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AMC1 SPO.IDE.A.145 Flight data recorder
ED Decision 2016/012/R
OPERATIONAL PERFORMANCE REQUIREMENTS FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2016 AND BEFORE 1 JANUARY 2023
(a)The operational performance requirements for flight data recorders (FDRs) should be those laid down in 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 flight data recorder should record, with reference to a timescale, the list of parameters in Table 1 and Table 2, as applicable.
(c)The parameters to be recorded should meet the performance specifications (designated ranges, sampling intervals, accuracy limits and minimum resolution in read-out) as defined in the relevant tables of 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.
Table 1: All Aeroplanes
No* | Parameter |
1a 1b 1c | Time; or Relative time count Global navigation satellite system (GNSS) time synchronisation |
2 | Pressure altitude |
3 | Indicated airspeed; or calibrated airspeed |
4 | Heading (primary flight crew reference) — when true or magnetic heading can be selected, the primary heading reference, a discrete indicating selection, should be recorded |
5 | Normal acceleration |
6 | Pitch attitude |
7 | Roll attitude |
8 | Manual radio transmission keying and CVR/FDR synchronisation reference. |
9 9a 9b | Engine thrust/power Parameters required to determine propulsive thrust/power on each engine Flight crew compartment thrust/power lever position for aeroplanes with no mechanical link between engine and flight crew compartment)) |
14 | Total or outside air temperature |
16 | Longitudinal acceleration (body axis) |
17 | Lateral acceleration |
18 18a 18b 18c | Primary flight control surface and/or primary flight control pilot input (for aeroplanes with control systems in which movement of a control surface will back drive the pilot’s control, ‘or’ applies. For aeroplanes with control systems in which movement of a control surface will not back drive the pilot’s control, ‘and’ applies. For multiple or split surfaces, a suitable combination of inputs is acceptable instead of recording each surface separately. For aeroplanes that have a flight control break-away capability that allows either pilot to operate the controls independently, record both inputs): Pitch axis Roll axis Yaw axis |
19 | Pitch trim surface position |
23 | Marker beacon passage |
24 | Warnings - in addition to the master warning each ‘red’ warning (including smoke warnings from other compartments) should be recorded when the warning condition cannot be determined from other parameters or from the CVR |
25 | Each navigation receiver frequency selection |
27 | Air–ground status. Air–ground status and a sensor of each landing gear if installed |
* The number in the left hand column reflects the serial number depicted in EUROCAE ED-112.
Table 2: Aeroplanes for which the data source for the parameter is either used by aeroplane systems or is available on the instrument panel for use by the flight crew to operate the aeroplane
No* | Parameter |
10 10a 10b | Flaps Trailing edge flap position Flight crew compartment control selection |
11 11a 11b | Slats Leading edge flap (slat) position Flight crew compartment control selection |
12 | Thrust reverse status |
13 13a 13b 13c 13d | Ground spoiler and speed brake: Ground spoiler position Ground spoiler selection Speed brake position Speed brake selection |
15 | Autopilot, autothrottle, automatic flight control system (AFCS) mode and engagement status |
20 | Radio altitude. For autoland/Category III operations, each radio altimeter should be recorded. |
21
21b 21c | Vertical deviation – the approach aid in use should be recorded. For autoland/Category III operations, each system should be recorded. ILS/GPS/GLS glide path MLS elevation Integrated approach navigation (IAN)/integrated area navigation (IRNAV), vertical deviation |
22 22a 22b 22c | Horizontal deviation — the approach aid in use should be recorded. For autoland/CAT III operations, each system should be recorded. It is acceptable to arrange them so that at least one is recorded every second). ILS/GPS/GLS localiser MLS azimuth GNSS approach path/IRNAV lateral deviation |
26 26a 26b | Distance measuring equipment (DME) 1 and 2 distances Distance to runway threshold(GLS) Distance to missed approach point (IRNAV/IAN) |
28 28a 28b 28c | Ground proximity warning system (GPWS)/TAWS/ground collision avoidance system (GCAS) status: Selection of terrain display mode, including pop-up display status Terrain alerts, including cautions and warnings and advisories On/off switch position |
29 | Angle of attack |
30 30a 30b | Low pressure warning (each system ): Hydraulic pressure Pneumatic pressure |
31 | Ground speed |
32 32a 32b | Landing gear: Landing gear position Gear selector position |
33 33a 33b 33c 33d 33e 33f | Navigation data: Drift angle Wind speed Wind direction Latitude Longitude GNSS augmentation in use |
34 34a 34b | Brakes: Left and right brake pressure Left and right brake pedal position |
35 35a 35b 35c 35d 35e 35f 35g 35h | Additional engine parameters (if not already recorded in parameter 9 of Table 1 of AMC1 SPO.IDE.A.145 and if the aeroplane is equipped with a suitable data source): Engine pressure ratio (EPR) N1 Indicated vibration level N2 Exhaust gas temperature (EGT) Fuel flow Fuel cut-off lever position N3 |
36 36a 36b 36c 36d 36e | Traffic alert and collision avoidance system (TCAS)/ACAS - a suitable combination of discretes should be recorded to determine the status of the system: Combined control Vertical control Up advisory Down advisory Sensitivity level |
37 | Wind shear warning |
38 38a 38b | Selected barometric setting Pilot Co-pilot |
39 | Selected altitude (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
40 | Selected speed (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
41 | Selected Mach (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
42 | Selected vertical speed (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
43 | Selected heading (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
44 44a 44b 44c | Selected flight path (All pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically: Course/desired track (DSTRK) Path angle Coordinates of final approach path (IRNAV/IAN) |
45 | Selected decision height — to be recorded for the aeroplane where the parameter is displayed electronically |
46 46a 46b | Electronic flight instrument system (EFIS) display format: Pilot Co-pilot |
47 | Multi-function/engine/alerts display format |
48 | AC electrical bus status — each bus |
49 | DC electrical bus status — each bus |
50 | Engine bleed valve position |
51 | Auxiliary power unit (APU) bleed valve position |
52 | Computer failure — (all critical flight and engine control systems) |
53 | Engine thrust command |
54 | Engine thrust target |
55 | Computed centre of gravity (CG) |
56 | Fuel quantity in CG trim tank |
57 | Head-up display in use |
58 | Para visual display on |
59 | Operational stall protection, stick shaker and pusher activation |
60 60a 60b 60c 60d 60e 60f | Primary navigation system reference: GNSS Inertial navigational system (INS) VHF omnidirectional radio range (VOR)/DME MLS Loran C ILS |
61 | Ice detection |
62 | Engine warning — each engine vibration |
63 | Engine warning — each engine over temperature |
64 | Engine warning — each engine oil pressure low |
65 | Engine warning — each engine over speed |
66 | Yaw trim surface position |
67 | Roll trim surface position |
68 | Yaw or sideslip angle |
69 | De-icing and/or anti-icing systems selection |
70 | Hydraulic pressure — each system |
71 | Loss of cabin pressure |
72 | Trim control input position in the flight crew compartment, pitch — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded |
73 | Trim control input position in the flight crew compartment, roll — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded |
74 | Trim control input position in the flight crew compartment, yaw — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded |
75 75a 75b 75c | All flight control input forces (for fly-by-wire flight control systems, where control surface position is a function of the displacement of the control input device only, it is not necessary to record this parameter): Control wheel Control column Rudder pedal |
76 | Event marker |
77 | Date |
78 | Actual navigation performance (ANP) or estimate of position error (EPE) or estimate of position uncertainty (EPU) |
* The number in the left hand column reflects the serial number depicted in EUROCAE ED-112.
AMC2 SPO.IDE.A.145 Flight data recorder
ED Decision 2021/005/R
OPERATIONAL PERFORMANCE REQUIREMENTS FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2023
(a)The operational performance requirements for flight data recorders (FDRs) should be those laid down in EUROCAE Document 112A (Minimum Operational Performance Specification for Crash Protected Airborne Recorder Systems) dated September 2013, or any later equivalent standard produced by EUROCAE.
(b)The FDR should, with reference to a timescale, record:
(1)the list of parameters in Table 1 below;
(2)the additional parameters listed in Table 2 below, when the information data source for the parameter is used by aeroplane systems or is available on the instrument panel for use by the flight crew to operate the aeroplane; and
(3)any dedicated parameters related to novel or unique design or operational characteristics of the aeroplane as determined by the Agency.
(c)The parameters to be recorded should meet the performance specifications (range, sampling intervals, accuracy limits and resolution in read-out) as defined in the relevant tables of EUROCAE Document 112A, or any later equivalent standard produced by EUROCAE.
Table 1: FDR — all aeroplanes
No* | Parameter |
1a 1b 1c | Time; or Relative time count Global navigation satellite system (GNSS) time synchronisation |
2 | Pressure altitude (including altitude values displayed on each flight crew member’s primary flight display, unless the aeroplane is type certified before 1 January 2023 and recording the values displayed at the captain position or the first officer position would require extensive modification) |
3 | Indicated airspeed or calibrated airspeed (including values of indicated airspeed or calibrated airspeed displayed on each flight crew member’s primary flight display, unless the aeroplane is type certified before 1 January 2023 and recording the values displayed at the captain position or the first officer position would require extensive modification) |
4 | Heading (primary flight crew reference) — when true or magnetic heading can be selected, the primary heading reference, a discrete indicating selection should be recorded |
5 | Normal acceleration |
6 | Pitch attitude — pitch attitude values displayed on each flight crew member’s primary flight display should be recorded, unless the aeroplane is type certified before 1 January 2023 and recording the values displayed at the captain position or the first officer position would require extensive modification. |
7 | Roll attitude — roll attitude values displayed on each flight crew member’s primary flight display should be recorded, unless the aeroplane is type certified before 1 January 2023 and recording the values displayed at the captain position or the first officer position would require extensive modification. |
8 | Manual radio transmission keying and CVR/FDR synchronisation reference |
9 9a
| Engine thrust/power: Parameters required to determine propulsive thrust/power on each engine, in both normal and reverse thrust Flight crew compartment thrust/power lever position (for aeroplanes with non-mechanically linked engine controls in the flight crew compartment) |
14 | Total or outside air temperature |
16 | Longitudinal acceleration (body axis) |
17 | Lateral acceleration |
18 18b 18c | Primary flight control surface and/or primary flight control pilot input (For aeroplanes with control systems in which the movement of a control surface will back drive the pilot’s control, ‘or’ applies. For aeroplanes with control systems in which the movement of a control surface will not back drive the pilot’s control, ‘and’ applies. For multiple or split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. For aeroplanes that have a flight control break-away capability that allows either pilot to operate the controls independently, record both inputs): Roll axis Yaw axis |
19 | Pitch trim surface position |
23 | Marker beacon passage |
24 | Warnings — in addition to the master warning, each ‘red’ warning that cannot be determined from other parameters or from the CVR and each smoke warning from other compartments should be recorded. |
25 | Each navigation receiver frequency selection |
27 | Air–ground status. Air–ground status and a sensor of each landing gear if installed |
* The number in the left-hand column reflects the serial number depicted in EUROCAE Document 112A.
Table 2: FDR — Aeroplanes for which the data source for the parameter is either used by the aeroplane systems or is available on the instrument panel for use by the flight crew to operate the aeroplane
No* | Parameter |
10 10a 10b | Flaps: Trailing edge flap position Flight crew compartment control selection |
11 11a 11b | Slats: Leading edge flap (slat) position Flight crew compartment control selection |
12 | Thrust reverse status |
13 13a 13b 13c 13d | Ground spoiler and speed brake: Ground spoiler position Ground spoiler selection Speed brake position Speed brake selection |
15 | Autopilot, autothrottle and automatic flight control system (AFCS): mode and engagement status (showing which systems are engaged and which primary modes are controlling the flight path and speed of the aircraft) |
20 | Radio altitude. For auto-land/category III operations, each radio altimeter should be recorded. |
21 21a 21b 21c | Vertical deviation — the approach aid in use should be recorded. For auto-land/category III operations, each system should be recorded: ILS/GPS/GLS glide path MLS elevation Integrated approach navigation (IAN)/Integrated Area Navigation (IRNAV), vertical deviation |
22 22a 22b 22c | Horizontal deviation — the approach aid in use should be recorded. For auto-land/category III operations, each system should be recorded: ILS/GPS/GLS localiser MLS azimuth Integrated approach navigation (IAN) /Integrated Area Navigation IRNAV lateral deviation, vertical deviation |
26 26a 26b | Distance measuring equipment (DME) 1 and 2 distances: Distance to runway threshold (GLS) Distance to missed approach point (IRNAV/IAN) |
28
28b 28c | Ground proximity warning system (GPWS)/terrain awareness warning system (TAWS)/ground collision avoidance system (GCAS) status — a suitable combination of discretes unless recorder capacity is limited in which case a single discrete for all modes is acceptable: Selection of terrain display mode, including pop-up display status Terrain alerts, including cautions and warnings and advisories On/off switch position |
29 | Angle of attack |
30 30a 30b | Low pressure warning (each system): Hydraulic pressure Pneumatic pressure |
31 | Ground speed |
32 32a 32b | Landing gear: Landing gear position Gear selector position |
33 33a 33b 33c 33d 33e 33f | Navigation data: Drift angle Wind speed Wind direction Latitude Longitude GNSS augmentation in use |
34 34a 34b | Brakes: Left and right brake pressure Left and right brake pedal position |
35 35a 35b 35c 35d 35e 35f 35g 35h 35i | Additional engine parameters (if not already recorded in Parameter 9 of Table 1, and if the aeroplane is equipped with a suitable data source): Engine pressure ratio (EPR) N1 Indicated vibration level N2 Exhaust gas temperature (EGT) Fuel flow Fuel cut-off lever position N3 Engine fuel metering valve position (or equivalent parameter from the system that directly controls the flow of fuel into the engine) — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification. |
36 36a 36b 36c 36d 36e | Traffic alert and collision avoidance system (TCAS)/airborne collision avoidance system (ACAS) — a suitable combination of discretes should be recorded to determine the status of the system: Combined control Vertical control Up advisory Down advisory Sensitivity level |
37 | Wind shear warning |
38 38a 38b | Selected barometric setting — to be recorded for the aeroplane where the parameter is displayed electronically: Pilot selected barometric setting Co-pilot selected barometric setting |
39 | Selected altitude (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
40 | Selected speed (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
41 | Selected Mach (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
42 | Selected vertical speed (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
43 | Selected heading (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically |
44 44a 44b 44c | Selected flight path (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically: Course/desired track (DSTRK) Path angle Coordinates of final approach path (IRNAV/IAN) |
45 | Selected decision height — to be recorded for the aeroplane where the parameter is displayed electronically |
46 46a 46b | Electronic flight instrument system (EFIS) display format, showing the display system status: Pilot Co-pilot |
47 | Multi-function/engine/alerts display format, showing the display system status |
48 | Alternating current (AC) electrical bus status — each bus |
49 | Direct current (DC) electrical bus status — each bus |
50 | Engine bleed valve(s) position |
51 | Auxiliary power unit (APU) bleed valve(s) position |
52 | Computer failure — all critical flight and engine control systems |
53 | Engine thrust command |
54 | Engine thrust target |
55 | Computed centre of gravity (CG) |
56 | Fuel quantity in CG trim tank |
57 | Head-up display in use |
58 | Paravisual display on |
59 | Operational stall protection, stick shaker and pusher activation |
60 60a 60b 60c 60d 60e 60f | Primary navigation system reference: GNSS Inertial navigational system (INS) VHF omnidirectional radio range (VOR)/distance measuring equipment (DME) MLS Loran C ILS |
61 | Ice detection |
62 | Engine warning — each engine vibration |
63 | Engine warning — each engine over temperature |
64 | Engine warning — each engine oil pressure low |
65 | Engine warning — each engine overspeed |
66 | Yaw trim surface position |
67 | Roll trim surface position |
68 | Yaw or sideslip angle |
69 | De-icing and/or anti-icing systems selection |
70 | Hydraulic pressure — each system |
71 | Loss of cabin pressure |
72 | Trim control input position in the flight crew compartment, pitch — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded. |
73 | Trim control input position in the flight crew compartment, roll — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded. |
74 | Trim control input position in the flight crew compartment, yaw — when mechanical means for control inputs are not available, displayed trim position or trim command should be recorded. |
75 75a 75b 75c | All flight control input forces (for fly-by-wire flight control systems, where control surface position is a function of the displacement of the control input device only, it is not necessary to record this parameter): Control wheel input forces Control column input forces Rudder pedal input forces |
76 | Event marker |
77 | Date |
78 | Actual navigation performance (ANP) or estimate of position error (EPE) or estimate of position uncertainty (EPU) |
79 | Cabin pressure altitude — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification |
80 | Aeroplane computed weight — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification |
81 81a 81b 81c 81d | Flight director command: Left flight director pitch command — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification Left flight director roll command — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification Right flight director pitch command — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification Right flight director roll command — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification |
82 | Vertical speed — for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification |
* The number in the left-hand column reflects the serial number depicted in EUROCAE Document 112A.
SPO.IDE.A.146 Lightweight flight recorder
Regulation (EU) 2019/1387
(a)Turbine-engined aeroplanes with an MCTOM of 2 250 kg or more and aeroplanes with an MOPSC of more than 9 shall be equipped with a flight recorder if all the following conditions are met:
(1)they are not within the scope of point SPO.IDE.A.145(a);
(2)they are used for commercial operations;
(3)they are first issued with an individual CofA on or after 5 September 2022.
(b)The flight recorder shall record, by means of flight data or images, information that is sufficient to determine the flight path and aircraft speed.
(c)The flight recorder shall be capable of retaining the flight data and the images recorded during at least the preceding 5 hours.
(d)The flight recorder shall automatically start to record prior to the aeroplane being capable of moving under its own power and shall stop automatically after the aeroplane is no longer capable of moving under its own power.
(e)If the flight recorder records images or audio of the flight crew compartment, then a function shall be provided which can be operated by the pilot-in-command and which modifies image and audio recordings made before the operation of that function, so that those recordings cannot be retrieved using normal replay or copying techniques.
AMC1 SPO.IDE.A.146 Lightweight flight recorder
ED Decision 2021/005/R
OPERATIONAL PERFORMANCE REQUIREMENTS
(a)If the flight recorder records flight data, it should record at least the following parameters:
(1)relative time count,
(2)pitch attitude or pitch rate,
(3)roll attitude or roll rate,
(4)heading (magnetic or true) or yaw rate,
(5)latitude,
(6)longitude,
(7)positioning system: estimated error (if available),
(8)pressure altitude or altitude from a positioning system,
(9)time,
(10)ground speed,
(11)positioning system: track (if available),
(12)normal acceleration,
(13)longitudinal acceleration,
(14)lateral acceleration.
(b)If the flight recorder records images, it should capture views of the main instrument displays at the pilot station, or at both pilot stations when the aeroplane is certified for operation with a minimum crew of two pilots. The recorded image quality should allow reading the following indications during most of the flight:
(1)magnetic heading,
(2)time,
(3)pressure altitude,
(4)indicated airspeed,
(5)vertical speed,
(6)turn and slip,
(7)attitude,
(8)Mach number (if displayed),
(9)stabilised heading, and
(10) tachometer indication or equivalent indication of propulsive thrust or power.
(c)If the flight recorder records a combination of images and flight data, each flight parameter listed in (a) should be recorded as flight data or by means of images.
(d)The flight parameters listed in (a), which are recorded as flight data, should meet the performance specifications (range, sampling intervals, accuracy limits and resolution in read-out) as defined in the relevant table of EUROCAE Document ED-112 ‘Minimum Operational Performance Specification for Crash Protected Airborne Recorder Systems’, dated March 2003, or EUROCAE Document ED-155 ‘Minimum Operational Performance Specification for Lightweight Flight Recording Systems’, dated July 2009, or any later equivalent standard accepted by EASA.
(e)The operational performance requirements for the flight recorder should be those laid down in:
(1)EUROCAE Document ED-155 or any later equivalent standard accepted by EASA for lightweight flight recorders; or
(2)EUROCAE Document ED-112 or any later equivalent standard accepted by EASA for crash-protected flight recorders.
GM1 SPO.IDE.A.146 Lightweight flight recorder
ED Decision 2021/005/R
ADDITIONAL USEFUL INFORMATION
(a)Experience has shown the usefulness, for analysing incidents and for training purposes, of recording additional information. In particular, cockpit audio and information on the handling of the aircraft (such as position of flight controls, position of engine controls, fuel and oil indications, aircraft configuration selection), and an external view are very useful for such purposes. To capture such information, simple equipment such as an integrated microphone and integrated camera may be sufficient.
(b)If the flight recorder includes optional capabilities such as described in (a), their recording duration is recommended to be at least 2 hours.
(c)If the flight recorder is capable of acquiring flight parameters from some aircraft system, it is advised to give priority to the flight parameters listed in Annex II-B to EUROCAE Document ED-155 or the flight parameters listed in Annex II-A to EUROCAE Document ED-112. Indeed, these flight parameters were selected based on their relevance in many safety investigations.
GM1 SPO.IDE.A.146(e) Lightweight flight recorder
ED Decision 2021/005/R
FUNCTION TO MODIFY IMAGE AND AUDIO RECORDINGS
The purpose of the function modifying image and audio recordings is to allow the flight crew to protect their privacy by making such recordings inaccessible using normal techniques. The activation of this function is subject to the approval of the pilot-in-command (refer to SPO.GEN.107). However, the equipment manufacturer or a safety investigation authority might still be able to retrieve these recordings using special techniques.
GM2 SPO.IDE.A.146 Lightweight flight recorder
ED Decision 2021/005/R
INSTALLATION OF CAMERAS
When cameras are installed for the purpose of SPO.IDE.A.146, it is advised to install them so that they do not capture images of head and shoulders of the flight crew members whilst seated in their normal operating position.
GM3 SPO.IDE.A.146 Lightweight flight recorder
ED Decision 2021/005/R
RECORDING ACCURACY OF ATTITUDE RATE PARAMETERS
In the case of attitude rate parameters (pitch rate parameter, yaw rate parameter, roll rate parameter), the accuracy limit specified in EUROCAE Document ED-155, dated July 2009, was found to be unclear. Therefore, the following additional guidance is provided:
(a)If the attitude rate parameter is provided by an approved system of the aeroplane, accuracy greater than as provided by this system is not expected for this attitude rate parameter.
(b)If the attitude rate parameter is provided by a dedicated gyroscope, it is advisable that the gyroscope meets the following performance:
(1)errors caused by linear accelerations less than ±3°/sec (equivalent to ±1% of 300°/sec recording range) for all combinations of parameter values and linear acceleration values in the respective ranges [-300°/sec; +300°/sec] and [-3g; +6g];
(2)errors caused by to temperature less than ±5°/sec for all combinations of parameter values and temperature values in the respective ranges [-300°/sec; +300°/sec] and [-40°C; +85°C];
(3)angular random walk of the gyroscope equal to or less than 2°/sqrt(hour); and
(4)bias stability of the gyroscope significantly less than 360°/hour (for instance, 50°/hour).
SPO.IDE.A.150 Data link recording
Regulation (EU) 2015/2338
(a)Aeroplanes first issued with an individual CofA on or after 1 January 2016 that have the capability to operate data link communications and are required to be equipped with a CVR shall record on a recorder, where applicable:
(1)data link communication messages related to ATS communications to and from the aeroplane, including messages applying to the following applications:
(i)data link initiation;
(ii)controller-pilot communication;
(iii)addressed surveillance;
(iv)flight information;
(v)as far as is practicable, given the architecture of the system, aircraft broadcast surveillance;
(vi)as far as is practicable, given the architecture of the system, aircraft operational control data; and
(vii)as far as is practicable, given the architecture of the system, graphics;
(2)information that enables correlation to any associated records related to data link communications and stored separately from the aeroplane; and
(3)information on the time and priority of data link communications messages, taking into account the system’s architecture.
(b)The recorder shall use a digital method of recording and storing data and information and a method for readily retrieving that data. The recording method shall allow the data to match the data recorded on the ground.
(c)The recorder shall be capable of retaining data recorded for at least the same duration as set out for CVRs in SPO.IDE.A.140.
(d)If the recorder 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 recorder is deployable, it shall have an automatic emergency locator transmitter.
(e)The requirements applicable to the start and stop logic of the recorder are the same as the requirements applicable to the start and stop logic of the CVR contained in SPO.IDE.A.140(d) and (e).
AMC1 SPO.IDE.A.150 Data link recording
ED Decision 2014/018/R
GENERAL
(a)As a means of compliance with SPO.IDE.A.150(a) the recorder on which the data link messages are recorded may be:
(1)the CVR;
(2)the FDR;
(3)a combination recorder when SPO.IDE.A.155 is applicable; or
(4)a dedicated flight recorder. In that case, the operational performance requirements for this recorder should be those laid down in 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)As a means of compliance with SPO.IDE.A.150(a)(2) the operator should enable correlation by providing information that allows an accident investigator to understand what data was provided to the aircraft and, when the provider identification is contained in the message, by which provider.
(c)The timing information associated with the data link communications messages required to be recorded by SPO.IDE.A.150(a)(3) should be capable of being determined from the airborne-based recordings. This timing information should include at least the following:
(1)the time each message was generated;
(2)the time any message was available to be displayed by the flight crew;
(3)the time each message was actually displayed or recalled from a queue; and
(4)the time of each status change.
(d)The message priority should be recorded when it is defined by the protocol of the data link communication message being recorded.
(e)The expression ‘taking into account the system’s architecture’, in SPO.IDE.A.150(a)(3), means that the recording of the specified information may be omitted if the existing source systems involved would require a major upgrade. The following should be considered:
(1)the extent of the modification required;
(2)the down-time period; and
(3)equipment software development.
(f)Data link communications messages that support the applications in Table 1 below should be recorded.
(g)Further details on the recording requirements can be found in the recording requirement matrix in Appendix D.2 of EUROCAE Document ED-93 (Minimum Aviation System Performance Specification for CNS/ATM Recorder Systems), dated November 1998.
Table 1: Data link recording
Item No | Application Type | Application Description | Required Recording Content |
1 | Data link initiation | This includes any application used to log on to, or initiate, a data link service. In future air navigation system (FANS)-1/A and air traffic navigation (ATN), these are ATS facilities notification (AFN) and context management (CM), respectively. | C |
2 | Controller/pilot communication | This includes any application used to exchange requests, clearances, instructions and reports between the flight crew and controllers on the ground. In FANS-1/A and ATN, this includes the controller pilot data link communications (CPDLC) application. It also includes applications used for the exchange of oceanic clearances (OCL) and departure clearances (DCL), as well as data link delivery of taxi clearances. | C |
3 | Addressed surveillance | This includes any surveillance application in which the ground sets up contracts for delivery of surveillance data. In FANS-1/A and ATN, this includes the automatic dependent surveillance-contract (ADS-C) application. | C, F2 |
4 | Flight information | This includes any application used for delivery of flight information data to specific aeroplanes. This includes for example digital automatic terminal information service (D ATIS), data link operational terminal information service (D OTIS), digital weather information services (data link-meteorological aerodrome or aeronautical report (D-METAR) or terminal weather information for pilots (TWIP)), data link flight information service (D-FIS), and Notice to Airmen (electronic NOTAM) delivery. | C |
5 | Broadcast surveillance | This includes elementary and enhanced surveillance systems, as well as automatic dependent surveillance-broadcast (ADS-B) output data. | M*, F2 |
6 | Aeronautical operational control (AOC) data | This includes any application transmitting or receiving data used for AOC purposes (in accordance with the ICAO definition of AOC). Such systems may also process aeronautical administrative communication (AAC) messages, but there is no requirement to record AAC messages | M* |
7 | Graphics | This includes any application receiving graphical data to be used for operational purposes (i.e. excluding applications that are receiving such things as updates to manuals). | M* F1 |