50 

14 CFR Ch. I (1–1–14 Edition) 

Pt. 60, App. A 

T

ABLE

A2A—F

ULL

F

LIGHT

S

IMULATOR

(FFS) O

BJECTIVE

T

ESTS

—Continued 

QPS Requirements 

Information 

Test 

Tolerance 

Flight conditions 

Test details 

Simulator level 

Notes 

Entry No. 

Title 

A B 

C 

D 

2.a.5.

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

Rudder Pedal Steering 

Calibration.

±

2

° 

nosewheel 

angle

...........

Ground

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

Record results of an uninterrupted con-

trol sweep to the stops.

X X X X 

2.a.6.

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

Pitch Trim Indicator vs. 

Surface Position Cali-

bration.

±

0.5

° 

of computed trim sur-

face angle.

Ground

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

X 

X 

X 

X 

The purpose of the 

test is to compare 

FFS against design 

data or equivalent. 

2.a.7.

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

Pitch Trim Rate

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

±

10% trim rate (

°

/sec)

..........

Ground 

and 

approach

The trim rate must be checked using the 

pilot primary trim (ground) and using 

the autopilot or pilot primary trim in 

flight at go-around flight conditions.

X X X X 

2.a.8.

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

Alignment of Flight Deck 

Throttle Lever vs. Se-

lected Engine Param-

eter.

±

5

° 

of throttle lever angle, or 

±

3% N1, or 

±

.03 EPR, or 

±

3% maximum rated 

manifold pressure, or 

±

3% 

torque. For propeller-driv-

en airplanes where the 

propeller control levers do 

not have angular travel, a 

tolerance of 

±

0.8 inch (

±

2 

cm.) applies.

Ground

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

Requires simultaneous recording for all 

engines. The tolerances apply against 

airplane data and between engines. In 

the case of propeller powered air-

planes, if a propeller lever is present, 

it must also be checked. For airplanes 

with throttle ‘‘detents,’’ all detents must 

be presented. May be a series of 

snapshot test results.

X X X X 

2.a.9.

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

Brake Pedal Position vs. 

Force and Brake Sys-

tem Pressure Calibra-

tion.

±

5 lb (2.2 daN) or 10% 

force, 

±

150 psi (1.0 MPa) 

or 

±

10% brake system 

pressure.

Ground

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

Hydraulic system pressure must be re-

lated to pedal position through a 

ground static test.

X X X X 

FFS 

computer 

output 

results may be used 

to show compliance. 

2.b.

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

Dynamic Control Tests. 

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

Tests 2.b.1., 2.b.2., and 2.b.3. are not applicable if dynamic response is generated solely by use of airplan

e hardware in the 

FFS. Power setting is that required for level flight unless otherwise specified. 

....

....

....

....

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