時(shí)間：2015-01-22 15:18來源：藍(lán)天飛行翻譯公司 作者：民航翻譯 點(diǎn)擊：次
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To view this page ensure that Adobe Flash Player version 9.0.124 or greater is installed. (1) Engine thrust power: propulsive thrust/power on each engine, cockpit thrust/power lever position. (2) Thrust reverse status*. (3) Engine thrust command*. (4) Engine thrust target*. (5) Engine bleed valve position*. (6) Additional engine parameters*: EPR, N1, indicated vibration level, N2, EGT, TLA, fuel flow, fuel cut-off lever position, N3. (f) Parameters – Configuration. The following parameters satisfy the requirements for configuration: (1) Pitch trim surface position. (2) Flaps*: trailing edge flap position, cockpit control selection. (3) Slats*: leading edge flap (slat) position, cockpit control selection. (4) Landing Gear*: landing gear, gear selector position. (5) Yaw trim surface position*. (6) Roll trim surface position* (7) Cockpit trim control input position pitch*. (8) Cockpit trim control input position roll*. (9) Cockpit trim control input position yaw*. (10) Ground spoiler and speed brake*: Ground spoiler position, ground spoiler selection, speed brake position, speed brake selection. (11) De-icing and/or anti-icing systems selection*. (12) Hydraulic pressure (each system)*. (13) Fuel quantity*. (14) AC electrical bus status*. (15) DC electrical bus status*. (16) APU bleed valve position*. (17) Computed centre of gravity*. (g) Parameters – Operation. The following parameters satisfy the requirements for operation: (1) Warnings. (2) Primary flight control surface and primary flight control pilot input: pitch axis, roll axis, yaw axis. (3) Marker beacon passage. (4) Each navigation receiver frequency selection. (5) Manual radio transmission keying and CVR/FDR synchronisation reference. (6) Autopilot/autothrottle/AFCS mode and engagement status*. (7) Selected barometric setting*: pilot first officer (co-pilot). (8) Selected altitude (all pilot selectable modes of operation)*. (9) Selected speed (all pilot selectable modes of operation)*. (10) Selected MACH (all pilot selectable modes of operation)*. (11) Selected vertical speed (all pilot selectable modes of operation)*. (12) Selected heading (all pilot selectable modes of operation)*. (13) Selected flight path (all pilot selectable modes of operation)*; course/DSTRK, path angle. (14) Selected decision height*. (15) EFIS display format*: pilot, first officer (co-pilot). (16) Multi-function/engine/alerts display format *. (17) GPWS/TAWS/GCAS status*: selection of terrain display mode including pop-up display status, terrain alerts, both cautions and warning, and advisories, on/off switch position. (18) Low pressure warning*: hydraulic pressure, pneumatic pressure. (19) Computer failure*. (20) Loss of cabin pressure*. (21) TCAS/ACAS (traffic alert and collision avoidance system/airborne collision avoidance system)*. (22) Ice detection*. (23) Engine warning each engine vibration*. (24) Engine warning each engine overtemperature*. (25) Engine warning each engine oil pressure low*. (26) Engine warning each engine overspeed*. (27) Wind shear warning*. (28) Operational stall protection, stick shaker and pusher activation*. (h) All cockpit flight control forces*: control wheel, control column, rudder pedal cockpit input forces. (i) Vertical deviation*: ILS glide path, MLS elevation, GNSS approach path. (j) Horizontal deviation*: ILS localizer, MLS azimuth, GNSS approach path. (k) DME 1 and 2 distances*. (l) Primary navigation system reference*: GNSS, INS, VOR/DME, MLS, Loran C, ILS. (m) Brakes*: left and right brake pressure, left and right brake pedal position. (n) Date*. (o) Event marker*. (p) Head up display in use*. (q) Para visual display on*. Note 1: Parameter guidance for range, sampling, accuracy and resolution are as contained in the EUROCAE ED-112, Minimum Operational Performance Specification (MOPS) for Crash Protected Airborne Recorder Systems, or equivalent documents. Note 2: It is not intended that aeroplanes issued with an individual certificate of airworthiness before 1 January 2016 be modified to meet the range, sampling, accuracy or resolution guidance detailed in this Appendix. (r) Parameters – Flight Path and Speed as Displayed to the Pilot. The parameters that satisfy the requirements for flight path and speed as displayed to the pilot(s) are listed below. The parameters without an (*) are mandatory parameters which shall be recorded. In addition, the parameters designed by an (*) shall be recorded if an information source for the parameter is displayed to the pilot and is practicable to record: (1) Pressure altitude (2) Indicated airspeed or calibrated airspeed (3) Heading (primary flight crew reference) (4) Pitch attitude (5) Roll attitude (6) Engine thrust/power (7) Landing-gear status* (8) Total or outside air temperature* (9) Time* (10) Navigation data*: drift angle, wind speed, wind direction, latitude/longitude (11) Radio altitude* ICAO Annex 6, Part I; Appendix 8: .2.2; 2.2.1; 2.2.2; 2.2.2.1; 2.2.2.2; 2.2.2.3; 2.2.2.4; 2.2.2.5; 2.2.2.6;2.2.2.7;2.2.2.8;2.2.2.9.; ICAO Annex 6, Part I, Section II: Appendix 2.3: 2.2; 2.2.1; 2.2.2; 2.2.2.1; 2.2.2.2; 2.2.2.3; 2.2.2.4; 2.2.2.5; 2.2.2.6: 2.2.2.7; 2.2.2.8; 2.2.2.9. Table — Parameter Guidance for Crash Protected Flight Data Recorders – Aeroplanes The first 16 (or 15) parameters satisfy the requirements for a Type II and Type IIA FDR. The first 32 parameters satisfy the requirements for a Type I FDR. The total 78 parameters satisfy the requirements for a Type IA FDR. Serial number Parameter Measurement range Maximum Sampling and Recording interval (seconds) Accuracy limits (sensor input compared to FDR read-out) Recording resolution 1 Time (UTC when available, otherwise relative time count or GPS sync) 24 hours 4 ±0.125% per hour 1 second 2 Pressure-altitude– -300 m (-1 000 ft) to maximum certificated altitude of aircraft 1 500 m (5 000 ft) 1 ±30 m to ±200 m (±100 ft to ±700 ft) 1.5 m (5 ft) 3 Indicated airspeed or calibrated airspeed 95 km/h (50 kt) to max VSo (Note 1) VSo to 1.2 VD (Note 2) 1 ±5% ±3% 1 kt (0.5 kt recommended) 4 Heading (primary flight crew reference) 360 degrees 1 ±2˚ 0.5˚ 5 Normal acceleration (Note 3)– -3 g to +6 g 0.125 ±1% of maximum range excluding datum error of ±5% 0.004 g 6 Pitch attitude ±75 ° or usable range whichever is greater ±0.25 ±2 ˚ 0.5˚ 7 Roll attitude ±180˚ ±0.25 ±2˚ 0.5˚ 8 Radio transmission keying On-off one discrete) 1 9 Power on each engine (Note 4) Full range 1 (per engine) ±2% 0.2% of full range or the resolution required to operate the aircraft 10* Trailing edge flap and cockpit control selection Full range or each discrete position 2 ±5% or as pilot’s indicator 0.5% of full range or the resolution required to operate the aircraft 11* Leading edge flap and cockpit control selection Full range or each discrete position 2 ±5% or as pilot’s indicator 0.5% of full range or the resolution required to operate the aircraft 12* Thrust reverser position Stowed, in transit, and reverse 1 (per engine) 13* Ground spoiler/speed brake selection (selection and position) Full range or each discrete position 1 ±2% unless higher accuracy uniquely required 0.2% of full range 14 Outside air temperature Sensor range 2 ±2˚ C 0.3˚C 15* Autopilot/auto throttle/AFCS mode and engagement status A suitable combination of discretes 1 16 Longitudinal acceleration (Note 3) +/-1 g 0.25 ±0.015 g excluding a datum error of ±0.05 g 0.004 g 17 Lateral acceleration (Note 3) ±1 g 0.25 ±0.015 g excluding a datum error of ±0.05 g 0.004 g 18 Pilot input and/or control surface position-primary controls (pitch, roll, yaw) (Note 5) (Note 6) Full range ±0.25 ±2˚ unless higher accuracy uniquely required 0.2% of full range or as installed 19 Pitch trim position Full range 1 ±3% unless higher accuracy uniquely required 0.3% of full range or as installed 20* Radio altitude– -6 m to 750 m (–20 ft to 2 500 ft) 1 ±0.6 m (±2 ft) or ±3% whichever is greater below 150 m (500 ft) and ±5% above 150 m (500 ft) 0.3 m (1 ft) below 150 m (500 ft); 0.3 m (1 ft) + 0.5% of full range above 150 m (500 ft) 21* Vertical beam deviation (ILS/GPS/GLS glide path, MLS elevation, IRNAV/IAN vertical deviation) Signal range 1 ±3% 0.3% of full range 22* Horizontal beam deviation (ILS/GPS/GLS localizer, MLS azimuth, IRNAV/IAN lateral deviation) Signal range 1 ±3% 0.3% of full range 23 Marker beacon passage Discrete 1 24 Master warning Discrete 1 25 NAV receiver frequency selection (Note 7) Full range 4 As installed 26* DME 1 and 2 distance (includes Distance to runway threshold (GLS) and Distance to missed approach point (IRNAV/IAN) (Notes 7 and 8 0 – 370 km (0-200 NM) 4 As installed 1852 m (1 NM) 27 Air/ground status Discrete 1 28* GPWS/TAWS/GCAS status (selection of terrain display mode including pop-up display status) and (Terrain alerts, both cautions and warnings, and advisories) and (on/off switch position) Discrete 1 29* Angle of attack Full range 0.5 As installed 0.3% of full range 30* Hydraulics, each system (low pressure) Discrete 2 0.5% of full range |
