TM 55-1510-221-10
b.
A point at which a definite radio fix can be established.
Service Ceiling
The altitude at which the minimum rate of climb of 100 feet per min-
ute can be attained for existing aircraft weight.
Takeoff Weight
The weight of the aircraft at liftoff from the runway.
Weight and Balance Terminology.
Arm
Approved Loading Envelope
Basic Empty Weight
Center-of-Gravity
CG Limits
Datum
Engine Oil
Empty Weight
Landing Weight
Maximum Weight
Moment
Standard
Station
Takeoff Weight
Unusable Fuel
Usable Fuel
Useful Load
Miscellaneous Abbreviations.
Deg
DN
FT
FT LB
The distance from the center of gravity of an object to a line about
which moments are to be computed.
Those combinations of aircraft weight and center of gravity which
define the limits beyond which loading is not approved.
The aircraft weight with unusable fuel, full oil, and full operating flu-
ids.
A point at which the weight of an object may be considered concen-
trated for weight and balance purposes.
CG limits are the extremes of movement which the CG can have with-
out making the aircraft unsafe to fly. The CG of the loaded aircraft
must be within these limits at takeoff, in the air, and on landing.
A vertical plane perpendicular to the aircraft longitudinal axis from
which fore and aft (usually aft) measurements are made for weight and
balance purposes.
That portion of the engine oil which can be drained from the engine.
The aircraft weight with fixed ballast, unusable fuel, engine oil, engine
coolant, hydraulic fluid, and in other respects as required by applicable
regulatory standards.
The weight of the aircraft at landing touchdown.
The largest weight allowed by design, structural, performance or other
limitations.
A measure of the rotational tendency of a weight, about a specified
line, mathematically equal to the product of the weight and the arm.
Weights corresponding to the aircraft as offered with seating and inte-
rior, avionics, accessories, fixed ballast and other equipment specified
by the manufacturer as composing a standard aircraft.
The longitudinal distance from some point to the zero datum or zero
fuselage station.
The weight of the aircraft at liftoff.
The fuel remaining after consumption of usable fuel.
That portion of the total fuel which is available for consumption as
determined in accordance with applicable regulatory standards.
The difference between the aircraft ramp weight and basic empty
weight.
Degrees
Down
Foot or feet
Foot-pounds
B - 4
