NIVEL RNG MRO A320-2026 ATA 57

1. Where is the center wing located in the aircraft's fuselage?. a. Between the main frames Fr 36 and 42. b. Between the main frames Fr 20 and 30. c. Between the main frames Fr 1 and 10. d. In the rear fuselage.

2. How is maintenance access to the center wing box typically achieved?. a. Through two rectangular openings in the rear spar. b. Through triangular openings in the rear spar. c. Through circular openings in the rear spar. d. Through the top skin panels of the center wing box.

3. What fittings ensure the junction between the center wing box and the outer wing box?. a. Upper cruciform fitting and lower triform fitting. b. Upper triangular fitting and lower square fitting. c. Upper circular fitting and lower rectangular fitting. d. Upper hexagonal fitting and lower oval fitting.

4. What does the upper cruciform fitting make the junction between?. a. Center wing box top skin panels, outer wing box top skin panels, fuselage, and Rib 1. b. Center wing box top skin panels and bottom skin panels. c. Center wing box and outer wing box bottom skin panels. d. Outer wing box top skin panels and fuselage.

5. What part of the outer wing contains the top and bottom skin panels, ribs, and stringers?. a. Outer wing box. b. Wing tip. c. Leading edge and leading edge devices. d. Trailing edge and trailing edge devices.

6. How many top skin panels are there in the outer wing box?. a. Two. b. Three. c. Four. d. Five.

7. How many top skin panels are there in the outer wing box?. a. Two. b. Three. c. Four. d. Five.

8. What do the wing spars extend from in the outer wing?. a. Rib 1 to Rib 27. b. The center wing box. c. The fuselage. d. Rib 22 to Rib 27.

9. How many load-carrying access panels are there in the outer wing box between Rib 14 and Rib 27?. a. Fourteen. b. Seven. c. Three. d. Twenty-one.

10. How are the non load-carrying access panels between Rib 1 and Rib 13 attached to the wing?. a. Clamped on the wing skin. b. Bolted through the skin panel. c. Welded to the fuselage. d. Riveted to the center wing box.

11. What parts of the wing require reinforcement when sharklets are installed?. a. Wing front spar, fixed leading edge structure, wing rear spars, fixed trailing edge structure, wing covers, wing ribs. b. Wing tip, wing root, winglets, winglet ribs. c. Center wing box, winglet attachment points, ailerons. d. Wing stringers, wing skin panels, trailing edge devices.

12. How is Rib 27 modified when sharklets are installed on the aircraft?. a. It becomes a box Rib instead of a traditional single-sided Rib. b. It is removed from the wing. c. It is strengthened with additional materials. d. It is shifted to a different location on the wing.

13. What is the composition of the D-nose assembly in the fixed leading edge?. a. Made of aluminum alloy parts. b. Made of Carbon Fiber Reinforced Plastic. c. Made of stainless steel. d. Made of honeycomb core.

14. Which component holds the pylon shroud panels?. a. D-nose assembly. b. Support ribs. c. Sub spar. d. Pylon ribs.

15. What is the composition of the D-nose assembly in the fixed leading edge?. a. Made of aluminum alloy parts. b. Made of Carbon Fiber Reinforced Plastic. c. Made of stainless steel. d. Made of honeycomb core.

16. Which component holds the pylon shroud panels?. a. D-nose assembly. b. Support ribs. c. Sub spar. d. Pylon ribs.

17. How many tracks support Slat 1?. a. 2. b. 4. c. 5. d. 3.

18. Which slats receive de-icing through the bleed air system?. a. Slats 1 and 2. b. Slats 3 to 5. c. Slats 1 to 3. d. Slats 4 and 5.

19. Where is the fixed trailing edge located?. a. Forward of the wing front spar. b. Aft of the wing rear spar. c. Between the wing box and LE spar. d. On the wing leading edge.

20. What are the trailing edge devices?. a. Two flaps, one aileron, five spoilers. b. Three flaps, two ailerons, four spoilers. c. Two flaps, two ailerons, six spoilers. d. One flap, one aileron, four spoilers.

21. How many flaps are installed on the TE of the outer wing?. a. 1. b. 2. c. 3. d. 4.

22. What is the function of the rubbing strip on the inboard flap?. a. To enhance aerodynamics. b. To provide additional support. c. To prevent corrosion. d. To protect the top skin from damage.

23. How many wing tracks support and drive the outboard flap in the A318-A319-A320?. a. 1. b. 2. c. 3. d. 4.

24. What is the unique feature of the A321 flaps compared to the A318-A319-A320?. a. They have a tab on the trailing edge. b. They are made entirely of aluminum alloy. c. They are larger in size. d. They have no leading edge.

25. How many spoilers are connected to the middle and outer sections of the rear spar?. a. 1. b. 2. c. 3. d. 4.

26. Which spoilers have a rubbing strip attached to their trailing edge?. a. Spoilers 1 & 2. b. Spoilers 3 & 4. c. Spoilers 4 & 5. d. All spoilers.

27. What is the primary material used for the top and bottom skins of the spoilers?. a. Aluminum alloy. b. Carbon Fiber Reinforced Plastic (CFRP). c. Stainless steel. d. Honeycomb core.

28. Where is the aileron located in relation to the outer flap?. a. Inboard. b. Outboard. c. Above. d. Below.

29. What material is primarily used for the aileron's skin?. a. Aluminum alloy. b. Carbon Fiber Reinforced Plastic (CFRP). c. Stainless steel. d. Honeycomb core.

30. What is the primary material used for the sides and trailing edge profile of the spoilers?. a. Aluminum alloy. b. Carbon Fiber Reinforced Plastic (CFRP). c. Stainless steel. d. Honeycomb core.

31. Which spoiler is connected to the false rear spar?. a. Spoiler 1. b. Spoiler 2. c. Spoiler 3. d. Spoiler 4.

32. How are the bottom surface access panels of the fixed leading edge attached?. a. With screws. b. With adhesive. c. With quick release fasteners. d. With bolts.

33. Which component of the A321 flaps is made of honeycomb core with a skin made of aluminum sheet metal?. a. Leading edge. b. Flap box. c. Trailing edge. d. Tab.

34. What is the primary function of the rubbing strip on the outer surface of the top skin of the flaps?. a. To enhance aerodynamics. b. To provide additional support. c. To prevent corrosion. d. To protect from damage.

35. The fixed Leading Edge (LE) assembly is located behind the front spar of the wing-box. a. True. b. False.

36. The bottom surface access panels are made of Carbon Fiber Reinforced Plastic (CFRP) and are attached with screws. a. True. b. False.

37. The wing leading edge is fitted with five slats. a. True. b. False.

38. The trailing edge devices consist of three flaps, one aileron, and six spoilers. a. True. b. False.

39. Two flaps are installed on the TE of the outer wing, and they are connected by an interconnection strut. a. True. b. False.

40. The inboard flap of A318-A319-A320 is supported by three tracks. a. True. b. False.

41. The outboard flap of A318-A319-A320 has a leading edge made of stainless steel. a. True. b. False.

42. The A321 flaps are fowler flaps without any tabs on the trailing edge. a. True. b. False.

43. There are six spoilers on the upper surface of the wing trailing edge. a. True. b. False.