444 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 60, App. D 

T

ABLE

D2A—F

LIGHT

T

RAINING

D

EVICE

(FTD) O

BJECTIVE

T

ESTS

—Continued 

QPS requirements 

Information 

Test 

Tolerances 

Flight conditions 

Test details 

FTD level 

Notes 

Entry No. 

Title 

5 6 7 

Performance and 

Trimmed Flight Con-
trol Positions.

Vertical Velocity—

±

100 fpm (61 

m/sec) or 

±

10% Pitch Atti-

tude—

±

1.5

° 

Sideslip Angle— 

±

2

° 

Longitudinal Control Posi-

tion—

±

5% Lateral Control Posi-

tion—

±

5% Directional Control 

Position—

±

5% Collective Con-

trol Position—

±

5%.

All engines operating 
One engine inoper-

ative.

Augmentation Sys-

tem(s) On and Off.

Record results for two gross 

weight and CG combinations. 
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 Positions.

Torque—

±

3% Pitch Attitude— 

±

1.5

° 

Sideslip Angle—

±

2

° 

Lon-

gitudinal Control Position—

±

5% 

Lateral Control Position—

±

5% 

Directional Control Position— 

±

5% Collective Control Posi-

tion—

±

5%.

At or near 1,000 fpm 

(5 m/sec) rate of 
descent (RoD) at 
normal approach 
speed.

Augmentation Sys-

tem(s) On and Off.

Record results for two gross 

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

X X X 

1.h.2. .....................

Autorotation Perform-

ance and Trimmed 
Flight Control Posi-
tions.

Pitch Attitude—

±

1.5

° 

Sideslip 

Angle—

±

2

° 

Longitudinal Con-

trol Position—

±

5% Lateral Con-

trol Position—

±

5% Directional 

Control Position—

±

5% Collec-

tive Control Position—

±

5%.

Steady descents. 

Augmentation Sys-
tem(s) On and Off.

Record results for two gross 

weight conditions. Data must 
be recorded for normal oper-
ating RPM. (Rotor speed toler-
ance applies only if collective 
control position is full down.) 
Data must be recorded for 
speeds from 50 kts, 

±

5 kts 

through at least maximum glide 
distance airspeed. May be a 
series of snapshot tests.

X X X 

1.i. ..........................

Autorotation. 

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