[Code of Federal Regulations] [Title 14, Volume 2] [Revised as of January 1, 2008] From the U.S. Government Printing Office via GPO Access [CITE: 14CFR125 App D] [Page 1034-1035] TITLE 14--AERONAUTICS AND SPACE CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) PART 125_CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT--Table of Contents Subpart M_Continued Airworthiness and Safety Improvements Sec. Appendix D to Part 125--Airplane Flight Recorder Specification ---------------------------------------------------------------------------------------------------------------- Accuracy sensor Parameters Range input to DFDR Sampling interval Resolution \4\ readout (per second) read out ---------------------------------------------------------------------------------------------------------------- Time (GMT or Frame Counter) 24 Hrs............ 0.125% Per seconds). frame). Hour. Altitude........................ -1,000 ft to max 100 to 7 aircraft. 00 ft (See Table 1, TSO-C51a). Airspeed........................ 50 KIAS to Vso, 5%, 3 %. Heading......................... 360[deg].......... 2[deg]. Normal Acceleration (Vertical).. -3g to +6g........ 1% of max range excluding datum error of 5%. Pitch Attitude.................. 75[deg]. eq>2[deg]. Roll Attitude................... 180[deg]. eq>2[deg]. Radio Transmitter Keying........ On-Off (Discrete). .................. 1................. .................. Thrust/Power on Each Engine..... Full range forward 2%. Trailing Edge Flap or Cockpit Full range or each 3[deg] or as pilot's Indicator. Leading Edge Flap or Cockpit Full range or each 3[deg] or as pilot's indicator. Thrust Reverser Position........ Stowed, in .................. 1 (per 4 seconds .................. transit, and per engine). reverse (Discrete). Ground Spoiler Position/Speed Full range or each 2% unless higher accuracy uniquely required. Marker Beacon Passage........... Discrete.......... .................. 1................. .................. Autopilot Engagement............ Discrete.......... .................. 1................. .................. Longitudinal Acceleration....... 1g. eq>1.5% max range excluding datum error of 5 %. Pilot Input and/or Surface Full range........ 2[deg] unless (Pitch, Roll, Yaw) \3\. higher accuracy uniquely required. Lateral Acceleration............ 1g. eq>1.5% max range excluding datum error of 5 %. Pitch Trim Position............. Full range........ 3% unless higher accuracy uniquely required. Glideslope Deviation............ 400 Microamps. eq>3%. Localizer Deviation............. 400 Microamps. eq>3%. AFCS Mode and Engagement Status. Discrete.......... .................. 1................. .................. Radio Altitude.................. -20 ft to 2,500 ft 2 Ft or 3 % Whichever is Greater Below 500 Ft and 5 % Above 500 Ft. Master Warning.................. Discrete.......... .................. 1................. .................. Main Gear Squat Switch Status... Discrete.......... .................. 1................. .................. Angle of Attack (if recorded As installed...... As installed...... 2................. 0.3% \2\. directly). Outside Air Temperature or Total -50[deg] C to 2[deg] C. Hydraulics, Each System Low Discrete.......... .................. 0.5............... or 0.5% \2\. Pressure. Groundspeed..................... As Installed...... Most Accurate 1................. 0.2% \2\. Systems Installed (IMS Equipped Aircraft Only). ---------------------------------------------------------------------------------------------------------------- If additional recording capacity is available, recording of the following parameters is recommended. The parameters are listed in order of significance: ---------------------------------------------------------------------------------------------------------------- Drift Angle..................... When available. As As installed...... 4................. .................. installed. Wind Speed and Direction........ When available. As As installed...... 4................. .................. installed. Latitude and Longitude.......... When available. As As installed...... 4................. .................. installed. Brake pressure/Brake pedal As installed...... As installed...... 1................. .................. position. Additional engine parameters: EPR......................... As installed...... As installed...... 1 (per engine).... .................. N \1\....................... As installed...... As installed...... 1 (per engine).... .................. N \2\....................... As installed...... As installed...... 1 (per engine).... .................. EGT......................... As installed...... As installed...... 1 (per engine).... .................. Throttle Lever Position......... As installed...... As installed...... 1 (per engine).... .................. [[Page 1035]] Fuel Flow....................... As installed...... As installed...... 1 (per engine).... .................. TCAS: TA.......................... As installed...... As installed...... 1................. .................. RA.......................... As installed...... As installed...... 1................. .................. Sensitivity level (as As installed...... As installed...... 2................. .................. selected by crew). GPWS (ground proximity warning Discrete.......... .................. 1................. .................. system). Landing gear or gear selector Discrete.......... .................. 0.25 (1 per 4 .................. position. seconds). DME 1 and 2 Distance............ 0-200 NM;......... As installed...... 0.25.............. 1 mi. Nav 1 and 2 Frequency Selection. Full range........ As installed...... 0.25.............. .................. ---------------------------------------------------------------------------------------------------------------- \1\ When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the derivation of altitude to 5 feet. \2\ Percent of full range. \3\ For airplanes that can demonstrate the capability of deriving either the control input on control movement (one from the other) for all modes of operation and flight regimes, the ``or'' applies. For airplanes with non- mechanical control systems (fly-by-wire) the ``and'' applies. In airplanes with split surfaces, suitable combination of inputs is acceptable in lieu of recording each surface separately. \4\ This column applies to aircraft manufactured after October 11, 1991. [Doc. No. 25530, 53 FR 26150, July 11, 1988; 53 FR 30906, Aug. 16, 1988]