225 

Federal Aviation Administration, DOT 

Pt. 60, App. C 

1.j.3.

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

Balked Landing

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

Airspeed—

±

3 kts, Altitude— 

±

20 ft. (6.1m), Torque— 

±

3%, Rotor Speed—

±

1.5%, 

Pitch Attitude—

±

1.5

°

, Bank 

Attitude—

±

1.5

°

, Heading— 

±

2

°

, Longitudinal Control 

Position—

±

10%, Lateral 

Control Position—

±

10%, 

Directional Control Posi-

tion—

±

10%, Collective 

Control Position—

±

10%. 

Approach

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

Record the results for the 

maneuver initiated from a 

stabilized approach at the 

landing decision point 

(LDP). 

X X X 

1.j.4.

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

Autorotational Landing. 

Torque—

±

3%, Rotor 

Speed—

±

3%, Vertical Ve-

locity—

±

100 fpm (0.50m/ 

sec) or 10%, Pitch Atti-

tude—

±

2

°

, Bank Attitude— 

±

2

°

, Heading—

±

5

°

, Longi-

tudinal Control Position— 

±

10%, Lateral Control Posi-

tion—

±

10%, Directional 

Control Position—

±

10%, 

Collective Control Posi-

tion—

±

10%. 

Landing

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

Record the results of an 

autorotational deceleration 

and landing from a sta-

bilized autorotational de-

scent, to touch down. If 

flight test data containing 

all required parameters for 

a complete power-off land-

ing is not available from 

the aircraft manufacturer 

for this test and other quali-

fied flight test personnel 

are not available to acquire 

this data, the sponsor may 

coordinate with the NSPM 

to determine if it is appro-

priate to accept alternative 

testing means. 

X 

X 

Alternative approaches for 

acquiring this data may be 

acceptable, depending on 

the aircraft as well as the 

personnel and the data re-

cording, reduction, and in-

terpretation facilities to be 

used, are: (1) a simulated 

autorotational flare and re-

duction of rate of descent 

(ROD) at altitude; or (2) a 

power-on termination fol-

lowing an autorotational 

approach and flare. 

2. Handling Qualities 

2.a.

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

Control System Mechanical Characteristics 

For simulators requiring Static or Dynamic tests at the controls (i.e., cyclic, collective, and pedal), special test fixtures w

ill not 

be required during initial or upgrade evaluations if the sponsor’s QTG/MQTG shows both test fixture results and the results of 

an alternative approach, such as computer plots produced concurrently showing satisfactory agreement. Repeat of the alter-

native method during the initial or upgrade evaluation satisfies this test requirement. For initial and upgrade evaluations, th

e 

control dynamic characteristics must be measured at and recorded directly from the flight deck controls, and must be accom-

plished in hover, climb, cruise, and autorotation. 

Contact the NSPM for clari-

fication of any issue re-

garding helicopters with re-

versible controls or where 

the required validation data 

is not attainable. 

VerDate Mar<15>2010 

20:48 Jan 30, 2014

Jkt 232047

PO 00000

Frm 00235

Fmt 8010

Sfmt 8002

Q:\14\14V2.TXT

ofr150

PsN: PC150