maximum force can be determined by mul-
tiplying the weight of the cargo item by the applicable
load factor. These established load factors (the ratio be-
tween the total force and the weight of the cargo item) are
1.5 to the side and rear, 3.0 up, 6.6 down, and 9.0 for-