(i) Time;
(ii) Altitude;
(iii) Airspeed;
(iv) Vertical acceleration;
(v) Heading;
(vi) Time of each radio transmission to
or from air traffic control;
(vii) Pitch attitude;
(viii) Roll attitude;
(ix) Longitudinal acceleration;
(x) Control column or pitch control
surface position; and
(xi) Thrust of each engine.
(2) Except as provided in paragraph
(b)(3) of this section for aircraft type certificated after September 30,
1969, the following parameters must be recorded:
(i) Time;
(ii) Altitude;
(iii) Airspeed;
(iv) Vertical acceleration;
(v) Heading;
(vi) Time of each radio transmission
either to or from air traffic control;
(vii) Pitch attitude;
(viii) Roll attitude;
(ix) Longitudinal acceleration;
(x) Pitch trim position;
(xi) Control column or pitch control
surface position;
(xii) Control wheel or lateral control
surface position;
(xiii) Rudder pedal or yaw control
surface position;
(xiv) Thrust of each engine;
(xv) Position of each thrust reverser;
(xvi) Trailing edge flap or cockpit flap
control position; and
(xvii) Leading edge flap or cockpit flap
control position.
(3) For aircraft manufactured after
October 11, 1991, all of the parameters listed in appendix D or E of this
part, as applicable, must be recorded.
(c) Whenever a flight recorder required
by this section is installed, it must be operated continuously from the
instant the airplane begins the takeoff roll or the rotorcraft begins the
lift-off until the airplane has completed the landing roll or the
rotorcraft has landed at its destination.
(d) Except as provided in paragraph (c)
of this section, and except for recorded data erased as authorized in this
paragraph, each certificate holder shall keep the recorded data prescribed
in paragraph (a) of this section until the aircraft has been operating for
at least 25 hours of the operating time specified in paragraph (c) of this
section. In addition, each certificate holder shall keep the recorded data
prescribed in paragraph (b) of this section for an airplane until the
airplane has been operating for at least 25 hours, and for a rotorcraft
until the rotorcraft has been operating for at least 10 hours, of the
operating time specified in paragraph (c) of this section. A total of 1
hour of recorded data may be erased for the purpose of testing the flight
recorder or the flight recorder system. Any erasure made in accordance
with this paragraph must be of the oldest recorded data accumulated at the
time of testing. Except as provided in paragraph (c) of this section, no
record need be kept more than 60 days.
(e) In the event of an accident or
occurrence that requires the immediate notification of the National
Transportation Safety Board under 49 CFR part 830 of its regulations and
that results in termination of the flight, the certificate holder shall
remove the recording media from the aircraft and keep the recorded data
required by paragraphs (a) and (b) of this section for at least 60 days or
for a longer period upon request of the Board or the Administrator.
(f)(1) For airplanes manufactured on or
before August 18, 2000, and all other aircraft, each flight recorder
required by this section must be installed in accordance with the
requirements of §23.1459, 25.1459, 27.1459, or 29.1459, as appropriate, of
this chapter. The correlation required by paragraph (c) of §23.1459,
25.1459, 27.1459, or 29.1459, as appropriate, of this chapter need be
established only on one aircraft of a group of aircraft:
(i) That are of the same type;
(ii) On which the flight recorder models
and their installations are the same; and
(iii) On which there are no differences
in the type designs with respect to the installation of the first pilot's
instruments associated with the flight recorder. The most recent
instrument calibration, including the recording medium from which this
calibration is derived, and the recorder correlation must be retained by
the certificate holder.
(f)(2) For airplanes manufactured after
August 18, 2000, each flight data recorder system required by this section
must be installed in accordance with the requirements of §23.1459 (a),
(b), (d) and (e) of this chapter, or §25.1459 (a), (b), (d), and (e) of
this chapter. A correlation must be established between the values
recorded by the flight data recorder and the corresponding values being
measured. The correlation must contain a sufficient number of correlation
points to accurately establish the conversion from the recorded values to
engineering units or discrete state over the full operating range of the
parameter. Except for airplanes having separate altitude and airspeed
sensors that are an integral part of the flight data recorder system, a
single correlation may be established for any group of airplanes --
(i) That are of the same type;
(ii) On which the flight recorder system
and its installation are the same; and
(iii) On which there is no difference in
the type design with respect to the installation of those sensors
associated with the flight data recorder system. Documentation sufficient
to convert recorded data into the engineering units and discrete values
specified in the applicable appendix must be maintained by the certificate
holder.
(g) Each flight recorder required by
this section that records the data specified in paragraphs (a) and (b) of
this section must have an approved device to assist in locating that
recorder under water.
(h) The operational parameters required
to be recorded by digital flight data recorders required by paragraphs (i)
and (j) of this section are as follows, the phrase "when an information
source is installed" following a parameter indicates that recording of
that parameter is not intended to require a change in installed equipment.
(1) Time;
(2) Pressure altitude;
(3) Indicated airspeed;
(4) Heading -- primary flight crew
reference (if selectable, record discrete, true or magnetic);
(5) Normal acceleration (Vertical);
(6) Pitch attitude;
(7) Roll attitude;
(8) Manual radio transmitter keying, or
CVR/DFDR synchronization reference;
(9) Thrust/power of each engine --
primary flight crew reference;
(10) Autopilot engagement status;
(11) Longitudinal acceleration;
(12) Pitch control input;
(13) Lateral control input;
(14) Rudder pedal input;
(15) Primary pitch control surface
position;
(16) Primary lateral control surface
position;
(17) Primary yaw control surface
position;
(18) Lateral acceleration;
(19) Pitch trim surface position or
parameters of paragraph (h)(82) of this section if currently recorded;
(20) Trailing edge flap or cockpit flap
control selection (except when parameters of paragraph (h)(85) of this
section apply);
(21) Leading edge flap or cockpit flap
control selection (except when parameters of paragraph (h)(86) of this
section apply);
(22) Each Thrust reverser position (or
equivalent for propeller airplane);
(23) Ground spoiler position or speed
brake selection (except when parameters of paragraph (h)(87) of this
section apply);
(24) Outside or total air temperature;
(25) Automatic Flight Control System (AFCS)
modes and engagement status, including autothrottle;
(26) Radio altitude (when an information
source is installed);
(27) Localizer deviation, MLS Azimuth;
(28) Glideslope deviation, MLS
Elevation;
(29) Marker beacon passage;
(30) Master warning;
(31) Air/ground sensor (primary airplane
system reference nose or main gear);
(32) Angle of attack (when information
source is installed);
(33) Hydraulic pressure low (each
system);
(34) Ground speed (when an information
source is installed);
(35) Ground proximity warning system;
(36) Landing gear position or landing
gear cockpit control selection;
(37) Drift angle (when an information
source is installed);
(38) Wind speed and direction (when an
information source is installed);
(39) Latitude and longitude (when an
information source is installed);
(40) Stick shaker/pusher (when an
information source is installed);
(41) Windshear (when an information
source is installed);
(42) Throttle/power lever position;
(43) Additional engine parameters (as
designated in appendix F of this part);
(44) Traffic alert and collision
avoidance system;
(45) DME 1 and 2 distances;
(46) Nav 1 and 2 selected frequency;
(47) Selected barometric setting (when
an information source is installed);
(48) Selected altitude (when an
information source is installed);
(49) Selected speed (when an information
source is installed);
(50) Selected mach (when an information
source is installed);
(51) Selected vertical speed (when an
information source is installed);
(52) Selected heading (when an
information source is installed);
(53) Selected flight path (when an
information source is installed);
(54) Selected decision height (when an
information source is installed);
(55) EFIS display format;
(56) Multi-function/engine/alerts
display format;
(57) Thrust command (when an information
source is installed);
(58) Thrust target (when an information
source is installed);
(59) Fuel quantity in CG trim tank (when
an information source is installed);
(60) Primary Navigation System
Reference;
(61) Icing (when an information source
is installed);
(62) Engine warning each engine
vibration (when an information source is installed);
(63) Engine warning each engine over
temp. (when an information source is installed);
(64) Engine warning each engine oil
pressure low (when an information source is installed);
(65) Engine warning each engine over
speed (when an information source is installed;
(66) Yaw trim surface position;
(67) Roll trim surface position;
(68) Brake pressure (selected system);
(69) Brake pedal application (left and
right);
(70) Yaw or sideslip angle (when an
information source is installed);
(71) Engine bleed valve position (when
an information source is installed);
(72) De-icing or anti-icing system
selection (when an information source is installed);
(73) Computed center of gravity (when an
information source is installed);
(74) AC electrical bus status;
(75) DC electrical bus status;
(76) APU bleed valve position (when an
information source is installed);
(77) Hydraulic pressure (each system);
(78) Loss of cabin pressure;
(79) Computer failure;
(80) Heads-up display (when an
information source is installed);
(81) Para-visual display (when an
information source is installed);
(82) Cockpit trim control input position
-- pitch;
(83) Cockpit trim control input position
-- roll;
(84) Cockpit trim control input position
-- yaw;
(85) Trailing edge flap and cockpit flap
control position;
(86) Leading edge flap and cockpit flap
control position;
(87) Ground spoiler position and speed
brake selection; and
(88) All cockpit flight control input
forces (control wheel, control column, rudder pedal).
(i) For all turbine-engine powered
airplanes with a seating configuration, excluding any required crewmember
seat, of 10 to 30 passenger seats, manufactured after August 18, 2000 --
(1) The parameters listed in paragraphs
(h)(1) through (h)(57) of this section must be recorded within the ranges,
accuracies, resolutions, and recording intervals specified in Appendix F
of this part.
(2) Commensurate with the capacity of
the recording system, all additional parameters for which information
sources are installed and which are connected to the recording system must
be recorded within the ranges, accuracies, resolutions, and sampling
intervals specified in Appendix F of this part.
(j) For all turbine-engine-powered
airplanes with a seating configuration, excluding any required crewmember
seat, of 10 to 30 passenger seats, that are manufactured after August 19,
2002 the parameters listed in paragraph (a)(1) through (a)(88) of this
section must be recorded within the ranges, accuracies, resolutions, and
recording intervals specified in Appendix F of this part.
(k) For airplanes manufactured before
August 18, 1997 the following airplane type need not comply with this
section: deHavilland DHC-6.
[Doc. No. 25530, 53 FR 26151, July 11, 1988, as
amended by Amdt. 135-69, 62 FR 38396, July 17, 1997; 62 FR 48135, Sept.
12, 1997]