74 + Interview Questions in Landing Gear And Subsystems in Aircraft Design Page 2 InterviewSolution

51.	A twin business engine is designed in such way that the load of 250 unit is carried out by the tire. Find the appropriate ratio of the diameter to the width of main wheel.(a) 3.8(b) 2.13(c) 5.6(d) 9.8I have been asked this question by my college professor while I was bunking the class.I would like to ask this question from Landing Gear in portion Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT ANSWER is (a) 3.8 For explanation I WOULD say: Given, twin business jet, LOAD W = 250 unit. Ratio of diameter to width D / w = 2.299W^0.091 = 2.299250^0.091 = 3.8.

Discussion

52.	A bomber aircraft has following data. Weight on wheel is 80 unit. Calculate the width of main wheel.(a) 0.8546(b) 3.45(c) 6.78(d) 0.2345I got this question in final exam.Origin of the question is Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT ANSWER is (a) 0.8546 To elaborate: For bomber, weight W = 80 unit. Width of MAIN wheel d = 0.1043W^0.48 = 0.104380^0.48 = 0.8546 unit.

Discussion

53.	Following diagram represents ______(a) gear retraction geometry in the nacelle(b) gear retraction in fuselage(c) gear retraction in wing fuselage junction(d) gear retraction at wing tipThe question was asked in an online quiz.Origin of the question is Gear-Retraction Geometry topic in section Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) gear retraction geometry in the nacelle To elaborate: Typical, gear retraction inside the nacelle is shown in the diagram. This type of arrangement can be SEEN in EARLY PROP aircraft. Gear retraction in FUSELAGE or WING fuselage junction are nearly similar to each other.

Discussion

54.	Determine weight carried by wheel if inflation pressure is 100 psi and footprint area is 80 inch^2.(a) 8000 lb force(b) 900(c) 200 lb of force(d) 120This question was addressed to me in my homework.Asked question is from Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct OPTION is (a) 8000 lb FORCE Explanation: Given, inflation pressure P = 100 psi, AREA a = 80 in^2. Weight W = Pa = 10080 = 8000 lb of force.

Discussion

55.	Following diagram represents ______(a) wing podded retraction(b) fuselage podded retraction(c) lift curve(d) tail plane retractionThe question was posed to me in my homework.This interesting question is from Gear-Retraction Geometry in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Correct ANSWER is (a) wing podded retraction To elaborate: A typical wing podded GEAR retraction is shown in the diagram. Fuselage Podded will not be retracted INSIDE wing. Lift curve is used to represent relationship between lift and ANGLE of attack. Lift curve is very IMPORTANT parameter.

Discussion

56.	Which of the following is disadvantage of tail dragger?(a) Inherent unstable(b) Most stable(c) Inherent stable(d) It has 4 wheels to support the aircraftThis question was posed to me during an interview.This key question is from Landing Gear Arrangements in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct option is (a) Inherent unstable The BEST explanation: Tail dragger arrangement consists total of 3 wheels: 2 main and 1 auxiliary. Tail dragger arrangement is inherently Unstable. Tail dragger arrangement PROVIDES more PROPELLER clearance and it is lighter in WEIGHT.

Discussion

57.	Following diagram represents __________(a) typical seaplane geometry(b) schematic diagram of F16(c) mig29 design(d) typical aerostatsThis question was posed to me during an internship interview.This question is from Landing Gear and Subsystems in section Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) typical seaplane GEOMETRY Explanation: A typical seaplane geometry is shown in the diagram. A seaplane is unique kind of plane which is capable of takeoff and land through WATER. F16 and Mig21 are fighter aircraft and are not SEAPLANES. Aerostats is different type of aircraft.

Discussion

58.	An aircraft is supported by bicycle landing gear arrangement. If wheel base is 10 unit then, scale location of CG.(a) 5 unit aft from front wheel(b) 10 unit(c) 20 unit from front wheel(d) 25 unit from back wheelI have been asked this question in an interview.I'm obligated to ask this question of Landing Gear Arrangements topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT ANSWER is (a) 5 unit aft from front WHEEL The explanation is: Typically, for bicycle landing gear CG is aft of the midpoint between TWO wheels measured from front wheel. Hence, LOCATION of CG = distance/2 = 10/2 = 5 unit aft from front wheel.

Discussion

59.	Typically, seaplanes can be categorized as ______________(a) floatplanes, flying boat, etc(b) floatplanes only(c) flying boat only(d) aerostats onlyI had been asked this question in an internship interview.The origin of the question is Landing Gear and Subsystems in portion Landing Gear and Subsystems of Aircraft Design
Answer» Right option is (a) floatplanes, flying boat, etc Easy explanation: Typically, seaplanes can be divided as FOLLOWS: Floatplanes, flying boat etc. Aerostats are TYPE of aircraft. Aerostats are driven based on buoyancy. They are lighter than air VEHICLE. TYPICAL seaplanes are CATEGORIZED as heavier than air vehicle.

Discussion

60.	Which of the following is considered to be correct subsystem to deflect control surface?(a) Hydraulic system(b) Pneumatic subsystem(c) Fuel system(d) Deice systemThe question was asked in an interview.Query is from Subsystems topic in portion Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT CHOICE is (a) HYDRAULIC system To explain: Hydraulic subsystem will be correct choice for control surface DEFLECTION. Pneumatic subsystem is used for low power or pressure requirements. Fuel system includes fuel TANKS, fuel lines etc.

Discussion

61.	Avionics stands for __________(a) aviation electronics(b) airfare electrons(c) aviation electrical(d) prop aircraftI have been asked this question at a job interview.My question comes from Subsystems topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» The correct answer is (a) aviation electronics Explanation: Avionics SYSTEM stands for Aviation electronics. A typical avionics system include radar, radio, flight INSTRUMENTS, flight CONTROL computer etc. It is required to consider sufficient VOLUME for avionics system. Prop aircraft consists of a propeller and other primary segments.

Discussion

62.	A general aviation aircraft has impact Weight on wheel about 100 unit. Find the required diameter.(a) 7.53 unit(b) 9.753 unit(c) 10.98 unit(d) 11 unitI have been asked this question in a job interview.This intriguing question originated from Landing Gear in chapter Landing Gear and Subsystems of Aircraft Design
Answer» RIGHT answer is (a) 7.53 unit Best explanation: GIVEN, Weight on wheel W = 100 unit. For, general AVIATION aircraft Diameter D = 1.51W0.349 = 1.51100^0.349 = 7.53 unit.

Discussion

63.	Following diagram represents _________(a) single main landing gear arrangement(b) wing lofting(c) empennage section(d) thrust loading chartI had been asked this question in an interview for job.I'd like to ask this question from Landing Gear Arrangements in portion Landing Gear and Subsystems of Aircraft Design
Answer» Correct option is (a) single main landing GEAR arrangement Easiest explanation: Above diagram is SHOWING typical single main landing gear arrangement. Lofting is used to generate overall wing shape via conic lofting method. Empennage is tail portion of the aircraft. THRUST LOADING is defined as thrust to weight ratio.

Discussion

64.	If a seaplane needs to be designed then, which of the following could be considered as an application of the seaplane?(a) Search and rescue mission(b) Can be operated for every wave size in sea(c) Low value of wing loading(d) Ratio of weight to reference area is minimum among the other types of aircraftI got this question in homework.My question comes from Landing Gear and Subsystems in portion Landing Gear and Subsystems of Aircraft Design
Answer» CORRECT option is (a) Search and rescue mission The EXPLANATION is: A typical seaplane can land and takeoff through water only. If we were given the task to design a seaplane then, one of the most applicable use of such plane would be for search and rescue. In fact, SEAPLANES are being used for such tasks. However, seaplanes cannot be used for every SIZE of WAVE.

Discussion

65.	Following diagram represents ____________(a) simple oleo schematic(b) drag polar(c) wheel base distance only(d) wheel track onlyThe question was asked in exam.My question is from Landing Gear topic in section Landing Gear and Subsystems of Aircraft Design
Answer» The correct option is (a) simple oleo schematic The BEST I can explain: A typical oleo mechanism is shown in the diagram. Simple oleo system has been ILLUSTRATED in the figure. Drag polar is graphical representation of drag characteristics. Wheel track and base DISTANCE are related to wheel terminology not to shock absorber.

Discussion

66.	Typically, an aircraft weighing lower than 50000 lb will adopt __________(a) single main gear(b) bicycle(c) tail dragger(d) tricycleThe question was asked in examination.I'm obligated to ask this question of Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Right option is (a) single MAIN gear The best explanation: Given, WEIGHT W = 50000 LB. If weight w < 50000 lb then, the single main LANDING gear arrangement is used. Other arrangements are used if weight w is > 50000 lb.

Discussion

67.	What is the function of the undercarriage?(a) To absorb the shock during landing(b) To provide lift(c) To increase lift at landing(d) To carry cargo at airportThis question was addressed to me by my college director while I was bunking the class.My doubt is from Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Correct ANSWER is (a) To absorb the shock during LANDING Easy explanation: Undercarriage should absorb the shock or impact during landing and make ride smooth during taxiing. Lift is primarily generated by wings. Lift can be INCREASED by high lift devices. Cargo container is used to CARRY cargo.

Discussion

68.	Stroke of a shock absorber is defined as _________(a) required deflection of the shock absorbing system(b) lift required at takeoff(c) length of crank shaft of engine(d) piston distance travelled inside engineI had been asked this question by my school principal while I was bunking the class.I need to ask this question from Landing Gear topic in division Landing Gear and Subsystems of Aircraft Design
Answer» Right answer is (a) REQUIRED deflection of the shock absorbing SYSTEM Easy explanation: Stroke of ABSORBER can be defined as the required deflection of the shock absorbing system. Stroke of the shock absorber DEPENDS upon NUMBER of factors such as shock absorbing material etc. Lift required at takeoff will be more than its weight.

Discussion

69.	Following diagram represents _________(a) tricycle(b) bicycle(c) quadric cycle(d) tail pusherI got this question in an internship interview.My question is based upon Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design
Answer» RIGHT option is (a) tricycle Explanation: Typical tricycle landing gear arrangement is SHOWN in the above diagram. As shown in the diagram, two MAIN landing gears are located after the c.g. It has an auxiliary THIRD wheel which is placed forward of the centre of GRAVITY.

Discussion

70.	Only dynamic loading should be used for determining the nose wheel tire sizing.(a) True(b) FalseThis question was addressed to me during an interview for a job.The above asked question is from Landing Gear in portion Landing Gear and Subsystems of Aircraft Design
Answer» The correct option is (b) False Explanation: Tires selection is done by FINDING the smallest tire which can carry the CALCULATED maximum loads. Both static and dynamic LOADING should be used to EVALUATE size of nose wheel tire.

Discussion

71.	An aircraft has weight of 300N at the time of landing. Calculate braking K.E. if stall speed is 10 m/s.(a) 1.529 KJ(b) 156 KJ(c) 23 KJ(d) 23.45 KJI got this question in an interview.Enquiry is from Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Correct option is (a) 1.529 KJ Easiest explanation: GIVEN, Weight W = 300N, stall SPEED v = 10 m/s Braking K.E. = 0.5Wv^2 / g = 0.530010^2 / 9.81 = 1.529 KJ.

Discussion

72.	Stroke depends on ___________(a) vertical velocity at touchdown(b) vertical velocity at climb(c) rate of climb(d) lift by wing at cruiseI have been asked this question by my school teacher while I was bunking the class.My doubt stems from Landing Gear in division Landing Gear and Subsystems of Aircraft Design
Answer» The CORRECT choice is (a) vertical velocity at touchdown Explanation: Stroke is defined as the amount of deflection required by SHOCK absorbing system. Deflection required by shock absorber depends upon number of parameters. For example, vertical velocity at touchdown is ONE of the IMPORTANT factor affecting the stroke of the shock absorber. Lift at cruise will be same as WEIGHT at cruise.

Discussion

73.	The hull of seaplane is based on the planning-hull concept.(a) True(b) FalseThis question was addressed to me during an interview for a job.I'd like to ask this question from Landing Gear and Subsystems in chapter Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) True To explain I would say: Hull SIZING is one of the important factor in seaplane design. The seaplane hull and pontoon of float PLANE are based on the planning-hull concept. Typically, BOTTOM is fairly FLAT. This allows the aircraft to skim on the water.

Discussion

74.	Following diagram represents _________(a) Typical APU system at tail(b) Hydraulic system(c) Thrust augmentation(d) Fuel systemI have been asked this question in unit test.My question is based upon Subsystems in division Landing Gear and Subsystems of Aircraft Design
Answer» Correct choice is (a) Typical APU SYSTEM at tail Easiest explanation: APU is an example of subsystem of aircraft. HYDRAULIC system is used for higher output power. THRUST augmentation is used to increase the AMOUNT Thrust. Thrust augmentation can be used for short takeoff distance.

Discussion

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A bomber aircraft has following data. Weight on wheel is 80 unit. Calculate the width of main wheel.(a) 0.8546(b) 3.45(c) 6.78(d) 0.2345I got this question in final exam.Origin of the question is Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design

Determine weight carried by wheel if inflation pressure is 100 psi and footprint area is 80 inch^2.(a) 8000 lb force(b) 900(c) 200 lb of force(d) 120This question was addressed to me in my homework.Asked question is from Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design

Following diagram represents ______(a) wing podded retraction(b) fuselage podded retraction(c) lift curve(d) tail plane retractionThe question was posed to me in my homework.This interesting question is from Gear-Retraction Geometry in chapter Landing Gear and Subsystems of Aircraft Design

Which of the following is considered to be correct subsystem to deflect control surface?(a) Hydraulic system(b) Pneumatic subsystem(c) Fuel system(d) Deice systemThe question was asked in an interview.Query is from Subsystems topic in portion Landing Gear and Subsystems of Aircraft Design

Avionics stands for __________(a) aviation electronics(b) airfare electrons(c) aviation electrical(d) prop aircraftI have been asked this question at a job interview.My question comes from Subsystems topic in chapter Landing Gear and Subsystems of Aircraft Design

Following diagram represents ____________(a) simple oleo schematic(b) drag polar(c) wheel base distance only(d) wheel track onlyThe question was asked in exam.My question is from Landing Gear topic in section Landing Gear and Subsystems of Aircraft Design

Typically, an aircraft weighing lower than 50000 lb will adopt __________(a) single main gear(b) bicycle(c) tail dragger(d) tricycleThe question was asked in examination.I'm obligated to ask this question of Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design

Following diagram represents _________(a) tricycle(b) bicycle(c) quadric cycle(d) tail pusherI got this question in an internship interview.My question is based upon Landing Gear Arrangements topic in division Landing Gear and Subsystems of Aircraft Design

Only dynamic loading should be used for determining the nose wheel tire sizing.(a) True(b) FalseThis question was addressed to me during an interview for a job.The above asked question is from Landing Gear in portion Landing Gear and Subsystems of Aircraft Design

An aircraft has weight of 300N at the time of landing. Calculate braking K.E. if stall speed is 10 m/s.(a) 1.529 KJ(b) 156 KJ(c) 23 KJ(d) 23.45 KJI got this question in an interview.Enquiry is from Landing Gear topic in chapter Landing Gear and Subsystems of Aircraft Design

The hull of seaplane is based on the planning-hull concept.(a) True(b) FalseThis question was addressed to me during an interview for a job.I'd like to ask this question from Landing Gear and Subsystems in chapter Landing Gear and Subsystems of Aircraft Design

Following diagram represents _________(a) Typical APU system at tail(b) Hydraulic system(c) Thrust augmentation(d) Fuel systemI have been asked this question in unit test.My question is based upon Subsystems in division Landing Gear and Subsystems of Aircraft Design