Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 2875

b) subject a person outside the aeroplane to harmful dazzle. 2007/70/II. szám Annex 8 — Airworthiness of Aircraft Part IIIB 2/3/04 IIIB-F-2 Note.— In order to avoid the effects mentioned in F.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. F.5 Electromagnetic interference protection Aeroplane electronic systems, particularly flight-critical and flight-essential systems, shall be protected against electromagnetic interference from both internal and external sources. F.6 Ice protection If certification for flight in icing conditions is requested, the aeroplane shall be shown to be able to operate safely in icing conditions likely to be encountered in all expected operating environments. 2007/70/II. szám ANNEX 8 IIIB-G-1 2/3/04 SUB-PART G. OPERATING LIMITATIONS AND INFORMATION G.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 a 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 this sub-part. G.2 Operating limitations G.2.1 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. G.2.2 Loading limitations The loading limitations shall include all limiting masses, centres of gravity positions, mass distributions, and floor loadings (see A.2.2). G.2.3 Airspeed limitations The airspeed limitations shall include all speeds (see C.5) 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. G.2.4 Powerplant limitations The powerplant limitations shall include all those established for the various powerplant components as installed in the aeroplane (see E.3.1 and E.3.5.3). G.2.5 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. G.2.6 Miscellaneous limitations Miscellaneous limitations shall include any necessary limitations with respect to conditions found to be prejudicial to the safety of the aeroplane (see A.2.1). G.2.7 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. G.2.8 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 G.2.8 because of the operational considerations involved. G.3 Operating information and procedures G.3.1 Types of eligible operations The particular types of operations for which the aeroplane has been shown to be eligible by virtue of compliance with the appropriate airworthiness requirements shall be listed. G.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 IIIB 2/3/04 IIIB-G-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. G.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. G.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 B.4.2.3 shall be scheduled. G.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, 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. G.4 Performance information The performance of the aeroplane shall be scheduled in accordance with B.2. There shall be included information regarding the various aeroplane configurations and powers or thrusts involved and the relevant speeds, together with information that would assist the flight crew in attaining the performance as scheduled. G.5 Flight manual A flight manual shall be made available. It shall identify clearly the specific aeroplane or series of aeroplanes to which it is related. The flight manual shall include at least the limitations, information and procedures specified in this sub-part, except those specified in G.7. G.6 Markings and placards G.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. G.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. G.7 Continuing airworthiness G.7.1 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 G.7.2, G.7.3 and G.7.4. G.7.2 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. G.7.3 Maintenance programme information Maintenance programme information shall include the maintenance tasks and the recommended intervals at which these tasks are to be performed. G.7.4 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. 20/5/06 No. 99 2007/70/II. szám ANNEX 8 IIIB-H-1 2/3/04 SUB-PART H. SYSTEMS SOFTWARE All systems software shall be designed and validated such as to ensure that the systems in which they are used perform their intended functions with a level of safety that complies with the requirements of Part IIIB, notably those of F.1.2 a) and F.1.3. Note.— Some States accept the use of national/international industry standards, such as RTCA/DO-178 or EUROCAE ED12, for the design and testing of systems software. 2007/70/II. szám ANNEX 8 IIIB-I-1 2/3/04 SUB-PART I. CRASHWORTHINESS AND CABIN SAFETY I.1 General Developments in the subject of crashworthiness shall be taken into account in the design of aeroplanes to improve the probability of occupant survival. I.2 Design emergency landing loads Emergency landing (crash) loads shall be determined for all categories of aeroplanes so that the interiors, furnishings, support structure and safety equipment can be designed to maximize survivability for the occupants. Items to be considered shall include:

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