Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 2824

b) subject an outside observer to harmful dazzle. Note.— In order to avoid the effects mentioned in 8.4.2, it will be necessary in some cases to provide means whereby the pilot can switch off or reduce the intensity of the flashing lights. * Please refer to 1.1.2 of this part. 2007/70/II. szám ANNEX 8 IIIA-9-1 2/3/04 CHAPTER 9. OPERATING LIMITATIONS AND INFORMATION 9.1 General The operating limitations within which compliance with the Standards of this Annex is determined, together with any other information necessary to the safe operation of the aeroplane, shall be made available by means of an aeroplane flight manual, markings and placards, and such other means as may effectively accomplish the purpose. The limitations and information shall include at least those prescribed in 9.2, 9.3 and 9.4. 9.2 Operating limitations Limitations which there is a risk of exceeding in flight and which are defined quantitatively shall be expressed in suitable units and corrected if necessary for errors in measurements so that the flight crew can, by reference to the instruments available to them, readily determine when the limitations are reached. 9.2.1 Loading limitations The loading limitations shall include all limiting masses, centres of gravity positions, mass distributions, and floor loadings (see 1.3.2). 9.2.2 Airspeed limitations The airspeed limitations shall include all speeds (see 3.2) that are limiting from the standpoint of structural integrity or flying qualities of the aeroplane, or from other considerations. These speeds shall be identified with respect to the appropriate aeroplane configurations and other pertinent factors. 9.2.3 Powerplant limitations The powerplant limitations shall include all those established for the various powerplant components as installed in the aeroplane (see 7.1.2 and 7.2.3). 9.2.4 Limitations on equipment and systems The limitations on equipment and systems shall include all those established for the various equipment and systems as installed in the aeroplane. 9.2.5 Miscellaneous limitations Miscellaneous limitations shall include any necessary limitations with respect to conditions found to be prejudicial to the safety of the aeroplane (see 1.3.1). 9.2.6 Flight crew limitations The flight crew limitations shall include the minimum number of flight crew personnel necessary to operate the aeroplane, having regard, among other things, to the accessibility to the appropriate crew members of all necessary controls and instruments and to the execution of the established emergency procedures. Note.— See Annex 6 — Operation of Aircraft, Parts I and II, for the circumstances in which the flight crew shall include members in addition to the minimum flight crew defined in this Annex. 9.2.7 Flying time limitation after system or power-unit failure The systems limitations shall include the maximum flying time for which system reliability has been established in relation to the approval of operations by aeroplanes with two turbine power-units beyond the threshold time established in accordance with 4.7 of Annex 6, Part I. Note.— The maximum time established in accordance with 4.7 of Annex 6, Part I, for a particular route may be less than that determined in accordance with 9.2.7 because of the operational considerations involved. 9.3 Operating information and procedures 9.3.1 Types of eligible operations There shall be listed the particular types of operations, as may be defined in Annex 6, Parts I and II, or be generally recognized, for which the aeroplane has been shown to be eligible by virtue of compliance with the appropriate airworthiness requirements. 9.3.2 Loading information The loading information shall include the empty mass of the aeroplane, together with a definition of the condition of the 2007/70/II. szám Annex 8 — Airworthiness of Aircraft Part IIIA 2/3/04 IIIA-9-2 aeroplane at the time of weighing, the corresponding centre of gravity position, and the reference points and datum lines to which the centre of gravity limits are related. Note.— Usually the empty mass excludes the mass of the crew and payload, the usable fuel supply and the drainable oil; it includes the mass of all fixed ballast, unusable fuel supply, undrainable oil, total quantity of engine coolant and total quantity of hydraulic fluid. 9.3.3 Operating procedures A description shall be given of normal and emergency operating procedures which are peculiar to the particular aeroplane and necessary for its safe operation. These shall include procedures to be followed in the event of failure of one or more power-units. 9.3.4 Handling information Sufficient information shall be given on any significant or unusual features of the aeroplane characteristics. Those stalling speeds or minimum steady flight speeds required to be established by 2.3.4.3 shall be scheduled. 9.3.5 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 and for which the application for certification was submitted on or after 12 March 2000, a least-risk location on the aeroplane shall be identified where a bomb or other explosive device may be placed to minimize the effects on the aeroplane in the case of detonation. 9.4 Performance information The performance of the aeroplane shall be scheduled in accordance with 2.2. There shall be included information regarding the various aeroplane configurations and powers involved and the relevant speeds, together with information that would assist the flight crew in attaining the performance as scheduled. 9.5 Aeroplane flight manual An aeroplane flight manual shall be made available. It shall identify clearly the specific aeroplane or series of aeroplanes to which it is related. The aeroplane flight manual shall include at least the limitations, information and procedures specified in this chapter. 9.6 Markings and placards 9.6.1 Markings and placards on instruments, equipment, controls, etc., shall include such limitations or information as necessary for the direct attention of the flight crew during flight. 9.6.2 Markings and placards or instructions shall be provided to give any information that is essential to the ground crew in order to preclude the possibility of mistakes in ground servicing (e.g. towing, refuelling) that could pass unnoticed and that could jeopardize the safety of the aeroplane in subsequent flights. 20/5/06 No. 99 2007/70/II. szám ANNEX 8 IIIA-10-1 2/3/04 CHAPTER 10. CONTINUING AIRWORTHINESS — MAINTENANCE INFORMATION 10.1 General Information for use in developing procedures for maintaining the aeroplane in an airworthy condition shall be made available. The information shall include that described in 10.2, 10.3 and 10.4. 10.2 Maintenance information Maintenance information shall include a description of the aeroplane and recommended methods for the accomplishment of maintenance tasks. Such information shall include guidance on defect diagnosis. 10.3 Maintenance programme information Maintenance programme information shall include the maintenance tasks and the recommended intervals at which these tasks are to be performed. 10.4 Maintenance information resulting from the type design approval Maintenance tasks and frequencies that have been specified as mandatory by the State of Design in approval of the type design shall be identified as such. 2007/70/II. szám ANNEX 8 IIIA-11-1 2/3/04 CHAPTER 11. SECURITY 11.1 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). 11.2 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 and for which the application for certification was submitted on or after 12 March 2000, 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. 11.3 Protection of the flight crew compartment 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, 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. 11.4 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 and for which the application for certification was submitted on or after 12 March 2000, 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 IIIB-A-1 2/3/04 PART IIIB. AEROPLANES OVER 5 700 KG FOR WHICH APPLICATION FOR CERTIFICATION WAS SUBMITTED ON OR AFTER 2 MARCH 2004 SUB-PART A. GENERAL A.1 Applicability A.1.1 The Standards of Part IIIB are applicable in respect of all aeroplanes designated in A.1.2 for which an application for the issue of a type certificate is submitted to the appropriate national authorities on or after 2 March 2004. A.1.2 Except for those Standards and Recommended Practices which specify a different applicability, the Standards and Recommended Practices of Part IIIB shall apply to all 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 1.— The aeroplanes described in A.1.2 are known in some States as transport category aeroplanes. Note 2.— 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. A.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 aeroplanes designated in A.1.2 shall be at least substantially equivalent to the overall level intended by the broad Standards of Part IIIB. A.1.4 Unless otherwise stated, the Standards apply to the complete aeroplane including power-units, systems and equipment. A.2 Operating limitations A.2.1 Limiting conditions shall be established for the aeroplane, its power-units and its equipment (see G.2). Compliance with the Standards of Part IIIB shall be established assuming that the aeroplane is operated within the limitations specified. The limitations shall include a margin of safety to render the likelihood of accidents arising therefrom extremely remote. Note.— Guidance material concerning the expression “extremely remote” is contained in the Airworthiness Manual (Doc 9760), Volume II, Part A. A.2.2 Limiting ranges of mass, centre of gravity location, load distribution, speeds, ambient air temperature and altitude or pressure-altitude shall be established within which compliance with all the pertinent Standards in Part IIIB is shown. 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.— 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). A.3 Unsafe features and characteristics Under all anticipated operating conditions, the aeroplane shall not possess any feature or characteristic that renders it unsafe. A.4 Proof of compliance Compliance with the appropriate airworthiness requirements shall be based on evidence from tests, calculations or any acceptable combination of tests and calculations, provided that in each case the accuracy achieved will be such as to provide reasonable assurance that the aeroplane, its components and equipment comply with the requirements and are reliable and function correctly under the anticipated operating conditions. 20/5/06 No. 99 2007/70/II. szám ANNEX 8 IIIB-B-1 2/3/04 SUB-PART B. FLIGHT B.1 General B.1.1 Compliance with the Standards prescribed in Sub-part B shall be established by flight or other tests conducted upon an aeroplane or aeroplanes of the type for which a Type Certificate 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. B.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. B.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. B.2 Performance design parameters B.2.1 Sufficient data on the performance of the aeroplane shall be determined and scheduled in the 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. B.2.2 Achieving 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). B.2.3 The scheduled performance of the aeroplane shall be consistent with compliance with A.2.1 and with the operation in logical combinations of those of the aeroplane’s systems and equipment, the operation of which may affect performance. B.2.4 Minimum performance At the maximum mass scheduled (see B.2.7) 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 B.2.5 and B.2.6, 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. B.2.5 Take-off

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