347 

Federal Aviation Administration, DOT 

Pt. 60, App. C 

2.a.5. ..........

Control Dynamics (all axes) ..

±

10% of time for first zero 

crossing and 

±

10 (N + 1)% 

of period thereafter, 

±

10% 

of amplitude of first over-
shoot, 20% of amplitude of 
2nd and subsequent over-
shoots greater than 5% of 
initial displacement, 

±

1 

overshoot. 

Hover/Cruise, Trim On, Fric-

tion Off. 

Results must be recorded for 

a normal control displace-
ment in both directions in 
each axis. 

X 

X  Typically, control displace-

ment of 25% to 50% is 
necessary for proper exci-
tation. Control Dynamics 
for irreversible control sys-
tems may be evaluated in 
a ground/static condition. 
Additional information on 
control dynamics is found 
later in this attachment. 
‘‘N’’ is the sequential period 
of a full cycle of oscillation. 

2.a.6. ..........

Control System Freeplay .......

±

0.10 inches (

±

2.5 mm). 

Ground; Static conditions; 

with the hydraulic system 
(if applicable) pressurized; 
supplemental hydraulic 
pressurization system may 
be used. 

Record and compare results 

for all controls. 

X 

X 

X  Flight Test Data for this test 

does not require the rotor 
to be engaged/turning. 

2.b. .............

Low Airspeed Handling Qualities 

2.b.1. ..........

Trimmed Flight Control Posi-

tions. 

Torque—

±

3%, Pitch Atti-

tude—

±

1.5

°

, Bank Atti-

tude—

±

2

°

, Longitudinal 

Control Position—

±

5%. 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%. 

Translational Flight IGE— 

Sideward, rearward, and 
forward flight. Augmenta-
tion On and Off. 

Record results for several air-

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

X X 

2.b.2. ..........

Critical Azimuth .....................

Torque—

±

3%, Pitch Atti-

tude—

±

1.5

°

, Bank Atti-

tude—

±

2

°

, Longitudinal 

Control Position—

±

5%, 

Lateral Control Position— 

±

5%, Directional Control 

Position—

±

5%, Collective 

Control Position—

±

5%. 

Stationary Hover. Augmenta-

tion On and Off. 

Record results for three rel-

ative wind directions (in-
cluding the most critical 
case) in the critical quad-
rant. May be a series of 
snapshot tests. 

X X 

2.b.3. ..........

Control Response 

2.b.3.a. .......

Longitudinal ...........................

Pitch Rate—

±

10% or 

±

2

°

/ 

sec., Pitch Attitude 
Change—

±

10% or 1.5

°

. 

Hover Augmentation On and 

Off. 

Record results for a step con-

trol input. The Off-axis re-
sponse must show correct 
trend for unaugmented 
cases. 

X 

X  This is a ‘‘short time’’ test 

conducted in a hover, in 
ground effect, without en-
tering translational flight, to 
provide better visual ref-
erence. 

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