--- title: "CAT.IDE.H.190 Flight data recorder — Part-CAT · Avioverse" description: "The following helicopters shall be equipped with an FDR that uses a digital method of recording and storing data and for which a method of readily…" url: "https://avioverse.aero/regulations/easa/air-ops/part-cat/subpart-d/cat-ide-h-190" --- # CAT.IDE.H.190 Flight data recorder ANNEX IV (Part-CAT) · Regulation (EU) No 965/2012 · EAR revision 27 Mar 2026 IR Implementing rule ## CAT.IDE.H.190 Flight data recorder (a) The following helicopters shall be equipped with an FDR 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) helicopters with an MCTOM of more than 3 175 kg and first issued with an individual CofA on or after 1 August 1999; (2) helicopters with an MCTOM of more than 7 000 kg, or an MOPSC of more than nine, and first issued with an individual CofA on or after 1 January 1989 but before 1 August 1999. (b) The FDR shall record the parameters required to determine accurately the: (1) flight path, speed, attitude, engine power, operation and configuration and be capable of retaining the data recorded during at least the preceding 10 hours, for helicopters referred to in (a)(1) and first issued with an individual CofA on or after 1 January 2016; (2) flight path, speed, attitude, engine power and operation and be capable of retaining the data recorded during at least the preceding eight hours, for helicopters referred to in (a)(1) and first issued with an individual CofA before 1 January 2016; (3) flight path, speed, attitude, engine power and operation and be capable of retaining the data recorded during at least the preceding five hours, for helicopters referred to in (a)(2). (c) Data shall be obtained from [helicopter](https://avioverse.aero/glossary/easa/helicopter) sources that enable accurate correlation with information displayed to the flight crew. (d) The FDR shall automatically start to record the data prior to the helicopter being capable of moving under its own power and shall stop automatically after the helicopter 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 1 January 2020 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.H.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.H.190 Flight data recorder LIST OF PARAMETERS TO BE RECORDED FOR HELICOPTERS HAVING AN MCTOM OF MORE THAN 3 175 KG AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 AUGUST 1999 AND BEFORE 1 JANUARY 2016 AND HELICOPTERS HAVING AN MCTOM OF MORE THAN 7 000 KG OR AN MOPSC OF MORE THAN 9 AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 JANUARY 1989 AND BEFORE 1 AUGUST 1999 (a) The FDR should, with reference to a timescale, record: (1) for helicopters with an MCTOM between 3 175 kg and 7 000 kg the parameters listed in Table 1 below; (2) for helicopters with an MCTOM of more than 7 000 kg the parameters listed in Table 2 below; (3) for helicopters equipped with electronic display systems, the additional parameters listed in Table 3 below; and (4) any dedicated parameters relating to novel or unique design or operational characteristics of the [helicopter](https://avioverse.aero/glossary/easa/helicopter). (b) The FDR of helicopters with an MCTOM of more than 7 000 kg does not need to record parameter 19 of Table 2 below, if any of the following conditions are met: (1) the sensor is not readily available; or (2) a change is required in the equipment that generates the data. (c) Individual parameters that can be derived by calculation from the other recorded parameters need not to be recorded, if agreed by the competent authority. (d) The parameters should meet, as far as practicable, the performance specifications (range, sampling intervals, accuracy limits and resolution in read-out) defined in AMC3 CAT.IDE.H.190. (e) If recording capacity is available, as many of the additional parameters as possible specified in table II-A.2 of EUROCAE Document ED 112 dated March 2003 should be recorded. (f) For the purpose of this AMC, a sensor is considered ‘readily available’ when it is already available or can be easily incorporated. Table 1 Helicopters with an MCTOM of 7 000 kg or less | 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 | Power on each engine (free power turbine speed and engine torque)/cockpit power control position (if applicable) | | 10a 10b | Main rotor speed Rotor brake (if installed) | | 11 11a 11b 11c 11d 11e 11f | Primary flight controls — pilot input and control output position (if applicable) Collective pitch Longitudinal cyclic pitch Lateral cyclic pitch Tail rotor pedal Controllable stabiliser Hydraulic selection | | 13 | Outside air temperature | | 14 | Autopilot engagement status | | 15 | Stability augmentation system engagement | | 26 | Warnings | Table 2 Helicopters with an MCTOM of more than 7 000 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 | Power on each engine (free power turbine speed and engine torque)/cockpit power control position (if applicable) | | 10a 10b | Main rotor speed Rotor brake (if installed) | | 11 11a 11b 11c 11d 11e 11f | Primary flight controls — pilot input and control output position (if applicable) Collective pitch Longitudinal cyclic pitch Lateral cyclic pitch Tail rotor pedal Controllable stabiliser Hydraulic selection | | 12 | Hydraulics low pressure | | 13 | Outside air temperature | | 14 | AFCS mode and engagement status | | 15 | Stability augmentation system engagement | | 16 | Main gear box oil pressure | | 17 | Main gear box oil temperature | | 18 | Yaw rate or yaw acceleration | | 19 | Indicated sling load force (if installed) | | 20 | Longitudinal acceleration (body axis) | | 21 | Lateral acceleration | | 22 | Radio altitude | | 23 | Vertical beam deviation (ILS glide path or MLS elevation) | | 24 | Horizontal beam deviation (ILS localiser or MLS azimuth) | | 25 | Marker beacon passage | | 26 | Warnings | | 27 | Reserved (navigation receiver frequency selection is recommended) | | 28 | Reserved (DME distance is recommended) | | 29 | Reserved (navigation data are recommended) | | 30 | Landing gear or gear selector position | Table 3 Helicopters equipped with electronic display systems | No | Parameter | | -- | ------------------------------------------------ | | 38 | Selected barometric setting (each pilot station) | | 39 | Selected altitude | | 40 | Selected speed | | 41 | Selected Mach | | 42 | Selected vertical speed | | 43 | Selected heading | | 44 | Selected flight path | | 45 | Selected decision height | | 46 | EFIS display format | | 47 | Multi-function/engine/alerts display format | AMC · AMC2 CAT.IDE.H.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 ## AMC3 CAT.IDE.H.190 Flight data recorder PERFORMANCE SPECIFICATIONS FOR THE PARAMETERS TO BE RECORDED FOR HELICOPTERS HAVING AN MCTOM OF MORE THAN 3 175 KG AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 AUGUST 1999 AND BEFORE 1 JANUARY 2016 AND HELICOPTERS HAVING AN MCTOM OF MORE THAN 7 000 KG OR AN MOPSC OF MORE THAN 9 AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 JANUARY 1989 AND BEFORE 1 AUGUST 1999 Table 1 Helicopters with an MCTOM of 7 000 kg or less | No | Parameter | Range | Sampling interval in seconds | Accuracy Limits (sensor input compared to FDR read out) | Minimum Resolution in read out | Remarks | | ----- | ---------------------------------------------------------------------- | ---------------------------------------------------------------- | ---------------------------- | ------------------------------------------------------------------- | ------------------------------ | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | 1 | Time or relative time count | | | | | | | 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 20 000 ft | 1 | ±100 ft to ±700 ft Refer to table II.A-2 of EUROCAE Document ED-112 | 25 ft | | | 3 | Indicated airspeed or calibrated airspeed | As the installed measuring system | 1 | ± 5 % or ± 10 kt, whichever is greater | 1 kt | | | 4 | Heading | 360 ° | 1 | ± 5° | 1° | | | 5 | Normal acceleration | - 3 g to + 6 g | 0.125 | ± 0.2 g in addition to a maximum offset of ± 0.3 g | 0.01 g | The resolution may be rounded from 0.01 g to 0.05 g, provided that one sample is recorded at full resolution at least every 4 seconds. | | 6 | Pitch attitude | 100 % of usable range | 0.5 | ± 2 degrees | 0.8 degree | | | 7 | Roll attitude | ± 60 ° or 100 % of usable range from installed system if greater | 0.5 | ± 2 degrees | 0.8 degree | . | | 8 | Manual radio transmission keying | Discrete(s) | 1 | - | - | Preferably each [crew member](https://avioverse.aero/glossary/easa/crew-member) but one discrete acceptable for all transmissions. | | 9 | Power on each engine | Full range | Each engine each second | ± 5 % | 1 % of full range | Sufficient parameters, e.g. Power Turbine Speed and Engine Torque should be recorded to enable engine power to be determined. A margin for possible overspeed should be provided. Data may be obtained from cockpit indicators used for [aircraft](https://avioverse.aero/glossary/easa/aircraft) certification. Parameter 9c is required for helicopters with non-mechanically linked cockpit-engine controls | | 9a | Power turbine speed | Maximum range | | | | | | 9b | Engine torque | Maximum range | | | | | | 9c | Cockpit power control position | Full range or each discrete position | Each control each second | ±2 % or sufficient to determine any gated position | 2 % of full range | | | 10 | Rotor | | | | | | | 10a | Main rotor speed | Maximum range | 1 | ± 5 % | 1 % of full range | | | 10b | Rotor brake | Discrete | 1 | - | | Where available | | 11 | Primary flight controls - Pilot input and/or\* control output position | | | | | \* For helicopters 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 helicopters 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. | | 11a | Collective pitch | Full range | 0.5 | ± 3 % | 1 % of full range | | | 11b | Longitudinal cyclic pitch | | 0.5 | | | | | 11c | Lateral cyclic pitch | | 0.5 | | | | | 11d | Tail rotor pedal | | 0.5 | | | | | 11e | Controllable stabiliser | | 0.5 | | | | | 11f | Hydraulic selection | Discretes | 1 | - | - | | | 12 | Outside air temperature | Available range from installed system | 2 | ± 2 °C | 0.3°C | | | 13 | Autopilot engagement status | Discrete(s) | 1 | | | Where practicable, discretes should show which primary modes are controlling the flight path of the [helicopter](https://avioverse.aero/glossary/easa/helicopter) | | 14 | Stability augmentation system engagement | Discrete(s) | 1 | | | | | 15 | Warnings | Discrete(s) | 1 | - | - | A discrete should be recorded for the master warning, low hydraulic pressure (each system) gearbox low oil pressure and SAS fault status. Other ‘red’ warnings should be recorded where the warning condition cannot be determined from other parameters or from the cockpit voice recorder. | Table 2 Helicopters with an MCTOM of more than 7 000 kg | N° | Parameter | Range | Sampling interval in seconds | Accuracy Limits (sensor input compared to FDR read out) | Minimum Resolution in read out | Remarks | | ------ | ---------------------------------------------------------------------- | ---------------------------------------------------------------- | ---------------------------- | -------------------------------------------------------------------------------------------------- | ---------------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ | | 1 | Time or relative time count | | | | | | | 1a or | Time | 24 hours | 4 | ± 0.125 % per hour | 1 second | (a) UTC time preferred where available. | | 1b | Relative time count | 0 to 4095 | 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 +5 000 ft | 1 | ± 100 ft to ± 700 ft Refer to table II-A.3 EUROCAE Document ED-112 | 5 ft | Should be obtained from the air data computer when installed. | | 3 | Indicated airspeed or calibrated airspeed | As the installed measuring system | 1 | ± 3 % | 1 kt | Should be obtained from the air data computer when installed. | | 4 | Heading | 360 degrees | 1 | ± 2 degrees | 0.5 degree | | | 5 | Normal acceleration | -3 g to +6 g | 0.125 | 1 % of 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 | 0.5 | ± 2 degrees | 0.5 degree | | | 7 | Roll attitude | ± 180 degrees | 0.5 | ± 2 degrees | 0.5 degree | . | | 8 | Manual radio transmission Keying and CVR/FDR synchronisation reference | Discrete(s) | 1 | - | - | Preferably each 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. | | 9 | Power on each engine | Full range | Each engine each second | ± 2 % | 0.2 % of full range | Sufficient parameters e.g. Power Turbine Speed and engine torque should be recorded to enable engine power to be determined. A margin for possible overspeed should be provided. | | 9a | Free power turbine speed (NF) | 0-130 % | | | | | | 9b | Engine torque | Full range | | | | | | 9c | Cockpit power control position | Full range or each discrete position | Each control each second | ± 2 % or sufficient to determine any gated position | 2 % of full range | Parameter 9c is required for helicopters with non-mechanically linked cockpit-engine controls | | 10 10a | Rotor Main rotor speed | 50 to 130 % | 0.5 | 2 % | 0.3 % of full range | . | | 10b | Rotor brake | Discrete | 1 | | | Where available | | 11 | Primary flight controls - Pilot input and/or\* control output position | | | | | \* For helicopters 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 helicopters 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. | | 11a | Collective pitch | Full range | 0.5 | ± 3 % unless higher accuracy is uniquely required | 0.5 % of operating range | | | 11b | Longitudinal cyclic pitch | | 0.5 | | | | | 11c | Lateral cyclic pitch | | 0.5 | | | | | 11d | Tail rotor pedal | | 0.5 | | | | | 11e | Controllable stabiliser | | 0.5 | | | | | 11f | Hydraulic selection | Discrete(s) | 1 | - | - | | | 12 | Hydraulics low pressure | Discrete(s) | 1 | - | - | Each essential system should be recorded. | | 13 | Outside air temperature | -50° to +90°C or available sensor range | 2 | ± 2°C | 0.3°C | | | 14 | 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 of the helicopter. | | 15 | Stability augmentation system engagement | Discrete | 1 | - | - | | | 16 | Main gearbox oil pressure | As installed | 1 | As installed | 6.895 kN/m² (1 psi) | | | 17 | Main gearbox oil temperature | As installed | 2 | As installed | 1°C | | | 18 | Yaw rate | ± 400 degrees/second | 0.25 | ± 1 % | 2 degrees per second | An equivalent yaw acceleration is an acceptable alternative. | | 19 | Indicated sling load force | 0 to 200 % of maximum certified load | 0.5 | ± 3 % of maximum certified load | 0.5 % for maximum certified load | With reasonable practicability if sling load indicator is installed. | | 20 | Longitudinal acceleration (body axis) | ± 1 g | 0.25 | ±1.5 % of range excluding a datum error of ±5 % | 0.004 g | See comment to parameter 5. | | 21 | Lateral acceleration | ± 1 g | 0.25 | ±1.5 % of range excluding a datum error of ±5 % | 0.004 g | See comment to parameter 5. | | 22 | 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 | | | 23 | Vertical beam deviation | | 1 | As installed ± 3 % recommended | 0.3 % of full range | Data from both the ILS and MLS systems need not to be recorded at the same time. The approach aid in use should be recorded. | | 23a | ILS glide path | ± 0.22 DDM or available sensor range as installed | | | | | | 23b | MLS elevation | +0.9 to +30 degrees | | | | | | 24 | Horizontal beam deviation | | 1 | As installed. ± 3 % recommended | 0.3 % of full range | See comment to parameter 23 | | 24a | ILS localiser | ± 0.22 DDM or available sensor range as installed | | | | | | 24b | MLS azimuth | ± 62 degrees | | | | | | 25 | Marker beacon passage | Discrete | 1 | - | - | One discrete is acceptable for all markers. | | 26 | Warnings | Discretes | 1 | - | - | A discrete should be recorded for the master warning, gearbox low oil pressure and SAS failure. Other ‘red’ warnings should be recorded where the warning condition cannot be determined from other parameters or from the cockpit voice recorder. | | 27 | Reserved | | | | | | | 28 | Reserved | | | | | | | 29 | Reserved | | | | | | | 30 | Landing gear or gear selector position | Discrete(s) | 4 | - | - | Where installed. | Table 3 Helicopters equipped with electronic display systems | N° | Parameter | Range | Sampling interval in seconds | Accuracy Limits (sensor input compared to FDR read out) | Minimum Resolution in read out | Remarks | | --- | ------------------------------------------------ | ------------ | ---------------------------- | ------------------------------------------------------- | ------------------------------ | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | 38 | Selected barometric setting (each pilot station) | As installed | 64 | As installed | 1 mb | Where practicable, a sampling interval of 4 seconds is recommended. | | 38a | Pilot | | | | | | | 38b | Co-pilot | | | | | | | 39 | Selected altitude | As installed | 1 | As installed | 100 ft | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 39a | Manual | | | | | | | 39b | Automatic | | | | | | | 40 | Selected speed | As installed | 1 | As installed | 1 kt | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 40a | Manual | | | | | | | 40b | Automatic | | | | | | | 41 | Selected Mach | As installed | 1 | As installed | 0.01 | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 41a | Manual | | | | | | | 41b | Automatic | | | | | | | 42 | Selected vertical speed | As installed | 1 | As installed | 100 ft/min | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 42a | Manual | | | | | | | 42b | Automatic | | | | | | | 43 | Selected heading | 360 degrees | 1 | As installed | 100 ft /min | Where capacity is limited, a sampling interval of 64 seconds is permissible. | | 44 | Selected flight path | | 1 | As installed | | | | 44a | Course/DSTRK | | | | 1 degree | | | 44b | Path angle | | | | 0.1 degree | | | 45 | Selected decision height | 0-500 ft | 64 | As installed | 1ft | | | 46 | EFIS display format | Discrete(s) | 4 | - | - | Discretes should show the display system status e.g. normal, fail, composite, [sector](https://avioverse.aero/glossary/easa/sector), plan, rose, nav aids, wxr, range, copy | | 46a | Pilot | | | | | | | 46b | Co-pilot | | | | | | | 47 | Multi-function/engine/alerts display format | Discrete(s) | 4 | - | - | Discretes should show the display system status, e.g. normal, fail, and the identity of the display pages for the emergency procedures and checklists. Information in checklists and procedures need not be recorded. | The term ‘where practicable’ used in the remarks column of Table 3 means that account should be taken of the following: (a) if the sensor is already available or can be easily incorporated; (b) sufficient capacity is available in the [flight recorder](https://avioverse.aero/glossary/easa/flight-recorder) system; (c) for navigational data (nav frequency selection, DME distance, latitude, longitude, groundspeed and drift) the signals are available in digital form; (d) the extent of modification required; (e) the down-time period; and (f) equipment software development. AMC · AMC3 CAT.IDE.H.190 — Regulation (EU) No 965/2012 · ED Decision 2014/015/R · Air OPS Easy Access Rules · EAR revision 27 Mar 2026 GM Guidance material ## GM1 CAT.IDE.H.190 Flight data recorder GENERAL For the purpose of AMC2 CAT.IDE.H.190(b), a sensor is considered ‘readily available’ when it is already available or can be easily incorporated. GM · GM1 CAT.IDE.H.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.