14 CFR Appendix C to Part 135, Helicopter Flight Recorder Specifications

Appendix C to Part 135 - Helicopter Flight Recorder Specifications
Parameters Range Installed system 1 minimum accuracy (to recovered data) Sampling interval (per second) Resolution 3 read out
Relative time (from recorded on prior to takeoff) 25 hr minimum ±0.125% per hour 1 1 sec.
Indicated airspeed Vm in to VD (KIAS) (minimum airspeed signal attainable with installed pilot-static system) ±5% or ±10 kts., whichever is greater 1 1 kt.
Altitude −1,000 ft. to 20,000 ft. pressure altitude ±100 to ±700 ft. (see Table 1, TSO C51-a) 1 25 to 150 ft.
Magnetic heading 360° ±5° 1 1°.
Vertical acceleration −3g to 6g ±0.2g in addition to ±0.3g maximum datum 4 (or 1 per second where peaks, ref. to 1g are recorded) 0.05g.
Longitudinal acceleration ±1.0g ±1.5% max. range excluding datum error of ±5% 2 0.03g.
Pitch attitude 100% of usable range ±2° 1 0.8°.
Roll attitude ±60° or 100% of usable range, whichever is greater ±2° 1 0.8°.
Altitude rate ±8,000 fpm ±10% Resolution 250 fpm below 12,000 ft. indicated 1 250 fpm below 12,000.
Engine Power, Each Engine
Main rotor speed Maximum range ±5% 1 1% 2
Free or power turbine Maximum range 5% 1 1% 2
Engine torque Maximum range ±5% 1 1% 2
Flight Control - Hydraulic Pressure
Primary (discrete) High/low 1
Secondary - if applicable (discrete) High/low 1
Radio transmitter keying (discrete) On/off 1
Autopilot engaged (discrete) Engaged or disengaged 1
SAS status - engaged (discrete) Engaged/disengaged 1
SAS fault status (discrete) Fault/OK 1
Flight Controls
Collective 4 Full range ±3% 2 1% 2
Pedal Position 4 Full range ±3% 2 1% 2
Lat. Cyclic 4 Full range ±3% 2 1% 2
Long. Cyclic 4 Full range ±3% 2 1% 2
Controllable Stabilator Position 4 Full range ±3% 2 1% 2

1 When data sources are aircraft instruments (except altimeters) of acceptable quality to fly the aircraft the recording system excluding these sensors (but including all other characteristics of the recording system) shall contribute no more than half of the values in this column.

2 Per cent of full range.

3 This column applies to aircraft manufactured after October 11, 1991.

4 For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4.

[Doc. No. 25530, 53 FR 26152, July 11, 1988; 53 FR 30906, Aug. 16, 1988, as amended by Amdt. 135-69, 62 FR 38397, July 17, 1997; Amdt. 135-113, 73 FR 12570, Mar. 7, 2008; 73 FR 15281, Mar. 21, 2008; Amdt. 135-121, 75 FR 17047, Apr. 5, 2010]

Title 14 published on 03-May-2017 03:58

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 135 after this date.

  • 2017-02-08; vol. 82 # 25 - Wednesday, February 8, 2017
    1. 82 FR 9677 - Revisions to Operational Requirements for the Use of Enhanced Flight Vision Systems (EFVS) and to Pilot Compartment View Requirements for Vision Systems
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final rule; delay of effective date.
      The effective date of the rule amending 14 CFR parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 published at 81 FR 90126, December 13, 2016, is delayed until March 21, 2017, except for the amendments to §§ 61.66 (amendatory instruction no. 15), 91.175 (amendatory instruction no. 18), 91.1039 (amendatory instruction no. 23), 121.651 (amendatory instruction no. 27), 125.325 (amendatory instruction no. 33), 125.381 (amendatory instruction no. 35), and 135.225 (amendatory instruction no. 38), which are effective March 13, 2018.
      14 CFR Parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135