Specifications

INTRODUCTION
MODEL 560
True Airspeed (KTAS): The airspeed (knots) of an airplane relative to undisturbed air.
UHF: Ultra High Frequency
Unusable Fuel: Fuel remaining after fuel runout tests have been completed in
accordance with governmental regulations.
U.S.: United States
Usable Fuel: Fuel available for flight planning.
USB: Upper Side Band
V
1
: Takeoff decision speed. The distance to continue the takeoff to 35
feet will not exceed the scheduled takeoff field length if recognition
occurred at V
1
(accelerate-go). The distance to bring the airplane
to a full stop (accelerate-stop) will not exceed the scheduled takeoff
field length provided that the brakes are applied at V
1
.
V
2
: Takeoff safety speed. This climb speed is the actual speed at 35
feet above the runway surface as demonstrated in flight during
takeoff with one engine inoperative.
V
35
: This climb speed is the actual speed at 35 feet above the runway
surface as demonstrated in flight during takeoff with both engines
operating.
V
A
: The maneuvering speed is the maximum speed at which application
of full available aerodynamic control will not overstress the airplane.
V
APP
: The landing approach airspeed (1.3 VS
1
) with 15-degree flap
position, landing gear UP.
V
ENR
: Single-engine enroute climb speed.
V
FE
: Maximum flap extended speed. The highest speed permissible with
wing flaps in a prescribed extended position.
V
LE
: Maximum landing gear extended speed. The maximum speed at
which an airplane can safely be flown with the landing gear
extended.
V
LO
: Maximum landing gear operating speed. The maximum speed at
which the landing gear can be safely extended or retracted. The
Model 560 has different V
L0
speeds for extension and retraction.
V
MCA
: Minimum airspeed in flight at which directional control can be
maintained, when one engine is suddenly made inoperative. V
MC
A
is a function of engine thrust which varies with altitude and
temperature. The V
MCA
presented in Section I was determined for
maximum thrust. V
MCA
= 86 KIAS.
V
MCG
: Minimum airspeed on the ground at which directional control can be
maintained, when one engine is suddenly made inoperative, using
only aerodynamic controls. V
MCG
is a function of engine thrust
which varies with altitude and temperature. The V
MC
G
presented in
Section I was determined for maximum thrust.
7° Flaps, V
MCG
= 96 KIAS.
15° Flaps, V
MCG
= 92 KIAS.
V
MCL
: Minimum airspeed in the air, in the landing configuration, at which
directional control can be maintained, when one engine is suddenly
made inoperative. V
MCL
is a function of engine thrust which varies
with altitude and temperature. The V
MCL
is 88 KIAS at maximum
takeoff thrust.
I 56OMB-01 Configuration AA Introduction-11