345 

Federal Aviation Administration, DOT 

Pt. 60, App. C 

1.j.3. ............

Balked Landing ......................

Airspeed—

±

3 kts, Altitude— 

±

20 ft. (6.1m), Torque— 

±

3%, Rotor Speed—

±

1.5%, 

Pitch Attitude—

±

1.5

°

, Bank 

Attitude—

±

1.5

°

, Heading— 

±

2

°

, Longitudinal Control 

Position—

±

10%, Lateral 

Control Position—

±

10%, 

Directional Control Posi-
tion—

±

10%, Collective 

Control Position—

±

10%. 

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

Record the results for the 

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

X X X 

1.j.4. ............

Autorotational Landing. 

Torque—

±

3%, Rotor 

Speed—

±

3%, Vertical Ve-

locity—

±

100 fpm (0.50m/ 

sec) or 10%, Pitch Atti-
tude—

±

2

°

, Bank Attitude— 

±

2

°

, Heading—

±

5

°

, Longi-

tudinal Control Position— 

±

10%, Lateral Control Posi-

tion—

±

10%, Directional 

Control Position—

±

10%, 

Collective Control Posi-
tion—

±

10%. 

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

Record the results of an 

autorotational deceleration 
and landing from a sta-
bilized autorotational de-
scent, to touch down. If 
flight test data containing 
all required parameters for 
a complete power-off land-
ing is not available from 
the aircraft manufacturer 
for this test and other quali-
fied flight test personnel 
are not available to acquire 
this data, the sponsor may 
coordinate with the NSPM 
to determine if it is appro-
priate to accept alternative 
testing means. 

X 

X  Alternative approaches for 

acquiring this data may be 
acceptable, depending on 
the aircraft as well as the 
personnel and the data re-
cording, reduction, and in-
terpretation facilities to be 
used, are: (1) a simulated 
autorotational flare and re-
duction of rate of descent 
(ROD) at altitude; or (2) a 
power-on termination fol-
lowing an autorotational 
approach and flare. 

2. Handling Qualities 

2.a. .............

Control System Mechanical Characteristics 

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 alter-
native 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 accom-
plished in hover, climb, cruise, and autorotation. 

Contact the NSPM for clari-

fication of any issue re-
garding helicopters with re-
versible controls or where 
the required validation data 
is not attainable. 

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