343 

Federal Aviation Administration, DOT 

Pt. 60, App. C 

Performance and Trimmed 

Flight Control Positions. 

Torque—

±

3%, Pitch Atti-

tude—

±

1.5

°

, Sideslip 

Angle—

±

2

°

, Longitudinal 

Control Position—

±

5%, 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%. 

Cruise (Augmentation On and 

Off). 

Record results for two gross 

weight and CG combina-
tions with varying trim 
speeds throughout the air-
speed envelope. May be a 
series of snapshot tests. 

X 

X 

X  This test validates perform-

ance at speeds above 
maximum endurance air-
speed. 

1.g. .............

Climb 

Performance and Trimmed 

Flight Control Positions. 

Vertical Velocity—

±

100 fpm 

(6.1m/sec) or 

±

10%, Pitch 

Attitude—

±

1.5

°

, Sideslip 

Angle—

±

2

°

, Longitudinal 

Control Position—

±

5%, 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%. 

All engines operating; One 

engine inoperative; Aug-
mentation System(s) On 
and Off. 

Record results for two gross 

weight and CG combina-
tions. The data presented 
must be for normal climb 
power conditions. May be a 
series of snapshot tests. 

X X X 

1.h. .............

Descent 

1.h.1. ..........

Descent Performance and 

Trimmed Flight Control Po-
sitions. 

Torque—

±

3%, Pitch Atti-

tude—

±

1.5

°

, Sideslip 

Angle—

±

2

°

, Longitudinal 

Control Position—

±

5%, 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%. 

At or near 1,000 fpm (5 m/ 

sec) rate of descent (RoD) 
at normal approach speed. 
Augmentation System(s) 
On and Off. 

Results must be recorded for 

two gross weight and CG 
combinations. May be a 
series of snapshot tests. 

X X X 

1.h.2. ..........

Autorotation Performance 

and Trimmed Flight Control 
Positions. 

Pitch Attitude—

±

1.5

°

, Sideslip 

Angle—

±

2

°

, Longitudinal 

Control Position—

±

5%, 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%, 

Vertical Velocity—

±

100 fpm 

or 10%, Rotor Speed— 

±

1.5%. 

Steady descents. Augmenta-

tion System(s) On and Off. 

Record results for two gross 

weight conditions. Data 
must be recorded for nor-
mal operating RPM. (Rotor 
speed tolerance applies 
only if collective control po-
sition is full down.) Data 
must be recorded for 
speeds from 50 kts, 

±

5 kts, 

through at least maximum 
glide distance airspeed, or 
maximum allowable auto-
rotation airspeed, which-
ever is slower. May be a 
series of snapshot tests. 

X X X 

1.i. ...............

Autorotation 

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