--- title: "CAT.IDE.A.190 Flight data recorder — Part-CAT · Avioverse" description: "The following aeroplanes shall be equipped with a flight data recorder (FDR) that uses a digital method of recording and storing data and for which a…" url: "https://avioverse.aero/regulations/easa/air-ops/part-cat/subpart-d/cat-ide-a-190" --- # CAT.IDE.A.190 Flight data recorder ANNEX IV (Part-CAT) · Regulation (EU) No 965/2012 · EAR revision 27 Mar 2026 IR Implementing rule ## CAT.IDE.A.190 Flight data recorder (a) The following aeroplanes shall be equipped with a [flight data recorder (FDR)](https://avioverse.aero/glossary/easa/flight-data-recorder) that uses a digital method of recording and storing data and for which a method of readily retrieving that data from the storage medium is available: (1) aeroplanes with an MCTOM of more than 5 700 kg and first issued with an individual CofA on or after 1 June 1990; (2) turbine-engined aeroplanes with an MCTOM of more than 5 700 kg and first issued with an individual CofA before 1 June 1990; and (3) multi-engined turbine-powered aeroplanes with an MCTOM of 5 700 kg or less, with an MOPSC of more than nine and first issued with an individual CofA on or after 1 April 1998. (b) The FDR shall record: (1) time, altitude, airspeed, normal acceleration and heading and be capable of retaining the data recorded during at least the preceding 25 hours for aeroplanes referred to in (a)(2) with an MCTOM of less than 27 000 kg; (2) the parameters required to determine accurately the [aeroplane](https://avioverse.aero/glossary/easa/aeroplane) flight path, speed, attitude, engine power and configuration of lift and drag devices and be capable of retaining the data recorded during at least the preceding 25 hours, for aeroplanes referred to in (a)(1) with an MCTOM of less than 27 000 kg and first issued with an individual CofA before 1 January 2016; (3) the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power, configuration and operation and be capable of retaining the data recorded during at least the preceding 25 hours, for aeroplanes referred to in (a)(1) and (a)(2) with an MCTOM of over 27 000 kg and first issued with an individual CofA before 1 January 2016; (4) the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power and configuration of lift and drag devices and be capable of retaining the data recorded during at least the preceding 10 hours, in the case of aeroplanes referred to in (a)(3) and first issued with an individual CofA before 1 January 2016; or (5) the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power, configuration and operation and be capable of retaining the data recorded during at least the preceding 25 hours, for aeroplanes referred to in (a)(1) and (a)(3) and first issued with an individual CofA on or after 1 January 2016. (c) Data shall be obtained from aeroplane sources that enable accurate correlation with information displayed to the flight crew. (d) The FDR shall start to record the data prior to the aeroplane being capable of moving under its own power and shall stop after the aeroplane is incapable of moving under its own power. In addition, in the case of aeroplanes issued with an individual CofA on or after 1 April 1998, the FDR shall start automatically to record the data prior to the aeroplane being capable of moving under its own power and shall stop automatically after the aeroplane is incapable of moving under its own power. (e) If the FDR is not deployable, it shall have a device to assist in locating it under water. By 16 June 2018 at the latest, this device shall have a minimum underwater transmission time of 90 days. If the FDR is deployable, it shall have an automatic emergency locator transmitter. IR · CAT.IDE.A.190 — Regulation (EU) No 965/2012 · Regulation (EU) 2015/2338 · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 AMC Acceptable means of compliance ## AMC2 CAT.IDE.A.190 Flight data recorder OPERATIONAL PERFORMANCE REQUIREMENTS FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 APRIL 1998 AND BEFORE 1 JANUARY 2016 (a) The operational performance requirements for FDRs should be those laid down in EUROCAE Document ED-55 (Minimum Operational Performance Requirements For Flight Data Recorder Systems) dated May 1990, or EUROCAE Document ED-112 (Minimum Operational Performance Specification for Crash Protected Airborne Recorder Systems) dated March 2003, including amendments No 1 and No°2, or any later equivalent standard produced by EUROCAE. (b) The FDR should record, with reference to a timescale: (1) the parameters listed in Table 1a or Table 1b below, as applicable; (2) the additional parameters listed in Table 2 below, for those aeroplanes with an MCTOM exceeding 27 000 kg; (3) any dedicated parameters relating to novel or unique design or operational characteristics of the [aeroplane](https://avioverse.aero/glossary/easa/aeroplane) as determined by the competent authority; and (4) the additional parameters listed in Table 3 below, for those aeroplanes equipped with electronic display systems. (c) The FDR of aeroplanes first issued with an individual CofA before 20 August 2002 and equipped with an electronic display system does not need to record those parameters listed in Table 3 for which: (1) the sensor is not available; (2) the aeroplane system or equipment generating the data needs to be modified; or (3) the signals are incompatible with the recording system; (d) The FDR of aeroplanes first issued with an individual CofA on or after 1 April 1998 but not later than 1 April 2001 is not required to comply with (b) above if: (1) compliance with (a) cannot be achieved without extensive modification to the aeroplane system and equipment other than the flight recording system; and (2) the FDR of the aeroplane can comply with AMC4 CAT.IDE.A.190(a) except that parameter 15b in Table 1 of AMC4 CAT.IDE.A.190 need not be recorded. (e) The parameters to be recorded should meet, as far as practicable, the performance specifications (ranges, sampling intervals, accuracy limits, and resolution in read-out) defined in Table 1 of AMC3 CAT.IDE.A.190. (f) For aeroplanes with novel or unique design or operational characteristics, the additional parameters should be those required in accordance with applicable [Certification Specifications](https://avioverse.aero/glossary/easa/certification-specifications) during type or supplemental certification or validation. (g) If recording capacity is available, as many as possible of the additional parameters specified in table II-A.1 of EUROCAE Document ED 112 dated March 2003 should be recorded. Table 1a FDR — Aeroplanes with an MCTOM of more than 5 700 kg | No | Parameter | | -- | ------------------------------------------------------------------------------------------------------------ | | 1 | Time or relative time count | | 2 | Pressure altitude | | 3 | Indicated airspeed or calibrated airspeed | | 4 | Heading | | 5 | Normal acceleration | | 6 | Pitch attitude | | 7 | Roll attitude | | 8 | Manual radio transmission keying | | 9 | Propulsive thrust/power on each engine and flight crew compartment thrust/power lever position if applicable | | 10 | Trailing edge flap or flight crew compartment control selection | | 11 | Leading edge flap or flight crew compartment control selection | | 12 | Thrust reverse status | | 13 | Ground spoiler position and/or speed brake selection | | 14 | Total or outside air temperature | | 15 | Autopilot, autothrottle and AFCS mode and engagement status | | 16 | Longitudinal acceleration (body axis) | | 17 | Lateral acceleration | Table 1b FDR — Aeroplanes with an MCTOM 5 700 kg or below | No | Parameter | | -- | ------------------------------------------------------------------------------------------------------------ | | 1 | Time or relative time count | | 2 | Pressure altitude | | 3 | Indicated airspeed or calibrated airspeed | | 4 | Heading | | 5 | Normal acceleration | | 6 | Pitch attitude | | 7 | Roll attitude | | 8 | Manual radio transmission keying | | 9 | Propulsive thrust/power on each engine and flight crew compartment thrust/power lever position if applicable | | 10 | Trailing edge flap or flight crew compartment control selection | | 11 | Leading edge flap or flight crew compartment control selection | | 12 | Thrust reverse status | | 13 | Ground spoiler position and/or speed brake selection | | 14 | Total or outside air temperature | | 15 | Autopilot/autothrottle engagement status | | 16 | Longitudinal acceleration (body axis) | | 17 | Angle of attack (if a suitable sensor is available) | Table 2 FDR — Additional parameters for aeroplanes with an MCTOM of more than 27 000 kg | No | Parameter | | -- | ---------------------------------------------------------------------------------------- | | 18 | Primary flight controls — control surface position and/or pilot input (pitch, roll, yaw) | | 19 | Pitch trim position | | 20 | Radio altitude | | 21 | Vertical beam deviation (ILS or GLS glide path or MLS elevation) | | 22 | Horizontal beam deviation (ILS localiser or GLS lateral deviation or MLS azimuth) | | 23 | Marker beacon passage | | 24 | Warnings | | 25 | Reserved (navigation receiver frequency selection or GLS channel is recommended) | | 26 | Reserved (DME or GLS distance is recommended) | | 27 | Landing gear squat switch status or air/ground status | | 28 | Ground proximity warning system | | 29 | Angle of attack | | 30 | Low pressure warning (hydraulic and pneumatic power) | | 31 | Groundspeed | | 32 | Landing gear or gear selector position | Table 3 FDR — Aeroplanes equipped with electronic display systems | No | Parameter | | -- | ------------------------------------------------ | | 33 | Selected barometric setting (each pilot station) | | 34 | Selected altitude | | 35 | Selected speed | | 36 | Selected Mach | | 37 | Selected vertical speed | | 38 | Selected heading | | 39 | Selected flight path | | 40 | Selected decision height | | 41 | EFIS display format | | 42 | Multi-function/engine/alerts display format | AMC · AMC2 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2022/012/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 AMC Acceptable means of compliance ## AMC3 CAT.IDE.A.190 Flight data recorder PERFORMANCE SPECIFICATIONS FOR THE PARAMETERS TO BE RECORDED FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 APRIL 1998 AND BEFORE 1 JANUARY 2016 Table 1: FDR | No | Parameter | Range | Sampling interval in seconds | Accuracy limits (sensor input compared to FDR readout) | Recommended resolution in readout | Remarks | | ----- | ----------------------------------------------------------------------- | ----------------------------------------------------------------------------------------------------------------- | ----------------------------------- | ----------------------------------------------------------------------------------------------- | --------------------------------------------------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | 1a or | Time | 24 hours | 4 | ± 0.125 % per hour | 1 second | (a) UTC time preferred where available. | | 1b | Relative time count | 0 to 4 095 | 4 | ± 0.125 % per hour | | (b) Counter increments every 4 seconds of system operation. | | 2 | Pressure altitude | -1 000 ft to maximum certificated altitude of [aircraft](https://avioverse.aero/glossary/easa/aircraft) +5 000 ft | 1 | ±100 ft to ±700 ft Refer to Table II-A.3 of EUROCAE Document ED-112 | 5 ft | Should be obtained from air data computer when installed. | | 3 | Indicated airspeed or calibrated airspeed | 50 kt or minimum value installed pitot static system to Max VS0 Max VS0 to 1.2 VD | 1 | ±5 % ±3 % | 1 kt (0.5 kt recommended) | Should be obtained from air data computer when installed. VS0: stalling speed or minimum steady flight speed in the landing configuration VD design diving speed | | 4 | Heading | 360 degrees | 1 | ±2 degrees | 0.5 degrees | | | 5 | Normal acceleration | -3 g to +6 g | 0.125 | 1 % of maximum range excluding a datum error of 5 % | 0.004 g | The recording resolution may be rounded from 0.004 g to 0.01 g provided that one sample is recorded at full resolution at least every 4 seconds. | | 6 | Pitch attitude | ±75 degrees | 0.25 | ±2 degrees | 0.5 degrees | | | 7 | Roll attitude | ±180 degrees | 0.5 | ±2 degrees | 0.5 degrees | | | 8 | Manual radio transmission keying | Discrete | 1 | - | - | Preferably each [crew member](https://avioverse.aero/glossary/easa/crew-member) but one discrete acceptable for all transmissions provided that the replay of a recording made by any required recorder can be synchronised in time with any other required recording to within 1 second. | | 9a | Propulsive thrust/power on each engine | Full range | Each engine each second | ±2 % | 0.2 % of full range | Sufficient parameters, e.g. EPR/N, or Torque/NP as appropriate to the particular engine must be recorded to determine power in both normal and reverse thrust. A margin for possible overspeed should be provided. | | 9b | Flight crew compartment thrust/power lever position | Full range | Each lever each second | ±2 % or sufficient to determine any gated position | 2 % of full range | Parameter 9b must be recorded for aeroplanes with non-mechanically linked cockpit-engine controls, otherwise recommended. | | 10 | Trailing edge flap or flight crew compartment control selection | Full range or each discrete position | 2 | ±3° or as pilot’s indicator and sufficient to determine each discrete position | 0.5 % of full range | Flap position and cockpit control may be sampled at 4-second intervals so as to give a data point each 2 seconds. | | 11 | Leading edge flap or flight crew compartment control selection | Full range or each discrete position | 1 | ±3° or as pilot’s indicator and sufficient to determine each discrete position | 0.5 % of full range | Left and right sides, or flap position and cockpit control may be sampled at 2-second intervals so as to give a data point each second. | | 12 | Thrust reverser status | Turbo-jet: stowed, in transit and reverse Turbo-prop: reverse | Each reverser each second | - | - | Turbo-jet: 2 discretes enable the 3 states to be determined Turbo-prop: 1 discrete | | 13 | Ground spoiler and/or speed brake selection | Full range or each discrete position | 0.5 | ±2º unless higher accuracy uniquely required | 0.2 % of full range | Sufficient to determine use of the cockpit selector and the activation and positions of the surfaces | | 14 | Outside air temperatures or total air temperature | -50°C to +90°C or available sensor range | 2 | ±2ºC | 0.3ºC | | | 15 | Autopilot/Autothrottle/AFCS mode and engagement status | A suitable combination of discretes | 1 | - | - | Discretes should show which systems are engaged and which primary modes are controlling the flight path and speed of the aircraft. | | 16 | Longitudinal acceleration (Body axis) | ± 1 g | 0.25 | ±1.5 % of maximum range excluding a datum error of ±5 % | 0.004 g | The recording resolution may be rounded from 0.004 g to 0.01 g provided that one sample is recorded at full resolution at least every 4 seconds. | | 17 | Lateral acceleration | ±1 g | 0.25 | ±1.5 % of maximum range excluding a datum error of ±5 % | 0.004 g | The recording resolution may be rounded from 0.004 g to 0.01 g provided that one sample is recorded at full resolution at least every 4 seconds. | | 18 | Primary flight controls, control surface positions and/or\* pilot input | Full range | 1 | ±2º unless higher accuracy uniquely required | 0.2 % of full range | \*For aeroplanes that can demonstrate the capability of deriving either the control input or control movement (one from the other) for all modes of operation and flight regimes, the ‘or’ applies. For aeroplanes with non-mechanical control systems, the ‘and’ applies. Where the input controls for each pilot can be operated independently, both inputs will need to be recorded. For multiple or split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. | | 18a | Pitch axis | | 0.25 | | | | | 18b | Roll axis | | 0.25 | | | | | 18c | Yaw axis | | 0.5 | | | | | 19 | Pitch trim position | Full range | 1 | ±3 % unless higher accuracy uniquely required | 0.3 % of full range | Where dual surfaces are provided it is permissible to record each surface alternately. | | 20 | Radio altitude | -20 ft to +2 500 ft | 1 | As installed ±2 ft or ±3 % whichever is greater below 500 ft and ±5 % above 500 ft recommended. | 1 ft below 500 ft, 1 ft +0.5 % of full range above 500 ft | For auto-land/category III operations, each radio altimeter should be recorded, but arranged so that at least one is recorded each second. | | 21 | Vertical beam deviation | | 1 | As installed ±3 % recommended | 0.3 % of full range | Data from all of the ILS, GLS and MLS systems need not to be recorded at the same time. The approach aid in use should be recorded. For auto-land/ category III operations, each radio altimeter should be recorded, but arranged so that at least one is recorded each second. | | 21a | ILS or GLS glide path | ±0.22 DDM or available sensor range as installed | | | | | | 21b | MLS elevation | 0.9° to 30° | | | | | | 22 | Horizontal beam deviation | Signal range | 1 | As installed ±3 % recommended | 0.3 % of full range | See parameter 21 remarks. | | 22a | ILS localiser or GLS lateral deviation | ±0.22 DDM or available sensor range as installed | | | | | | 22b | MLS azimuth | ±62° | | | | | | 23 | Marker beacon passage | Discrete | 1 | — | — | A single discrete is acceptable for all markers. | | 24 | Warnings | Discretes | 1 | – | – | A discrete must be recorded for the master warning. Each ‘red’ warning (including lavatory smoke) should be recorded when the warning condition cannot be determined from other parameters or from the cockpit voice recorder. | | 25 | Reserved | – | – | – | – | | | 26 | Reserved | – | – | – | – | | | 27 | Landing gear squat switch status | Discrete(s) | 1 (0.25 recommended for main gears) | – | – | Discretes should be recorded for the nose and main landing gears. | | 28 | Ground proximity warning system (GPWS) | Discrete | 1 | – | – | A suitable combination of discretes unless recorder capacity is limited in which case a single discrete for all modes is acceptable. | | 29 | Angle of attack | As installed | 0.5 | As installed | 0.3 % of full range | If left and right sensors are available, each may be recorded at 1-second intervals so as to give a data point each half second. | | 30 | Low pressure warning | Discrete(s) or available sensor range | 2 | - | 0.5 % of full range | Each essential system to be recorded. | | 30a | Hydraulic power | | | | | | | 30b | Pneumatic power | | | | | | | 31 | Groundspeed | As installed | 1 | Data should be obtained from the most accurate system | 1 kt | | | 32 | Landing gear or gear selector position | Discrete(s) | 4 | - | – | A suitable combination of discretes should be recorded. | | 33 | Selected barometric setting (each pilot station) | As installed | 64 | As installed | 1 mb | Where practicable, a sampling interval of 4 seconds is recommended | | 33a | Pilot | | | | | | | 33b | Co-pilot | | | | | | | 34 | Selected altitude | As installed | 1 | As installed | 100 ft | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 34a | Manual | | | | | | | 34b | Automatic | | | | | | | 35 | Selected speed | As installed | 1 | As installed | 1 kt | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 35a | Manual | | | | | | | 35b | Automatic | | | | | | | 36 | Selected Mach | As installed | 1 | As installed | 0.01 | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 36a | Manual | | | | | | | 36b | Automatic | | | | | | | 37 | Selected vertical speed | As installed | 1 | As installed | 100 ft/min | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 37a | Manual | | | | | | | 37b | Automatic | | | | | | | 38 | Selected heading | 360 degrees | 1 | As installed | 1 degree | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 39 | Selected flight path | | 1 | As installed | | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 39a | Course/DSTRK | 360 degrees | | | | | | 39b | Path Angle | As installed | | | | | | 40 | Selected decision height | 0-500 ft | 64 | As installed | 1 ft | | | 41 | EFIS display format | Discrete(s) | 4 | – | – | Discretes should show the display system status e.g. off, normal, fail, composite, [sector](https://avioverse.aero/glossary/easa/sector), plan, rose, nav aids, wxr, range, copy. | | 41a | Pilot | | | | | | | 41b | Co-pilot | | | | | | | 42 | Multifunction/Engine/Alerts display format | Discrete(s) | 4 | – | – | Discretes should show the display system status e.g. off, normal, fail, and the identity of display pages for emergency procedures and checklists. Information in checklists and procedures need not be recorded. | AMC · AMC3 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2022/012/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 AMC Acceptable means of compliance ## AMC4 CAT.IDE.A.190 Flight data recorder LIST OF PARAMETERS TO BE RECORDED FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JUNE 1990 UP TO AND INCLUDING 31 MARCH 1998 (a) The FDR should, with reference to a timescale, record: (1) the parameters listed in Table 1 below; and (2) the additional parameters listed in Table 2 below for those aeroplanes with an MCTOM exceeding 27 000 kg. (b) The FDR of aeroplanes having an MCTOM of 27 000 kg or below does not need to record parameters 14 and 15b of Table 1 below if any of the following conditions are met: (1) the sensor is not readily available; (2) sufficient capacity is not available in the [flight recorder](https://avioverse.aero/glossary/easa/flight-recorder) system; or (3) a change is required in the equipment that generates the data. (c) The FDR of aeroplanes having an MCTOM exceeding 27 000 kg does not need to record parameter 15b of Table 1 below, and parameters 23, 24, 25, 26, 27, 28, 29, 30 and 31 of Table 2 below, if any of the following conditions are met: (1) the sensor is not readily available; (2) sufficient capacity is not available in the FDR system; (3) a change is required in the equipment that generates the data; or (4) for navigational data (NAV frequency selection, DME distance, latitude, longitude, ground speed and drift), the signals are not available in digital form. (d) The FDR does not need to record individual parameters that can be derived by calculation from the other recorded parameters. (e) The parameters to be recorded should meet, as far as practicable, the performance specifications (range, sampling intervals, accuracy limits, and resolution in read-out) defined in Table 1 of AMC5 CAT.IDE.A.190. Table 1 Flight data recorder — Aeroplanes with an MCTOM of more than 5 700 kg | No | Parameter | | ------- | --------------------------------------------------------------------------------------------------------------------------- | | 1 | Time or relative time count | | 2 | Pressure altitude | | 3 | Indicated airspeed or calibrated airspeed | | 4 | Heading | | 5 | Normal acceleration | | 6 | Pitch attitude | | 7 | Roll attitude | | 8 | Manual radio transmission keying unless an alternate means to synchronise FDR and CVR recordings is provided | | 9 | Power on each engine | | 10 | Trailing edge flap or flight crew compartment control selection | | 11 | Leading edge flap or flight crew compartment control selection | | 12 | Thrust reverse position (for turbojet aeroplanes only) | | 13 | Ground spoiler position and/or speed brake selection | | 14 | Outside air temperature or total air temperature | | 15a 15b | Autopilot engagement status Autopilot operating modes, autothrottle and AFCS systems engagement status and operating modes. | Table 2 Flight data recorder — Additional parameters for aeroplanes with an MCTOM of more than 27 000 kg | No | Parameter | | -- | ------------------------------------------------------------------------------------------- | | 16 | Longitudinal acceleration | | 17 | Lateral acceleration | | 18 | Primary flight controls — control surface position and/or pilot input (pitch, roll and yaw) | | 19 | Pitch trim position | | 20 | Radio altitude | | 21 | Glide path deviation | | 22 | Localiser deviation | | 23 | Marker beacon passage | | 24 | Master warning | | 25 | NAV 1 and NAV 2 frequency selection | | 26 | DME 1 and DME 2 distance | | 27 | Landing gear squat switch status | | 28 | Ground proximity warning system (GPWS) | | 29 | Angle of attack | | 30 | Hydraulics, each system (low pressure) | | 31 | Navigation data | | 32 | Landing gear or gear selector position | AMC · AMC4 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2019/019/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 AMC Acceptable means of compliance ## AMC5 CAT.IDE.A.190 Flight data recorder PERFORMANCE SPECIFICATIONS FOR THE PARAMETERS TO BE RECORDED FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL COFA UP TO AND INCLUDING 31 MARCH 1998 Table 1: Flight data recorder | No | Parameter | Range | Sampling interval in seconds | Accuracy limits (sensor input compared to FDR readout) | Recommended resolution in readout | Remarks | | ------- | --------------------------------------------------------------------------------------------------------------------------- | ----------------------------------------------------------------------------------------------------------------- | ---------------------------- | --------------------------------------------------------------------- | ------------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | 1 | Time or relative time count | 24 hours | 4 | ±0.125 % per hour | 1 second | Coordinated universal time (UTC) preferred where available, otherwise elapsed time | | 2 | Pressure altitude | -1 000 ft to maximum certificated altitude of [aircraft](https://avioverse.aero/glossary/easa/aircraft) +5 000 ft | 1 | ±100 ft to ±700 ft | 5 ft | For altitude record error see EASA ETSO-C124a | | 3 | Indicated airspeed or calibrated airspeed | 50 kt to max VS0 Max VS0 to 1.2 VD | 1 | ±5 % ±3 % | 1 kt | VS0 stalling speed or minimum steady flight speed in the landing configuration VD design diving speed | | 4 | Heading | 360 degrees | 1 | ±2 degrees | 0.5 degrees | | | 5 | Normal acceleration | -3 g to +6 g | 0.125 ± | ±1 % of maximum range excluding a datum error of ±5 % | 0.004 g | | | 6 | Pitch attitude | ±75 degrees | 1 | ±2 degrees | 0.5 degrees | | | 7 | Roll attitude | ±180 degrees | 1 | ±2 degrees | 0.5 degrees | | | 8 | Manual radio transmission keying | Discrete | 1 | - | - | On-off (one discrete). An FDR/CVR time synchronisation signal complying with 4.2.1 of EUROCAE ED-55 is considered to be an acceptable [alternative means of compliance](https://avioverse.aero/glossary/easa/alternative-means-of-compliance). | | 9 | Power on each engine | Full range | Each engine each second | ±2 % | 0.2 % of full range | Sufficient parameters e.g. EPR/N, or Torque/NP as appropriate to the particular engine should be recorded to determine power. | | 10 | Trailing edge flap or flight crew compartment control selection | Full range or each discrete position | 2 | ±5 % or as pilot’s indicator | 0.5 % of full range | | | 11 | Leading edge flap or flight crew compartment control selection | Full range or each discrete position | 2 | - | 0.5 % of full range | | | 12 | Thrust reverser position | Stowed, in transit and reverse | Each reverser each second | ±2 % unless higher accuracy uniquely required | - | | | 13 | Ground spoiler and/or speed brake selection | Full range or each discrete position | 1 | ±2 degrees | 0.2 % of full range | | | 14 | Outside air temperatures or total air temperature | Sensor range | 2 | - | 0.3ºC | | | 15a 15b | Autopilot engagement status Autopilot operating modes, auto-throttle and AFCS systems engagement status and operating modes | A suitable combination of discretes | 1 | | - | | | 16 | Longitudinal acceleration | ± 1 g | 0.25 | ±1.5 % of maximum range excluding a datum error of ±5 % | 0.004 g | | | 17 | Lateral acceleration | ±1 g | 0.25 | ±1.5 % of maximum range excluding a datum error of ±5 % | 0.004 g | | | 18 | Primary flight controls, control surface positions and/or pilot input (pitch, roll, yaw) | Full range | 1 | ±2 degrees unless higher accuracy uniquely required | 0.2 % of full range | For aeroplanes with conventional control systems, ‘or’ applies. For aeroplanes with non-mechanical control systems, ‘and’ applies. For aeroplanes with split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. | | 19 | Pitch trim position | Full range | 1 | ±3 % unless higher accuracy uniquely required | 0.3 % of full range | | | 20 | Radio altitude | -20 ft to +2 500 ft | 1 | ±2 ft or ±3 % whichever is greater below 500 ft and ±5 % above 500 ft | 1 ft below 500 ft, 1 ft +5 % of full range above 500 ft | As installed. Accuracy limits are recommended | | 21 | Glide path deviation | Signal range | 1 | ±3 % | 0.3 % of full range | As installed. Accuracy limits are recommended | | 22 | Localiser deviation | Signal range | 1 | ±3 % | 0.3 % of full range | As installed. Accuracy limits are recommended. | | 23 | Marker beacon passage | Discrete | 1 | – | – | A single discrete is acceptable for all markers. | | 24 | Master warning | Discrete | 1 | – | – | | | 25 | NAV 1 and 2 frequency selection | Full range | 4 | As installed | – | | | 26 | DME 1 and 2 distance | 0-200 NM | 4 | As installed | – | Recording of latitude and longitude from INS or other navigation system is a preferred alternative. | | 27 | Landing gear squat switch status | Discrete | 1 | – | – | | | 28 | Ground proximity warning system (GPWS) | Discrete | 1 | – | – | | | 29 | Angle of attack | Full range | 0.5 | As installed | 0.3 % of full range | | | 30 | Hydraulics | Discrete(s) | 2 | – | – | | | 31 | Navigation data | As installed | 1 | As installed | – | | | 32 | Landing gear or gear selector position | Discrete | 4 | As installed | – | | \* The number in the left hand column reflects the serial number depicted in EUROCAE Document ED-112. AMC · AMC5 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2015/007/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 AMC Acceptable means of compliance ## AMC6 CAT.IDE.A.190 Flight data recorder LIST OF PARAMETERS TO BE RECORDED FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA BEFORE 1 JUNE 1990 (a) The FDR should, with reference to a timescale, record: (1) the parameters listed in Table 1 below; (2) the additional parameters 6 to 15b of Table 2 below, for aeroplanes with an MCTOM exceeding 5 700 kg but not exceeding 27 000 kg and first issued with an individual CofA on or after 1 January 1989, when the following conditions are met: (i) sufficient capacity is available on a [flight recorder](https://avioverse.aero/glossary/easa/flight-recorder) system; (ii) the sensor is readily available; and (iii) a change is not required in the equipment that generates the data; (3) the additional parameters from 6 to 15b of Table 2 below, for aeroplanes with a maximum certificated [take-off mass](https://avioverse.aero/glossary/easa/take-off-mass) exceeding 27 000 kg that are of a type first type certified after 30 September 1969; and (4) the additional parameters listed in Table 2 below for aeroplanes with an MCTOM exceeding 27 000 kg and first issued with an individual CofA on or after 1 January 1987, when the following conditions are met: (i) sufficient capacity is available on a flight recorder system; (ii) the sensor is readily available; and (iii) a change is not required in the equipment that generates the data. (b) The FDR of aeroplanes with an MCTOM exceeding 27 000 kg that are of a type first type certified after 30 September 1969 does not need to record the parameters 13, 14 and 15b in Table 2 below, when any of the following conditions are met: (1) sufficient capacity is not available on a flight recorder system; (2) the sensor is not readily available; and (3) a change is required in the equipment that generates the data. (c) The parameters to be recorded should meet, as far as practicable, the performance specifications (range, sampling intervals, accuracy limits, and resolution in read-out) defined in Table 1 of AMC5 CAT.IDE.A.190). (d) When so determined by the Agency, the FDR does not need to record individual parameters that can be derived by calculation from the other recorded parameters. Table 1 Flight data recorder — aeroplanes with an MCTOM exceeding 5 700 kg | No | Parameter | | -- | ----------------------------------------- | | 1 | Time or relative time count | | 2 | Pressure altitude | | 3 | Indicated airspeed or calibrated airspeed | | 4 | Heading | | 5 | Normal acceleration | \* The number in the left hand column reflects the serial number depicted in EUROCAE Document ED-112. Table 2 Additional parameters for aeroplanes under conditions of AMC6 CAT.IDE.A.190, 1 & 2 | No | Parameter | | ------- | ---------------------------------------------------------------------------------------------------------------------------- | | 6 | Pitch attitude | | 7 | Roll attitude | | 8 | Manual radio transmission keying unless an alternate means to synchronise the FDR and CVR recordings is provided | | 9 | Power on each engine | | 10 | Trailing edge flap or flight crew compartment control selection | | 11 | Leading edge flap or flight crew compartment control selection | | 12 | Thrust reverse position (for turbojet aeroplanes only) | | 13 | Ground spoiler position and/or speed brake selection | | 14 | Outside air temperature (OAT) or total air temperature | | 15a 15b | Autopilot engagement status Autopilot operating modes, autothrottle and AFCS, systems engagement status and operating modes. | | 16 | Longitudinal acceleration | | 17 | Lateral acceleration | | 18 | Primary flight controls — control surface position and/or pilot input (pitch, roll and yaw) | | 19 | Pitch trim position | | 20 | Radio altitude | | 21 | Glide path deviation | | 22 | Localiser deviation | | 23 | Marker beacon passage | | 24 | Master warning | | 25 | NAV 1 and NAV 2 frequency selection | | 26 | DME 1 and DME 2 distance | | 27 | Landing gear squat switch status | | 28 | Ground proximity warning system (GPWS) | | 29 | Angle of attack | | 30 | Hydraulics, each system (low pressure) | | 31 | Navigation data (latitude, longitude, ground speed and drift angle) | | 32 | Landing gear or gear selector position | \* The number in the left hand column reflects the serial number depicted in EUROCAE Document ED-112. AMC · AMC6 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2019/019/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 GM Guidance material ## GM1 CAT.IDE.A.190 Flight data recorder GENERAL (a) The alleviation of AMC2 CAT.IDE.A.190(d) affects a small number of aeroplanes first issued with an individual CofA on or after 1 April 1998 that were either constructed prior to this date or to a specification in force just prior to this date. These aeroplanes may not comply fully with AMC2 CAT.IDE.A.190(b), but are able to comply with AMC4 CAT.IDE.A.190. In addition, this alleviation applies only if compliance with AMC2 CAT.IDE.A.190(b) would imply significant modifications to the [aeroplane](https://avioverse.aero/glossary/easa/aeroplane) with a severe re-certification effort. (b) Flight data recorder systems installed on board aeroplanes first issued with an individual CofA up to and including 31 March 1998, and for which the recorded parameters do not comply with the performance specifications of Table 1 of AMC5 CAT.IDE.A.190 (i.e. range, sampling intervals, accuracy limits and recommended resolution readout) may be acceptable to the Agency. (c) The alleviations of AMC4 CAT.IDE.A.190(b) and (c), and AMC6 CAT.IDE.A.190(b), are acceptable only if adding the recording of missing parameters to the existing flight data recorder system would require a major upgrade of the system itself. Account is taken of the following: (1) The extent of the modification required; (2) The downtime period; and (3) Equipment software development. (d) For the purpose of AMC4 CAT.IDE.A.190(b) and (c), and AMC6 CAT.IDE.A.190(a) and (b), ‘capacity available’ refers to the space on both the flight data acquisition unit and the flight data recorder not allocated for recording the required parameters, or the parameters recorded for the purpose of the Flight Data Monitoring programme, as determined by the Agency. (e) For the purpose of AMC4 CAT.IDE.A.190(b) and (c), and AMC6 CAT.IDE.A.190(a) and (b), a sensor is considered ‘readily available’ when it is already available or can be easily incorporated. (f) For aeroplanes first issued with an individual CofA up to and including 31 March 1998, the recording of the following additional parameters may be considered: (1) Remaining parameters in Table 2 of AMC4 CAT.IDE.A.190 or Table 2 of AMC6 CAT.IDE.A.190 as applicable; (2) Any dedicated parameter relating to novel or unique design or operational characteristics of the aeroplane; (3) operational information from electronic display systems, such as EFIS, ECAM or EICAS, with the following order of priority: (i) parameters selected by the flight crew relating to the desired flight path, e.g. barometric pressure setting, selected altitude, selected airspeed, decision height, and autoflight system engagement and mode indications if not recorded from another source; (ii) display system selection/status, e.g. [SECTOR](https://avioverse.aero/glossary/easa/sector), PLAN, ROSE, NAV, WXR, COMPOSITE, COPY, etc.; (iii) warning and alerts; (iv) the identity of displayed pages from emergency procedures and checklists. (4) retardation information including brake application for use in the investigation of landing overruns or rejected take offs; and (5) additional engine parameters (EPR, N1, EGT, fuel flow, etc.). GM · GM1 CAT.IDE.A.190 — Regulation (EU) No 965/2012 · ED Decision 2014/015/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 [All rules in SUBPART D: INSTRUMENTS, DATA, EQUIPMENT](https://avioverse.aero/regulations/easa/air-ops/part-cat/subpart-d) Consolidated from the EASA Easy Access Rules (revision 27 Mar 2026, extracted 13 Oct 2026) for convenience. Not the official publication — verify against the Official Journal of the European Union and the EASA publications before operational use.