49
Federal Aviation Administration, DOT
Pt. 60, App. A
2.a.1.a.
..........
Pitch Controller Position
vs. Force and Surface
Position Calibration.
±
2 lb (0.9 daN) breakout,
±
10% or
±
5 lb (2.2 daN)
force,
±
2
°
elevator.
Ground
.........................
Record results for an uninterrupted con-
trol sweep to the stops.
X
X
X
X
Test results should be
validated (where
possible) with in-
flight data from tests
such as longitudinal
static stability or
stalls. Static and dy-
namic flight control
tests should be ac-
complished at the
same feel or impact
pressures.
2.a.1.b.
..........
(Reserved)
2.a.2.a.
..........
Roll Controller Position
vs. Force and Surface
Position Calibration.
±
2 lb (0.9 daN) breakout,
±
10% or
±
3 lb (1.3 daN)
force,
±
2
°
aileron,
±
3
°
spoiler angle.
Ground
.........................
Record results for an uninterrupted con-
trol sweep to the stops.
X
X
X
X
Test results should be
validated with in-
flight data from tests
such as engine out
trims, or steady
state sideslips. Stat-
ic and dynamic flight
control tests should
be accomplished at
the same feel or im-
pact pressures.
2.a.2.b.
..........
(Reserved)
2.a.3.a.
..........
Rudder Pedal Position
vs. Force and Surface
Position Calibration.
±
5 lb (2.2 daN) breakout,
±
10% or
±
5 lb (2.2 daN)
force,
±
2
°
rudder angle.
Ground
.........................
Record results for an uninterrupted con-
trol sweep to the stops.
X
X
X
X
Test results should be
validated with in-
flight data from tests
such as engine out
trims, or steady
state sideslips. Stat-
ic and dynamic flight
control tests should
be accomplished at
the same feel or im-
pact pressures.
2.a.3.b.
..........
(Reserved)
2.a.4.
.............
Nosewheel Steering Con-
troller Force and Posi-
tion Calibration.
±
2 lb (0.9 daN) breakout,
±
10% or
±
3 lb (1.3 daN)
force,
±
2
°
nosewheel
angle.
Ground
.........................
Record results of an uninterrupted con-
trol sweep to the stops.
X X X X
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