14 CFR 125.226 -- Digital flight data recorders.

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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

§ 125.226 Digital flight data recorders.
(a)  Except as provided in paragraph (l) of this section, no person may operate under this part a turbineengine-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
recorders required by 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 (a)(82) of this section if currently recorded;
(20)  Trailing edge flap or cockpit flap control selection (except when parameters of paragraph (a)(85) of
this section apply);
(21)  Leading edge flap or cockpit flap control selection (except when parameters of paragraph (a)(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 (a)(87) of
this section apply);
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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

(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 designed in appendix E 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);

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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

(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 of 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;

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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

(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;
(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 manufactured on or before October 11, 1991,
by August 20, 2001—
(1)  For airplanes not equipped as of July 16, 1996, with a flight data acquisition unit (FDAU), the
parameters listed 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
parameter.
(ii)  Parameters listed in paragraphs (a)(12) through (a)(17) each may be recorded from a single
source.
(2)  For airplanes that were equipped as of July 16, 1996, with a flight data acquisition unit (FDAU), the
parameters listed in paragraphs (a)(1) through (a)(22) of this section must be recorded within the
ranges, accuracies, and recording intervals specified in Appendix 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 required 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 maintenance 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.
(c)  For all turbine-engine-powered transport category airplanes manufactured 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 Appendix 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
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 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 compliance with paragraph (c)(1) of this section is accomplished.
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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

(d)  For all turbine-engine-powered transport category airplanes that were manufactured after October 11,
1991—
(1)  The parameters listed in paragraphs (a)(1) through (a)(34) of this section must be recorded within
the ranges, accuracies, resolutions, and recording 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, accuracies, resolutions, and sampling intervals 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 paragraph (a) (1) through (57) of this section must be recorded within the
ranges, accuracies, resolutions, and recording intervals specified in Appendix E 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 E
of this part.
(3)  In addition to the requirements of paragraphs (e)(1) and (e)(2) of this section, all Boeing 737 model
airplanes must also comply with the requirements of paragraph (n) of this section, as applicable.
(f)  For all turbine-engine-powered transport category airplanes manufactured after August 19, 2002—
(1)  The parameters listed in paragraphs (a)(1) through (a)(88) of this section must be recorded within
the ranges, accuracies, resolutions, and recording 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 paragraph (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 recorded 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 accordance with this paragraph must be
of the oldest recorded data accumulated at the time of testing. Except as provided in paragraph (i) of this
section, no record need to be kept more than 60 days.
(i)  In the event of an accident or occurrence that requires immediate notification of the National
Transportation Safety Board under 49 CFR 830 of its regulations and that results in termination of the
flight, the certificate holder shall remove the recorder from the airplane and keep the recorder data
prescribed by this section, as appropriate, 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 installed in accordance with the
requirements of § 25.1459(a) (except paragraphs (a)(3)(ii) and (7)), (b), (d) and (e) of this chapter. A
correlation must be established between the values recorded by the flight data recorder and the
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eCFR :: 14 CFR 125.226 -- Digital flight data recorders. (FAR 125.226)

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—
(1)  That are of the same type;
(2)  On which the flight recorder system and its installation are the same; and
(3)  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.
(k)  Each flight data recorder required by this section must have an approved device to assist in locating that
recorder 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 applicable paragraphs of § 125.225 of this chapter, 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 airplane 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 Dynamics Convair 600, General
Dynamics Convair 640, deHavilland Aircraft Company Ltd. DHC–7, Fairchild Industries FH 227,
Fokker F–27 (except Mark 50), F–28 Mark 1000 and Mark 4000, Gulfstream Aerospace G–159,
Jetstream 4100 Series, Lockheed Aircraft Corporation Electra 10–A, Lockheed Aircraft Corporation
Electra 10–B, Lockheed Aircraft Corporation Electra 10–E, Lockheed 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 requirements of this section that are manufactured on or after April 7, 2010, must
have a flight data recorder installed 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 parameters listed in paragraphs (a)(88) through (a)
(91) of this section within the ranges, accuracies, resolutions, and recording intervals specified in
Appendix 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]

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