Federal Aviation Administration, DOT Parameters Range Pt. 121, App. B Resolution 4 readout Accuracy sensor input to DFDR readout Sampling interval (per second) 1 (per 4 seconds per engine). 1 ........................ 0.2% 2. 1 ........................ 1 ........................ 4 ........................ 0.01g. 1 ........................ 0.2% 2. 4 ........................ 0.01g. 1 ........................ 0.3% 2. 1 ........................ 1 ........................ 1 ........................ 0.3% 2. 0.3% 2. 1 ........................ 1 ft + 5% 2 above 500-. Thrust Reverser Position ........ Stowed, In Transit, and Reverse (Discrete). ................................................ Ground Spoiler Position/ Speed Brake Selection. Marker Beacon Passage ........ Autopilot Engagement ............ Longitudinal Acceleration ....... Full Range or Each Discrete Position. Discrete .......................... Discrete .......................... Section1g .................................. Pilot Input and/or Surface Position - Primary Controls (Pitch, Roll, Yaw) 3. Lateral Acceleration ................ Full Range ...................... Section2% Unless Higher Accuracy Uniquely Required. ................................................ ................................................ Section1.5% max range excluding datum error of Section5%. Section2Section Unless Higher Accuracy Uniquely Required. Pitch Trim Position ................. Full Range ...................... Glideslope Deviation .............. Localizer Deviation ................. AFCS Mode and Engagement Status. Radio Altitude ......................... Section400 Microamps ............. Section400 Microamps ............. Discrete .......................... Master Warning ...................... Main Gear Squat Switch Status. Angle of Attack (if recorded directly).. Outside Air Temperature or Total Air Temperature.. Hydraulics, Each System Low Pressure. Groundspeed. ......................... Discrete .......................... Discrete .......................... Section2 Ft or Section3% Whichever is Greater Below 500 Ft and Section5% Above 500 Ft. ................................................ ................................................ As installed ..................... As installed ............................ 2 ........................ 0.3% 2 Section50 SectionC to + 90 SectionC ......... Section2 Sectionc ...................................... 0.5 ..................... 0.3 Sectionc Discrete .......................... ................................................ 0.5 ..................... or 0.5% 2 As installed ..................... Most Accurate Systems Installed (IMS Equipped Aircraft Only). 1 ........................ 0.2% 2 Section1g .................................. Section20 ft to 2,500 ft ........... Section1.5% max range excluding datum error of Section5%. Section3% Unless Higher Accuracy Uniquely Required. Section3% ....................................... Section3% ....................................... ................................................ 1 ........................ 1 ........................ If additional recording capacity is available, recording of the following parameters is recommended. The parameters are listed in order of significance: Drift Angle ............................... Wind Speed and Direction ..... Latitude and Longitude ........... Brake pressure/Brake pedal position. Additional engine parameters: EPR ................................. N1 .................................... N2 .................................... EGT ................................. Throttle Lever Position ........... Fuel Flow ................................ TCAS: TA .................................... RA ................................... Sensitivity level (as selected by crew). GPWS (ground proximity warning system). Landing gear or gear selector position. DME 1 and 2 Distance ........... Nav 1 and 2 Frequency Selection. When available, As installed. When available, As installed. When available, As installed. As installed ..................... As installed ............................ 4 ........................ As installed ............................ 4 ........................ As installed ............................ 4 ........................ As installed ............................ 1 ........................ As As As As As As As As As As As As 1 1 1 1 1 1 installed installed installed installed installed installed ..................... ..................... ..................... ..................... ..................... ..................... installed installed installed installed installed installed ............................ ............................ ............................ ............................ ............................ ............................ (per (per (per (per (per (per engine). engine). engine). engine). engine). engine). .. .. .. .. .. .. As installed ..................... As installed ..................... As installed ..................... As installed ............................ As installed ............................ As installed ............................ 1 ........................ 1 ........................ 2 ........................ Discrete .......................... ................................................ 1 ........................ Discrete .......................... ................................................ 0-200 NM; ...................... Full range ....................... As installed ............................ As installed ............................ 0.25 (1 per 4 seconds). 0.25 ................... 0.25 ................... 1 mi. 1 When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the derivation of altitude to 5 feet. 2 Per cent 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-bywire) 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. 257 VerDate Sep<11>2014 08:20 May 17, 2019 Jkt 247048 PO 00000 Frm 00267 Fmt 8010 Sfmt 8002 Y:\SGML\247048.XXX 247048