71 

Federal Aviation Administration, DOT 

Pt. 60, App. A 

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

The visible segment in the 

simulator must be 

±

20% 

of the segment computed 

to be visible from the air-

plane flight deck. This tol-

erance may be applied at 

the far end of the dis-

played segment. However, 

lights and ground objects 

computed to be visible 

from the airplane flight 

deck at the near end of 

the visible segment must 

be visible in the simulator.

Landing configuration, 

with the aircraft 

trimmed for the ap-

propriate airspeed, 

where the MLG are 

at 100 ft (30 m) 

above the plane of 

the touchdown zone, 

while on the elec-

tronic glide slope 

with an RVR value 

set at 1,200 ft (350 

m).

The QTG must contain appropriate cal-

culations and a drawing showing the 

pertinent data used to establish the 

airplane location and the segment of 

the ground that is visible considering 

design eyepoint, the airplane attitude, 

flight deck cut-off angle, and a visibility 

of 1200 ft (350 m) RVR. Simulator 

performance must be measured 

against the QTG calculations. The 

data submitted must include at least 

the following:.

(1) Static airplane dimensions as follows: 

(i) Horizontal and vertical distance from 

main landing gear (MLG) to glideslope 

reception antenna. 

(ii) Horizontal and vertical distance from 

MLG to pilot’s eyepoint. 

(iii) Static flight deck cutoff angle. 

(2) Approach data as follows: 

(i) Identification of runway. 

(ii) Horizontal distance from runway 

threshold to glideslope intercept with 

runway. 

(iii) Glideslope angle. 

(iv) Airplane pitch angle on approach. 

(3) Airplane data for manual testing: 

(i) Gross weight. 

(ii) Airplane configuration. 

(iii) Approach airspeed. If non-homoge-

nous fog is used to obscure visibility, 

the vertical variation in horizontal visi-

bility must be described and be in-

cluded in the slant range visibility cal-

culation used in the computations. 

X X X X 

Pre-position 

for 

this 

test is encouraged 

but may be achieved 

via manual or auto-

pilot control to the 

desired position. 

5. Sound System. 

The sponsor will not be required to repeat the airplane tests (i.e., tests 5.a.1. through 5.a.8. (or 5.b.1. through 5.b.9.) and

 5.c., as appropriate) 

during continuing qualification evaluations if frequency response and background noise test results are within tolerance when c

ompared to 

the initial qualification evaluation results, and the sponsor shows that no software changes have occurred that will affect the

 airplane test re-

sults. If the frequency response test method is chosen and fails, the sponsor may elect to fix the frequency response problem a

nd repeat the 

test or the sponsor may elect to repeat the airplane tests. If the airplane tests are repeated during continuing qualification 

evaluations, the re-

sults may be compared against initial qualification evaluation results or airplane master data. All tests in this section must 

be presented using 

an unweighted 

1

⁄

3

-octave band format from band 17 to 42 (50 Hz to 16 kHz). A minimum 20 second average must be taken at the location 

corresponding to the airplane data set. The airplane and flight simulator results must be produced using comparable data analys

is tech-

niques..

5.a.

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

Turbo-jet airplanes. 

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