Pt. 121, App. M 14 CFR Ch. I (1-1-19 Edition) The recorded values must meet the designated range, resolution and accuracy requirements during static and dynamic conditions. Dynamic condition means the parameter is experiencing change at the maximum rate attainable, including the maximum rate of reversal. All data recorded must be correlated in time to within one second. Parameters Range Accuracy (sensor input) Seconds per sampling interval 84. Cockpit trim control input position - yaw. Full range .......... Section5% ................... 1 ........................ 0.3% of full range. 85. Trailing edge flap and cockpit flap control position. Full Range ......... Section5% ................... 2 ........................ 0.5% of full range. 86. Leading edge flap and cockpit flap control position. 87. Ground spoiler position and speed brake selection. 88. All cockpit flight control input forces (control wheel, control column, rudder pedal) 18 19. Full Range or Discrete. Section5% ................... 1 ........................ 0.5% of full range Full range or discrete. Section5% ................... 0.5 ..................... 0.3% of full range. Full range .......... Control wheel Section70 lbs. Control column Section85 lbs. Rudder pedal Section165 lbs. Section5% ................... 1 ........................ 0.3% of full range. 0.5 ..................... 1% of full range. 89. Yaw damper Discrete (on/off) status. 90. Yaw damper Full range .......... command. 91. Standby rudDiscrete ............. der valve status. Resolution Remarks Where mechanical means for control input are not available, cockpit display trim positions should be recorded. Trailing edge flaps and cockpit flap control position may each be sampled alternately at 4 second intervals to provide a sample each 0.5 second. For fly-by-wire flight control systems, where flight control surface position is a function of the displacement of the control input device only, it is not necessary to record this parameter. For airplanes that have a flight control break away capability that allows either pilot to operate the control independently, record both control force inputs. The control force inputs may be sampled alternately once per 2 seconds to produce the sampling interval of 1. 0.5 ..................... As installed ........ 0.5. 1 For A300 B2/B4 airplanes, resolution = 6 seconds. A330/A340 series airplanes, resolution = 0.703Section. A318/A319/A320/A321 series airplanes, resolution = 0.275% (0.088Section>0.064Section). For A330/A340 series airplanes, resolution = 2.20%(0.703Section>0.064Section). 4 For A318/A319/A320/A321 series airplanes, resolution = 0.22% (0.088Section>0.080Section). For A330/A340 series airplanes, resolution = 1.76% (0.703Section>0.080Section). 5 For A330/A340 series airplanes, resolution = 1.18% (0.703Section >0.120Section). For A330/A340 series airplanes, seconds per sampling interval = 1. 6 For A330/A340 series airplanes, resolution = 0.783% (0.352Section>0.090Section). 7 For A330/A340 series airplanes, aileron resolution = 0.704% (0.352Section>0.100Section). For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703Section>0.100Section). 8 For A330/A340 series airplanes, resolution = 0.30% (0.176Section>0.12Section). For A330/A340 series airplanes, seconds per sampling interval = 1. 9 For B-717 series airplanes, resolution = .005g. For Dassault F900C/F900EX airplanes, resolution = .007g. 10 For A330/A340 series airplanes, resolution = 1.05% (0.250Section>0.120Section). 11 For A330/A340 series airplanes, resolution = 1.05% (0.250Section>0.120Section). For A300 B2/B4 series airplanes, resolution = 0.92% (0.230Section>0.125Section). 12 For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703Section>0.100Section). 13 For A330/A340 series airplanes, resolution = 0.5SectionC. 14 For Dassault F900C/F900EX airplanes, Radio altitude resolution = 1.25 ft. 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%. 18 For 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. 2 For 3 For 304 VerDate Sep<11>2014 08:20 May 17, 2019 Jkt 247048 PO 00000 Frm 00314 Fmt 8010 Sfmt 8002 Y:\SGML\247048.XXX 247048