Publication: Magyar Közlöny
Issue: MK-2009-104 (Year: 2009, Number: 104)
Era: 2004-2010
Section: 
Paragraph Index: 885

c) changes to Standards related to pressure-altitude data sources used by transponders as of 1 January 2009 and 1 January 2012. 14 March 2007 16 July 2007 22 November 2007 1 July 2008 1 January 2009 1 January 2012 Amendment Source(s) Subject(s) Adopted Effective Applicable 22/11/07 No. 31 Chapter 1 Annex 6 — Operation of Aircraft 1-5 1/11/01 Operator. A person, organization or enterprise engaged in or offering to engage in an aircraft operation. Operator’s maintenance control manual. A document which describes the operator’s procedures necessary to ensure that all scheduled and unscheduled maintenance is performed on the operator’s aircraft on time and in a controlled and satisfactory manner. Pilot-in-command. The pilot designated by the operator, or in the case of general aviation, the owner, as being in command and charged with the safe conduct of a flight. Pressure-altitude. An atmospheric pressure expressed in terms of altitude which corresponds to that pressure in the Standard Atmosphere*. Psychoactive substances. Alcohol, opioids, cannabinoids, sedatives and hypnotics, cocaine, other psychostimulants, hallucinogens, and volatile solvents, whereas coffee and tobacco are excluded. Repair. The restoration of an aeronautical product to an airworthy condition to ensure that the aircraft continues to comply with the design aspects of the appropriate airworthiness requirements used for the issuance of the type certificate for the respective aircraft type, after it has been damaged or subjected to wear. Required communication performance (RCP). A statement of the performance requirements for operational communication in support of specific ATM functions. Required communication performance type (RCP type). A label (e.g. RCP 240) that represents the values assigned to RCP parameters for communication transaction time, continuity, availability and integrity. Required navigation performance (RNP). A statement of the navigation performance necessary for operation within a defined airspace. Note.— Navigation performance and requirements are defined for a particular RNP type and/or application. Rest period. Any period of time on the ground during which a flight crew member is relieved of all duties by the operator. RNP type. A containment value expressed as a distance in nautical miles from the intended position within which flights would be for at least 95 per cent of the total flying time. Example.— RNP 4 represents a navigation accuracy of plus or minus 7.4 km (4 NM) on a 95 per cent containment basis. Runway visual range (RVR). The range over which the pilot of an aircraft on the centre line of a runway can see the runway surface markings or the lights delineating the runway or identifying its centre line. Safe forced landing. Unavoidable landing or ditching with a reasonable expectancy of no injuries to persons in the aircraft or on the surface. Safety management system. A systematic approach to managing safety, including the necessary organizational structures, accountabilities, policies and procedures. Safety programme. An integrated set of regulations and activities aimed at improving safety. Small aeroplane. An aeroplane of a maximum certificated take-off mass of 5 700 kg or less. State of Registry. The State on whose register the aircraft is entered. Note.— In the case of the registration of aircraft of an international operating agency on other than a national basis, the States constituting the agency are jointly and severally bound to assume the obligations which, under the Chicago Convention, attach to a State of Registry. See, in this regard, the Council Resolution of 14 December 1967 on Nationality and Registration of Aircraft Operated by International Operating Agencies which can be found in Policy and Guidance Material on the Economic Regulation of International Air Transport (Doc 9587). State of the Operator. The State in which the operator’s principal place of business is located or, if there is no such place of business, the operator’s permanent residence. Target level of safety (TLS). A generic term representing the level of risk which is considered acceptable in particular circumstances. Total vertical error (TVE). The vertical geometric difference between the actual pressure altitude flown by an aircraft and its assigned pressure altitude (flight level). Visual meteorological conditions (VMC). Meteorological conditions expressed in terms of visibility, distance from cloud, and ceiling**, equal to or better than specified minima. Note.— The specified minima are contained in Chapter 4 of Annex 2. ** As defined in Annex 8. ** As defined in Annex 2. 22/11/07 No. 31 Chapter 6 Annex 6 — Operation of Aircraft 6-3 1/11/01 23/11/06 No. 30 Note.— This Standard does not require any aeroplane to have break-in areas. 6.3 Flight recorders Note 1.— Flight recorders comprise two systems, a flight data recorder (FDR) and a cockpit voice recorder (CVR). Note 2.— Combination recorders (FDR/CVR) can only be used to meet the flight recorder equipage requirements as specifically indicated in this Annex. Note 3.— Detailed guidance on flight recorders is contained in Attachment D. 6.3.1 Flight data recorders — types 6.3.1.1 A Type I FDR shall record the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power, configuration and operation. 6.3.1.2 Types II and IIA FDRs shall record the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power and configuration of lift and drag devices. 6.3.1.3 The use of engraving metal foil FDRs shall be discontinued by 1 January 1995. 6.3.1.4 Recommendation.— The use of analogue FDRs using frequency modulation (FM) should be discontinued by 5 November 1998. 6.3.1.4.1 The use of photographic film FDRs shall be discontinued from 1 January 2003. 6.3.1.5 All aeroplanes for which the individual certificate of airworthiness is first issued after 1 January 2005, which utilize data link communications and are required to carry a CVR, shall record on a flight recorder, all data link communications to and from the aeroplane. The minimum recording duration shall be equal to the duration of the CVR, and shall be correlated to the recorded cockpit audio. 6.3.1.5.1 From 1 January 2007, all aeroplanes which utilize data link communications and are required to carry a CVR shall record on a flight recorder, all data link communications to and from the aeroplane. The minimum recording duration shall be equal to the duration of the CVR, and shall be correlated to the recorded cockpit audio. 6.3.1.5.2 Sufficient information to derive the content of the data link communications message and, whenever practical, the time the message was displayed to or generated by the crew shall be recorded. Note.— Data link communications include, but are not limited to, automatic dependent surveillance — contract (ADS-C), controller-pilot data link communications (CPDLC), data link-flight information services (D-FIS) and aeronautical operational control (AOC) messages. 6.3.1.6 Recommendation.— All aeroplanes of a maximum certificated take-off mass over 5 700 kg, required to be equipped with an FDR and a CVR, may alternatively be equipped with two combination recorders (FDR/CVR). 6.3.1.7 Recommendation.— All multi-engined turbinepowered aeroplanes of a maximum certificated take-off mass of 5 700 kg or less, required to be equipped with an FDR and/or a CVR, may alternatively be equipped with one combination recorder (FDR/CVR). 6.3.1.8 A Type IA FDR shall record the parameters required to determine accurately the aeroplane flight path, speed, attitude, engine power, configuration and operation. The parameters that satisfy the requirements for a Type IA FDR are listed in the paragraphs below. The parameters without an asterisk (*) are mandatory parameters which shall be recorded. In addition, the parameters designated by an asterisk (*) shall be recorded if an information data source for the parameter is used by aeroplane systems or the flight crew to operate the aeroplane. 6.3.1.8.1 The following parameters satisfy the requirements for flight path and speed: – Pressure altitude – Indicated airspeed or calibrated airspeed – Air-ground status and each landing gear air-ground sensor when practicable – Total or outside air temperature – Heading (primary flight crew reference) – Normal acceleration – Lateral acceleration – Longitudinal acceleration (body axis) – Time or relative time count – Navigation data*: drift angle, wind speed, wind direction, latitude/longitude – Groundspeed* – Radio altitude* 6.3.1.8.2 The following parameters satisfy the requirements for attitude: – Pitch attitude – Roll attitude – Yaw or sideslip angle* – Angle of attack* 6.3.1.8.3 The following parameters satisfy the requirements for engine power: – Engine thrust/power: propulsive thrust/power on each engine, cockpit thrust/power lever position – Thrust reverse status* 22/11/07 No. 31 Annex 6 — Operation of Aircraft Part I 1/11/01 6-4 23/11/06 No. 30 – Engine thrust command* – Engine thrust target* – Engine bleed valve position* – Additional engine parameters*: EPR, N1, indicated vibration level, N2, EGT, TLA, fuel flow, fuel cut-off lever position, N3 6.3.1.8.4 The following parameters satisfy the requirements for configuration: – Pitch trim surface position – Flaps*: trailing edge flap position, cockpit control selection – Slats*: leading edge flap (slat) position, cockpit control selection – Landing gear*: landing gear, gear selector position – Yaw trim surface position* – Roll trim surface position* – Cockpit trim control input position pitch* – Cockpit trim control input position roll* – Cockpit trim control input position yaw* – Ground spoiler and speed brake*: Ground spoiler position, ground spoiler selection, speed brake position, speed brake selection – De-icing and/or anti-icing systems selection* – Hydraulic pressure (each system)* – Fuel quantity* – AC electrical bus status* – DC electrical bus status* – APU bleed valve position* – Computed centre of gravity* 6.3.1.8.5 The following parameters satisfy the requirements for operation: – Warnings – Primary flight control surface and primary flight control pilot input: pitch axis, roll axis, yaw axis – Marker beacon passage – Each navigation receiver frequency selection – Manual radio transmission keying and CVR/FDR synchronization reference – Autopilot/autothrottle/AFCS mode and engagement status* – Selected barometric setting*: pilot, first officer – Selected altitude (all pilot selectable modes of operation)* – Selected speed (all pilot selectable modes of operation)* – Selected Mach (all pilot selectable modes of operation)* – Selected vertical speed (all pilot selectable modes of operation)* – Selected heading (all pilot selectable modes of operation)* – Selected flight path (all pilot selectable modes of operation)*: course/DSTRK, path angle – Selected decision height* – EFIS display format*: pilot, first officer – Multi-function/engine/alerts display format* – GPWS/TAWS/GCAS status*: selection of terrain display mode including pop-up display status, terrain alerts, both cautions and warnings, and advisories, on/off switch position – Low pressure warning*: hydraulic pressure, pneumatic pressure – Computer failure* – Loss of cabin pressure* – TCAS/ACAS (traffic alert and collision avoidance system/airborne collision avoidance system)* – Ice detection* – Engine warning each engine vibration* – Engine warning each engine over temperature* – Engine warning each engine oil pressure low* – Engine warning each engine over speed* – Wind shear warning* – Operational stall protection, stick shaker and pusher activation* – All cockpit flight control input forces*: control wheel, control column, rudder pedal cockpit input forces – Vertical deviation*: ILS glide path, MLS elevation, GNSS approach path – Horizontal deviation*: ILS localizer, MLS azimuth, GNSS approach path – DME 1 and 2 distances* – Primary navigation system reference*: GNSS, INS, VOR/DME, MLS, Loran C, ILS – Brakes*: left and right brake pressure, left and right brake pedal position – Date* – Event marker* – Head up display in use* – Para visual display on* Note 1.— Parameter requirements, including range, sampling, accuracy and resolution, are as contained in the Minimum Operational Performance Specification (MOPS) document for Flight Recorder Systems of the European Organization for Civil Aviation Equipment (EUROCAE) or equivalent documents. Note 2.— The number of parameters to be recorded will depend on aeroplane complexity. Parameters without an (*) are to be recorded regardless of aeroplane complexity. Those parameters designated by an (*) are to be recorded if an information source for the parameter is used by aeroplane systems and/or flight crew to operate the aeroplane. 6.3.2 Flight data recorders — duration All FDRs shall be capable of retaining the information recorded during at least the last 25 hours of their operation, except for the Type IIA FDR which shall be capable of retaining the information recorded during at least the last 30 minutes of its operation. 6.3.3 Flight data recorders — aeroplanes for which the individual certificate of airworthiness is first issued on or after 1 January 1989 6.3.3.1 All aeroplanes of a maximum certificated take-off mass of over 27 000 kg shall be equipped with a Type I FDR. Chapter 6 Annex 6 — Operation of Aircraft 6-9 1/11/01 23/11/06 No. 30 whenever such aeroplanes are being operated in areas where thunderstorms or other potentially hazardous weather conditions, regarded as detectable with airborne weather radar, may be expected to exist along the route either at night or under instrument meteorological conditions. 6.12 All aeroplanes operated above 15 000 m (49 000 ft) — radiation indicator All aeroplanes intended to be operated above 15 000 m (49 000 ft) shall carry equipment to measure and indicate continuously the dose rate of total cosmic radiation being received (i.e. the total of ionizing and neutron radiation of galactic and solar origin) and the cumulative dose on each flight. The display unit of the equipment shall be readily visible to a flight crew member. Note.— The equipment is calibrated on the basis of assumptions acceptable to the appropriate national authorities. 6.13 All aeroplanes complying with the noise certification Standards in Annex 16, Volume I An aeroplane shall carry a document attesting noise certification. When the document, or a suitable statement attesting noise certification as contained in another document approved by the State of Registry, is issued in a language other than English, it shall include an English translation. Note.— The attestation may be contained in any document, carried on board, approved by the State of Registry. 6.14 Mach number indicator All aeroplanes with speed limitations expressed in terms of Mach number, shall be equipped with a Mach number indicator. Note.— This does not preclude the use of the airspeed indicator to derive Mach number for ATS purposes. 6.15 Aeroplanes required to be equipped with ground proximity warning systems (GPWS) 6.15.1 All turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 5 700 kg or authorized to carry more than nine passengers shall be equipped with a ground proximity warning system. 6.15.2 All turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 15 000 kg or authorized to carry more than 30 passengers shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. 6.15.3 All turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 5 700 kg or authorized to carry more than nine passengers, for which the individual certificate of airworthiness is first issued on or after 1 January 2004, shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. 6.15.4 From 1 January 2007, all turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 5 700 kg or authorized to carry more than nine passengers, shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. 6.15.5 Recommendation.— All turbine-engined aeroplanes of a maximum certificated take-off mass of 5 700 kg or less and authorized to carry more than five but not more than nine passengers should be equipped with a ground proximity warning system which provides the warnings of 6.15.8 a) and

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