74 + Interview Questions in Landing Gear And Subsystems in Aircraft Design Page 1 InterviewSolution

1.	Following diagram represents _________(a) multi bogey(b) pusher prop(c) wing(d) bicycleI have been asked this question in an online quiz.My question comes from Landing Gear Arrangements in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct option is (a) multi bogey Explanation: Above DIAGRAM is illustrating a typical multi- bogey landing gear ARRANGEMENT. As shown in the diagram, multi bogey arrangement has more than 4 WHEELS to support higher IMPACT loads and to carry heavy structure. Pusher prop is TYPE of engine propulsion system.

Discussion

2.	Following diagram represents ____________(a) bicycle(b) tricycle(c) tail dragger(d) quadrupleI have been asked this question by my school principal while I was bunking the class.This is a very interesting question from Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) bicycle Easiest explanation: Typical bicycle landing GEAR arrangement is shown in the above diagram. As shown in the diagram, bicycle arrangement has 2 main landing gear and SMALL outrigger wheels. It REQUIRES flat attitude for OPERATION.

Discussion

3.	What is the location of main wheel in tricycle gear?(a) After CG of the aircraft(b) At CG(c) Before CG(d) At noseThis question was posed to me during an interview for a job.The above asked question is from Landing Gear Arrangements in section Landing Gear and Subsystems of Aircraft Design
Answer» Right ANSWER is (a) After CG of the aircraft To elaborate: Main wheel is located after the cg of the aircraft in typical tricycle landing gear arrangement. This arrangement is stable. An AUXILIARY wheel is located ahead of cg of the aircraft. It can be used for LARGE crab angle as well.

Discussion

4.	Let’s consider we want to design a seaplane which has the deadrise angle of 10° then, what should be the stall speed in in miles per hour?(a) 40mph(b) 89mph(c) 10mph(d) 21.9mphThe question was asked during a job interview.My doubt is from Landing Gear and Subsystems in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct answer is (a) 40MPH Explanation: Given, ɑdeadrise = 10° Now, stall SPEED can be given by, V = 2 * ɑdeadrise + 20 = 2*10 + 20 = 40mph.

Discussion

5.	Which of the following is correct?(a) Sway brace is typically used for main landing gear(b) Lift is always same as weight(c) Lift opposes the aircraft forward motion(d) Drag is propulsive force produced by landing gear to accelerate an aircraftThe question was asked in semester exam.My question is based upon Gear-Retraction Geometry in section Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT answer is (a) Sway brace is typically used for MAIN landing gear The best I can explain: Sway brace term is typically used for main landing gear. It is also used to withstand aerodynamic loads and breaking loads. They are used to provide lateral SUPPORT for the gears. AIRCRAFT FORWARD motion is primarily opposed by drag. Lift is not always same as weight.

Discussion

6.	Following diagram represents _________(a) tail dragger(b) bicycle(c) tricycle(d) single mainThe question was asked in an interview.Query is from Landing Gear Arrangements in section Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT option is (a) tail dragger For explanation: Above DIAGRAM is REPRESENTING a typical tail dragger landing gear arrangement. As shown in the diagram, tail dragger configuration has two main gears located ahead of cg. It also INCLUDES an auxiliary wheel at tail as shown in the diagram.

Discussion

7.	We should always use tail dragger arrangement for every aircraft.(a) True(b) FalseThis question was addressed to me in semester exam.My question is based upon Landing Gear Arrangements topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT choice is (b) False For explanation I would say: Tail dragger ARRANGEMENT was most widely used during first 40 to 50 years of AVIATION. Nowadays, this arrangement is limited to general aviation aircraft. This arrangement is inherently Unstable but are lighter in weight and provides more prop clearance.

Discussion

8.	Which of the following is correct?(a) Landing gear is also termed as undercarriage(b) Tail dragger arrangement is most stable(c) Lift coefficient is same as weight always(d) Lift to thrust is called thrust loadingI have been asked this question during an interview for a job.My question is based upon Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Correct answer is (a) Landing gear is also termed as undercarriage Easiest EXPLANATION: Landing gear is also called undercarriage. TAIL dragger arrangement is inherently Unstable. Lift coefficient cannot be same as WEIGHT always. Lift to drag ratio is called AERODYNAMIC efficiency and very important parameter for aerodynamic consideration.

Discussion

9.	Following diagram represents ______(a) gear retraction geometry(b) in cockpit(c) gear load chart(d) drag polarThis question was addressed to me during an online exam.Origin of the question is Gear-Retraction Geometry in section Landing Gear and Subsystems of Aircraft Design
Answer» Right choice is (a) GEAR retraction geometry To explain I would say: Landing gear retraction is one of the important FACTOR of landing gear design. TYPICAL gear retraction geometry is shown in the above diagram. As shown in the diagram undercarriage is RETRACTED inside the WING fuselage junction.

Discussion

10.	Which of the following is correct?(a) Solid spring shock absorber is heavier than the other types(b) Lift to drag ratio is always unity(c) Weight at takeoff is same as weight at landing(d) Thrust is same as drag alwaysThis question was addressed to me during an interview.Origin of the question is Landing Gear in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) SOLID spring shock ABSORBER is heavier than the other types Explanation: Solid spring shock absorber is heavier than the other types Lift to DRAG is not necessarily be unit ALWAYS. TYPICALLY, a good design will have lift to drag ratio more than 1. During flight weight decreases and as a result takeoff weight and weight during landing will not be same.

Discussion

11.	Drag brace is used to __________(a) withstand aerodynamic loads and breaking loads(b) reduce drag(c) lowers the weight of an aircraft(d) decrease the drag produced by gear onlyThe question was asked during an interview for a job.Question is taken from Gear-Retraction Geometry topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Correct answer is (a) WITHSTAND aerodynamic loads and breaking loads For EXPLANATION I WOULD say: Typical landing gear retraction arrangement includes a diagonal arm. This diagonal arm for nose wheel is called DRAG BRACE. Drag brace is used to withstand the breaking loads and aerodynamic loads as well.

Discussion

12.	If a seaplane has velocity at stall as V mph then, what will be the value of deadrise angle?(a) ɑdeadrise = 0.5(v – 20) degree(b) ɑdeadrise = 0.5(v / 20) degree(c) ɑdeadrise = 0.5v degree(d) ɑdeadrise = 0.5(v^2 – 20) degreeThis question was addressed to me during an interview.I'd like to ask this question from Landing Gear and Subsystems topic in section Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT choice is (a) ɑdeadrise = 0.5(v – 20) degree The EXPLANATION is: When we USE V SHAPED bottom on SEAPLANE, deadrise is then defined as the height of the V and angle is called deadrise angle. Typically, deadrise angle can be approximated as follows, ɑdeadrise = 0.5(v – 20) degree where, v is stall speed in mph.

Discussion

13.	An aircraft is designed to have landing weight of 2500N and stall speed V of 9.8m/s. How much kinetic energy should be absorbed by wheel? Consider number of wheels with brake is 2.(a) 6125J(b) 5.98 KJ(c) 2100(d) 235 KJThe question was asked in unit test.The doubt is from Landing Gear in division Landing Gear and Subsystems of Aircraft Design
Answer» The correct OPTION is (a) 6125J Easy explanation: GIVEN, LANDING weight W = 2500N, stall speed v = 9.8m/s. NUMBER of wheels N = 2. Kinetic energy K.E. = 0.5Wv^2/gn = 0.525009.8^2/9.812 = 6125 J.

Discussion

14.	Which of the following is an example of a shock absorber?(a) Solid spring shock arrangement(b) Lift curve slope(c) Flap(d) ElevatorI got this question by my college professor while I was bunking the class.The above asked question is from Landing Gear in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Right OPTION is (a) Solid spring shock ARRANGEMENT To explain I WOULD say: Solid spring shock arrangement is an example of shock absorber. Lift curve slope is defined as change in lift by change in alpha. Flap is secondary control SURFACE.

Discussion

15.	Which of the following is correct?(a) Typically, bottom of the seaplane is fairly flat(b) Lift is same as weight always(c) Drag polar will show thrust vs weight(d) Seaplanes cannot land on waterI have been asked this question in semester exam.My question is from Landing Gear and Subsystems topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Correct option is (a) Typically, BOTTOM of the seaplane is fairly flat The explanation: Typically, bottom of SEAPLANES are MADE fairly flat so that seaplane can skim on the top of water even at high speeds. Lift is not always same as weight. Drag polar is schematic DIAGRAM illustrating relationship between drag coefficient and lift coefficient.

Discussion

16.	If an aircraft has gear load factor of 3 and average total load during deflection is 180 unit then, find how much weight is carried during landing.(a) 60 unit(b) 10 unit(c) 100 unit(d) 283 unitThis question was posed to me during an interview.This intriguing question originated from Landing Gear in portion Landing Gear and Subsystems of Aircraft Design
Answer» The correct option is (a) 60 UNIT Explanation: Weight during landing W = LOAD L / GEAR load factor = 180/3 = 60 unit.

Discussion

17.	What is tipback angle?(a) Maximum attitude of an aircraft with tail touching the ground with struts fully extended(b) Wing loading divided by span(c) Lift to drag ratio(d) Maximum altitude of an aircraftI got this question during an interview.My question is taken from Landing Gear Arrangements in section Landing Gear and Subsystems of Aircraft Design
Answer» Correct OPTION is (a) Maximum attitude of an aircraft with tail TOUCHING the ground with struts fully EXTENDED Explanation: Tipback angle is defined as Maximum attitude of an aircraft with tail touching the ground and the struts are completely extended. Wing loading is the ratio of weight and reference area. LIFT to drag ratio is called aerodynamic efficiency.

Discussion

18.	Which of the following is correct?(a) The solid spring year deflects with some lateral motion(b) Lift is always same as weight(c) Drag polar shows lift variation with velocity(d) Thrust loading at landing is same as wing lift alwaysI have been asked this question during an interview.Question is taken from Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT option is (a) The solid spring year deflects with some LATERAL motion The best I can explain: Some lateral motion can be OBSERVED when we deflect solid spring. Lift is same as weight during cruise. Drag polar does not show lift variation with VELOCITY. Thrust loading is ratio of Thrust and weight which cannot be same as lift.

Discussion

19.	If an aircraft has sink speed at touchdown as 9 ft/s then, find the stroke in inches approximately.(a) 9 in(b) 19 in(c) 1 in(d) 2 inThe question was posed to me in an international level competition.Query is from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Right CHOICE is (a) 9 in The explanation: Given, SINK SPEED = 9 fps. Required STROKE in inch = vertical or sink speed = 9 inch.

Discussion

20.	If piston diameter of an oleo system is given by 20 unit then, find the approximate value of typical external diameter of the same oleo system.(a) 26 unit(b) 10 unit(c) 50 unit(d) 200 unitI have been asked this question by my college professor while I was bunking the class.The query is from Landing Gear in portion Landing Gear and Subsystems of Aircraft Design
Answer» RIGHT choice is (a) 26 UNIT Explanation: Approximate value of EXTERNAL diameter can be given by, D = PISTON diameter + 0.3* piston diameter = 20 + 0.3*20 = 26 unit.

Discussion

21.	An oleo is used as shock absorber in an aircraft. Determine at which external diameter we should design oleo if load on the oleo is 100 pounds.(a) 0.4 unit(b) 0.9 unit(c) 2.9 unit(d) 3.4 unitI have been asked this question in an online interview.Enquiry is from Landing Gear in division Landing Gear and Subsystems of Aircraft Design
Answer» Right answer is (a) 0.4 unit To EXPLAIN: DIAMETER of OLEO d = 0.04(length of oleo)^0.5 = 0.04(100)^0.5 = 0.4 unit.

Discussion

22.	Hydraulic system affect conceptual design based on __________(a) hydraulic pump space requirements(b) space for control surface(c) secondary control surface(d) lift required at tailThe question was asked during an interview.The origin of the question is Subsystems topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) hydraulic PUMP space requirements For EXPLANATION: A TYPICAL hydraulic system will affect conceptual DESIGN based on space requirements for PUMPS typically. Control surface are located at the wing or at tail section. Lift required at tail will be affected by which type of airfoil is used.

Discussion

23.	Which of the following is an example of seaplane?(a) Curtiss NC(b) A321 neo(c) Voodoo(d) Cessna 172The question was asked in unit test.I'm obligated to ask this question of Landing Gear and Subsystems in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Right ANSWER is (a) Curtiss NC The explanation is: Curtiss NC is an example of seaplane. A321 neo is a commercial fixed wing aircraft that can only land or TAKEOFF from the airfields. Cessna 172 is a prop aircraft that is not a seaplane.

Discussion

24.	Let’s consider we need to design avionics system for general aviation aircraft. If empty weight of aircraft is 100 unit then what will be the approximate range of required avionics weight.(a) 1 unit to 3 unit(b) 0.3 to 0.5 units(c) 0.58 units(d) 4 to 5 unitsThe question was posed to me in an international level competition.This intriguing question comes from Subsystems topic in division Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) 1 unit to 3 unit For EXPLANATION: Given, empty WEIGHT, W = 100 unit. Typically, RANGE of avionics weight can be ESTIMATED as follows. Avionics weight range = 0.01W to 0.03W = 0.01100 to 0.03100 = 1 unit – 3 unit.

Discussion

25.	Jet fighter aircraft is designed to operate from rough unpaved runway. Find the diameter of wheel if wheel needs to carry weight of 200 unit.(a) 10.23 unit(b) 23.1(c) 34.2 unit(d) 1.023 unitI got this question in a national level competition.I'm obligated to ask this question of Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) 10.23 unit Explanation: Given, ROUGH unpaved RUNWAY, Weight on WHEELS W = 200 unit. Diameter d = 1.59W^0.302 = 1.59200^0.302 = 7.87 unit Now, actual diameter D = d + 0.3d = 7.87 + 0.37.87 = 10.23 unit.

Discussion

26.	Determine the gear load factor if landing weight is 250 unit and average total load during deflection is 550 unit.(a) 2.2(b) 4(c) 4.5(d) 8.9This question was posed to me during an online interview.The doubt is from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Right choice is (a) 2.2 Easy explanation: Load FACTOR is GIVEN by, Load factor N = AVERAGE load/ WEIGHT during LANDING = 550/250 = 2.2.

Discussion

27.	Following diagram represents ______(a) typical fuselage Podded retraction(b) tail tip podded(c) wingtip retraction(d) thrust requiredI have been asked this question at a job interview.This interesting question is from Gear-Retraction Geometry in portion Landing Gear and Subsystems of Aircraft Design
Answer» Right CHOICE is (a) typical fuselage PODDED retraction The explanation: Above diagram is representing the typical layout of fuselage Podded retraction geometry. Here, landing gear will be retracted INSIDE the fuselage section of the AIRCRAFT. Thrust required will be BASED on operating conditions. At cruise, thrust required is equal to drag.

Discussion

28.	For higher landing speed, deadrise angle should be __________(a) higher(b) lower(c) lowest(d) independent of speedI have been asked this question in final exam.The above asked question is from Landing Gear and Subsystems topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» RIGHT OPTION is (a) higher Explanation: Deadrise is defined as the height of V in v shaped bottom. The ANGLE is CALLED deadrise angle. Deadrise angle should increase for higher landing speed. Deadrise angle is increased towards the NOSE of the plane. Deadrise is dependent on speed also.

Discussion

29.	A typical electrical system may include _________(a) generators, transformers, cables, etc(b) only generator(c) drag polar system(d) only transformersI have been asked this question in examination.Question is taken from Subsystems in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) generators, TRANSFORMERS, cables, etc Best explanation: A typical electrical system consists of generators, transformers, cables etc. It is USED to provide electrical energy. DRAG polar is GRAPHICAL representation of drag. It is used to show relationship between drag and lift.

Discussion

30.	Which type of shock absorber is most widely used nowadays?(a) Oleo(b) Signal beam type(c) Aurora beam type(d) Longerons type alwaysI have been asked this question in semester exam.The origin of the question is Landing Gear in section Landing Gear and Subsystems of Aircraft Design
Answer» Right OPTION is (a) Oleo Explanation: Oleo type shock ABSORBER is widely used shock absorber. LONGERONS are structural elements of the aircraft. They are straight and heavy. They are lesser in number and OPPOSES the BENDING.

Discussion

31.	A typical glider will solely rely on tires for shock absorption.(a) True(b) FalseThis question was posed to me by my school principal while I was bunking the class.My question comes from Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» Right answer is (a) True Explanation: Typically, tires can provide some shock ABSORBING characteristics by DEFLECTION. Gliders or SAIL PLANES are built with rigid axles typically. Hence, they solely rely upon the tires for shock absorption. Hence, the CORRECT answer will be true.

Discussion

32.	Which of the following is an example of an aircraft subsystem?(a) Pneumatic(b) Gear retraction(c) Landing gear(d) High lift deviceThe question was asked during an online interview.The doubt is from Subsystems in chapter Landing Gear and Subsystems of Aircraft Design
Answer» RIGHT answer is (a) Pneumatic The EXPLANATION: Pneumatic SYSTEM is an example of aircraft SUBSYSTEM. Gear retraction refers to the method and configuration through which landing gears are RETRACTED in the aircraft. Landing gear are used to withstand impact during landing.

Discussion

33.	Following diagram represents _____________(a) simplified hydraulic system(b) wing loading diagram(c) pneumatic subsystem(d) fuel tank locationThis question was posed to me during an internship interview.The query is from Subsystems topic in section Landing Gear and Subsystems of Aircraft Design
Answer» Right answer is (a) simplified hydraulic system The best explanation: A typical hydraulic system is shown. A simplified hydraulic system can be observed in the diagram. As shown in the diagram a simplified hydraulic system INCLUDES actuators, feed LINES ETC. Fuel tank can be located in fuselage, in WING or in TAIL.

Discussion

34.	What is seaplane?(a) Plane which can land and takeoff from the water(b) Plane which can only land on water(c) Plane which can only took off from water(d) Seaplane is always same as any other plane in terms of landing and takeoff locationI had been asked this question in homework.My enquiry is from Landing Gear and Subsystems in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Right ANSWER is (a) Plane which can land and TAKEOFF from the water To explain: Typical definition of a seaplane is as FOLLOWS: plane which takes off from water and lands on water is known as a seaplane. Seaplanes are capable of landing and takeoff from water. Seaplanes are not necessarily same as other TYPES of aircrafts.

Discussion

35.	Following diagram represents ______(a) in the fuselage gear retraction(b) in wing retraction(c) retraction in cockpit(d) headroomThe question was asked during an interview.This intriguing question originated from Gear-Retraction Geometry topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Correct answer is (a) in the fuselage GEAR retraction For explanation: Typical gear retraction in the Fuselage is shown in the above DIAGRAM. It is SIMILAR to in the WING retraction geometry with difference being in the LOCATION of retraction. Here, gear will be retracted in the fuselage itself. Headroom is related to passenger cabin.

Discussion

36.	Following diagram represents _________(a) wheel diameter for braking(b) lift curve(c) drag curve slope(d) drag polarThe question was asked in class test.My enquiry is from Landing Gear in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT choice is (a) wheel diameter for BRAKING Easy explanation: Above FIGURE is used for initial and statistical estimation of required wheel rim diameter. This estimation is based on kinetic energy absorption at the time of braking. Lift CURVE represents relationship between lift and AOA.

Discussion

37.	If tire pressure is 25 psi then, determine minimum dynamic hydroplaning speed.(a) 45 knots(b) 25 psi(c) 369 knot(d) 25 knotsThis question was posed to me in an interview for internship.My enquiry is from Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) 45 knots The explanation is: Given, tire PRESSURE P = 25 psi Minimum DYNAMIC hydroplaning speed V can be estimated by using, V = 9p^0.5 = 925^0.5 = 9*5 = 45 knots.

Discussion

38.	If a tire has diameter of 18 in and rolling radius of 6 in then, what will be the approximate value of stroke of the tire?(a) 3 in(b) 4 in(c) 5 in(d) 8 inI got this question in examination.This intriguing question comes from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT option is (a) 3 in The explanation: STROKE = (diameter/2) – rolling radius = (18/2) – 6 = 9 – 6 = 3 in.

Discussion

39.	Following diagram represents ___________(a) sliding pivot mechanism(b) lift augmentation(c) thrust augmentation(d) drag polarI had been asked this question in class test.My question is taken from Gear-Retraction Geometry topic in section Landing Gear and Subsystems of Aircraft Design
Answer» Correct ANSWER is (a) sliding pivot MECHANISM To explain: The above FIGURE is illustrating a typical sliding pivot mechanism. It is different from the typical four bar linkage system. Lift augmentation is used to INCREASE lift. Thrust can be increased by thrust augmentation. Drag POLAR is graph showing relationship between drag and lift.

Discussion

40.	A seaplane has beam of 5 unit then, estimate the step size required for given seaplane.(a) 0.25 unit(b) 9 unit(c) 1.2 unit(d) 4.6 unitThe question was asked in an interview for job.My query is from Landing Gear and Subsystems topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Right OPTION is (a) 0.25 UNIT To explain: Approximate value of step SIZE = 0.05BEAM = 0.055 = 0.25 unit.

Discussion

41.	Most of the sea plane is designed with _________(a) v shaped bottom(b) h bottom(c) v shaped bottom only(d) flat bottom onlyThis question was addressed to me by my school teacher while I was bunking the class.This intriguing question comes from Landing Gear and Subsystems topic in division Landing Gear and Subsystems of Aircraft Design
Answer» The correct choice is (a) v shaped BOTTOM Easiest explanation: Most of the seaplanes are DESIGNED with V shaped bottom. The V shaped bottom can be used to REDUCE the water impact Loads. HOWEVER, few seaplanes were built with flat bottoms also. Hence, correct option will be v shaped bottom.

Discussion

42.	Pivot point is defined as?(a) The point at which the landing gear leg is attached to the aircraft(b) The point at which thrust forces is acting(c) The point with maximum lift to drag(d) CG of only quadric cycle gearI had been asked this question in an online interview.The query is from Gear-Retraction Geometry in portion Landing Gear and Subsystems of Aircraft Design
Answer» Right choice is (a) The point at which the LANDING gear LEG is attached to the aircraft For EXPLANATION: The point at which landing gear or undercarriage leg is attached to the aircraft is known as pivot point. This pivot point can be located anywhere ALONG the normal bisector to the line joining the up and down wheel positions. Lift to drag will be maximum at thrust required minimum.

Discussion

43.	What is the following is correct?(a) Quadricycle landing gear arrangement requires Flat takeoff attitude(b) Lift is always same as weight(c) Drag is always higher than weight(d) Thrust loading is weight to lift ratioThe question was asked in exam.This interesting question is from Landing Gear Arrangements topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» Right CHOICE is (a) QUADRICYCLE landing gear arrangement requires Flat takeoff attitude For explanation I would say: Quadricycle landing gear arrangement requires flat attitude for takeoff and landing. It is similar to bicycle arrangement. LIFT is not ALWAYS same as weight. THRUST loading is ratio of thrust to weight.

Discussion

44.	Evaluate width of the wheel if weight carried by it is 200 unit. Consider general aviation aircraft.(a) 3.73 unit(b) 9 unit(c) 7 unit(d) 9/7 unitThe question was asked in a job interview.This question is from Landing Gear in section Landing Gear and Subsystems of Aircraft Design
Answer» Correct answer is (a) 3.73 unit The EXPLANATION is: GIVEN, Weight W = 200 unit WIDTH of general AVIATION is given by, Width w = 0.715W^0.312 = 0.715200^0.312 = 3.73 unit.

Discussion

45.	Following diagram represents ______(a) in the wing gear retraction(b) cockpit(c) cargo containers(d) tail PoddedI have been asked this question by my school principal while I was bunking the class.My doubt is from Gear-Retraction Geometry topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct option is (a) in the WING gear retraction Easy explanation: As shown in FIGURE, a typical gear retraction geometry is shown. As shown in the figure, gear is retracted inside the wing. Hence, it is called in the wing retraction geometry. Cockpit is FRONT section of an aircraft through where PILOT controls the aircraft.

Discussion

46.	None of the seaplanes can ever land on airfields.(a) True(b) FalseI have been asked this question in exam.The doubt is from Landing Gear and Subsystems in section Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) True The explanation is: There are some seaplanes which are able to LAND on AIRFIELDS. These are more broadly known as amphibious AIRCRAFT. They are designed in such way that they can land and TAKEOFF through both water and land. Hence, given statement is not correct. Therefore, the answer will be ‘ false’.

Discussion

47.	A pneumatic subsystem is used to ______________(a) provide compressed air for pressurization(b) more pressure output(c) deflect control surface(d) provide electrical powerI have been asked this question in an interview.Question is from Subsystems in portion Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT answer is (a) provide compressed air for pressurization To explain: A typical PNEUMATIC system is used for OPERATION requiring less AMOUNT of power or pressure. It is used to provide compressed air for pressurization of the aircraft. More pressure OUTPUT can be achieved by using hydraulic system.

Discussion

48.	APU exhaust should be directed upward.(a) True(b) FalseI had been asked this question during an internship interview.My question is based upon Subsystems in division Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) True Easiest explanation: Typically, APU is nothing but another JET engine that requires its own INLET and outlet. An APU is used to provide ground power. Exhaust from the APU should be directed upward is true. This is DONE in order to REDUCE the amount of noise produced by inlet and exhaust.

Discussion

49.	Following diagram represents ________(a) quadricycle(b) tail pusher(c) tail dragger(d) bicycleThe question was asked in an online interview.I'd like to ask this question from Landing Gear Arrangements topic in section Landing Gear and Subsystems of Aircraft Design
Answer» Right ANSWER is (a) quadricycle Explanation: Typical quadricycle LANDING gear arrangement is shown in the above diagram. As shown in the diagram, quadricycle landing gear arrangement has 4 landing gears. It is similar to BICYCLE but WHEELS are at sides of the fuselage.

Discussion

50.	The term marked by ‘?’ in the following diagram is called __________(a) Overturn angle(b) Overnose angle(c) Grazing angle(d) AOAI got this question by my school principal while I was bunking the class.The above asked question is from Landing Gear Arrangements in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT answer is (a) OVERTURN angle Easy explanation: The term marked is CALLED overturn angle. It is measure of the tendency to overturn during taxied around sharp corner. For typical aircrafts this should not be more than 63°. AOA is angle between relative freestream VELOCITY and CHORD.

Discussion

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Following diagram represents _________(a) multi bogey(b) pusher prop(c) wing(d) bicycleI have been asked this question in an online quiz.My question comes from Landing Gear Arrangements in portion Landing Gear and Subsystems of Aircraft Design

What is the location of main wheel in tricycle gear?(a) After CG of the aircraft(b) At CG(c) Before CG(d) At noseThis question was posed to me during an interview for a job.The above asked question is from Landing Gear Arrangements in section Landing Gear and Subsystems of Aircraft Design

Following diagram represents _________(a) tail dragger(b) bicycle(c) tricycle(d) single mainThe question was asked in an interview.Query is from Landing Gear Arrangements in section Landing Gear and Subsystems of Aircraft Design

We should always use tail dragger arrangement for every aircraft.(a) True(b) FalseThis question was addressed to me in semester exam.My question is based upon Landing Gear Arrangements topic in chapter Landing Gear and Subsystems of Aircraft Design

Following diagram represents ______(a) gear retraction geometry(b) in cockpit(c) gear load chart(d) drag polarThis question was addressed to me during an online exam.Origin of the question is Gear-Retraction Geometry in section Landing Gear and Subsystems of Aircraft Design

If an aircraft has sink speed at touchdown as 9 ft/s then, find the stroke in inches approximately.(a) 9 in(b) 19 in(c) 1 in(d) 2 inThe question was posed to me in an international level competition.Query is from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design

Which of the following is an example of seaplane?(a) Curtiss NC(b) A321 neo(c) Voodoo(d) Cessna 172The question was asked in unit test.I'm obligated to ask this question of Landing Gear and Subsystems in chapter Landing Gear and Subsystems of Aircraft Design

Determine the gear load factor if landing weight is 250 unit and average total load during deflection is 550 unit.(a) 2.2(b) 4(c) 4.5(d) 8.9This question was posed to me during an online interview.The doubt is from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design

For higher landing speed, deadrise angle should be __________(a) higher(b) lower(c) lowest(d) independent of speedI have been asked this question in final exam.The above asked question is from Landing Gear and Subsystems topic in portion Landing Gear and Subsystems of Aircraft Design

A typical electrical system may include _________(a) generators, transformers, cables, etc(b) only generator(c) drag polar system(d) only transformersI have been asked this question in examination.Question is taken from Subsystems in chapter Landing Gear and Subsystems of Aircraft Design

Which type of shock absorber is most widely used nowadays?(a) Oleo(b) Signal beam type(c) Aurora beam type(d) Longerons type alwaysI have been asked this question in semester exam.The origin of the question is Landing Gear in section Landing Gear and Subsystems of Aircraft Design

A typical glider will solely rely on tires for shock absorption.(a) True(b) FalseThis question was posed to me by my school principal while I was bunking the class.My question comes from Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design

Which of the following is an example of an aircraft subsystem?(a) Pneumatic(b) Gear retraction(c) Landing gear(d) High lift deviceThe question was asked during an online interview.The doubt is from Subsystems in chapter Landing Gear and Subsystems of Aircraft Design

Following diagram represents _____________(a) simplified hydraulic system(b) wing loading diagram(c) pneumatic subsystem(d) fuel tank locationThis question was posed to me during an internship interview.The query is from Subsystems topic in section Landing Gear and Subsystems of Aircraft Design

Following diagram represents _________(a) wheel diameter for braking(b) lift curve(c) drag curve slope(d) drag polarThe question was asked in class test.My enquiry is from Landing Gear in chapter Landing Gear and Subsystems of Aircraft Design

If tire pressure is 25 psi then, determine minimum dynamic hydroplaning speed.(a) 45 knots(b) 25 psi(c) 369 knot(d) 25 knotsThis question was posed to me in an interview for internship.My enquiry is from Landing Gear topic in portion Landing Gear and Subsystems of Aircraft Design

Following diagram represents ___________(a) sliding pivot mechanism(b) lift augmentation(c) thrust augmentation(d) drag polarI had been asked this question in class test.My question is taken from Gear-Retraction Geometry topic in section Landing Gear and Subsystems of Aircraft Design

A seaplane has beam of 5 unit then, estimate the step size required for given seaplane.(a) 0.25 unit(b) 9 unit(c) 1.2 unit(d) 4.6 unitThe question was asked in an interview for job.My query is from Landing Gear and Subsystems topic in division Landing Gear and Subsystems of Aircraft Design

Evaluate width of the wheel if weight carried by it is 200 unit. Consider general aviation aircraft.(a) 3.73 unit(b) 9 unit(c) 7 unit(d) 9/7 unitThe question was asked in a job interview.This question is from Landing Gear in section Landing Gear and Subsystems of Aircraft Design

None of the seaplanes can ever land on airfields.(a) True(b) FalseI have been asked this question in exam.The doubt is from Landing Gear and Subsystems in section Landing Gear and Subsystems of Aircraft Design

APU exhaust should be directed upward.(a) True(b) FalseI had been asked this question during an internship interview.My question is based upon Subsystems in division Landing Gear and Subsystems of Aircraft Design

Following diagram represents ________(a) quadricycle(b) tail pusher(c) tail dragger(d) bicycleThe question was asked in an online interview.I'd like to ask this question from Landing Gear Arrangements topic in section Landing Gear and Subsystems of Aircraft Design