[Code of Federal Regulations]
[Title 14, Volume 2]
[Revised as of January 1, 2008]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR121 App M]
[Page 968-974]
TITLE 14--AERONAUTICS AND SPACE
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
(CONTINUED)
PART 121_OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS--Table of Contents
Subpart AA_Continued Airworthiness and Safety Improvements
Sec. Appendix M to Part 121--Airplane Flight Recorder Specifications
The recorded values must meet the designated range, resolution, and accuracy requirements during dynamic and static conditions. All data recorded must
be correlated in time to within one second.
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Accuracy (sensor Seconds per sampling
Parameters Range input) interval Resolution Remarks
--------------------------------------------------------------------------------------------------------------------------------------------------------
1. Time or Relative Times 24 Hrs, 0 to 4095..... 0.125% Per Hour. when available.
Count increments
each 4 second of
system operation.
2. Pressure Altitude............... -1000 ft to max 100 to 700 air data computer
ft (see table, TSO when practicable.
C124a or TSO C51a).
3. Indicated airspeed or Calibrated 50 KIAS or minimum 5% and 3%. air data computer
when practicable.
4. Heading (Primary flight crew 0-360[deg] and 2[deg]. heading can be
``mag''. selected as the
primary heading
reference, a
discrete indicating
selection must be
recorded.
5. Normal acceleration (vertical) -3g to +6g............ 1% of max range
excluding datum error
of 5%.
6. Pitch Attitude.................. 75[deg]. eq>2[deg]. airplanes operated 0.25 is recommended.
under Sec.
121.344(f).
7. Roll attitude \2\............... 180[deg]. eq>2[deg]. airplanes operated 0.5 is recommended.
under Sec.
121.344(f).
8. Manual Radio Transmitter Keying On-Off (Discrete)..... ...................... 1.................... ..................... Preferably each crew
or CVR/DFDR synchronization None.................. member but one
reference. discrete acceptable
for all transmission
provided the CVR/FDR
system complies with
TSO C124a CVR
synchronization
requirements
(paragraph 4.2.1 ED-
55).
9. Thrust/power on each engine-- Full range forward.... 2%. (e.g. EPR, N1 or
Torque, NP) as
appropriate to the
particular engine
being recorded to
determine power in
forward and reverse
thrust, including
potential overspeed
condition.
10. Autopilot Engagement........... Discrete ``on'' or ...................... 1.................... ..................... .....................
``off''.
11. Longitudinal Acceleration...... 1g. eq>1.5% max. range
excluding datum error
of 5%.
12a. Pitch Control(s) position (non- Full Range............ 2[deg] Unless airplanes operated have a flight
Higher Accuracy under Sec. control break away
Uniquely Required. 121.344(f). capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
interval of 0.5 or
0.25, as applicable.
12b. Pitch Control(s) position (fly- Full Range............ 2[deg] Unless airplanes operated
Higher Accuracy under Sec.
Uniquely Required.. 121.344(f)..
[[Page 969]]
13a. Lateral Control position(s) Full Range............ 2[deg] Unless airplanes operated have a flight
Higher Accuracy under Sec. control break away
Uniquely Required. 121.344(f). capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
interval of 0.5 or
0.25, as applicable.
13b. Lateral Control position(s) Full Range............ 2[deg] Unless airplanes operated
Higher Accuracy under Sec.
Uniquely Required. 121.344(f).
14a. Yaw control position(s) (non- Full range............ 2[deg] Unless have a flight
higher accuracy control break away
uniquely required. capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
interval of 0.5.
14b. Yaw Control position(s) (fly- Full Range............ 2[deg] Unless
Higher Accuracy
Uniquely Required.
15. Pitch Control Surface(s) Full Range............ 2[deg] Unless airplanes operated with multiple or
Higher Accuracy under Sec. split surfaces, a
Uniquely Required.. 121.344(f).. suitable combination
of inputs is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sampling
interval of 0.5 or
0.25.
16. Lateral control surface(s) Full range............ 2[deg] Unless airplanes operated combination of
higher accuracy under Sec. surface position
uniquely required. 121.344(f). sensors is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sampling
interval of 0.5 or
0.25.
17. Yaw Control Surface(s) Full Range............ 2[deg] Unless multiple or split
Higher Accuracy surfaces, a suitable
Uniquely Required. combination of
surface position
sensors is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sapling
interval of 0.5.
18. Lateral Acceleration........... 1g. eq>1.5% max. range
excluding datum error
of 5%.
19. Pitch Trim Surface Position.... Full Range............ 3[deg] Unless
Higher Accuracy
Uniquely Required.
[[Page 970]]
20. Trailing Edge Flap or Cockpit Full Range or Each 3[deg] or as cockpit control may
Pilot's indicator. each be sampled at 4
second intervals, to
give a data point
every 2 seconds.
21. Leading Edge Flap or Cockpit Full Range or Each 3[deg] or as or flap position and
Pilot's indicator and cockpit control may
sufficient to each be sampled at 4
determine each second intervals, so
discrete position. as to give a data
point every 2
seconds.
22. Each Thrust Reverser Position Stowed, In Transit, ...................... 1 (per engine)....... ..................... Turbo-jet--2
(or equivalent for propeller and Reverse discretes enable the
airplane). (Discrete). 3 states to be
determined.
Turbo-prop--discrete.
23. Ground spoiler position or Full range or each 2[deg] Unless airplanes operated
higher accuracy under Sec.
uniquely required. 121.344(f).
24. Outside Air Temperature or -50 [deg]C to +90 2 [deg]C.
25. Autopilot/Autothrottle/AFCS A suitable combination ...................... 1.................... ..................... Discretes should show
Mode and Engagement Status. of discretes. which systems are
engaged and which
primary modes are
controlling the
flight path and
speed of the
aircraft.
26. Radio Altitude \14\............ -20 ft to 2,500 ft.... 2 ft or 3% radio altimeter
whichever is greater should be recorded,
below 500 ft and but arranged so that
5% above 500 ft. recorded each
second.
27. Localizer Deviation, MLS 400 Microamps or minus3% 3 operations. Each
available sensor recommended. system should be
range as installed. recorded but
62[deg]. least one is
recorded each
second. It is not
necessary to record
ILS and MLS at the
same time, only the
approach aid in use
need be recorded.
28. Glideslope Deviation, MLS 400 Microamps or recommended. 3 operations. Each
Deviation. available sensor system should be
range as installed recorded but
0.9 to +30[deg]....... arranged so that at
least one is
recorded each
second. It is not
necessary to record
ILS and MLS at the
same time, only the
approach aid in use
need be recorded.
29. Marker Beacon Passage.......... Discrete ``on'' or ...................... 1.................... ..................... A single discrete is
``off''. acceptable for all
markers.
30. Master Warning................. Discrete.............. ...................... 1.................... ..................... Record the master
warning and record
each ``red'' warning
that cannot be
determined from
other parameters or
from the cockpit
voice recorder.
31. Air/ground sensor (primary Discrete ``air'' or ...................... 1 (0.25 recommended).
airplane system reference nose or ``ground''.
main gear).
[[Page 971]]
32. Angle of Attack (If measured As installed.......... As installed.......... 2 or 0.5 for 0.3% of full range... If left and right
directly). airplanes operated sensors are
under Sec. available, each may
121.344(f). be recorded at 4 or
1 second intervals,
as appropriate, so
as to give a data
point at 2 seconds
or 0.5 second, as
required.
33. Hydraulic Pressure Low, Each Discrete or available 5%.
or ``normal''.
34. Groundspeed.................... As Installed.......... Most Accurate Systems 1.................... 0.2% of full range...
Installed.
35. GPWS (ground proximity warning Discrete ``warning'' ...................... 1.................... ..................... A suitable
system). or ``off''. combination of
discretes unless
recorder capacity is
limited in which
case a single
discrete for all
modes is acceptable.
36. Landing Gear Position or Discrete.............. ...................... 4.................... ..................... A suitable
Landing gear cockpit control combination of
selection. discretes should be
recorded.
37. Drift Angle.\15\............... As installed.......... As installed.......... 4.................... 0.1[deg]............. .....................
38. Wind Speed and Direction....... As installed.......... As installed.......... 4.................... 1 knot, and 1.0[deg].
39. Latitude and Longitude......... As installed.......... As installed.......... 4.................... 0.002[deg], or as Provided by the
installed. Primary Navigation
System Reference.
Where capacity
permits Latitude/
longitude resolution
should be
0.0002[deg].
40. Stick shaker and pusher Discrete(s) ``on'' or ...................... 1.................... ..................... A suitable
activation. ``off''. combination of
discretes to
determine
activation.
41. Windshear Detection............ Discrete ``warning'' ...................... 1....................
or ``off''.
42. Throttle/power Leverl Full Range............ 2%. non-mechanically
linked cockpit
engine controls.
43. Additional Engine Parameters... As installed.......... As installed.......... Each engine each 2% of full range..... Where capacity
second. permits, the
preferred priority
is indicated
vibration level, N2,
EGT, Fuel Flow, Fuel
Cut-off lever
position and N3,
unless engine
manufacturer
recommends
otherwise.
44. Traffic Alert and Collision Discretes............. As installed.......... 1.................... ..................... A suitable
Avoidance System (TCAS). combination of
discretes should be
recorded to
determine the status
of--Combined
Control, Vertical
Control, Up
Advisory, and Down
Advisory. (ref.
ARINC Characteristic
735 Attachment 6E,
TCAS VERTICAL RA
DATA OUTPUT WORD.)
45. DME 1 and 2 Distance........... 0-200 NM.............. As installed.......... 4.................... 1 NM................. 1 mile
46. Nav 1 and 2 Selected Frequency. Full Range............ As installed.......... 4.................... ..................... Sufficient to
determine selected
frequency
47. Selected barometric setting.... Full Range............ 5%.
48. Selected Altitude.............. Full Range............ 5%.
49. Selected speed................. Full Range............ 5%.
[[Page 972]]
50. Selected Mach.................. Full Range............ 5%.
51. Selected vertical speed........ Full Range............ 5%.
52. Selected heading............... Full Range............ 5%.
53. Selected flight path........... Full Range............ 5%.
54. Selected decision height....... Full Range............ 5%.
55. EFIS display format............ Discrete(s)........... ...................... 4.................... ..................... Discretes should show
the display system
status (e.g., off,
normal, fail,
composite, sector,
plan, nav aids,
weather radar,
range, copy.
56. Multi-function/Engine Alerts Discrete(s)........... ...................... 4.................... ..................... Discretes should show
Display format. the display system
status (e.g., off,
normal, fail, and
the identity of
display pages for
emergency
procedures, need not
be recorded.
57. Thrust command.\17\............ Full Range............ 2%.
58. Thrust target.................. Full Range............ 2%.
59. Fuel quantity in CG trim tank.. Full Range............ 5%.
60. Primary Navigation System Discrete GPS, INS, VOR/ ...................... 4.................... ..................... A suitable
Reference. DME, MLS, Loran C, combination of
Omega, Localizer discretes to
Glideslope. determine the
Primary Navigation
System reference.
61. Ice Detection.................. Discrete ``ice'' or ...................... 4
``no ice''.
62. Engine warning each engine Discrete.............. ...................... 1
vibration.
63. Engine warning each engine over Discrete.............. ...................... 1
temp.
64. Engine warning each engine oil Discrete.............. ...................... 1
pressure low.
65. Engine warning each engine over Discrete.............. ...................... 1
speed.
66. Yaw Trim Surface Position...... Full Range............ 3% Unless Higher
Accuracy Uniquely
Required.
67. Roll Trim Surface Position..... Full Range............ 3% Unless Higher
Accuracy Uniquely
Required.
68. Brake Pressure (left and right) As installed.......... 5%. effort applied by
pilots or by
autobrakes.
69. Brake Pedal Application (left Discrete or Analog 5% (Analog). applied by pilots.
``off''.
70. Yaw or sideslip angle.......... Full Range............ 5%.
71. Engine bleed valve position.... Discrete ``open'' or ...................... 4
``closed''.
72. De-icing or anti-icing system Discrete ``on'' or ...................... 4
selection. ``off''.
73. Computed center of gravity..... Full Range............ 5%.
[[Page 973]]
74. AC electrical bus status....... Discrete ``power'' or ...................... 4.................... ..................... Each bus.
``off''.
75. DC electrical bus status....... Discrete ``power'' or ...................... 4.................... ..................... Each bus.
``off''.
76 APU bleed valve position........ Discrete ``open'' or ...................... 4
``closed''.
77. Hydraulic Pressure (each Full range............ 5%.
78. Loss of cabin pressure......... Discrete ``loss'' or ...................... 1....................
``normal''.
79. Computer failure (critical Discrete ``fail'' or ...................... 4....................
flight and engine control systems). ``normal''.
80. Heads-up display (when an Discrete(s) ``on'' or ...................... 4
information source is installed). ``off''.
81. Para-visual display (when an Discrete(s) ``on'' or
information source is installed). ``off''.
82. Cockpit trim control input Full Range............ 5%. means for control
inputs are not
available, cockpit
display trim
positions should be
recorded.
83. Cockpit trim control input Full Range............ 5%. means for control
inputs are not
available, cockpit
display trim
position should be
recorded.
84. Cockpit trim control input Full range............ 5%. means for control
input are not
available, cockpit
display trim
positions should be
recorded.
85. Trailing edge flap and cockpit Full Range............ 5%. and cockpit flap
control position may
each be sampled
alternately at 4
second intervals to
provide a sample
each 0.5 second.
86. Leading edge flap and cockpit Full Range or Discrete 5%.
87. Ground spoiler position and Full range or discrete 5%.
[[Page 974]]
88. All cockpit flight control Full range control 5%. flight control
control column, rudder pedal). thn-eq>70 lb control systems, where
column 85 rudder surface position is
pedal 165. displacement of the
control input device
only, it is not
necessary to record
this parameter. 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
alternately once per
2 seconds to produce
the sampling
interval of 1.
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\1\ For A300 B2/B4 airplanes, resolution=6 seconds.
\2\ For A330/A340 series airplanes, resolution=0.703[deg].
\3\ For A318/A319/A320/A321 series airplanes, resolution=0.275% (0.088[deg]0.064[deg]).
For A330/A340 series airplanes, resolution=2.20%(0.703[deg]0.064[deg]).
\4\ For A318/A319/A320/A321 series airplanes, resolution=0.22% (0.088[deg]0.080[deg]).
For A330/A340 series airplanes, resolution=1.76% (0.703[deg]0.080[deg]).
\5\ For A330/A340 series airplanes, resolution = 1.18% (0.703[deg]0.120[deg]).
\6\ For A330/A340 series airplanes, resolution=0.783% (0.352[deg]0.090[deg]).
\7\ For A330/A340 series airplanes, aileron resolution = 0.704% (0.352[deg]0.100[deg]). For A330/A340 series airplanes, spoiler resolution =
1.406% (0.703[deg]0.100[deg]).
\8\ For A330/A340 series airplanes, resolution=0.30% (0.176[deg]0.12[deg]).
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[deg]0.120[deg]).
\11\ For A330/A340 series airplanes, resolution = 1.05% (0.250[deg]0.120[deg]). For A300 B2/B4 series airplanes, resolution = 0.92%
(0.230[deg]0.125[deg]).
\12\ For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703[deg]0.100[deg]).
\13\ For A330/A340 series airplanes, resolution=0.5[deg]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 active 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%.
[Doc. No. 28109, 62 FR 38382, July 17, 1997; 62 FR 48135, Sept. 12,
1997, as amended by Amdt. 121-271, 64 FR 46120, Aug. 24, 1999; Amdt.
121-278, 65 FR 51745, Aug. 24, 2000; 65 FR 81733, Dec. 27, 2000; Amdt.
121-292, 67 FR 54323, Aug. 21, 2002; Amdt. 121-300, 68 FR 42936, July
18, 2003; 68 FR 50069, Aug. 20, 2003; 68 FR 53877, Sept. 15, 2003; 70 FR
41134, July 18, 2005]