282 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 60, App. B 

T

ABLE

B2F—A

LTERNATIVE

D

ATA

S

OURCES

, P

ROCEDURES

, 

AND

I

NSTRUMENTATION

L

EVEL

6 FTD— 

Continued 

QPS Requirements 

The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix 

B are not used. 

Information 

Objective test reference number 

and title 

Alternative data sources, procedures, and instrumentation 

Notes 

1.b.7. ................................................
Performance. 
Takeoff. 
Rejected takeoff. 

Data may be acquired through a synchronized video recording of a 

stop watch and the calibrated airplane airspeed indicator. Hand- 
record the flight conditions and airplane configuration.

This test is re-

quired only if 
RTO is 
sought. 

1.c.1. ................................................
Performance. 
Climb. 
Normal climb all engines operating. 

Data may be acquired with a synchronized video of calibrated airplane 

instruments and engine power throughout the climb range.

1.f.1. .................................................
Performance. 
Engines. 
Acceleration 

Data may be acquired with a synchronized video recording of engine 

instruments and throttle position.

1.f.2. .................................................
Performance. 
Engines. 
Deceleration 

Data may be acquired with a synchronized video recording of engine 

instruments and throttle position.

2.a.1.a. .............................................
Handling qualities. 
Static control tests. 
Pitch controller position vs. force 

and surface position calibration. 

Surface position data may be acquired from flight data recorder (FDR) 

sensor or, if no FDR sensor, at selected, significant column positions 
(encompassing significant column position data points), acceptable 
to the NSPM, using a control surface protractor on the ground. Force 
data may be acquired by using a hand held force gauge at the same 
column position data points.

For airplanes 

with reversible 
control sys-
tems, surface 
position data 
acquisition 
should be ac-
complished 
with winds 
less than 5 
kts. 

2.a.2.a. .............................................
Handling qualities. 
Static control tests. 
Wheel position vs. force and sur-

face position calibration. 

Surface position data may be acquired from flight data recorder (FDR) 

sensor or, if no FDR sensor, at selected, significant wheel positions 
(encompassing significant wheel position data points), acceptable to 
the NSPM, using a control surface protractor on the ground. Force 
data may be acquired by using a hand held force gauge at the same 
wheel position data points.

For airplanes 

with reversible 
control sys-
tems, surface 
position data 
acquisition 
should be ac-
complished 
with winds 
less than 5 
kts. 

2.a.3.a. .............................................
Handling qualities. 
Static control tests. 
Rudder pedal position vs. force and 

surface position calibration. 

Surface position data may be acquired from flight data recorder (FDR) 

sensor or, if no FDR sensor, at selected, significant rudder pedal po-
sitions (encompassing significant rudder pedal position data points), 
acceptable to the NSPM, using a control surface protractor on the 
ground. Force data may be acquired by using a hand held force 
gauge at the same rudder pedal position data points.

For airplanes 

with reversible 
control sys-
tems, surface 
position data 
acquisition 
should be ac-
complished 
with winds 
less than 5 
kts. 

2.a.4. ................................................
Handling qualities. 
Static control tests. 
Nosewheel steering force. 

Breakout data may be acquired with a hand held force gauge. The re-

mainder of the force to the stops may be calculated if the force 
gauge and a protractor are used to measure force after breakout for 
at least 25% of the total displacement capability.

2.a.5. ................................................
Handling qualities. 
Static control tests. 
Rudder pedal steering calibration. 

Data may be acquired through the use of force pads on the rudder 

pedals and a pedal position measurement device, together with de-
sign data for nosewheel position.

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