Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 2905

d) physical comfort. 2007/70/II. szám ANNEX 8 IIIB-K-1 2/3/04 SUB-PART K. SECURITY K.1 Aeroplanes used for domestic commercial operations Recommendation.— International Standards and Recommended Practices set forth in this chapter should be applied by all Contracting States for aeroplanes engaged in domestic commercial operations (air services). K.2 Least-risk bomb location For aeroplanes of a maximum certificated take-off mass in excess of 45 500 kg or with a passenger seating capacity greater than 60, consideration shall be given during the design of the aeroplane to the provision of a least-risk bomb location so as to minimize the effects of a bomb on the aeroplane and its occupants. K.3 Protection of the flight crew compartment K.3.1 In all aeroplanes, which are required by Annex 6, Part I, Chapter 13 to have an approved flight crew compartment door, and for which an application for the issue of a type certificate is first submitted to the appropriate national authority on or after 20 May 2006, the flight crew compartment bulkheads, floors and ceilings shall be designed to resist penetration by small arms fire and grenade shrapnel and to resist forcible intrusions, if these areas are accessible in flight to passengers and cabin crew. K.3.2 Recommendation.— In all aeroplanes, which are required by Annex 6, Part I, Chapter 13 to have an approved flight crew compartment door, and for which an application for amending the type certificate to include a derivative type design is submitted to the appropriate national authority on or after 20 May 2006, consideration should be given to reinforcing the flight crew compartment bulkheads, floors and ceilings so as to resist penetration by small arms fire and grenade shrapnel and to resist forcible intrusions, if these areas are accessible in flight to passengers and cabin crew. Note.— Standards and Recommended Practices concerning the requirements for the flight crew compartment door in all commercial passenger-carrying aeroplanes are contained in Annex 6, Part I, Chapter 13. K.4 Interior design For aeroplanes of a maximum certificated take-off mass in excess of 45 500 kg or with a passenger seating capacity greater than 60, consideration shall be given to design features that will deter the easy concealment of weapons, explosives or other dangerous objects on board aircraft and that will facilitate search procedures for such objects. 20/5/06 No. 99 2007/70/II. szám ANNEX 8 IV-1-1 2/3/04 PART IV. HELICOPTERS CHAPTER 1. GENERAL 1.1 Applicability 1.1.1 The Standards of Part IV are applicable in respect of all helicopters designated in 1.1.2 that are of types of which the prototype is submitted to the appropriate national authorities for certification on or after 22 March 1991. Note.— The Council recognizes that the Standards relating to fire protection, crash survival and provisions for emergency are very important to safety and urges the implementation of the substance of these Standards as soon as it is feasible and practicable before the applicable date. 1.1.2 The Standards of Part IV shall apply to helicopters 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. 1.1.3 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 helicopters designated in 1.1.2 shall be at least substantially equivalent to the overall level intended by the broad Standards of Part IV. 1.1.4 Unless otherwise stated, the Standards apply to the complete helicopter including power-units, systems and equipment. 1.2 Limitations 1.2.1 Limiting conditions shall be established for the helicopter, its power-units and its equipment (see 9.2). Compliance with the Standards of Part IV shall be established assuming that the helicopter is operated within the limitations specified. The limitations shall be sufficiently removed from any conditions prejudicial to the safety of the helicopter to render the likelihood of accidents arising therefrom extremely remote. 1.2.2 Limiting ranges of mass, centre of gravity location, load distribution, speeds and ambient conditions shall be established within which compliance with all the pertinent Standards in Part IV 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 helicopter limitations: — maximum certificated take-off (including lift-off) mass — maximum certificated ground-taxiing mass — maximum certificated landing mass — most forward, rearward, and lateral centre of gravity positions in various configurations — maximum certificated cargo sling mass. Note 3.— Maximum operating mass may be limited by the application of Noise Certification Standards (see Annex 16, Vol. I, and Annex 6, Part III). 1.3 Unsafe features and characteristics The helicopter shall not possess any feature or characteristic that renders it unsafe under the anticipated operating conditions. 1.4 Proof of compliance 1.4.1 Compliance with the appropriate airworthiness requirements shall be based on evidence either from tests, calculations, calculations based on tests, or other methods, 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. 1.4.2 The tests of 1.4.1 shall be such as to provide reasonable assurance that the helicopter, its components and equipment are reliable and function correctly under the anticipated operating conditions. 2007/70/II. szám ANNEX 8 IV-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 a helicopter or helicopters of the type for which a Certificate of Airworthiness is sought, or by calculations (or other methods) based on such tests, provided that the results obtained by calculations (or other methods) 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 helicopter mass and centre of gravity position, within the range of loading conditions for which certification is sought. 2.1.3 Where necessary, appropriate helicopter configurations shall be established for the determination of performance in the various stages of flight and for the investigation of the helicopter’s flying qualities. 2.2 Performance 2.2.1 General 2.2.1.1 Sufficient data on the performance of the helicopter shall be determined and scheduled in the helicopter flight manual to provide operators with the necessary information for the purpose of determining the total mass of the helicopter 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 helicopter shall take into consideration human performance and in particular shall not require exceptional skill or alertness on the part of the pilot. 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 helicopter shall be consistent with compliance with 1.2.1 and with the operation in logical combinations of those of the helicopter’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 take-off or landing site elevation or pressure-altitude either in the standard atmosphere or in specified still air atmospheric conditions, and, for water operations, in specified conditions of smooth water, the helicopter shall be capable of accomplishing the minimum performances specified in 2.2.2.1 and 2.2.2.2, respectively, not considering obstacles, or final approach and take-off area length. Note.— This Standard permits the maximum take-off mass and maximum landing mass to be scheduled in the helicopter flight manual against, for example at the take-off or landing site: — elevation, or — pressure-altitude, or — pressure-altitude and atmospheric temperature, so as to be readily usable when applying the national code on helicopter performance operating limitations. 2.2.2.1 Take-off

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