Federal Aviation Administration, DOT

Pt. 60, App. C

TABLE C3D - FUNCTIONS AND SUBJECTIVE TESTS - Continued
QPS requirements
Motion system (and special
aerodynamic model) effects

C

D

9. ..............

Tire failure dynamics:
Procedure: Simulate a single tire failure and a
multiple tire failure

X

X

10. ............

Engine malfunction and engine damage:
Procedure: The characteristics of an engine
malfunction as prescribed in the malfunction
definition document for the particular flight
simulator must describe the special motion
effects felt by the pilot. Note the associated
engine instruments varying according to the
nature of the malfunction and note the replication of the effects of the airframe vibration

X

X

X

11. ............

Tail boom strikes:
Procedure: Tail-strikes can be checked by
over-rotation of the helicopter at a quick
stop or autorotation to the ground

X

X

X

The motion effect should be felt as a noticeable nose down pitching moment.

12. ............

Vortex Ring State (Settling with Power):
Procedure: Specific procedures may differ between helicopters and may be prescribed by
the Helicopter Manufacturer or other subject
matter expert. However, the following information is provided for illustrative purposes
* * * To enter the maneuver, reduce power
below hover power. Hold altitude with aft cyclic until the airspeed approaches 20 knots.
Then allow the sink rate to increase to 300
feet per minute or more as the attitude is
adjusted to obtain an airspeed of less than
10 knots

X

X

When the aircraft begins to shudder, the application of additional up collective increases
the vibration and sink rate. One recovery
method is to decrease collective to enter
vertical autorotation and/or use cyclic inputs
to gain horizontal airspeed and exit from
vortex ring state.

13. ............

Retreating Blade Stall:
Procedure: Specific procedures may differ between helicopters and may be prescribed by
the Helicopter Manufacturer or other subject
matter expert. However, the following information is provided for illustrative purposes:
To enter the maneuver, increase forward
airspeed; the effect will be recognized
through the development of a low frequency
vibration, pitching up of the nose, and a roll
in the direction of the retreating blade. High
weight, low rotor RPM, high density altitude,
turbulence or steep, abrupt turns are all conducive to retreating blade stall at high forward airspeeds

X

X

Correct recovery from retreating blade stall requires the collective to be lowered first,
which reduces blade angles and the angle
of attack. Aft cyclic can then be used to
slow the helicopter.

Entry No.

kpayne on VMOFRWIN702 with $$_JOB

Information
Simulator level
Notes
B

The pilot may notice some yawing with a multiple tire failure selected on the same side.
This should require the use of the pedal to
maintain control of the helicopter. Dependent on helicopter type, a single tire failure
may not be noticed by the pilot and may not
cause any special motion effect. Sound or
vibration may be associated with the actual
tire losing pressure.

403

VerDate Sep<11>2014

16:30 Jun 25, 2019

Jkt 247047

PO 00000

Frm 00413

Fmt 8010

Sfmt 8002

Q:\14\14V2.TXT

PC31