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Federal Aviation Regulation Appendix E to Part 125 - Airplane Flight Recorder Specifications
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Appendix E to Part 125 — Airplane Flight Recorder Specifications
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 Vso, 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 §125.226(f) 0.5° A sampling rate of 0.25 is recommended.
7. Roll Attitude2 ±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.
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 §125.226(f) 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 §125.226(f) 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 §125.226(f) 0.2% of full range For airplanes that have a flight control break away 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 §125.226(f) 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 interval of 0.5.
15. Pitch control surface(s) position6 18 Full range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §125.226(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 to produce the sampling interval of 0.5 or 0.25, as applicable.
16. Lateral control surface(s) position7 18 Full Range ±2° unless higher accuracy uniquely required 0.5 or 0.25 for airplanes operated under §125.226(f) 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) position8 18 Full range ±2° unless higher accuracy uniquely required 0.5 0.2% of full range For airplanes fitted 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.
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 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.
Turbo-prop—1 discrete.
23. Ground Spoiler Position or Speed Brake Selection12 Full Range or Each Position (discrete) ±2° Unless higher accuracy uniquely required 1 or 0.5 for airplanes operated under §125.226(f) 0.2% of full range
24. Outside Air Temperature or Total Air Temperature.13 −50 °C to +90 °C ±2 °C 2 0.3 °C.
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 installed. 0.9 to
+ 30° As installed ±3%
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 §125.226(f) 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.
37. Drift Angle.15 As installed As installed 4 0.1%.
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/longtitude resolution should be 0.0002°.
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.
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.
51. Selected vertical speed Full range ±5% 1 100 ft/min.
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 command.17 Full Range ±2% 2 2% of full range
60. Primary Navigation System Reference Discrete GPS, INS, VOR/DME, MLS, Loran C, Omega, Localizer Glideslope 4 A suitable combination of discrete to determine the Primary Navigation System reference.
70. Yaw or sideslip angle Full Range ±5% 1 0,5°.
71. Engine bleed valve position Decrete “open” or “closed” 4
76. APU bleed valve position Discrete “open” or “closed 4.
88. All cockpit flight control input forces (control wheel, control column, rudder pedal)18 19 Full range
3For A318/A319/A320/A321 series airplanes, resolution = 0.275% (0.088°>0.064°)
4For A318/A319/A320/A321 series airplanes, resolution = 0.22% (0.088°>0.080°)
6For A330/A340 series airplanes, resolution = 0.783% (0.352°>0.090°)
8For A330/A340 series airplanes, resolution = 0.30% (0.176°>0.12°)
10For A330/A340 series airplanes, resolution = 1.05% (0.250°>0.120°)
11For A330/A340 series airplanes, resolution = 1.05% (0.250°>0.120°). For A330 B2/B4 series airplanes, resolution = 0.92% (0.230°>0.125°).
13For A330/A340 series airplanes, resolution = 0.5°C.
18For 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 interval is prohibited.
19For all 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 38390, July 17, 1997; 62 FR 48135, Sept. 12, 1997, as amended by Amdt. 125–32, 64 FR 46121, Aug. 24, 1999; 65 FR 2295, Jan. 14, 2000; Amdt. 125–32, 65 FR 2295, Jan. 14, 2000; Amdt. 125–34, 65 FR 51745, Aug. 24, 2000; 65 FR 81735, Dec. 27, 2000; Amdt. 125–39, 67 FR 54323, Aug. 21, 2002; Amdt. 125–42, 68 FR 42937, July 18, 2003; 68 FR 50069, Aug. 20, 2003; 68 FR 53877, Sept. 15, 2003; Amdt. 125–54, 73 FR 12568, Mar. 7, 2008; Amdt. 125–56, 73 FR 73180, Dec. 2, 2008; Amdt. 125–60, 75 FR 17046, Apr. 5, 2010; Amdt. 125–59, 75 FR 7357, Feb. 19, 2010]
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