44
14 CFR Ch. I (1–1–14 Edition)
Pt. 60, App. A
T
ABLE
A2A—F
ULL
F
LIGHT
S
IMULATOR
(FFS) O
BJECTIVE
T
ESTS
—Continued
QPS Requirements
Information
Test
Tolerance
Flight conditions
Test details
Simulator level
Notes
Entry No.
Title
A B
C
D
1.b.4.
.............
Normal Takeoff
...............
±
3 kts airspeed
±
1.5
°
pitch
angle
±
1.5
°
angle of at-
tack
±
20 ft (6 m) height.
Additionally, for those sim-
ulators of airplanes with
reversible flight control
systems: Stick/Column
Force;
±
10% or
±
5 lb (2.2
daN).
Takeoff
.........................
Record takeoff profile from brake release
to at least 200 ft (61 m) above ground
level (AGL). If the airplane has more
than one certificated takeoff configura-
tions, a different configuration must be
used for each weight. Data are re-
quired for a takeoff weight at near
maximum takeoff weight with a mid-
center of gravity and for a light takeoff
weight with an aft center of gravity, as
defined in Appendix F of this part.
X
X
X
X
This test may be used
for ground accelera-
tion time and dis-
tance (1.b.1.). Plot-
ted data should be
shown using appro-
priate scales for
each portion of the
maneuver.
1.b.5.
.............
Critical Engine Failure on
Takeoff.
±
3 kts airspeed
±
1.5
°
pitch
angle,
±
1.5
°
angle of at-
tack,
±
20 ft (6 m) height,
±
3
°
heading angle,
±
2
°
bank angle,
±
2
°
sideslip
angle. Additionally, for
those simulators of air-
planes with reversible
flight control systems:
Stick/Column Force;
±
10%
or
±
5 lb (2.2 daN)); Wheel
Force;
±
10% or
±
3 lb (1.3
daN); and Rudder Pedal
Force;
±
10% or
±
5 lb (2.2
daN).
Takeoff
.........................
Record takeoff profile at near maximum
takeoff weight from prior to engine fail-
ure to at least 200 ft (61 m) AGL. En-
gine failure speed must be within
±
3
kts of airplane data.
X X X X
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