identifier: AMC & GM to Part-CAT — Issue 2, Amendment 7

beslut: ED Decision 2016/012/R

text: Annex I to ED Decision 2016/012/R ‘AMC and GM to Part-CAT — Issue 2, Amendment 7’

text: The Annex to Decision 2014/015/R is amended as follows: The text of the amendment is arranged to show deleted text, new or amended text as shown below: (a) deleted text is marked with strikethrough; (b) new or amended text is highlighted in grey; (c) an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: 1. Sub-paragraph (d) of GM2 CAT.GEN.MPA.195(b) is amended as follows: (…) (d) ‘continuous monitoring for proper operation’ means for a flight recorder system, a combination of system monitors and/or built-in test functions which operates continuously in order to detect the following: (1) loss of electrical power supply to the flight recorder system; (2) failure of the equipment performing acquisition and processing; (3) failure of the recording medium and/or drive mechanism; and (4) failure of the recorder to store the data in the recording medium as shown by checks of the recorded data including, as reasonably practicable for the storage medium concerned, correct correspondence with the input data. However, detections by the continuous monitoring for proper operation do not need to be automatically reported to the flight crew compartment.

text: 2. A new AMC to sub-paragraph (f)(1) of CAT.GEN.MPA.195 is introduced: AMC1 CAT.GEN.MPA.195(f)(1) Handling of flight recorder recordings: preservation, production, protection and use USE OF CVR RECORDINGS FOR MAINTAINING OR IMPROVING SAFETY (a) The procedure related to the handling of cockpit voice recorder (CVR) recordings should be written in a document which should be signed by all parties (airline management, crew member representatives nominated either by the union or the crew themselves, maintenance personnel representatives if applicable). This procedure should, as a minimum, define: (1) the method to obtain the consent of all crew members and maintenance personnel concerned; (2) an access and security policy that restricts access to CVR recordings and identified CVR transcripts to specifically authorised persons identified by their position; (3) a retention policy and accountability, including the measures to be taken to ensure the security of the CVR recordings and CVR transcripts and their protection from misuse. The retention policy should specify the period of time after which CVR recordings and identified CVR transcripts are destroyed; (4) a description of the uses made of the CVR recordings and of their transcripts; (5) the participation of flight crew member representatives in the assessment of the CVR recordings or their transcripts; (6) the conditions under which advisory briefing or remedial training should take place; this should always be carried out in a constructive and non-punitive manner; and (7) the conditions under which actions other than advisory briefing or remedial training may be taken for reasons of gross negligence or significant continuing safety concern. (b) Each time a CVR recording file is read out under the conditions defined by CAT.GEN.MPA.195(f)(1): (1) parts of the CVR recording file that contain information with a privacy content should be deleted to the extent possible, and it should not be permitted that the detail of information with a privacy content is transcribed; and (2) the operator should retain, and when requested, provide to the competent authority: (i) information on the use made (or the intended use) of the CVR recording; and (ii) evidence that the persons concerned consented to the use made (or the intended use) of the CVR recording file. (c) The safety manager or the person identified by the operator to fulfil this role should be responsible for the protection and use of the CVR recordings and of their transcripts, as well as the assessment of issues and their transmission to the manager(s) responsible for the process concerned. (d) In case a third party is involved in the use of CVR recordings, contractual agreements with this third party should, when applicable, cover the aspects enumerated in (a) and (b).

text: 3. A new GM to sub-paragraph (f)(1) of CAT.GEN.MPA.195 is introduced: GM1 CAT.GEN.MPA.195(f)(1) Handling of flight recorder recordings: preservation, production, protection and use USE OF CVR RECORDINGS FOR MAINTAINING OR IMPROVING SAFETY (a) The CVR is primarily a tool for the investigation of accidents and serious incidents by investigating authorities. Misuse of CVR recordings is a breach of the right to privacy and it works against an effective safety culture inside the operator. (b) It is noteworthy that the flight data recorder (FDR) may be used for a flight data monitoring (FDM) programme; however, in that case the principles of confidentiality and access restriction of the FDM programme apply to the FDR recordings. Because the CVR is recording the voices of the crew and verbal communications with a privacy content, the CVR recordings must be protected and handled with even more care than FDM data. (c) Therefore, the use of a CVR recording, when for purposes other than CVR serviceability or those laid down by

text: Regulation (EU) No 996/2010

text: , should be subject to the free prior consent of the persons concerned, and framed by a procedure that is endorsed by all parties and that protects the privacy of crew members and (if applicable) maintenance staff.

text: 4. A new AMC to sub-paragraph (f)(1a) of CAT.GEN.MPA.195 is introduced: AMC1 CAT.GEN.MPA.195(f)(1a) Handling of flight recorder recordings: preservation, production, protection and use CVR RECORDING INSPECTION FOR ENSURING SERVICEABILITY (a) When an inspection of the CVR recording is performed for ensuring audio quality and intelligibility of recorded communications: (1) the privacy of the CVR recording should be ensured (e.g. by locating the CVR replay equipment in a separated area and/or using headsets); (2) access to the CVR replay equipment should be restricted to specifically authorised persons; (3) provision should be made for the secure storage of the CVR recording medium, the CVR recording files and copies thereof; (4) the CVR recording files and copies thereof should be destroyed not earlier than two months and not later than one year after completion of the CVR recording inspection, except that audio samples with no privacy content may be retained for enhancing the CVR recording inspection (e.g. for comparing audio quality); (5) only the accountable manager of the operator, and when identified to comply with ORO.GEN.200, the safety manager should be entitled to request a copy of the CVR recording files. (b) The conditions enumerated in (a) should also be complied with if the inspection of the CVR recording is subcontracted to a third party. The contractual agreements with the third party should explicitly cover these aspects.

text: 5. A new AMC to sub-paragraph (f)(2) of CAT.GEN.MPA.195 is introduced: GM1 CAT.GEN.MPA.195(f)(2) Handling of flight recorder recordings: preservation, production, protection and use USE OF FDR DATA FOR AN FDM PROGRAMME The use of FDR data in the framework of an FDM programme may be acceptable if it fulfils the conditions set by sub-paragraph (f)(2) of CAT.GEN.MPA.195.

text: 6. The number and subtitle of AMC1 CAT.IDE.A.190 are amended as follows: AMC1.1 CAT.IDE.A.190 Flight data recorder OPERATIONAL PERFORMANCE REQUIREMENTS FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2016 AND BEFORE 1 JANUARY 2023

text: 7. In Table 1 of AMC1 CAT.IDE.A.190 (now renumbered AMC1.1 CAT.IDE.A.190), Parameter 27 is amended as follows: 27 Air–ground status. Air–ground status and a sensor of each landing gear if installed

text: 8. In Table 2 of AMC1 CAT.IDE.A.190 (now renumbered AMC1.1 CAT.IDE.A.190), (a) Parameter 15 is amended as follows: 15 Autopilot, autothrottle and automatic flight control system (AFCS) mode and engagement status (b) Parameter 21 is amended as follows: 21 Vertical deviation — the approach aid in use should be recorded. For auto-land/category III operations, each system should be recorded: 21a ILS/GPS/GLS glide path 21b MLS elevation 21c GNSS approach path Integrated approach navigation (IAN)/integrated area navigation (IRNAV), vertical deviation (c) Parameter No 32 is amended as follows: 32 Landing gear: 32a Landing gear position 32b Gear selector position (d) Parameter No 56 is amended as follows: 56 Fuel quantity or fuel quantity in CG trim tank (e) Parameters Nos 72, 73 and 74 are amended as follows: 72 Trim control input position in the flight crew compartment, pitch Flight crew compartment trim control input position pitch — when mechanical means for control inputs are not available, cockpit displayed trim positions or trim command should be recorded. 73 Trim control input position in the flight crew compartment, roll Flight crew compartment trim control input position roll — when mechanical means for control inputs are not available, flight crew compartment displayed trim positions or trim command should be recorded. 74 Trim control input position in the flight crew compartment, yaw Flight crew compartment trim control input position yaw — when mechanical means for control inputs are not available, flight crew compartment displayed trim positions or trim command should be recorded.

text: 9. A new AMC to CAT.IDE.A.190 is introduced and inserted between AMC1.1 CAT.IDE.A.190 and AMC2 CAT.IDE.A.190: AMC1.2 CAT.IDE.A.190 Flight data recorder OPERATIONAL PERFORMANCE REQUIREMENTS FOR AEROPLANES FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2023 (a) The operational performance requirements for 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 Time; or 1b Relative time count 1c Global navigation satellite system (GNSS) time synchronisation 2 Pressure altitude (including altitude values displayed on each flight crew member’s primary flight display) 3 Indicated airspeed or calibrated airspeed (including values of indicated airspeed or calibrated airspeed displayed on each flight crew member’s primary flight display) 4 Heading (primary flight crew reference) — when true or magnetic heading can be selected as 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. No* Parameter 8 Manual radio transmission keying and CVR/FDR synchronisation reference 9 Engine thrust/power: 9a Parameters required to determine propulsive thrust/power on each engine, in both normal and reverse thrust 9b 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 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): 18a Pitch axis 18b Roll axis 18c 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 Document112A. 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 Flaps: 10a Trailing edge flap position 10b Flight crew compartment control selection 11 Slats: No* Parameter 11a Leading edge flap (slat) position 11b Flight crew compartment control selection 12 Thrust reverse status 13 Ground spoiler and speed brake: 13a Ground spoiler position 13b Ground spoiler selection 13c Speed brake position 13d 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 Vertical deviation — the approach aid in use should be recorded. For auto-land/category III operations, each system should be recorded: 21a ILS/GPS/GLS glide path 21b MLS elevation 21c Integrated approach navigation (IAN) /Integrated Area Navigation (IRNAV), vertical deviation 22 Horizontal deviation — the approach aid in use should be recorded. For autoland/category III operations, each system should be recorded: 22a ILS/GPS/GLS localiser 22b MLS azimuth 22c GNSS approach path/IRNAV lateral deviation 26 Distance measuring equipment (DME) 1 and 2 distances: 26a Distance to runway threshold (GLS) 26b Distance to missed approach point (IRNAV/IAN) 28 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 28a Terrain alerts, including cautions and warnings and advisories 28b On/off switch position 28c 29 Angle of attack No* Parameter 30 Low pressure warning (each system ): 30a Hydraulic pressure 30b Pneumatic pressure 31 Ground speed 32 Landing gear: 32a Landing gear position 32b Gear selector position 33 Navigation data: 33a Drift angle 33b Wind speed 33c Wind direction 33d Latitude 33e Longitude 33f GNSS augmentation in use 34 Brakes: 34a Left and right brake pressure 34b Left and right brake pedal position 35 Additional engine parameters (if not already recorded in parameter 9 of Table 1, and if the aeroplane is equipped with a suitable data source): 35a Engine pressure ratio (EPR) 35b N1 35c Indicated vibration level 35d N2 35e Exhaust gas temperature (EGT) 35f Fuel flow 35g Fuel cut-off lever position 35h N3 35i 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 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: 36a Combined control No* Parameter 36b Vertical control 36c Up advisory 36d Down advisory 36e Sensitivity level 37 Wind shear warning 38 Selected barometric setting — to be recorded for the aeroplane where the parameter is displayed electronically: 38a Pilot selected barometric setting 38b 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 Selected flight path (all pilot selectable modes of operation) — to be recorded for the aeroplane where the parameter is displayed electronically: 44a Course/desired track (DSTRK) 44b Path angle 44c Coordinates of final approach path (IRNAV/IAN) 45 Selected decision height — to be recorded for the aeroplane where the parameter is displayed electronically 46 Electronic flight instrument system (EFIS) display format, showing the display system status: 46a Pilot 46b 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 No* Parameter 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 Primary navigation system reference: 60a GNSS 60b Inertial navigational system (INS) 60c VHF omnidirectional radio range (VOR)/distance measuring equipment (DME) 60d MLS 60e Loran C 60f 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 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 No* Parameter necessary to record this parameter): 75a Control wheel input forces 75b Control column input forces 75c 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 Flight director command: 81a Left flight director pitch command – for aeroplanes type certified before 1 January 2023, to be recorded only if this does not require extensive modification 81b Left flight director roll command – for aeroplanes type certified before 1 January 2023, to 81c be recorded only if this does not require extensive modification 81d 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.

text: 10. The number and subtitle of AMC1 CAT.IDE.H.190 are amended as follows: AMC1.1 CAT.IDE.H.190 Flight data recorder OPERATIONAL PERFORMANCE REQUIREMENTS FOR HELICOPTERS HAVING ANn MCTOM OF MORE THAN 3 175 KG AND FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2016 AND BEFORE 1 JANUARY 2023

text: 11. Paragraph (c) of AMC1 CAT.IDE.H.190 (now renumbered AMC1.1 CAT.IDE.H.190) is amended as follows: (c) The FDR parameters should meet, as far as practicable, the performance specifications (range, sampling intervals, accuracy limits and minimum resolution in read-out) defined in the operational performance requirements and specifications of EUROCAE Document ED-112, including amendments No 1 and No 2, or any later equivalent standard produced by EUROCAE.

text: 12. Parameter No 9 of Table 1 of AMC1 CAT.IDE.H.190 (now renumbered AMC1.1 CAT.IDE.H.190) is amended as follows: 9 Power on each engine: 9a Free power turbine speed (NF) 9b Engine torque 9c Engine gas generator speed (NG) 9d Cockpit Flight crew compartment power control position 9e Other parameters to enable engine power to be determined

text: 13. Parameter No 10 of Table 1 of AMC1 CAT.IDE.H.190 (now renumbered AMC1.1 CAT.IDE.H.190) is amended as follows: 10 Rotor: 10a Main rotor speed 10b Rotor brake (if installed)

text: 14. A new AMC to CAT.IDE.H.190 is introduced and inserted between AMC1 CAT.IDE.H.190 (now renumbered AMC1.1 CAT.IDE.H.190) and AMC2 CAT.IDE.A.190: AMC1.2 CAT.IDE.H.190 Flight data recorder OPERATIONAL PERFORMANCE REQUIREMENTS FOR HELICOPTERS HAVING AN MCTOM OF MORE THAN 3 175 KG AND FIRST ISSUED WITH AN INDIVIDUAL CofA ON OR AFTER 1 JANUARY 2023 (a) The operational performance requirements for 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 helicopter systems or is available on the instrument panel for use by the flight crew to operate the helicopter; and (3) any dedicated parameters related to novel or unique design or operational characteristics of the helicopter 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 helicopters 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 CVR/FDR synchronisation reference 9 Power on each engine: 9a Free power turbine speed (NF) 9b Engine torque 9c Engine gas generator speed (NG) 9d Flight crew compartment power control position 9e Other parameters to enable engine power to be determined 10 Rotor: 10a Main rotor speed 10b Rotor brake (if installed) 11 Primary flight controls — pilot input or control output position if it is possible to derive either the control input or the control movement (one from the other) for all modes of operation and flight regimes. Otherwise, pilot input and control output position: 11a Collective pitch 11b Longitudinal cyclic pitch 11c Lateral cyclic pitch 11d Tail rotor pedal 11e Controllable stabilator (if applicable) 11f Hydraulic selection 12 Hydraulics low pressure (each system should be recorded) 13 Outside air temperature 18 Yaw rate or yaw acceleration 20 Longitudinal acceleration (body axis) 21 Lateral acceleration 25 Marker beacon passage No* Parameter 26 Warnings — including master warning, gearbox low oil pressure and stability augmentation system failure, and other ‘red’ warnings where the warning condition cannot be determined from other parameters or from the cockpit voice recorder 27 Each navigation receiver frequency selection 37 Engine control modes * The number in the left-hand column reflects the serial numbers depicted in EUROCAE Document 112A. Table 2: FDR - Helicopters for which the data source for the parameter is either used by the helicopter systems or is available on the instrument panel for use by the flight crew to operate the helicopter No* Parameter 14 AFCS mode and engagement status (showing which systems are engaged and which primary modes are controlling the flight path) 15 Stability augmentation system engagement (each system should be recorded) 16 Main gear box oil pressure 17 Gear box oil temperature: 17a Main gear box oil temperature 17b Intermediate gear box oil temperature 17c Tail rotor gear box oil temperature 19 Indicated sling load force (if signals are readily available) 22 Radio altitude 23 Vertical deviation — the approach aid in use should be recorded: 23a ILS glide path 23b MLS elevation 23c GNSS approach path 24 Horizontal deviation — the approach aid in use should be recorded: 24a ILS localiser 24b MLS azimuth 24c GNSS approach path 28 DME 1 & 2 distances 29 Navigation data: 29a Drift angle 29b Wind speed 29c Wind direction 29d Latitude 29e Longitude No* Parameter 29f Ground speed 30 Landing gear or gear selector position 31 Engine exhaust gas temperature (T4) 32 Turbine inlet temperature (TIT)/interstage turbine temperature ITT) 33 Fuel contents 34 Altitude rate (vertical speed) — only necessary when available from cockpit instruments 35 Ice detection 36 Helicopter health and usage monitor system (HUMS): 36a Engine data 36b Chip detector 36c Track timing 36d Exceedance discretes 36e Broadband average engine vibration 38 Selected barometric setting — to be recorded for helicopters where the parameter is displayed electronically: 38a Pilot 38b Co-pilot 39 Selected altitude (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 40 Selected speed (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 41 Selected Mach (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 42 Selected vertical speed (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 43 Selected heading (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 44 Selected flight path (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 45 Selected decision height (all pilot selectable modes of operation) — to be recorded for the helicopters where the parameter is displayed electronically 46 EFIS display format (showing the display system status): 46a Pilot 46b First officer 47 Multi-function/engine/alerts display format (showing the display system status) 48 Event marker No* Parameter 49 Status of ground proximity warning system (GPWS)/terrain awareness warning system (TAWS)/ground collision avoidance system (GCAS): 49a Selection of terrain display mode including pop-up display status — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 49b Terrain alerts, both cautions and warnings, and advisories — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 49c On/off switch position – for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 50 Traffic alert and collision avoidance system (TCAS)/airborne collision avoidance system (ACAS): 50a Combined control — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 50b Vertical control — for helicopters type certified before 1 January 2023, to be recorded only 50c if this does not require extensive modification 50d Up advisory — for helicopters type certified before 1 January 2023, to be recorded only if 50e this does not require extensive modification Down advisory — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification Sensitivity level — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 51 Primary flight controls — pilot input forces: 51a Collective pitch — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 51b Longitudinal cyclic pitch — for helicopters type certified before 1 January 2023, to be 51c recorded only if this does not require extensive modification 51d Lateral cyclic pitch — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification Tail rotor pedal — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 52 Computed centre of gravity — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification 53 Helicopter computed weight — for helicopters type certified before 1 January 2023, to be recorded only if this does not require extensive modification


identifier: AMC & GM to Part-CAT — Issue 2, Amendment 8

amnesord: Part-CAT - Commercial Air Transport Operations

beslut: ED Decision 2016/022/R

publisher: Europeiska unionens byrå för luftfartssäkerhet

sprak: en

serie: amc-gm

text: Annex IV to ED Decision 2016/022/R ‘AMC and GM to Annex IV (Part-CAT) — Issue 2, Amendment 8’

type: rubrik

text: The Annex to ED Decision 2014/015/R is amended as follows: The text of the amendment is arranged to show deleted text, new or amended text as shown below: (a) deleted text is marked with strikethrough; (b) new or amended text is highlighted in grey; (c) an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

type: stycke

text: 1. AMC2 CAT.OP.MPA.105 Use of aerodromes and operating sites is deleted.

text: 2. AMC1 CAT.OP.MPA.120 Airborne radar approaches (ARAs) for overwater operations — helicopters is deleted.

text: 3. GM1 CAT.OP.MPA.120 Airborne radar approaches (ARAs) for overwater operations — helicopters is deleted.

text: 4. AMC1 CAT.OP.MPA.181(b)(1) Selection of aerodromes and operating sites — helicopters is deleted.

text: 5. AMC1 CAT.OP.MPA.181(d) Selection of aerodromes and operating sites — helicopters is deleted.

text: 6. GM1 CAT.OP.MPA.181 Selection of aerodromes and operating sites — helicopters is amended as follows: GM1 CAT.OP.MPA.181 Selection of aerodromes and operating sites — helicopters OFFSHORE ALTERNATES When operating offshore, any spare payload capacity should be used to carry additional fuel if it would facilitate the use of an onshore alternate aerodrome. LANDING FORECAST (…)

text: 7. AMC1 CAT.OP.MPA.281 In-flight fuel management — helicopters is amended as follows: AMC1 CAT.OP.MPA.281 In-flight fuel management — helicopters COMPLEX MOTOR-POWERED HELICOPTERS, OTHER THAN LOCAL OPERATIONS (…) (b) In-flight fuel management (1) If, as a result of an in-flight fuel check, the expected fuel remaining on arrival at the destination is less than the required alternate fuel plus final reserve fuel, the commander should: (i) divert; or (ii) replan the flight in accordance with CAT.OP.MPA.181 (d)(1)SPA.HOFO.120 unless he/she considers it safer to continue to the destination. (…)

text: 8. AMC1 CAT.IDE.H.310 Additional requirements for helicopters operating to or from helidecks located in a hostile sea area is deleted.

text: 9. AMC1 CAT.IDE.H.320(b) All helicopters on flight over water — ditching is amended as follows: AMC1 CAT.IDE.H.320(b) All helicopters on flight over water — ditching GENERAL The same considerations of AMC1 CAT.IDE.H.310AMC1 SPA.HOFO.165(d) should apply in respect of emergency flotation equipment.

text: 10. A new AMC1 CAT.POL.H.305(a) Operations without an assured safe forced landing capability is added: AMC1 CAT.POL.H.305(a) Operations without an assured safe forced landing capability VALIDITY OF THE RISK ASSESSMENT The operator should periodically review and update the procedures and associated risk assessments, pertaining to the granting of the CAT.POL.H.305(a) approval, to ensure that they are adequate and remain relevant for the operation.

text: 11. A new AMC1 CAT.POL.H.310(c)(2) and CAT.POL.H.325(c)(2) Take-off and landing is added: AMC1 CAT.POL.H.310(c)(2) and CAT.POL.H.325(c)(2) Take-off and landing FACTORS (a) To ensure that the necessary factors are taken into account, the operator should: (1) use take-off and landing procedures that are appropriate to the circumstances, and that minimise the risks of collision with obstacles at the individual offshore location under the prevailing conditions; and (2) use the aircraft flight manual (AFM) performance data or, where such data is not available, alternative data approved by the competent authority, which show take-off and landing masses that take into account drop-down and take-off deck-edge miss, under varying conditions of pressure altitude, temperature, and wind. (b) Replanning of offshore location take-off or landing masses during the flight should only be performed in accordance with procedures established in the operations manual (OM). These procedures should be simple and safe to carry out, with no significant increase in the crew workload during critical phases of the flight.

text: 12. AMC1 CAT.IDE.H.145 Radio altimeters is amended as follows: AMC1 CAT.IDE.H.145 Radio altimeters AUDIO WARNING DEVICE (a) The audio warning required in CAT.IDE.H.145 should be a voice warning. (b) The audio warning may be provided by a helicopter terrain awareness and warning system (HTAWS).

text: 13. A new AMC2 CAT.IDE.H.145 Radio altimeters is added: AMC2 CAT.IDE.H.145 Radio altimeters RADIO ALTIMETER DISPLAY The radio altimeter should be of an analogue type display presentation that requires minimal interpretation for both an instantaneous impression of absolute height and rate of change of height.

text: 14. A new GM1 CAT.IDE.H.145 Radio altimeters is added: GM1 CAT.IDE.H.145 Radio altimeters AUDIO-VOICE-ALERTING DEVICE (a) To be effective, the voice warning alert should be distinguishable from other warnings and should contain a clear and concise voice message. (b) The warning format should meet the following conditions: (1) the warning should be unique (i.e. voice); (2) it should not be inhibited by any other audio warnings, except by higher priority alerts such as helicopter terrain awareness and warning system (HTAWS); and (3) the urgency of the warning should be adequate to draw attention but not such as to cause undue annoyance during deliberate descents through the datum height. (c) The criteria above can be satisfactorily met if the warning format incorporates all of the following features: (1) a unique tone should precede the voice message; a further tone after the voice may enhance uniqueness and attract more attention without causing undue annoyance; (2) the perceived tone and voice should be moderately urgent; (3) the message should be compact as opposed to lengthy provided that the meaning is not compromised, e.g. ‘One fifty feet’ as opposed to ‘One hundred and fifty feet’; (4) an information message is preferable (e.g. ‘One hundred feet’); messages such as ‘Low height’ do not convey the correct impression during deliberate descents through the datum height; (5) command messages (e.g. ‘Pull up, pull up’) should not be used unless they relate specifically to height monitoring (e.g. ‘Check height’); and (6) the volume of the warning should be adequate and not variable below an acceptable minimum value. (d) Every effort should be made to prevent spurious warnings. (e) The height at which the audio warning is triggered by the radio altimeter should be such as to provide adequate warning for the pilot to take corrective action. It is envisaged that most installations will adopt a height in the range of 100–160 ft. The datum should not be adjustable in flight. (f) The preset datum height should not be set in a way that it coincides with commonly used instrument approach minima (i.e. 200 ft). Once triggered, the message should sound within 0.5 sec. (g) The voice warning should be triggered only whilst descending through the preset datum height and be inhibited whilst ascending.

text: 15. A new GM2 CAT.IDE.H.145 Radio altimeters is added: GM2 CAT.IDE.H.145 Radio altimeters RADIO ALTIMETER DISPLAY An analogue type display presentation may be, for example, a representation of a dial, ribbon or bar, but not a display that provides numbers only. An analogue type display may be embedded into an electronic flight instrument system (EFIS).

text: 16. A new GM1 CAT.IDE.H.320 Landing on water is added: GM1 CAT.IDE.H.320 Landing on water DESIGN FOR LANDING ON WATER A helicopter is designed for landing on water if safety provisions at least equivalent to those for ditching (CS 27.801/CS 29.801) are met.

type: vagledning

utgivare: easa


identifier: AMC & GM to Part-CAT — Issue 2, Amendment 9

beslut: ED Decision 2017/002/R

text: Annex I to Decision 2017/002/R

text: ‘AMC and GM to Part-CAT — Issue 2, Amendment 9’

text: The Annex to Decision 2014/015/R is hereby amended as follows: The text of the amendments is arranged to show deleted, new or amended text as shown below: — deleted text is marked with strike through; — new or amended text is highlighted in grey; and — an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: 1. AMC1 CAT.IDE.A.355 is amended as follows: AMC1 CAT.IDE.A.355 Electronic navigation data management ELECTRONIC NAVIGATION DATA PRODUCTS (a) When the operator of a complex motor-powered aeroplane uses a navigation database that supports an airborne navigation application as a primary means of navigation, the navigation database supplier should hold a Type 2 letter of acceptance (LoA), or equivalent, or be a Type 2 DAT provider certified in accordance with

text: Regulation (EU) 2017/373

text: or equivalent. (b) If this airborne navigation application is needed for an operation requiring a specific approval in accordance with Annex V (Part-SPA), the operator’s procedures should be based upon the Type 2 LoA acceptance process.

text: 2. GM1 CAT.IDE.A.355 is amended as follows: GM1 CAT.IDE.A.355 Electronic navigation data management LETTERS OF ACCEPTANCE AND STANDARDS FOR ELECTRONIC NAVIGATION DATA PRODUCTS (a) A Type 2 LoA is issued by the Agency in accordance with the Agency’s Opinion No 01/2005 on The Acceptance of Navigation Database Suppliers. The definitions of navigation database, navigation database supplier, data application integrator, Type 1 LoA and Type 2 LoA can be found in Opinion No 01/2005. (b) Equivalent to a Type 2 LoA is the FAA Type 2 LoA, issued in accordance with the Federal Aviation Administration (FAA) Advisory Circular AC 20-153 or AC 20-153A, and the Transport Canada Civil Aviation (TCCA) ‘Acknowledgement Letter of an Aeronautical Data Process’, which uses the same basis. (c) EUROCAE ED-76/Radio Technical Commission for Aeronautics (RTCA) DO-200A Standards for Processing Aeronautical Data contains guidance relating to the processes that the supplier may follow. (d) A ‘Type 2 DAT provider’ is an organisation as defined in

text: Article 2(5)

text: (b) of

text: Regulation (EU) 2017/373

text: . (e) Equivalent to a certified ‘Type 2 DAT provider’ is defined in any Aviation Safety Agreement between the European Union and a third country, including any Technical Implementation Procedures, or any Working Arrangements between EASA and the competent authority of a third country.