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Air Frame and Systems, Electrics, Powerplant and Emergency Equipments Air Frame and Systems, Electrics, Powerplant and Emergency Equipments AirFrame and Systems – Fuselage What are the most frequent used materials in a monocoque or semi-monocoque structure? A) Steel. B) Aluminium or magnesium alloy. C) Wood. D) Composite fibres A framework of truss type fuselage is used in: A) Medium range commuter type turbo-props B) Heavy wide bodied subsonic turbo-fan aircraft C) Light training aircraft mainly D) Supersonic aircraft A semi-monocoque fuselage has... in the longitudinal direction. Together with the frames, they resist... moments and axial forces. The skin panels are loaded mainly in... A) Stringers, bending, shear. B) Stringers, bending, buckling. C) Bars, buckling, bending. D) Spars, torsion, shear. Aircraft structures consists mainly of: A) Light alloy steel sheets with copper rivets and titanium or steel materials at points requiring high strength. B) Magnesium alloy sheets with aluminium rivets and titanium or steel at points requiring high strength. C) Aluminium sheets and rivets with titanium or steel materials at points requiring high strength. D) Aluminium alloy sheets and rivets with titanium or steel materials at points requiring high strength. What is the purpose of the stringers? A) To produce stress risers. B) To absorb the torsional and compressive stresses. C) To support the primary control surfaces. D) To prevent buckling and bending by supporting and stiffening the skin. The primary purpose of the fuselage is to: A) Provide access to the cockpit. B) House the crew and payload. C) Support the wings. D) Keep out adverse weather. Fatigue life of the fuselage is mostly based on: A) Number of cycles at maximum differential. B) Number of explosive decompressions. C) Number of times a certain load factor is exceeded. D) Number of pressurisation cycles. A damage tolerant structure: A) Need not be repaired until the aircraft undergoes deep maintenance. B) Is a structure which is free of cracks. C) Is replaced when it reaches its predicted life. D) Has degree of structural strength redundancy spread over a large area. In a stressed skin airframe structure for a pressurised aircraft: A) The rivets and skin are under tensile loads. B) The rivets and skin are under compressive loads. C) The rivets are under shear loads and the skin is under tensile loads. D) The rivets take a shear load and the skin is under compressive loads. During a violent avoidance manoeuvre, a light twin aircraft, certified to FAR 23 requirements was subjected to an instantaneous load factor of 4.2. The Flight Manual specifies that the aircraft is certified in the normal category for a load factor of -1.9 to +3.8. Considering the certification requirements and taking into account that the manufacturer of the twin did not include, during its conception, a supplementary margin in the flight envelope, it might be possible to observe: A) rupture of one or more structural components B) no distortion, permanent or temporary of the structure C) a permanent deformation of the structure D) a elastic deformation whilst the load was applied, but no permanent distortion Station numbers (Stn) and water lines (WL) are: A) Runway markings for guiding the aircraft to the terminal. B) Compass alignment markings. C) A means of locating airframe structure and components. D) Passenger seat locations. The Design Ultimate Load is minimum: A) 1.125 x Design Limit Load. B) 1.5 x Proof Load. C) 1.5 x Design Limit Load. D) 1.125 x Proof Load. The fuselage of an aircraft consists, among others, of stringers whose purpose is to: A) Provide sound and thermal isolation. B) Withstand the shear stresses. C) Assist the skin in absorbing the longitudinal traction-compression stresses. D) Integrate the strains due to pressurization to which the skin is subjected and convert them into a tensile stress. Aircraft wing construction which employs the principle of the skin taking part of the load is termed: A) Fail safe. B) Stressed skin. C) Monocoque. D) Semi monocoque. Which of the following statements about fuselage loading is true? A) Frames have no structural function. Skin and stringers take the full load. B) Frames, stringers and skin take the full load. C) Frames and stringers take the full load. Skin is only used as a cover. D) Skin and frames take the full load. Stringers are used to prevent skin buckling. For FAIL-SAFE designed structural parts: 1. The mounting principle is parallel mounting. 2. No routine check is necessary. 3. The member is removed at the end of the calculated life cycle. 4. Certain components may not be accessible. 5. The principle is the redundancy of components 6. The failure of a member causes the loads to be shared between the other system components. The combination regrouping all the correct statements is: A) 1,5,6 B) 1,3,4 C) 2,5,6 D) 2,3,4 The stresses present in all aircraft are: A) Drag, Thrust, Weight, Lift. B) Tension, Compression, Shear, Bending, Torsion. C) Tension, Compression, Strain, Shear. D) Tension, Drag, Shear, Compression, Bending. Station numbers and water lines are: A) Passenger seat locations. B) Runway markings for guiding the aircraft to the terminal. C) Compass alignment markings. D) A means of locating airframe structure and components. The airframe structure must remain substantially intact after experiencing: A) Three times the safety factor. B) The design ultimate load times a 1.5 safety factor. C) The design limit load times a 1.5 factor of safety. D) The design limit load plus the design ultimate load. Fatigue life of the fuselage is based on the: A) Number of explosive decompressions. B) Number of pressurisation cycles. C) Number of cycles at maximum differential. D) Number of landings only. Strain is defined as the: A) Yield point B) Expansion due to temperature rise C) Deformation due to stress D) Ultimate load The skin of a modern pressurised aircraft: A) Provides aerodynamic lift and prevents corrosion by keeping out adverse weather. B) Houses the crew and the payload. C) Is primary load bearing structure carrying much of the structural loads. D) Is made up of light alloy steel sheets built on the monocoque principle. Which of the following is true? A) Titanium alloy is used in aircraft construction because of its good wear resistance and high temperature tolerance. B Aluminium alloys are used in aircraft construction because it is light, easily machined and has good ) wear resistance. C) Super alloys are used because of their excellent corrosion resistance. D) Steel is used in aircraft because it is strong and heavy but has poor corrosion resistance. Aircraft skin is usually made of Al2024-alloy. This is... A) Pure aluminium. B) Pure aluminium with bronze. C) Pure aluminium with copper. D) Pure aluminium with zinc. Repetitive pressurisation cycles induce... stresses which... A) Differential, are negligible. B) Differential, cause fatigue cracks. C) Hoop, cause fatigue cracks. D) Hoop, are negligible. DURALUMIN alloys: 1. Have an aluminium-copper base. 2. Have an aluminium-magnesium base. 3. Are easy to weld. 4. Are difficult to weld. 5. Have a good thermal conductivity. 6. Have a poor air corrosion resistance The combination regrouping all the correct statements is: A) 1,3,6 B) 1,4,5 C) 2,3,6 D) 2,4,5 Among the different types of aircraft structures, the shell structures efficiently transmit the: 1. normal bending stresses 2. tangent bending stresses 3. torsional moment 4. shear stresses The combination regrouping all the correct statements is: A) 1, 2, 3 B) 1, 3, 4 C) 2, 3, 4 D) 1, 2, 4 On an aircraft which employs stressed skin construction: A) The skin of the airplane takes the majority of the structural load. B) The skin is fabric which is stretched over a structure, which in turn takes all of the load. C) The skin of the airplane takes no part of the load. D) Composite material should be used. The reason for the fact that an aeroplane designed for long distances cannot simply be used for short haul flights at higher frequencies is that: A) in that case some fuel tanks remain empty during the whole flight, which stresses the aeroplane's structure in an unacceptable way B The lifetime of the fatigue sensitive parts has been based on a determined load spectrum. ) C) these aeroplanes often consume too much fuel on short haul flights D) the procedures and checklists for this kind of aeroplanes will take too much time The fatigue life of an aircraft's pressure hull is based on: A) The total number of landings. B) The total number of explosive decompressions. C) The total number of pressurisations. D) The total number of negative differential pressure applications. 'Fail safe construction' is: A) A construction which is suitable for aerobatic flight. B) A simple and cheap type of construction. C) A type of construction in which the load is carried by other components if a part of the structure fails. D) A type of construction for small aircraft only. Which components do a semi-monocoque fuselage consists of? A) A stressed skin type of construction in which the stiffness of the skin provides a large measure of the strength of the structure. No truss or substructure is required. B) Metal stringers, bulkheads and fabric covering. C) A stressed skin structure in which the skin is supported by a lightweight framework, such as longerons, stringers and formers. D) Steel tubing, longerons and bulkhead wires. In the construction of airframes, the primary purpose of frames or formers is to: A) Form the entrance door posts. B) Oppose hoop stresses and provide shape and form to the fuselage.
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