kpayne on VMOFRWIN702 with $$_JOB

VerDate Sep<11>2014
Static Stability ................

Jkt 247047
PC31

X

X

X

X

X

The response for certain
helicopters may be
unrepeatable throughout
the stated time. In these
cases, the test should
show at least that a divergence is identifiable.
For example: Displacing
the cyclic for a given time
normally excites this test
or until a given pitch attitude is achieved and
then return the cyclic to
the original position. For
non-periodic responses,
results should show the
same convergent or divergent character as the
flight test data.

X

X

A control doublet inserted
at the natural frequency
of the aircraft normally
excites this test. However, while input doublets
are preferred over pulse
inputs for AugmentationOff tests, for Augmentation-On cases, when the
short term response exhibits 1st-order or deadbeat characteristics, longitudinal pulse inputs
may produce a more coherent response.

Dynamic Stability.
Long Term Response ...

Section10% of calculated period. Section10%
of time to 1-2 or double amplitude, or Section0.02 of damping ratio.
For non-periodic responses, the
time history must be matched
within Section3Section pitch; and Section5 kts airspeed over a 20 sec period following release of the controls.

Cruise Augmentation
On and Off.

Record results for three full cycles (6 overshoots after input
completed) or that sufficient to
determine time to 1-2 or double
amplitude, whichever is less.
For non-periodic responses, the
test may be terminated prior to
20 sec if the test pilot determines that the results are becoming uncontrollably divergent. Displace the cyclic for
one second or less to excite
the test. The result will be either convergent or divergent
and must be recorded. If this
method fails to excite the test,
displace the cyclic to the predetermined maximum desired
pitch attitude and return to the
original position. If this method
is used, record the results.

2.c.3.b. ...................

Short Term Response ...

Section1.5Section Pitch or Section2Section/sec. Pitch
Rate. Section0.1 g Normal Acceleration.

Cruise or Climb. Augmentation On and
Off.

Record results for at least two airspeeds.

Pt. 60, App. D

X

449

Q:\14\14V2.TXT

Record results for a minimum of
two speeds on each side of the
trim speed. May be a series of
snapshot tests.

2.c.3.a. ...................

Frm 00459
Sfmt 8002

Cruise or Climb.
Autorotation. Augmentation On and
Off.

2.c.3. ......................

PO 00000
Fmt 8010

Longitudinal Control Position:
Section10% of change from trim or
Section0.25 in. (6.3 mm) or Longitudinal Control Force: Section0.5 lb.
(0.223 daN) or Section10%.

Federal Aviation Administration, DOT

16:30 Jun 25, 2019

2.c.2. ......................