447 

Federal Aviation Administration, DOT 

Pt. 60, App. D 

2.a.2. .....................

Collective and Pedals ...

Breakout—

±

0.5 lb (0.224 daN) or 

25%. Force—

±

1.0 lb (0.224 

daN) or 10%.

Ground; Static condi-

tions. Trim On and 
Off. Friction Off. 
Augmentation On 
and Off.

Record results for an uninter-

rupted control sweep to the 
stops.

X X X 

2.a.3. .....................

Brake Pedal Force vs. 

Position.

±

5 lbs (2.224 daN) or 10% ..........

Ground; Static condi-

tions.

.......................................................

X X X 

2.a.4. .....................

Trim System Rate (all 

applicable systems).

Rate—

±

10% .................................

Ground; Static condi-

tions. Trim On. 
Friction Off.

The tolerance applies to the re-

corded value of the trim rate.

X X X 

2.a.5. .....................

Control Dynamics (all 

axes).

±

10% of time for first zero cross-

ing and 

±

10 (N + 1)% of period 

thereafter. 

±

10% of amplitude 

of first overshoot. 

±

20% of am-

plitude of 2nd and subsequent 
overshoots greater than 5% of 
initial displacement. 

±

1 over-

shoot.

Hover/Cruise Trim 

On Friction Off.

Results must be recorded for a 

normal control displacement in 
both directions in each axis, 
using 25% to 50% of full throw.

X 

X  Control Dynamics for irre-

versible control systems 
may be evaluated in a 
ground/static condition. 
Refer to paragraph 3 of 
this attachment for addi-
tional information. ‘‘N’’ is 
the sequential period of a 
full cycle of oscillation. 

2.a.6. .....................

Freeplay ........................

±

0.10 in. (

±

2.5 mm) ......................

Ground; Static condi-

tions.

Record and compare results for 

all controls.

X X X 

2.b. ........................

Low Airspeed Handling Qualities. 

2.b.1. .....................

Trimmed Flight Control 

Positions.

Torque 

±

3% Pitch Attitude 

±

1.5

° 

Bank Attitude 

±

2

° 

Longitudinal 

Control Position 

±

5% Lateral 

Control Position 

±

5% Direc-

tional Control Position 

±

5% 

Collective Control Position 

±

5%.

Translational Flight 

IGE—Sideward, 
rearward, and for-
ward flight. Aug-
mentation On and 
Off.

Record results for several air-

speed increments to the 
translational airspeed limits and 
for 45 kts. forward airspeed. 
May be a series of snapshot 
tests.

X 

2.b.2. .....................

Critical Azimuth .............

Torque 

±

3% Pitch Attitude 

±

1.5

°

, 

Bank Attitude 

±

2

°

, Longitudinal 

Control Position 

±

5%, Lateral 

Control Position 

±

5%, Direc-

tional Control Position 

±

5%, 

Collective Control Position 

±

5%.

Stationary Hover. 

Augmentation On 
and Off.

Record results for three relative 

wind directions (including the 
most critical case) in the critical 
quadrant. May be a series of 
snapshot tests.

X 

2.b.3. .....................

Control Response. 

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