Source: https://www.law.cornell.edu/cfr/text/14/appendix-E_to_part_125
Timestamp: 2017-02-27 23:05:11
Document Index: 151061407

Matched Legal Cases: ['art 125', 'art 125', 'art_125', 'art 125', 'art 125', '§ 125', '§ 125', '§ 125', '§ 125', 'art 125']

14 CFR Appendix E to Part 125, Airplane Flight Recorder Specifications | US Law | LII / Legal Information Institute
CFR › Title 14 › Chapter I › Subchapter G › Part 125 › Subpart M › Appendix E_to_part_125 14 CFR Appendix E to Part 125, Airplane Flight Recorder Specifications
There are 7 Updates appearing in the Federal Register for 14 CFR Part 125. View below or at eCFR (GPOAccess)
1. Time or Relative Times Counts. 1
50 KIAS or minimum value to Max Vso, to 1.2 V.D
4, Heading (Primary flight crew reference)
1 or 0.25 for airplanes operated under § 125.226(f)
A sampling rate of 0.5 is recommended. 8. Manual Radio Transmitter Keying or CVR/DFDR synchronization
9. Thrust/Power on each engine - primary flight crew reference
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.
0.5 or 0.25 for airplanes operated under § 125.226(f)
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.
14a.Yaw control position(s) (nonfly-by-wire) 5 18
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.
20. Trailing Edge Flap or Cockpit Control Selection. 10
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
Turbo-jet - 2 discretes enable the 3 states to be determined.
Turbo-prop - 1 discrete.
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
0.3 °C.
As installed. ±3%
±400 Microamps or available sensor range as installed. 0.9 to
As installed ±3%
Record the master warning and record each ‘red’ warning that cannot be determined from other parameters or from the cockpit voice recorder.
2 or 0.5 for airplanes operated under § 125.226(f)
37. Drift Angle. 15
Provided by the Primary Navigation System Reference. Where capacity permits Latitude/longtitude resolution should be 0.0002°.
42. Throttle/power lever position. 16
For airplanes with non-mechanically linked cockpit engine controls. 43. Additional Engine Parameters
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.)
Discretes should show the display system status (e.g., off, normal, fail, composite, sector, plan, nav aids, weather radar, range, copy).
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
A suitable combination of discrete to determine the Primary Navigation System reference.
Decrete “open” or “closed”
Discrete “open” or “closed
82. Cockpit trim control input position - pitch
83. Cockpit trim control input position - roll
Where mechanical means for control inputs are not available, cockpit display trim position should be recorded. 84. Cockpit trim control input position - yaw
88. All cockpit flight control input forces (control wheel, control column, rudder pedal) 18,19
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°)
8 For A330/A340 series airplanes, resolution = 0.30% (0.176°>0.12°)
For A330/A340 series airplanes, seconds per sampling interval = 1
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 A330 B2/B4 series airplanes, resolution = 0.92% (0.230°>0.125°).
13 For A330/A340 series airplanes, resolution = 0.5°C.
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%.
19 For 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; Amdt. 125-62, 78 FR 39971, July 3, 2013]
Title 14 published on 2015-11-17The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 125 after this date.2017-02-08; vol. 82 # 25 - Wednesday, February 8, 201782 FR 9677 - Revisions to Operational Requirements for the Use of Enhanced Flight Vision Systems (EFVS) and to Pilot Compartment View Requirements for Vision Systems