kpayne on VMOFRWIN702 with $$_JOB

VerDate Sep<11>2014
Hover/Cruise, Trim On, Friction Off.

Results must be recorded for
a normal control displacement in both directions in
each axis.

PO 00000

2.a.6. ..........

Control System Freeplay .......

Section0.10 inches (Section2.5 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.

2.b. .............

Low Airspeed Handling Qualities

2.b.1. ..........

Trimmed Flight Control Positions.

Torque - Section3%, Pitch Attitude - Section1.5Section, Bank Attitude - Section2Section, Longitudinal
Control Position - Section5%.
Lateral Control Position - 
Section5%, Directional Control
Position - Section5%, Collective
Control Position - Section5%.

Translational Flight IGE - 
Sideward, rearward, and
forward flight. Augmentation On and Off.

2.b.2. ..........

Critical Azimuth .....................

Torque - Section3%, Pitch Attitude - Section1.5Section, Bank Attitude - Section2Section, Longitudinal
Control Position - Section5%,
Lateral Control Position - 
Section5%, Directional Control
Position - Section5%, Collective
Control Position - Section5%.

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

Control Response

2.b.3.a. .......

Longitudinal ...........................

Pitch Rate - Section10% or Section2Section/
sec., Pitch Attitude
Change - Section10% or 1.5Section.

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PC31

X

X

Typically, control displacement of 25% to 50% is
necessary for proper excitation. Control Dynamics
for irreversible control systems 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.

X

X

Flight Test Data for this test
does not require the rotor
to be engaged/turning.

Record results for several airspeed increments to the
translational airspeed limits
and for 45 kts. forward airspeed. May be a series of
snapshot tests.

X

X

Stationary Hover. Augmentation On and Off.

Record results for three relative wind directions (including the most critical
case) in the critical quadrant. May be a series of
snapshot tests.

X

X

Hover Augmentation On and
Off.

Record results for a step control input. The Off-axis response must show correct
trend for unaugmented
cases.

X

X

X

This is a  - short time -  test
conducted in a hover, in
ground effect, without entering translational flight, to
provide better visual reference.

Pt. 60, App. C

Section10% of time for first zero
crossing and Section10 (N + 1)%
of period thereafter, Section10%
of amplitude of first overshoot, 20% of amplitude of
2nd and subsequent overshoots greater than 5% of
initial displacement, Section1
overshoot.

Jkt 247047

Control Dynamics (all axes) ..

Federal Aviation Administration, DOT

16:30 Jun 25, 2019

2.a.5. ..........