449
Federal Aviation Administration, DOT
§ 135.152
§ 135.152 Flight data recorders.
(a) Except as provided in paragraph
(k) of this section, no person may oper-
ate under this part a multi-engine, tur-
bine-engine powered airplane or rotor-
craft having a passenger seating con-
figuration, excluding any required
crewmember seat, of 10 to 19 seats, that
was either brought onto the U.S. reg-
ister after, or was registered outside
the United States and added to the op-
erator’s U.S. operations specifications
after, October 11, 1991, unless it is
equipped with one or more approved
flight recorders that use a digital
method of recording and storing data
and a method of readily retrieving that
data from the storage medium. The pa-
rameters specified in either Appendix B
or C of this part, as applicable must be
recorded within the range, accuracy,
resolution, and recording intervals as
specified. The recorder shall retain no
less than 25 hours of aircraft operation.
(b) After October 11, 1991, no person
may operate a multiengine, turbine-
powered airplane having a passenger
seating configuration of 20 to 30 seats
or a multiengine, turbine-powered
rotorcraft having a passenger seating
configuration of 20 or more seats unless
it is equipped with one or more ap-
proved flight recorders that utilize a
digital method of recording and storing
data, and a method of readily retriev-
ing that data from the storage me-
dium. The parameters in appendix D or
E of this part, as applicable, that are
set forth below, must be recorded with-
in the ranges, accuracies, resolutions,
and sampling intervals as specified.
(1) Except as provided in paragraph
(b)(3) of this section for aircraft type
certificated before October 1, 1969, the
following parameters must be recorded:
(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 re-
corded:
(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 re-
quired 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 com-
pleted the landing roll or the rotorcraft
has landed at its destination.
(d) Except as provided in paragraph
(c) of this section, and except for re-
corded 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 sec-
tion. In addition, each certificate hold-
er shall keep the recorded data pre-
scribed 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
450
14 CFR Ch. I (1–1–24 Edition)
§ 135.152
erased for the purpose of testing the
flight recorder or the flight recorder
system. Any erasure made in accord-
ance with this paragraph must be of
the oldest recorded data accumulated
at the time of testing. Except as pro-
vided in paragraph (c) of this section,
no record need be kept more than 60
days.
(e) In the event of an accident or oc-
currence that requires the immediate
notification of the National Transpor-
tation Safety Board under 49 CFR part
830 of its regulations and that results
in termination of the flight, the certifi-
cate 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 re-
quest of the Board or the Adminis-
trator.
(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 ac-
cordance with the requirements of
§ 23.1459 (except paragraphs (a)(3)(ii)
and (6)), § 25.1459 (except paragraphs
(a)(3)(ii) and (7)), § 27.1459 (except para-
graphs (a)(3)(ii) and (6)), or § 29.1459 (ex-
cept paragraphs (a)(3)(ii) and (6)), as
appropriate, of this chapter. The cor-
relation required by paragraph (c) of
§§ 23.1459, 25.1459, 27.1459, or 29.1459 of
this chapter, as appropriate, 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 mod-
els and their installations are the
same; and
(iii) On which there are no dif-
ferences in the type designs with re-
spect to the installation of the first pi-
lot’s instruments associated with the
flight recorder. The most recent instru-
ment calibration, including the record-
ing medium from which this calibra-
tion is derived, and the recorder cor-
relation must be retained by the cer-
tificate holder.
(2) For airplanes manufactured after
August 18, 2000, each flight data re-
corder system required by this section
must be installed in accordance with
the requirements of § 23.1459(a) (except
paragraphs (a)(3)(ii) and (6)), (b), (d)
and (e), or § 25.1459(a) (except para-
graphs (a)(3)(ii) and (7)), (b), (d) and (e)
of this chapter. A correlation must be
established between the values re-
corded by the flight data recorder and
the corresponding values being meas-
ured. The correlation must contain a
sufficient number of correlation points
to accurately establish the conversion
from the recorded values to engineer-
ing units or discrete state over the full
operating range of the parameter. Ex-
cept for airplanes having separate alti-
tude and airspeed sensors that are an
integral part of the flight data recorder
system, a single correlation may be es-
tablished for any group of airplanes—
(i) That are of the same type;
(ii) On which the flight recorder sys-
tem 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 main-
tained by the certificate holder.
(g) Each flight recorder required by
this section that records the data spec-
ified 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 re-
quired 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 param-
eter 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 ref-
erence (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 ref-
erence;
(9) Thrust/power of each engine—pri-
mary flight crew reference;
(10) Autopilot engagement status;
451
Federal Aviation Administration, DOT
§ 135.152
(11) Longitudinal acceleration;
(12) Pitch control input;
(13) Lateral control input;
(14) Rudder pedal input;
(15) Primary pitch control surface po-
sition;
(16) Primary lateral control surface
position;
(17) Primary yaw control surface po-
sition;
(18) Lateral acceleration;
(19) Pitch trim surface position or pa-
rameters of paragraph (h)(82) of this
section if currently recorded;
(20) Trailing edge flap or cockpit flap
control selection (except when param-
eters of paragraph (h)(85) of this sec-
tion apply);
(21) Leading edge flap or cockpit flap
control selection (except when param-
eters of paragraph (h)(86) of this sec-
tion apply);
(22) Each Thrust reverser position (or
equivalent for propeller airplane);
(23) Ground spoiler position or speed
brake selection (except when param-
eters of paragraph (h)(87) of this sec-
tion apply);
(24) Outside or total air temperature;
(25) Automatic Flight Control Sys-
tem (AFCS) modes and engagement
status, including autothrottle;
(26) Radio altitude (when an informa-
tion source is installed);
(27) Localizer deviation, MLS Azi-
muth;
(28) Glideslope deviation, MLS Ele-
vation;
(29) Marker beacon passage;
(30) Master warning;
(31) Air/ground sensor (primary air-
plane system reference nose or main
gear);
(32) Angle of attack (when informa-
tion source is installed);
(33) Hydraulic pressure low (each sys-
tem);
(34) Ground speed (when an informa-
tion source is installed);
(35) Ground proximity warning sys-
tem;
(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 in-
formation 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 avoid-
ance system;
(45) DME 1 and 2 distances;
(46) Nav 1 and 2 selected frequency;
(47) Selected barometric setting
(when an information source is in-
stalled);
(48) Selected altitude (when an infor-
mation source is installed);
(49) Selected speed (when an informa-
tion source is installed);
(50) Selected mach (when an informa-
tion source is installed);
(51) Selected vertical speed (when an
information source is installed);
(52) Selected heading (when an infor-
mation source is installed);
(53) Selected flight path (when an in-
formation source is installed);
(54) Selected decision height (when
an information source is installed);
(55) EFIS display format;
(56) Multi-function/engine/alerts dis-
play format;
(57) Thrust command (when an infor-
mation source is installed);
(58) Thrust target (when an informa-
tion source is installed);
(59) Fuel quantity in CG trim tank
(when an information source is in-
stalled);
(60) Primary Navigation System Ref-
erence;
(61) Icing (when an information
source is installed);
(62) Engine warning each engine vi-
bration (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);
452
14 CFR Ch. I (1–1–24 Edition)
§ 135.153
(70) Yaw or sideslip angle (when an
information source is installed);
(71) Engine bleed valve position
(when an information source is in-
stalled);
(72) De-icing or anti-icing system se-
lection (when an information source is
installed);
(73) Computed center of gravity
(when an information source is in-
stalled);
(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 sys-
tem);
(78) Loss of cabin pressure;
(79) Computer failure;
(80) Heads-up display (when an infor-
mation source is installed);
(81) Para-visual display (when an in-
formation source is installed);
(82) Cockpit trim control input posi-
tion—pitch;
(83) Cockpit trim control input posi-
tion—roll;
(84) Cockpit trim control input posi-
tion—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, manu-
factured after August 18, 2000—
(1) The parameters listed in para-
graphs (h)(1) through (h)(57) of this sec-
tion must be recorded within the
ranges, accuracies, resolutions, and re-
cording 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, ac-
curacies, resolutions, and sampling in-
tervals 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, ac-
curacies, resolutions, and recording in-
tervals specified in Appendix F of this
part.
(k) For aircraft manufactured before
August 18, 1997, the following aircraft
types need not comply with this sec-
tion: Bell 212, Bell 214ST, Bell 412, Bell
412SP, Boeing Chinook (BV–234), Boe-
ing/Kawasaki Vertol 107 (BV/KV–107–
II), deHavilland DHC–6, Eurocopter
Puma 330J, Sikorsky 58, Sikorsky 61N,
Sikorsky 76A.
(l) By April 7, 2012, all aircraft manu-
factured before April 7, 2010, must also
meet the requirements in § 23.1459(a)(7),
§ 25.1459(a)(8), § 27.1459(e), or § 29.1459(e)
of this chapter, as applicable.
(m) All aircraft manufactured on or
after April 7, 2010, must have a flight
data recorder installed that also—
(1) Meets the requirements of
§ 23.1459(a)(3), (a)(6), and (a)(7),
§ 25.1459(a)(3), (a)(7), and (a)(8),
§ 27.1459(a)(3), (a)(6), and (e), or
§ 29.1459(a)(3), (a)(6), and (e) of this
chapter, as applicable; and
(2) Retains the 25 hours of recorded
information required in paragraph (d)
of this section using a recorder that
meets the standards of TSO–C124a, or
later revision.
[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; Amdt. 135–
89, 68 FR 42939, July 18, 2003; Amdt. 135–113, 73
FR 12570, Mar. 7, 2008; Amdt. 135–113, 74 FR
32801, July 9, 2009]
§ 135.153 [Reserved]
§ 135.154 Terrain awareness and warn-
ing system.
(a)
Airplanes manufactured after March
29, 2002:
(1) No person may operate a turbine-
powered airplane configured with 10 or
more passenger seats, excluding any
pilot seat, unless that airplane is
equipped with an approved terrain
awareness and warning system that
meets the requirements for Class A
equipment in Technical Standard Order