53
Federal Aviation Administration, DOT
Pt. 60, App. A
2.b.3.
.............
Yaw Control
....................
For underdamped systems:
±
10% of time from 90% of
initial displacement (0.9
A
d
) to first zero crossing,
and
±
10 (n+1)% of period
thereafter.
±
10% ampli-
tude of first overshoot ap-
plied to all overshoots
greater than 5% of initial
displacement (.05 A
d
).
±
1
overshoot (first significant
overshoot must be
matched). For over-
damped systems:
±
10% of
time from 90% of initial
displacement (0.9 A
d
) to
10% of initial displace-
ment (0.1 A
d
). For the al-
ternate method (see para-
graph 4 of this attach-
ment). The slow sweep is
the equivalent to the static
test 2.a.3. For the mod-
erate and rapid sweeps:
±
2 lb (0.9 daN) or
±
10%
dynamic increment above
the static force.
Takeoff, Cruise, and
Landing.
Data must show normal control displace-
ment in both directions. Tolerance ap-
plies against the absolute values of
each period (considered independ-
ently). Normal control displacement for
this test is 25% to 50% of the max-
imum allowable yaw controller deflec-
tion for flight conditions limited by the
maneuvering load envelope.
X
X
‘‘n’’ is the sequential
period of a full cycle
of oscillation. Refer
to paragraph 4 of
this attachment for
more information.
Static and dynamic
flight control tests
should be accom-
plished at the same
feel or impact pres-
sures.
2.b.4.
.............
Small Control Inputs—
Pitch.
±
0.15
°
/sec body pitch rate or
±
20% of peak body pitch
rate applied throughout
the time history.
Approach
or
landing
....
Control inputs must be typical of minor
corrections made while established on
an ILS approach course, using from
0.5
°
/sec to 2
°
/sec pitch rate. The test
must be in both directions, showing
time history data from 5 seconds be-
fore until at least 5 seconds after initi-
ation of control input.
CCA: Test in normal and non-normal
control states.
X X
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