304
14 CFR Ch. I (1–1–19 Edition)
Pt. 121, App. M
The recorded values must meet the designated range, resolution and accuracy requirements during static and dynamic condi-
tions. Dynamic condition means the parameter is experiencing change at the maximum rate attainable, including the maximum
rate of reversal. All data recorded must be correlated in time to within one second.
Parameters Range
Accuracy (sensor
input)
Seconds per
sampling interval
Resolution Remarks
84. Cockpit trim
control input po-
sition—yaw.
Full range ..........
±
5% ...................
1 ........................
0.3% of full
range.
Where mechanical means for
control input are not avail-
able, cockpit display trim
positions should be re-
corded.
85. Trailing edge
flap and cockpit
flap control po-
sition.
Full Range .........
±
5% ...................
2 ........................
0.5% of full
range.
Trailing edge flaps and cock-
pit flap control position
may each be sampled al-
ternately at 4 second inter-
vals to provide a sample
each 0.5 second.
86. Leading edge
flap and cockpit
flap control po-
sition.
Full Range or
Discrete.
±
5% ...................
1 ........................
0.5% of full
range
87. Ground spoil-
er position and
speed brake se-
lection.
Full range or dis-
crete.
±
5% ...................
0.5 .....................
0.3% of full
range.
88. All cockpit
flight control
input forces
(control wheel,
control column,
rudder
pedal)
18 19
.
Full range ..........
Control wheel
±
70 lbs.
Control column
±
85 lbs.
Rudder pedal
±
165 lbs.
±
5% ...................
1 ........................
0.3% of full
range.
For fly-by-wire flight control
systems, where flight con-
trol surface position is a
function of the displace-
ment of the control input
device only, it is not nec-
essary to record this pa-
rameter. For airplanes that
have a flight control break
away capability that allows
either pilot to operate the
control independently,
record both control force
inputs. The control force
inputs may be sampled al-
ternately once per 2 sec-
onds to produce the sam-
pling interval of 1.
89. Yaw damper
status.
Discrete (on/off)
0.5 .....................
90. Yaw damper
command.
Full range ..........
As installed ........
0.5 .....................
1% of full range.
91. Standby rud-
der valve status.
Discrete .............
0.5.
1
For A300 B2/B4 airplanes, resolution = 6 seconds.
2
For A330/A340 series airplanes, resolution = 0.703
°
.
3
For A318/A319/A320/A321 series airplanes, resolution = 0.275% (0.088
°
>0.064
°
).
For A330/A340 series airplanes, resolution = 2.20%(0.703
°
>0.064
°
).
4
For A318/A319/A320/A321 series airplanes, resolution = 0.22% (0.088
°
>0.080
°
).
For A330/A340 series airplanes, resolution = 1.76% (0.703
°
>0.080
°
).
5
For A330/A340 series airplanes, resolution = 1.18% (0.703
°
>0.120
°
).
For A330/A340 series airplanes, seconds per sampling interval = 1.
6
For A330/A340 series airplanes, resolution = 0.783% (0.352
°
>0.090
°
).
7
For A330/A340 series airplanes, aileron resolution = 0.704% (0.352
°
>0.100
°
). For A330/A340 series airplanes, spoiler resolu-
tion = 1.406% (0.703
°
>0.100
°
).
8
For A330/A340 series airplanes, resolution = 0.30% (0.176
°
>0.12
°
).
For A330/A340 series airplanes, seconds per sampling interval = 1.
9
For B–717 series airplanes, resolution = .005g. For Dassault F900C/F900EX airplanes, resolution = .007g.
10
For A330/A340 series airplanes, resolution = 1.05% (0.250
°
>0.120
°
).
11
For A330/A340 series airplanes, resolution = 1.05% (0.250
°
>0.120
°
). For A300 B2/B4 series airplanes, resolution = 0.92%
(0.230
°
>0.125
°
).
12
For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703
°
>0.100
°
).
13
For A330/A340 series airplanes, resolution = 0.5
°
C.
14
For Dassault F900C/F900EX airplanes, Radio altitude resolution = 1.25 ft.
15
For A330/A340 series airplanes, resolution = 0.352 degrees.
16
For A318/A319/A320/A321 series airplanes, resolution = 4.32%. For A330/A340 series airplanes, resolution is 3.27% of full
range for throttle lever angle (TLA); for reverse thrust, reverse throttle lever angle (RLA) resolution is nonlinear over the active
reverse thrust range, which is 51.54 degrees to 96.14 degrees. The resolved element is 2.8 degrees uniformly over the entire ac-
tive reverse thrust range, or 2.9% of the full range value of 96.14 degrees.
17
For A318/A319/A320/A321 series airplanes, with IAE engines, resolution = 2.58%.
18
For all aircraft manufactured on or after December 6, 2010, the seconds per sampling interval is 0.125. Each input must be
recorded at this rate. Alternately sampling inputs (interleaving) to meet this sampling interval is prohibited.
VerDate Sep<11>2014
08:20 May 17, 2019
Jkt 247048
PO 00000
Frm 00314
Fmt 8010
Sfmt 8002
Y:\SGML\247048.XXX
247048