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Title 14: Aeronautics and Space PART 121—OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Subpart K—Instrument and Equipment Requirements
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§ 121.344 Digital flight data recorders for transport category airplanes.
(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; Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

1 of 7 10/20/2011 9:58 A M(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);
(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); Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

2 of 7 10/20/2011 9:58 A M(41) Windshear (when an information source is installed);
(42) Throttle/power lever position;
(43) Additional engine parameters (as designated in Appendix M 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; Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

3 of 7 10/20/2011 9:58 A M(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;
(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 p arameters listed in paragraphs (a)(1) through (a)(18) of this section must be recorded within the ranges and accuracies specified in Appendix B of this part, and— Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

4 of 7 10/20/2011 9:58 A M(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 p arameters listed in paragraphs (a)(1) through (a)(22) of this section must be recorded within the ranges, accuracies, and recording intervals specified in Appendix M 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 M 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 M of this part by August 20, 2001.
(3) That were subject to §121.343(e) of this part, all conditions of §121.343(e) must continue to be met until compliance with paragraph (c)(1) of this section is accomplished.
(d) For all turbine-engine-powered transport category airplanes that were manufactured after October 11, 1991—
(1) The parameters listed in paragraph (a)(1) through (a)(34) of this section must be recorded within the ranges, accuracies, resolutions, and recording intervals specified in Appendix M 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, 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 M 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 M 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 Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

5 of 7 10/20/2011 9:58 A Mthe ranges, accuracies, resolutions, and sampling intervals specified in Appendix M 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 M 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 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 (a)(7)), (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—
(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 §121.343 of this chapter, as appropriate: Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=b85610b6da0b0...

6 of 7 10/20/2011 9:58 A M(1) Airplanes that meet the State 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 SD 3–30, 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 digital flight data recorder installed that also—
(1) Meets the requirements of §25.1459(a)(3), (a)(7), and (a)(8) of this chapter; and
(2) Retains the 25 hours of recorded information required in paragraph (h) 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 M to this part. Compliance with this paragraph is required no later than February 2, 2011.
[Doc. No. 28109, 62 FR 38378, July 17, 1997; 62 FR 48135, Sept. 12, 1997, as amended by Amdt. 121–300, 68 FR 42936, July 18, 2003; 68 FR 50069, Aug. 20, 2003; Amdt. 121–338, 73 FR 12565, Mar. 7, 2008; Amdt. 121–342, 73 FR 73178, Dec. 2, 2008; Amdt. 121–338, 74 FR 32800, July 9, 2009]

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7 of 7 10/20/2011 9:58 A MHome Page> Executive Branch> Code of Federal Regulations > Electronic Code of Federal Regulations



### e-CFR Data is current as of October 6, 2011

Title 14: Aeronautics and Space PART 121—OPERATING REQUIREMENTS: DOM ESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Subpart DD—Special Federal Aviation Regulations
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Appendix M to Part 121—Airplane Flight Recorder Specifications
The recorded values must meet the designated range, resolution and accuracy requirements during static and

dynamic conditions. Dynamic condition means the parameter is experiencing change at the maximum rate attainable, including the maximum rate of reversal. All data recorded must be correlated in time to within one second.

Parameters Range Accuracy (sensor input) Seconds per sampling interval Resolution Remarks 1. Time or relative times
counts. 1 24 Hrs, 0 to 4095 ±0.125% per hour 4 1 sec UTC time preferred when available. Count increments each 4 seconds of system operation. 2. Pressure Altitude

− 1000 ft to

max certificated altitude of aircraft. +5000 ft ±100 to ±700 ft (see table, TSO C124a or TSO C51a) 1 5 ′to 35 ′ Data should be obtained from the air data computer when practicable.

3. Indicated airspeed or Calibrated airspeed 50 KIAS or minimum value to Max V so to 1.2 V. D ±5% and ±3% 1 1 kt Data should be obtained from the air data computer when practicable.

4. Heading (Primary flight crew reference) 0–360° and Discrete “true” or “mag” ±2° 1 0.5° When true or magnetic heading can be selected as the primary heading reference, a discrete indicating selection must be recorded. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

1 of 13 10/9/2011 5:08 PM5. Normal acceleration (vertical) 9 − 3g to +6g ±1% of max range excluding datum error of ±5% 0.125 0.004g

6. Pitch Attitude ±75° ±2° 1 or 0.25 for airplanes operated under §121.344(f) 0.5° A sampling rate of 0.25 is recommended.

7. Roll attitude 2 ±180° ±2° 1 or 0.5 for airplanes operated under §121.344(f) 0.5 A sampling rate of 0.5 is recommended.

8. Manual Radio Transmitter Keying or CVR/DFDR synchronization reference On-Off (Discrete) None 1 Preferably each crew member but one 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—primary flight crew reference Full range forward ±2% 1 (per engine) 0.3% of full range Sufficient parameters (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 “off” 1

11. Longitudinal Acceleration ±1g ±1.5% max. range excluding datum error of ±5% 0.25 0.004g

12a. Pitch control(s) position (nonfly-by-wire systems). 18 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.5% of full range For airplanes that have a flight control breakaway capability that allows either pilot to operate the Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

2 of 13 10/9/2011 5:08 PMcontrols 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-by-wire systems). 318 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.2% of full range

13a. Lateral controlposition(s) (nonflyby-wire). 18 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.2% of full range For airplanes that have a flight control breakaway 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) (fly-by-wire). 418 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.2% of full range.

14a. Yaw control position(s) (nonfly-by-wire). 518 Full Range ±2° unless higher accuracy uniquely required 0.5 0.3% of full range For airplanes that have a flight control breakaway 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. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

3 of 13 10/9/2011 5:08 PM14b. Yaw control position(s) (fly-by-wire). 18 Full Range ±2° unless higher accuracy uniquely required 0.5 0.2% of full range

15. Pitch control surface(s) position. 618 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.3% of full range For airplanes fitted with multiple or split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. The control surfaces may be sampled alternately once per second to produce the sampling interval of 0.5 or 0.25, as applicable. 16. Lateral control surface(s) position. 718 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §121.344(f) 0.3% of full range A suitable combination of surface position 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, as applicable. 17. Yaw control surface(s) position. 818 Full Range ±2° unless higher accuracy uniquely required 0.5 0.2% of full range For airplanes with multiple or split surfaces, a suitable combination of surface position 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. 18. Lateral Acceleration ±1g ±1.5% max. range 0.25 0.004g Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

4 of 13 10/9/2011 5:08 PMexcluding datum error of ±5% 19. Pitch Trim Surface Position Full Range ±3° Unless Higher Accuracy Uniquely Required 1 0.6% of full range

20. Tra iling Edge Flap or Cockpit Control Selection. 10 Full Range or Each Position (discrete) ±3° or as Pilot's indicator 2 0.5% of full range Flap position and cockpit control may each be sampled at 4 second intervals, to give a data point every 2 seconds. 21. Leading Edge Flap or Cockpit Control Selection. 11 Full Range or Each Discrete Position ±3° or as Pilot's indicator and sufficient to determine each discrete position 2 0.5% of full range Left and right sides, or flap position and cockpit control may each be sampled at 4 second intervals, so as to give a data point every 2 seconds. 22. Each Thrust Reverser Position (or equivalent for propeller airplane) Stowed, In Transit, and Reverse (Discrete) 1 (per engine) Turbo-jet—2 discretes enable the 3 states to be determined.Turboprop—discrete. 23. Ground spoiler position or brake selection 12 Full range or each position (discrete) ±2° Unless higher accuracy uniquely required 1 or 0.5 for airplanes operated under §121.344(f) 0.5% of full range

24. Outside Air Temperature or Total Air Temperature. 13 − 50 °C to +90 °C ±2 °C 2 0.3 °C

25. Autopilot/Autothrottle/AFCS Mode and Engagement Status A suitable combination of discretes 1 Discretes should show 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% whichever is greater below 500 ft and ±5% above 1 1 ft +5% above 500 ft For autoland/category 3 operations. Each radio altimeter should be recorded, Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

5 of 13 10/9/2011 5:08 PM500 ft but arranged so that at least one is recorded each second. 27. Localizer Deviation, MLS Azimuth, or GPS Latitude Deviation ±400 Microamps or available sensor range as installed ±62° As installed ±3% recommended 1 0.3% of full range For autoland/category 3 operations. Each system should be recorded but 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. 28. Glideslope Deviation, MLS Elevation, or GPS Vertical Deviation ±400 Microamps or available sensor range as installed 0.9 to +30° As installed +/3

− 3% recommended 1 0.3% of full range For autoland/category 3 operations. Each system should be recorded but 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 “off” 1 A single discrete is 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 airplane system reference nose or main gear) Discrete “air” or “ground” 1 (0.25 recommended)
32. Angle of Attack (If measured directly) As installed As installed 2 or 0.5 for airplanes operated under §121.344(f) 0.3% of full range If left and right sensors are available, each may be recorded at 4 or 1 second intervals, as Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

6 of 13 10/9/2011 5:08 PMappropriate, so as to give a data point at 2 seconds or 0.5 second, as required. 33. Hydraulic Pressure Low, Each System Discrete or available

sensor range, “low” or “normal” ±5% 2 0.5% of full range

34. Groundspeed As Installed Most Accurate Systems Installed 1 0.2% of full range

35. GPWS (ground prox imity warning system) Discrete “warning” or “off” 1 A suitable combination of discretes unless recorder capacity is limited in which case a single discrete for all modes is acceptable. 36. Landing Gear Position or Landing gear cockpit control selection Discrete 4 A suitable combination of discretes should be recorded. 37. Drift Angle. 15 As installed As installed 4 0.1° 38. Wind Speed and Direction As installed As installed 4 1 knot, and 1.0° 39. Latitude and Longitude As installed As installed 4 0.002°, or as installed Provided by the Primary Navigation System Reference. Where capacity permits Latitude/longitude resolution should be 0.0002°. 40. Stick shaker and pusher activation Discrete(s) “on” or “off” 1 A suitable combination of discretes to determine activation. 41. Windshear Detection Discrete “warning” or “off” 1

42. Throttle/power Leverl position. 16 Full Range ±2% 1 for each lever 2% of full range For airplanes with non-mechanically linked cockpit engine controls. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

7 of 13 10/9/2011 5:08 PM43. Additional Engine Parameters As installed As installed Each engine each second 2% of full range Where capacity 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 Avoidance System (TCAS) Discretes As installed 1 A suitable 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% (1 per 64 sec.) 0.2% of full range 48. Selected Altitude Full Range ±5% 1 100 ft 49. Selected speed Full Range ±5% 1 1 knot 50. Selected Mach Full Range ±5% 1 .01 51. Selected vertical speed Full Range ±5% 1 100 ft/min 52. Selected heading Full Range ±5% 1 1° 53. Selected flight path Full Range ±5% 1 1° 54. Selected decision height Full Range ±5% 64 1 ft 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. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

8 of 13 10/9/2011 5:08 PM56. Multi-function/Engine Alerts Display format Discrete(s) 4 Discretes should show 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% 2 2% of full range 58. Thrust target Full Range ±2% 4 2% of full range 59. Fuel quantity in CG trim tank Full Range ±5% (1 per 64 sec.) 1% of full range 60. Primary Navigation System Reference Discrete GPS, INS, VOR/DME, MLS, Loran C, Omega, Localizer Glideslope 4 A suitable combination of discretes to determine the Primary Navigation System reference.

61. Ice Detection Discrete “ice” or “no ice” 4

62. Engine warning each engine vibration Discrete 1
63. Engine warning each engine over temp Discrete 1
64. Engine warning each engine oil pressure low Discrete 1
65. Engine warning each engine over speed Discrete 1

66. Yaw Trim Surface Position Full Range ±3% Unless Higher Accuracy Uniquely Required 2 0.3% of full range

67. Roll Trim Surface Position Full Range ±3% Unless Higher Accuracy Uniquely Required 2 0.3% of full range

68. Brake Pressure (left and right) As installed ±5% 1 To determine braking effort applied by pilots or by autobrakes. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

9 of 13 10/9/2011 5:08 PM69. Brake Pedal Application (left and right) Discrete or Analog “applied” or “off” ±5% (Analog) 1 To determine braking applied by pilots.

70. Yaw or sideslip angle Full Range ±5% 1 0.5° 71. Engine bleed valve position Discrete “open” or “closed” 4

72. De-icing or anti-icing system selection Discrete “on” or “off” 4

73. Computed center of gravity Full Range ±5% (1 per 64 sec.) 1% of full range 74. AC electrical bus status Discrete “power” or “off” 4 Each bus.

75. DC electrical bus status Discrete “power” or “off” 4 Each bus.

76 APU bleed valve position Discrete “open” or “closed” 4

77. Hydraulic Pressure (each system) Full range ±5% 2 100 psi
78. Loss of cabin pressure Discrete “loss” or “normal” 1

79. Computer failure (critical flight and engine control systems) Discrete “fail” or “normal” 4

80. Heads-up display (when an information source is installed) Discrete(s) “on” or “off” 4

81. Para-visual display (when an information source is installed) Discrete(s) “on” or “off” 82. Cockpit trim control input position—pitch Full Range ±5% 1 0.2% of full range Where mechanical means for control inputs are not available, cockpit display trim positions should be recorded. 83. Cockpit trim control input position—roll Full Range ±5% 1 0.7% of full range Where mechanical means for control inputs are not available, cockpit display trim position should be recorded. Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

10 of 13 10/9/2011 5:08 PM84. Cockpit trim control input position—yaw Full range ±5% 1 0.3% of full range Where mechanical means for control input are not available, cockpit display trim positions should be recorded. 85. Tra iling edge flap and cockpit flap control position Full Range ±5% 2 0.5% of full range Trailing edge flaps 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 flap control position Full Range or Discrete ±5% 1 0.5% of full range 87. Ground spoiler position and speed brake selection Full range or discrete ±5% 0.5 0.3% of full range 88. All cockpit flight control input forces (control wheel, control column, rudder pedal) 18 19 Full range Control wheel ±70 lbs Control column ±85 lbs Rudder pedal ±165 lbs ±5% 1 0.3% of full range For fly-by-wire flight control systems, where flight control surface position is a function of the 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. 89. Yaw damper status Discrete (on/off) 0.5
90. Yaw damper command Full range As installed 0.5 1% of full range 91. Standby rudder valve status Discrete 0.5 Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

11 of 13 10/9/2011 5:08 PM1 For A300 B2/B4 airplanes, resolution=6 seconds.

2 For A330/A340 series airplanes, resolution=0.703°.

3 For A318/A319/A320/A321 series airplanes, resolution=0.275% (0.088°>0.064°).
For A330/A340 series airplanes, resolution=2.20%(0.703°>0.064°).

4 For A318/A319/A320/A321 series airplanes, resolution=0.22% (0.088°>0.080°).
For A330/A340 series airplanes, resolution=1.76% (0.703°>0.080°).

5 For A330/A340 series airplanes, resolution = 1.18% (0.703°>0.120°).

6 For A330/A340 series airplanes, resolution=0.783% (0.352°>0.090°).

7 For A330/A340 series airplanes, aileron resolution = 0.704% (0.352°>0.100°). For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703°>0.100°).

8 For A330/A340 series airplanes, resolution=0.30% (0.176°>0.12°).
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°>0.120°).

11 For A330/A340 series airplanes, resolution = 1.05% (0.250°>0.120°). For A300 B2/B4 series airplanes, resolution = 0.92% (0.230°>0.125°).

12 For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703°>0.100°).

13 For A330/A340 series airplanes, resolution=0.5°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%.

18 For all aircraft manufactured on or after December 6, 2010, the seconds per sampling interval is 0.125. Each input must be recorded at this rate. Alternately sampling inputs (interleaving) to meet this sampling Electronic Code of Federal Regulations: http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&sid=857685b5709e5...

12 of 13 10/9/2011 5:08 PMinterval is prohibited.

19 For 737 model airplanes manufactured between August 19, 2000 and April 6, 2010: the seconds per sampling interval is 0.5 per control input; the remarks regarding the sampling rate do not apply; a single control wheel force transducer installed on the left cable control is acceptable provided the left and right control wheel positions also are recorded.
[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; Amdt. 125–54, 73 FR 12566, Mar. 7, 2008; Amdt. 121–338, 73 FR 12566, Mar. 7, 2008; Amdt. 121–342, 73 FR 73179, Dec. 2, 2008; Amdt. 121–349, 75 FR 17046, Apr. 5, 2010; Amdt. 121–347, 75 FR 7356, Feb. 19, 2010]

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