1. Time or Relative Time Counts ¹

24 Hrs, 0 to 4095

±0.125% Per Hour

4

1 sec

UTC time preferred when available. Counter 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≢ and 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.

5. 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 § 135.152(j)

0.5°

A sampling rate of 0.25 is recommended.

7. Roll Attitude ²

±180°

±2°

1 or 0.5 0.5 airplanes operated under § 135.152(j)

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 § 135.152(j)

0.5% 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.

12b. Pitch control(s) position (fly-by-wire systems) ^{3 18}

Full Range

±2° unless higher accuracy uniquely required

0.5 or 0.25 for airplanes operated under § 135.152(j)

0.2% of full range

13a. Lateral control position(s) (nonfly-by-wire) ¹⁸

Full Range

±2° unless higher accuracy uniquely required

0.5 or 0.25 for airplanes operated under § 135.152(j)

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) ^{4 18}

Full Range

±2° unless higher accuracy uniquely required

0.5 or 0.25 for airplanes operated under § 135.152(j)

0.2% of full range

14a. Yaw control position(s) (nonfly-by-wire) ^{5 18}

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 of 0.5 or 0.25, as applicable.

14b. 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 ^{6 18}

Full Range

±2° unless higher accuracy uniquely required

0.5 or 0.25 for airplanes operated under § 135.152(j).

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 to produce the sampling interval of 0.5 or 0.25, as applicable.

16. Lateral control surface(s) position ^{7 18}

Full Range

±2° unless higher accuracy uniquely required

0.5 or 0.25 for airplanes operated under § 135.152(j)

0.2% 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 ^{8 18}

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 excluding datum error of ±5%

0.25

0.004g

19. Pitch Trim Surface Position

Full Range

±3° Unless Higher Accuracy Uniquely Required

1

0.6% of full range

20. Trailing 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 alternately 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, of flap position and cockpit control may each be sampled at 4 second intervals, so as to give a data point to 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 determinedTurbo-prop—1 discrete

23. Ground Spoiler Position or Speed Brake Selection ¹²

Full Range or Each Position (discrete)

±2° Unless Higher Accuracy Uniquely Required

1 or 0.5 for airplanes operated under § 135.152(j)

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 500 ft

1

1 ft + 5% above 500 ft

For autoland/category 3 operations. Each radio altimeter should be recorded, but arranged so that at least one is recorded each second.

27. Localizer Deviation, MLS Azimuth, or GPS Lateral 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 installed0.9 to + 30°

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.

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 § 135.152(j)

0.3% of full range

If left and right sensors are available, each may be recorded at 4 or 1 second intervals, as appropriate, 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 proximity 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 lever position ¹⁶

Full Range

±2%

1 for each lever

2% of full range

For airplanes with non-mechanically linked cockpit engine controls.

43. 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.

56. 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 comand 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, 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.

69. 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”

1.

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.

84. 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. Trailing 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

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 breakaway 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.