Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 2792

d) promulgating the information on those actions including that required in 4.3.2. 4.3.7 The State of Design shall ensure that in respect of aeroplanes over 5 700 kg maximum certificated take-off mass, there exists a continuing structural integrity programme to ensure the airworthiness of the aeroplane. The programme shall include specific information concerning corrosion prevention and control. 4.3.8 Each Contracting State shall establish, in respect of aeroplanes over 5 700 kg and helicopters over 3 180 kg maximum certificated take-off mass, the type of service information that is to be reported to its airworthiness authority by operators, organizations responsible for type design and maintenance organizations. Procedures for reporting this information shall also be established. 4.3.9 Where the State of Manufacture of an aircraft is other than the State of Design, there shall be an agreement acceptable to both States to ensure that the manufacturing organization cooperates with the organization responsible for the type design in assessing information received on experience with operating the aircraft. 2007/70/II. szám ANNEX 8 IIIA-1-1 2/3/04 PART III. LARGE AEROPLANES PART IIIA. AEROPLANES OVER 5 700 KG FOR WHICH APPLICATION FOR CERTIFICATION WAS SUBMITTED ON OR AFTER 13 JUNE 1960 BUT BEFORE 2 MARCH 2004 Note.— The provisions of Part IIIA are the same as those contained in Part III of Annex 8, Eighth Edition (including Amendment 97), except for modified applicability clauses and cross-references. CHAPTER 1. GENERAL 1.1 Applicability 1.1.1 The Standards of Part IIIA, except for those specified in 8.4, are applicable in respect of all aeroplanes designated in 1.1.3 that are of types of which the prototype is submitted to the appropriate national authorities for certification on or after 13 June 1960, but before 2 March 2004. 1.1.2 The Standards specified in 8.4 of Part IIIA are applicable in respect of all aeroplanes designated in 1.1.3 that are of types of which the prototype is submitted to the appropriate national authorities for certification on or after 22 March 1985, but before 2 March 2004. 1.1.3 Except for those Standards and Recommended Practices which specify a different applicability, the Standards and Recommended Practices of Part IIIA shall apply to aeroplanes of over 5 700 kg maximum certificated take-off mass intended for the carriage of passengers or cargo or mail in international air navigation. Note.— The following Standards do not include quantitative specifications comparable to those found in national airworthiness codes. In accordance with 3.2.2 of Part II, they are to be supplemented by national requirements prepared by Contracting States. 1.1.4 The level of airworthiness defined by the appropriate parts of the comprehensive and detailed national code referred to in 3.2.2 of Part II for the aeroplanes designated in 1.1.3 shall be at least substantially equivalent to the overall level intended by the broad Standards of Part IIIA. 1.1.5 Unless otherwise stated, the Standards apply to the complete aeroplane including power-units, systems and equipment. 1.2 Number of power-units The aeroplane shall have not less than two power-units. 1.3 Operating limitations 1.3.1 Limiting conditions shall be established for the aeroplane, its power-units and its equipment (see 9.2). Compliance with the Standards of Part IIIA shall be established assuming that the aeroplane is operated within the limitations specified. The limitations shall be sufficiently removed from any condition(s) prejudicial to the safety of the aeroplane to render the likelihood of accidents arising therefrom extremely remote. 1.3.2 Limiting ranges of mass, centre of gravity location, load distribution, speeds, and altitude or pressure-altitude shall be established within which compliance with all the pertinent Standards in Part IIIA is shown, except that combinations of conditions which are fundamentally impossible to achieve need not be considered. Note 1.— The maximum operating mass and centre of gravity limits may vary, for example, with each altitude and with each separate operating condition, e.g. take-off, en route, landing. Note 2.— The following items, for instance, may be considered as basic aeroplane limitations: — maximum certificated take-off mass — maximum certificated taxiing mass — maximum certificated landing mass — maximum certificated zero fuel mass — most forward and rearward centre of gravity positions in various configurations (take-off, en route, landing). Note 3.— Maximum operating mass may be limited by the application of Noise Certification Standards (see Annex 16, Vol. I, and Annex 6, Parts I and II). 20/5/06 No. 99 2007/70/II. szám Annex 8 — Airworthiness of Aircraft Part IIIA 2/3/04 IIIA-1-2 1.4 Unsafe features and characteristics The aeroplane shall not possess any feature or characteristic that renders it unsafe under the anticipated operating conditions. 1.5 Proof of compliance 1.5.1 Compliance with the appropriate airworthiness requirements shall be based on evidence either from tests, calculations, or calculations based on tests, provided that in each case the accuracy achieved will ensure a level of airworthiness equal to that which would be achieved were direct tests conducted. 1.5.2 The tests of 1.5.1 shall be such as to provide reasonable assurance that the aeroplane, its components and equipment are reliable and function correctly under the anticipated operating conditions. 2007/70/II. szám ANNEX 8 IIIA-2-1 2/3/04 CHAPTER 2. FLIGHT 2.1 General 2.1.1 Compliance with the Standards prescribed in Chapter 2 shall be established by flight or other tests conducted upon an aeroplane or aeroplanes of the type for which a Certificate of Airworthiness is sought, or by calculations based on such tests, provided that the results obtained by calculations are equal in accuracy to, or conservatively represent, the results of direct testing. 2.1.2 Compliance with each Standard shall be established for all applicable combinations of aeroplane mass and centre of gravity position, within the range of loading conditions for which certification is sought. 2.1.3 Where necessary, appropriate aeroplane configurations shall be established for the determination of performance in the various stages of flight and for the investigation of the aeroplane’s flying qualities. 2.2 Performance 2.2.1 General 2.2.1.1 Sufficient data on the performance of the aeroplane shall be determined and scheduled in the aeroplane flight manual to provide operators with the necessary information for the purpose of determining the total mass of the aeroplane on the basis of the values, peculiar to the proposed flight, of the relevant operational parameters, in order that the flight may be made with reasonable assurance that a safe minimum performance for that flight will be achieved. 2.2.1.2 The performance scheduled for the aeroplane shall take into consideration human performance and in particular shall not require exceptional skill or alertness on the part of the flight crew. Note.— Guidance material on human performance can be found in the Human Factors Training Manual (Doc 9683). 2.2.1.3 The scheduled performance of the aeroplane shall be consistent with compliance with 1.3.1 and with the operation in logical combinations of those of the aeroplane’s systems and equipment, the operation of which may affect performance. 2.2.2 Minimum performance At the maximum mass scheduled (see 2.2.3) for take-off and for landing as functions of the aerodrome elevation or pressure-altitude either in the standard atmosphere or in specified still air atmospheric conditions, and, for seaplanes, in specified conditions of smooth water, the aeroplane shall be capable of accomplishing the minimum performances specified in 2.2.2.1 and 2.2.2.2, respectively, not considering obstacles, or runway or water run length. Note.— This Standard permits the maximum take-off mass and maximum landing mass to be scheduled in the aeroplane flight manual against, for example: — aerodrome elevation, or — pressure-altitude at aerodrome level, or — pressure-altitude and atmospheric temperature at aerodrome level, so as to be readily usable when applying the national code on aeroplane performance operating limitations. 2.2.2.1 Take-off

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