403 

Federal Aviation Administration, DOT 

Pt. 60, App. C 

T

ABLE

C3D—F

UNCTIONS AND

S

UBJECTIVE

T

ESTS

—Continued 

QPS requirements 

Information 

Entry No. 

Motion system (and special 

aerodynamic model) effects 

Simulator level 

Notes 

B C D 

9. ..............

Tire failure dynamics: 

Procedure: Simulate a single tire failure and a 

multiple tire failure 

X 

X 

The pilot may notice some yawing with a mul-

tiple tire failure selected on the same side. 
This should require the use of the pedal to 
maintain control of the helicopter. Depend-
ent 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. 

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 rep-
lication of the effects of the airframe vibra-
tion 

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 notice-

able nose down pitching moment. 

12. ............

Vortex Ring State (Settling with Power): 

Procedure: Specific procedures may differ be-

tween helicopters and may be prescribed by 
the Helicopter Manufacturer or other subject 
matter expert. However, the following infor-
mation is provided for illustrative purposes 
* * * To enter the maneuver, reduce power 
below hover power. Hold altitude with aft cy-
clic 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 appli-

cation 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 be-

tween helicopters and may be prescribed by 
the Helicopter Manufacturer or other subject 
matter expert. However, the following infor-
mation 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 con-
ducive to retreating blade stall at high for-
ward airspeeds 

X 

X 

Correct recovery from retreating blade stall re-

quires 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. 

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