kpayne on VMOFRWIN702 with $$_JOB

VerDate Sep<11>2014
Jkt 247047
PO 00000

Ground; Static conditions. Trim On and
Off. Friction Off.
Augmentation On
and Off.

Record results for an uninterrupted control sweep to the
stops.

X

X

X

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

Brake Pedal Force vs.
Position.

Section5 lbs (2.224 daN) or 10% ..........

Ground; Static conditions.

.......................................................

X

X

X

2.a.4. .....................

Trim System Rate (all
applicable systems).

Rate - Section10% .................................

Ground; Static conditions. Trim On.
Friction Off.

The tolerance applies to the recorded value of the trim rate.

X

X

X

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

Control Dynamics (all
axes).

Section10% of time for first zero crossing and Section10 (N + 1)% of period
thereafter. Section10% of amplitude
of first overshoot. Section20% of amplitude of 2nd and subsequent
overshoots greater than 5% of
initial displacement. Section1 overshoot.

Hover/Cruise Trim
On Friction Off.

Results must be recorded for a
normal control displacement in
both directions in each axis,
using 25% to 50% of full throw.

X

X

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

Freeplay ........................

Section0.10 in. (Section2.5 mm) ......................

Ground; Static conditions.

Record and compare results for
all controls.

X

X

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

Low Airspeed Handling Qualities.

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

Trimmed Flight Control
Positions.

Torque Section3% Pitch Attitude Section1.5Section Translational Flight
Bank Attitude Section2Section Longitudinal
IGE - Sideward,
Control Position Section5% Lateral
rearward, and forControl Position Section5% Direcward flight. Augtional Control Position Section5%
mentation On and
Collective Control Position Section5%.
Off.

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

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

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

Torque Section3% Pitch Attitude Section1.5Section, Stationary Hover.
Bank Attitude Section2Section, Longitudinal
Augmentation On
Control Position Section5%, Lateral
and Off.
Control Position Section5%, Directional Control Position Section5%,
Collective Control Position Section5%.

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

X

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

Control Response.

Sfmt 8002

447

Fmt 8010

X

Control Dynamics for irreversible control systems
may be evaluated in a
ground/static condition.
Refer to paragraph 3 of
this attachment for additional information.  - N -  is
the sequential period of a
full cycle of oscillation.

Q:\14\14V2.TXT
PC31

Pt. 60, App. D

Breakout - Section0.5 lb (0.224 daN) or
25%. Force - Section1.0 lb (0.224
daN) or 10%.

Frm 00457

Collective and Pedals ...

Federal Aviation Administration, DOT

16:30 Jun 25, 2019

2.a.2. .....................