371
Federal Aviation Administration, DOT
Pt. 125, App. E
Parameters Range
Accuracy sensor input to
DFDR readout
Sampling inter-
val (per second)
Resolution
4
read out
GPWS (ground proximity warn-
ing system).
Discrete ........................
................................................
1 ........................
Landing gear or gear selector
position.
Discrete ........................
................................................
0.25 (1 per 4
seconds).
DME 1 and 2 Distance .............
0–200 NM; ...................
As installed .............................
0.25 ...................
1 mi.
Nav 1 and 2 Frequency Selec-
tion.
Full range .....................
As installed .............................
0.25 ...................
1
When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the derivation of altitude to
5 feet.
2
Percent of full range.
3
For airplanes that can demonstrate the capability of deriving either the control input on control movement (one from the
other) for all modes of operation and flight regimes, the ‘‘or’’ applies. For airplanes with non-mechanical control systems (fly-by-
wire) the ‘‘and’’ applies. In airplanes with split surfaces, suitable combination of inputs is acceptable in lieu of recording each sur-
face separately.
4
This column applies to aircraft manufactured after October 11, 1991.
[Doc. No. 25530, 53 FR 26150, July 11, 1988; 53 FR 30906, Aug. 16, 1988]
A
PPENDIX
E
TO
P
ART
125—A
IRPLANE
F
LIGHT
R
ECORDER
S
PECIFICATIONS
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
1. Time or Rel-
ative Times
Counts.
1
.
24 Hrs, 0 to
4095.
±
0.125% Per
Hour.
4 ........................
1 sec .................
UTC time preferred when
available. Count incre-
ments each 4 seconds of
system operation.
2. Pressure Alti-
tude.
¥
1000 ft to max
certificated alti-
tude of aircraft.
+ 5000 ft.
±
100 to
±
700 ft
(see table,
TSO C124a or
TSO C51a).
1 ........................
5
′
to 35
′
.............
Data should be obtained
from the air data computer
when practicable.
3. Indicated air-
speed or Cali-
brated airspeed.
50 KIAS or min-
imum value to
Max V
so
, to 1.2
V.
D
.
±
5% and
±
3% ....
1 ........................
1 kt ....................
Data should be obtained
from the air data computer
when practicable.
4, Heading (Pri-
mary flight crew
reference).
0–360
°
and Dis-
crete ‘‘true’’ or
‘‘mag’’.
±
2
°
.....................
1 ........................
0.5
°
....................
When true or magnetic head-
ing can be selected as the
primary heading reference,
a discrete indicating selec-
tion must be recorded.
5. Normal Accel-
eration
(Vertical)
9
.
¥
3g to + 6g ......
±
1% of max
range exclud-
ing datum
error of
±
5%.
0.125 .................
0.004g.
6. Pitch Attitude ..
±
75
°
...................
±
2
°
.....................
1 or 0.25 for air-
planes oper-
ated under
§ 125.226(f).
0.5
°
....................
A sampling rate of 0.25 is
recommended.
7. Roll Attitude
2
..
±
180
°
.................
±
2
°
.....................
1 or 0.5 for air-
planes oper-
ated under
§ 121.344(f).
0.5
°
....................
A sampling rate of 0.5 is rec-
ommended.
8. Manual Radio
Transmitter
Keying or CVR/
DFDR synchro-
nization
reference .............
On-Off (Discrete)
None.
...........................
1 ........................
...........................
Preferably each crew mem-
ber but one discrete ac-
ceptable for all trans-
mission provided the CVR/
FDR system complies with
TSO C124a CVR synchro-
nization requirements
(paragraph 4.2.1 ED–55).
9. Thrust/Power
on each en-
gine—primary
flight crew ref-
erence.
Full Range For-
ward.
±
2% ...................
1 (per engine) ...
0.3% of full
range.
Sufficient parameters (e.g.,
EPR, N1 or Torque, NP)
as appropriate to the par-
ticular engine being re-
corded to determine power
in forward and reverse
thrust, including potential
overspeed condition.
10. Autopilot En-
gagement.
Discrete ‘‘on’’ or
‘‘off’’.
...........................
1.
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