title-14-part-125-sec125-226

352

14 CFR Ch. I (1–1–24 Edition)

§ 125.226

§ 125.226 Digital flight data recorders.

(a) Except as provided in paragraph

(l) of this section, no person may oper-
ate under this part a turbine-engine-
powered transport category airplane
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 operational parameters required to
be recorded by digital flight data re-
corders required by this section are as
follows: the phrase ‘‘when an informa-
tion source is installed’’ following a pa-
rameter indicates that recording of
that parameter is not intended to re-
quire 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;
(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 (a)(82) of this
section if currently recorded;

(20) Trailing edge flap or cockpit flap

control selection (except when param-
eters of paragraph (a)(85) of this sec-
tion apply);

(21) Leading edge flap or cockpit flap

control selection (except when param-
eters of paragraph (a)(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 (a)(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

designed in appendix E 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);

353

Federal Aviation Administration, DOT

§ 125.226

(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);

(70) Yaw of 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;

(88) All cockpit flight control input

forces (control wheel, control column,
rudder pedal);

(89) Yaw damper status;
(90) Yaw damper command; and
(91) Standby rudder valve status.
(b) For all turbine-engine powered

transport category airplanes manufac-
tured on or before October 11, 1991, by
August 20, 2001—

(1) For airplanes not equipped as of

July 16, 1996, with a flight data acquisi-
tion unit (FDAU), the parameters list-
ed in paragraphs (a)(1) through (a)(18)
of this section must be recorded within
the ranges and accuracies specified in
Appendix D of this part, and—

(i) For airplanes with more than two

engines, the parameter described in
paragraph (a)(18) is not required unless
sufficient capacity is available on the
existing recorder to record that param-
eter.

(ii) Parameters listed in paragraphs

(a)(12) through (a)(17) each may be re-
corded from a single source.

(2) For airplanes that were equipped

as of July 16, 1996, with a flight data
acquisition unit (FDAU), the param-
eters listed in paragraphs (a)(1)
through (a)(22) of this section must be
recorded within the ranges, accuracies,
and recording intervals specified in Ap-
pendix E of this part. Parameters listed
in paragraphs (a)(12) through (a)(17)
each may be recorded from a single
source.

(3) The approved flight recorder re-

quired by this section must be installed
at the earliest time practicable, but no
later than the next heavy maintenance
check after August 18, 1999 and no later
than August 20, 2001. A heavy mainte-
nance check is considered to be any
time an airplane is scheduled to be out
of service for 4 or more days and is
scheduled to include access to major
structural components.

354

14 CFR Ch. I (1–1–24 Edition)

§ 125.226

transport category airplanes manufac-
tured on or before October 11, 1991—

(1) That were equipped as of July 16,

1996, with one or more digital data
bus(es) and an ARINC 717 digital flight
data acquisition unit (DFDAU) or
equivalent, the parameters specified in
paragraphs (a)(1) through (a)(22) of this
section must be recorded within the
ranges, accuracies, resolutions, and
sampling intervals specified in Appen-
dix E of this part by August 20, 2001.
Parameters listed in paragraphs (a)(12)
through (a)(14) each may be recorded
from a single source.

(2) Commensurate with the capacity

of the recording system (DFDAU or
equivalent and the DFDR), all addi-
tional parameters for which informa-
tion 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 E of this
part by August 20, 2001.

(3) That were subject to § 125.225(e) of

this part, all conditions of § 125.225(c)
must continue to be met until compli-
ance with paragraph (c)(1) of this sec-
tion is accomplished.

(d) For all turbine-engine-powered

transport category airplanes that were
manufactured after October 11, 1991—

(1) The parameters listed in para-

graphs (a)(1) through (a)(34) of this sec-
tion must be recorded within the
ranges, accuracies, resolutions, and re-
cording intervals specified in Appendix
E of this part by August 20, 2001.
Paramaters listed in paragraphs (a)(12)
through (a)(14) each may be recorded
from a single source.

(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 E of this
part by August 20, 2001.

(e) For all turbine-engine-powered

transport category airplanes that are
manufactured after August 18, 2000—

(1) The parameters listed in para-

graph (a) (1) through (57) of this section
must be recorded within the ranges, ac-
curacies, resolutions, and recording in-

tervals specified in Appendix E of this
part.

(2) Commensurate with the capacity

(3) In addition to the requirements of

paragraphs (e)(1) and (e)(2) of this sec-
tion, all Boeing 737 model airplanes
must also comply with the require-
ments of paragraph (n) of this section,
as applicable.

(f) For all turbine-engine-powered

transport category airplanes manufac-
tured after August 19, 2002—

(1) The parameters listed in para-

graphs (a)(1) through (a)(88) of this sec-
tion must be recorded within the
ranges, accuracies, resolutions, and re-
cording intervals specified in Appendix
E to this part.

(2) In addition to the requirements of

paragraphs (f)(1) of this section, all
Boeing 737 model airplanes must also
comply with the requirements of para-
graph (n) of this section.

(g) Whenever a flight data recorder

required by this section is installed, it
must be operated continuously from
the instant the airplane begins its
takeoff roll until it has completed its
landing roll.

(h) Except as provided in paragraph

(i) of this section, and except for re-
corded data erased as authorized in
this paragraph, each certificate holder
shall keep the recorded data prescribed
by this section, as appropriate, until
the airplane has been operated for at
least 25 hours of the operating time
specified in § 121.359(a) of this part. 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 accord-
ance with this paragraph must be of
the oldest recorded data accumulated
at the time of testing. Except as pro-
vided in paragraph (i) of this section,
no record need to be kept more than 60
days.

(i) In the event of an accident or oc-

currence that requires immediate noti-
fication of the National Transportation

355

Federal Aviation Administration, DOT

§ 125.227

Safety Board under 49 CFR 830 of its
regulations and that results in termi-
nation of the flight, the certificate
holder shall remove the recorder from
the airplane and keep the recorder data
prescribed by this section, as appro-
priate, for at least 60 days or for a
longer period upon the request of the
Board or the Administrator.

(j) Each flight data recorder system

required by this section must be in-
stalled in accordance with the require-
ments of § 25.1459(a) (except paragraphs
(a)(3)(ii) and (7)), (b), (d) and (e) of this
chapter. A correlation must be estab-
lished between the values recorded by
the flight data recorder and the cor-
responding values being measured. The
correlation must contain a sufficient
number of correlation points to accu-
rately establish the conversion from
the recorded values to engineering
units or discrete state over the full op-
erating range of the parameter. Except
for airplanes having separate altitude
and airspeed sensors that are an inte-
gral part of the flight data recorder
system, a single correlation may be es-
tablished for any group of airplanes—

(1) That are of the same type;
(2) On which the flight recorder sys-

tem and its installation are the same;
and

(3) On which there is no difference in

the type design with respect to the in-
stallation 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.

(k) Each flight data recorder required

by this section must have an approved
device to assist in locating that re-
corder under water.

(l) The following airplanes that were

manufactured before August 18, 1997
need not comply with this section, but
must continue to comply with applica-
ble paragraphs of § 125.225 of this chap-
ter, as appropriate:

(1) Airplanes that meet the Stage 2

noise levels of part 36 of this chapter
and are subject to § 91.801(c) of this
chapter, until January 1, 2000. On and
after January 1, 2000, any Stage 2 air-
plane otherwise allowed to be operated
under Part 91 of this chapter must

comply with the applicable flight data
recorder requirements of this section
for that airplane.

(2) British Aerospace 1–11, General

Dynamics Convair 580, General Dynam-
ics Convair 600, General Dynamics
Convair 640, deHavilland Aircraft Com-
pany Ltd. DHC–7, Fairchild Industries
FH 227, Fokker F–27 (except Mark 50),
F–28 Mark 1000 and Mark 4000, Gulf-
stream Aerospace G–159, Jetstream 4100
Series, Lockheed Aircraft Corporation
Electra 10–A, Lockheed Aircraft Cor-
poration Electra 10–B, Lockheed Air-
craft Corporation Electra 10–E, Lock-
heed Aircraft Corporation Electra L–
188, Lockheed Martin Model 382 (L–100)
Hercules, Maryland Air Industries, Inc.
F27, Mitsubishi Heavy Industries, Ltd.
YS–11, Short Bros. Limited SD3–30,
Short Bros. Limited SD3–60.

(m) All aircraft subject to the re-

quirements of this section that are
manufactured on or after April 7, 2010,
must have a flight data recorder in-
stalled that also—

(1) Meets the requirements in

§ 25.1459(a)(3), (a)(7), and (a)(8) of this
chapter; and

(2) Retains the 25 hours of recorded

information required in paragraph (f)
of this section using a recorder that
meets the standards of TSO–C124a, or
later revision.

(n) In addition to all other applicable

requirements of this section, all Boeing
737 model airplanes manufactured after
August 18, 2000 must record the param-
eters listed in paragraphs (a)(88)
through (a)(91) of this section within
the ranges, accuracies, resolutions, and
recording intervals specified in Appen-
dix E to this part. Compliance with
this paragraph is required no later
than February 2, 2011.

[Doc. No. 28109, 62 FR 38387, July 17, 1997; 62
FR 48135, Sept. 12, 1997, as amended by Amdt.
125–42, 68 FR 42937, July 18, 2003; 68 FR 50069,
Aug. 20, 2003; Amdt. 125–54, 73 FR 12568, Mar.
7, 2008; Amdt. 125–56, 73 FR 73179, Dec. 2, 2008;
Amdt. 125–54, 74 FR 32801, 32804, July 9, 2009]

§ 125.227 Cockpit voice recorders.

(a) No certificate holder may operate

a large turbine engine powered airplane
or a large pressurized airplane with
four reciprocating engines unless an
approved cockpit voice recorder is in-
stalled in that airplane and is operated