Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 2804

e) VE1 to VEn, maximum speeds at which flaps and landing gears may be extended or other configuration changes be made. The speeds VA, VB, VC, and VE in a), b), c) and e) shall be sufficiently greater than the stalling speed of the aeroplane to safeguard against loss of control in turbulent air. 3.2.2 Limiting airspeeds Limiting airspeeds, based on the corresponding design airspeeds with safety margins, where appropriate, in accordance with 1.3.1 shall be included in the aeroplane flight manual as part of the operating limitations (see 9.2.2). 3.3 Flight loads The flight loading conditions of 3.3.1, 3.3.2 and 3.5 shall be considered for the range of mass and mass distributions prescribed in 3.1.1 and at airspeeds established in accordance with 3.2.1. Asymmetrical as well as symmetrical loading shall be taken into account. The air, inertia, and other loads resulting from the specified loading conditions shall be distributed so as to approximate actual conditions closely or to represent them conservatively. 3.3.1 Manoeuvring loads Manoeuvring loads shall be computed on the basis of manoeuvring load factors appropriate to the manoeuvres permitted by the operating limitations. They shall not be less than values that experience indicates will be adequate for the anticipated operating conditions. 3.3.2 Gust loads Gust loads shall be computed for vertical and horizontal gust velocities and gradients that statistics or other evidence indicate will be adequate for the anticipated operating conditions. 2007/70/II. szám Annex 8 — Airworthiness of Aircraft Part IIIA 2/3/04 IIIA-3-2 3.4 Ground and water loads The structure shall be able to withstand all the loads due to the reactions of the ground and water surface that are likely to arise during taxiing, take-off and landing. 3.4.1 Landing conditions The landing conditions at the design take-off mass and at the design landing mass shall include such symmetrical and asymmetrical attitudes of the aeroplane at ground or water contact, such velocities of descent and such other factors affecting the loads imposed upon the structure as might be present in the anticipated operating conditions. 3.5 Miscellaneous loads In addition to or in conjunction with the manoeuvring and gust loads and with the ground and water loads, consideration shall be given to all other loads (flight control loads, cabin pressures, effects of engine operation, loads due to changes of configuration, etc.) that are likely to occur in the anticipated operating conditions. 3.6 Flutter, divergence and vibration The aeroplane structure shall be designed to be free from flutter, structural divergence (i.e. unstable structural distortion due to aerodynamic loading), and loss of control due to structural deformation, at speeds within and sufficiently beyond the operating limitations to comply with 1.3.1. Adequate strength shall be provided to withstand the vibration and buffeting that might occur in the anticipated operating conditions. 3.7 Fatigue strength The strength and fabrication of the aeroplane shall be such as to ensure that the probability of disastrous fatigue failure of the aeroplane’s structure under repeated loads and vibratory loads in the anticipated operating conditions is extremely remote. 2007/70/II. szám ANNEX 8 IIIA-4-1 2/3/04 CHAPTER 4. DESIGN AND CONSTRUCTION 4.1 General Details of design and construction shall be such as to give reasonable assurance that all aeroplane parts will function effectively and reliably in the anticipated operating conditions. They shall be based upon practices that experience has proven to be satisfactory or that are substantiated by special tests or by other appropriate investigations or both. They shall observe Human Factors principles. Note.— Guidance material on Human Factors principles can be found in the Human Factors Training Manual (Doc 9683). 4.1.1 Substantiating tests The functioning of all moving parts essential to the safe operation of the aeroplane shall be demonstrated by suitable tests in order to ensure that they will function correctly under all operating conditions for such parts. 4.1.2 Materials All materials used in parts of the aeroplane essential for its safe operation shall conform to approved specifications. The approved specifications shall be such that materials accepted as complying with the specifications will have the essential properties assumed in the design. 4.1.3 Fabrication methods The methods of fabrication and assembly shall be such as to produce a consistently sound structure which shall be reliable with respect to maintenance of strength in service. 4.1.4 Protection The structure shall be protected against deterioration or loss of strength in service due to weathering, corrosion, abrasion, or other causes, which could pass unnoticed, taking into account the maintenance the aeroplane will receive. 4.1.5 Inspection provisions Adequate provision shall be made to permit any necessary examination, replacement, or reconditioning of parts of the aeroplane that require such attention, either periodically or after unusually severe operations. 4.1.6 Design features Special consideration shall be given to design features that affect the ability of the flight crew to maintain controlled flight. This shall include at least the following:

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