60
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
2.e.3.
.............
Crosswind Landing
.........
±
3 kt airspeed,
±
1.5
°
pitch
angle,
±
1.5
°
angle of at-
tack,
±
10% or
±
10 ft (3 m)
height
±
2
°
bank angle,
±
2
°
sideslip angle
±
3
°
heading
angle. Additionally, for
those simulators of air-
planes with reversible
flight control systems:
±
10% or
±
3 lb (1.3 daN)
wheel force
±
10% or
±
5 lb
(2.2 daN) rudder pedal
force.
Landing
........................
Record results from a minimum of 200 ft
(61 m) AGL, through nosewheel
touch-down, to 50% decrease in main
landing gear touchdown speed. Test
data must include information on wind
profile, for a crosswind (expressed as
direct head-wind and direct cross-wind
components) of 60% of the maximum
wind measured at 33 ft (10 m) above
the runway.
X
X
X
In those situations
where a maximum
crosswind or a max-
imum demonstrated
crosswind is not
known, contact the
NSPM.
2.e.4.
.............
One Engine Inoperative
Landing.
±
3 kt airspeed,
±
1.5
°
pitch
angle,
±
1.5
°
angle of at-
tack,
±
10% height or
±
10
ft (3 m);
±
2
°
bank angle,
±
2
°
sideslip angle,
±
3
°
heading.
Landing
........................
Record results from a minimum of 200 ft
(61 m) AGL, through nosewheel
touch-down, to 50% decrease in main
landing gear touchdown speed or less.
X X X
2.e.5.
.............
Autopilot landing (if appli-
cable).
±
5 ft (1.5 m) flare height,
±
0.5 sec T
f
, or
±
10%T
f
,
±
140 ft/min (0.7 m/sec)
rate of descent at touch-
down.
±
10 ft (3 m) lateral
deviation during rollout.
Landing
........................
If autopilot provides rollout guidance,
record lateral deviation from touch-
down to a 50% decrease in main land-
ing gear touchdown speed or less.
Time of autopilot flare mode engage
and main gear touchdown must be
noted.
X
X
X
See Appendix F of this
part for definition of
T
f
.
2.e.6.
.............
All engines operating,
autopilot, go around.
±
3 kt airspeed,
±
1.5
°
pitch
angle,
±
1.5
°
angle of at-
tack.
Normal, all-engines-operating, go around
with the autopilot engaged (if applica-
ble) at medium landing weight.
CCA: Test in normal or non-normal con-
trol states.
X X X
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