kpayne on VMOFRWIN702 with $$_JOB

VerDate Sep<11>2014
Airspeed - Section3 kts, Altitude - 
Section20 ft. (6.1m), Torque - 
Section3%, Rotor Speed - Section1.5%,
Pitch Attitude - Section1.5Section, Bank
Attitude - Section1.5Section, Heading - 
Section2Section, Longitudinal Control
Position - Section10%, Lateral
Control Position - Section10%,
Directional Control Position - Section10%, Collective
Control Position - Section10%.

Approach ...............................

Record the results for the
maneuver initiated from a
stabilized approach at the
landing decision point
(LDP).

1.j.4. ............

Autorotational Landing.

Torque - Section3%, Rotor
Speed - Section3%, Vertical Velocity - Section100 fpm (0.50m/
sec) or 10%, Pitch Attitude - Section2Section, Bank Attitude - 
Section2Section, Heading - Section5Section, Longitudinal Control Position - 
Section10%, Lateral Control Position - Section10%, Directional
Control Position - Section10%,
Collective Control Position - Section10%.

Landing ..................................

Record the results of an
autorotational deceleration
and landing from a stabilized autorotational descent, to touch down. If
flight test data containing
all required parameters for
a complete power-off landing is not available from
the aircraft manufacturer
for this test and other qualified flight test personnel
are not available to acquire
this data, the sponsor may
coordinate with the NSPM
to determine if it is appropriate to accept alternative
testing means.

Jkt 247047

Balked Landing ......................

X

PO 00000

X

X

X

X

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Sfmt 8002

345

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Alternative approaches for
acquiring this data may be
acceptable, depending on
the aircraft as well as the
personnel and the data recording, reduction, and interpretation facilities to be
used, are: (1) a simulated
autorotational flare and reduction of rate of descent
(ROD) at altitude; or (2) a
power-on termination following an autorotational
approach and flare.

Federal Aviation Administration, DOT

16:30 Jun 25, 2019

1.j.3. ............

Q:\14\14V2.TXT

2. Handling Qualities
2.a. .............

Control System Mechanical Characteristics

PC31

For simulators requiring Static or Dynamic tests at the controls (i.e., cyclic, collective, and pedal), special test fixtures will not
be required during initial or upgrade evaluations if the sponsor-s QTG/MQTG shows both test fixture results and the results of
an alternative approach, such as computer plots produced concurrently showing satisfactory agreement. Repeat of the alternative method during the initial or upgrade evaluation satisfies this test requirement. For initial and upgrade evaluations, the
control dynamic characteristics must be measured at and recorded directly from the flight deck controls, and must be accomplished in hover, climb, cruise, and autorotation.

Contact the NSPM for clarification of any issue regarding helicopters with reversible controls or where
the required validation data
is not attainable.

Pt. 60, App. C