55 

Federal Aviation Administration, DOT 

Pt. 60, App. A 

2.c.1.

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

Power Change Dynamics 

±

3 kt airspeed, 

±

100 ft (30 

m) altitude, 

±

20% or 

±

1.5

° 

pitch angle.

Approach

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

Power is changed from the thrust setting 

required for approach or level flight to 

maximum continuous thrust or go- 

around power setting. Record the un-

controlled free response from at least 

5 seconds before the power change is 

initiated to 15 seconds after the power 

change is completed.

CCA: Test in normal and non-normal 

control states. 

X X X X 

2.c.2.

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

Flap/Slat Change Dy-

namics.

±

3 kt airspeed, 

±

100 ft (30 

m) altitude, 

±

20% or 

±

1.5

° 

pitch angle.

Takeoff through initial 

flap retraction, and 

approach to landing.

Record the uncontrolled free response 

from at least 5 seconds before the 

configuration change is initiated to 15 

seconds after the configuration change 

is completed.

CCA: Test in normal and non-normal 

control states. 

X X X X 

2.c.3.

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

Spoiler/Speedbrake 

Change Dynamics.

±

3 kt airspeed, 

±

100 ft (30 

m) altitude, 

±

20% or 

±

1.5

° 

pitch angle.

Cruise

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

Record the uncontrolled free response 

from at least 5 seconds before the 

configuration change is initiated to 15 

seconds after the configuration change 

is completed. Record results for both 

extension and retraction.

CCA: Test in normal and non-normal 

control states. 

X X X X 

2.c.4.

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

Gear Change Dynamics

±

3 kt airspeed, 

±

100 ft (30 

m) altitude, 

±

20% or 

±

1.5

° 

pitch angle.

Takeoff (retraction), 

and Approach (ex-

tension).

Record the time history of uncontrolled 

free response for a time increment 

from at least 5 seconds before the 

configuration change is initiated to 15 

seconds after the configuration change 

is completed.

CCA: Test in normal and non-normal 

control states. 

X X X X 

2.c.5.

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

Longitudinal Trim

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

±

0.5

° 

trim surface angle, 

±

1

° 

elevator, 

±

1

° 

pitch angle, 

±

5% net thrust or equiva-

lent.

Cruise, Approach, and 

Landing.

Record steady-state condition with wings 

level and thrust set for level flight. May 

be a series of snapshot tests.

CCA: Test in normal or non-normal con-

trol states. 

X X X X 

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