227
Federal Aviation Administration, DOT
Pt. 60, App. C
2.a.5.
..........
Control Dynamics (all axes)
..
±
10% of time for first zero
crossing and
±
10 (N+1)%
of period thereafter,
±
10%
of amplitude of first over-
shoot, 20% of amplitude of
2nd and subsequent over-
shoots greater than 5% of
initial displacement,
±
1
overshoot.
Hover/Cruise, Trim On, Fric-
tion Off.
Results must be recorded for
a normal control displace-
ment in both directions in
each axis.
X
X
Typically, control displace-
ment of 25% to 50% is
necessary for proper exci-
tation. Control Dynamics
for irreversible control sys-
tems may be evaluated in
a ground/static condition.
Additional information on
control dynamics is found
later in this attachment.
‘‘N’’ is the sequential period
of a full cycle of oscillation.
2.a.6.
..........
Control System Freeplay
.......
±
0.10 inches (
±
2.5 mm).
Ground; Static conditions;
with the hydraulic system
(if applicable) pressurized;
supplemental hydraulic
pressurization system may
be used.
Record and compare results
for all controls.
X
X
X
Flight Test Data for this test
does not require the rotor
to be engaged/turning.
2.b.
.............
Low Airspeed Handling Qualities
2.b.1.
..........
Trimmed Flight Control Posi-
tions.
Torque—
±
3%, Pitch Atti-
tude—
±
1.5
°
, Bank Atti-
tude—
±
2
°
, Longitudinal
Control Position—
±
5%.
Lateral Control Position—
±
5%, Directional Control
Position—
±
5%, Collective
Control Position—
±
5%.
Translational Flight IGE—
Sideward, rearward, and
forward flight. Augmenta-
tion On and Off.
Record results for several air-
speed increments to the
translational airspeed limits
and for 45 kts. forward air-
speed. May be a series of
snapshot tests.
X X
2.b.2.
..........
Critical Azimuth
.....................
Torque—
±
3%, Pitch Atti-
tude—
±
1.5
°
, Bank Atti-
tude—
±
2
°
, Longitudinal
Control Position—
±
5%,
Lateral Control Position—
±
5%, Directional Control
Position—
±
5%, Collective
Control Position—
±
5%.
Stationary Hover. Augmenta-
tion On and Off.
Record results for three rel-
ative wind directions (in-
cluding the most critical
case) in the critical quad-
rant. May be a series of
snapshot tests.
X X
2.b.3.
..........
Control Response
2.b.3.a.
.......
Longitudinal
...........................
Pitch Rate—
±
10% or
±
2
°
/
sec., Pitch Attitude
Change—
±
10% or 1.5
°
.
Hover Augmentation On and
Off.
Record results for a step con-
trol input. The Off-axis re-
sponse must show correct
trend for unaugmented
cases.
X
X
This is a ‘‘short time’’ test
conducted in a hover, in
ground effect, without en-
tering translational flight, to
provide better visual ref-
erence.
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