SOP QUESTION BANK

FILL IN THE BLANKS

1. In Variometer additional LCD is provided to indicate flight time which starts

registering when speed exceeds 36 Kts for more than 05 seconds.

2. EGT warning is also displayed when engine is OFF.

3. In GPS Flight plan mode comprises of 50 – 300 way points and can log at
least 30 most recent flights.

4. Headwinds shorten take off and landing length required by 8 mtrs for every 3
Kts / 5 Kmph of increase in wind speed.

5. Max load per seat 110 Kgs.

6. Max -ve ‘G’ - 2 G

7. Torque 103 Nm (75.9 foot pounds) at 4800 RPM

8. EGT Normal 650 deg C – 885 deg C

9. Max difference in magneto Drop 115

10. Minimum Sink Rate Flaps 15° 460 feet per minute (2.3 m/sec)

11. Best L/D ratio Flaps 15° 17: 1

12. Max Speed V FE 25 (Flaps 25°) 55 Knots

13. Form – 700 completed in all respects and closed / signed before flying.

14. During Cockpit Pre-flight Inspection Main wing spar for connection, bolts &
nuts in position.

15. During inspection of Nose tyre for cuts, cracks and creep.

16. During warm up Engine throttle to be set to 2500, till oil temperature reaches
50 deg C

17. During Magneto drop check Select Left magneto switch off, note drop in RPM,
call out drop, not more than 300.

18. During taxy check RT permission from ATC for taxy.

19. During taxy check brake serviceability will be checked every 200 metres.

20. After takeoff Height 300 ft, speed 70 knots, select flaps to Flaps 0 position.
21. During switch off procedure Allow engine to cool down for 01 minute.

22 Fuel system comprises a vented fuselage fuel tank.

23. Fuel tank is located inside the fuselage with a Fuel shut off valve inside the
cockpit.

24. Draining of water / particles is achieved through draining contents of

Gascolator, located below the bottom Engine cowling.

25. Normal flight operation, mechanical fuel pump provides adequate fuel
pressure.

26. Surplus oil from lubrication points accumulates at the bottom of Crank case

27. The AC (Alternating Current) from the alternator is provided to a 12 Volt

Busbar through a Regulator Rectifier.

28. Instrument System is fitted with Digital / Analogue gauges for Airspeed,
Altitude,RPM and Vertical speed indications.

29. Communication & Navigation System includes a modern light weight radio
unit name XCOM VHF 760 Transreceiver

30. Variometer combines indication of Vertical speed in both meters per second
and feet per minute on analogue display and only in feet per minute on
digital LCD.

31. Soft grass runways (unpaved) tend to increase take off performance data by
20 %.

32. Wing surface area 9.29 Sq metres

33. Tested min safety factor 1.875.

34. Carryout weekly check for water contamination in fuel and especially for
aircrafts on ground for prolonged period.

35 The elevator and horizontal stabiliser area is 1.08sqmtr.

36 Cruise speed of aircraft 112knot.

37 The brake lever is located on central console in cockpit.

38 Minimum combined cockpit crew weight is 55 kg.

39 Recommended max RPM on ground is 5800.

40 In case of battery failure engine will continue to function, but restart will not
be possible.

41 The parachute and rocket system is installed behind right seat for emergency
rescue and its activation handle is located at overhead between both pilot.

42 The min sink rate is at 58knot.

43 Propeller is a two blade fixed pitch design, with propeller diameter of 1650
mm.

44. Maximum wind speed for parking outdoors without tie down is 15 Kts.

45 Normal circuit for Virus SW 80 aircraft shall be flown at 700 Feet AGL at a
speed of 70-75 KTS.
46 Battery is capable of operation within a temperature range of.-30 to
60.Celsius

47 In communication system The display also provides for low battery alert for
under voltage 10.5 and over voltage14.5volt.

47 GPS is Equipped with a lithium ion battery that lasts up to 5 hour.

48 Alternator gives 250 watt at 5500 RPM.

49 Wing Span of Aircraft is .10.5 m.

50 The aircraft ships with H type safety belts attached to the fuselage at three
mounting points.

51 Cockpit windshields, doors and overhead windows are transparent surfaces,

made of 2 mm anti uv GE tinted Lexan.

52 The engine is equipped with DRY sump forced Lubrication.

53 During flutter increase angle of attack and reduce throttle immediately.

54 Minimum height to commence the manoeuvre of stall is 1500 ft AGL.

55 Firewall is reinforced by heat and noise insulation using glass-flame

retardant sandwich.

56 Maximum operating altitude of battery is 5000 m.

57 Wheel track of Aircraft is 1.6 M.

58 The aircraft ships with H type safety belts attached to the fuselage at three
mounting points.
59 Metal parts used in the aircraft include tubes, sheet metal, rods, cable bolts
and nuts.

60 Cockpit windshields, doors and overhead windows are transparent surfaces,

made of 2 mm anti UV GE tinted Lexan.

61 Rate of fuel flow is calculated from .RPM..........and......Manifold Pr

Measurements.

62 Coolant flow for cooling cylinder heads is forced by

a.Engine/Camshaft..driven water pump, from radiator to cylinder heads.

63. Minimum height to commence the manoeuvre of stall is ...1500. ft AGL.

64. The speed indication turns red when speed exceeds 135 knots and starts to
pulse / blink when speed drops below 40 knots.

65. In communication system The display also provides for low battery alert for
under voltage 10.5 volt DC-and over voltage ---14.5 volt DC.

66. The engine is equipped with Dry Sump Forced Lubrication.

67. Oil after lubricating the engine is cooled by passing through a radiator.

68. Coolant temperature is displayed in deg Celsius.

69. Aspect ratio of aircraft (Virus) 11.8

70. Best Lift/Drag Ratio of Virus at Flap 15 Deg 17:1

71 During flutter increase angle of attack and reduce throttle immediately

72. The gear box provides a reduction ratio of 1: 2.27.

73 The engine power plant features Ram Air Cooled Cylinders, Liquid (Water)
Cooled Cylinder Heads and Oil Cooled moving parts.

74 Firewall is reinforced by heat and noise insulation using glass-flame

retardant sandwich.

75 Maximum wind speed for parking outdoors without tie down is 15 Kts.

76. Normal circuit for Virus SW 80 aircraft shall be flown at 700 AGL at a speed of
70 to 75 kts.
77. Draining of water / particles is achieved through draining contents of
Gascolator located below the bottom engine cowling.

78. Surplus oil from lubrication points accumulates at the bottom of Crankcase
and is forced back to oil tank by blow by gases.
79. Cooling system is designed for liquid cooling of cylinder heads and ram air
cooling of cylinders.

80. Fuel hoses are protected with glass and silicon rubber.

81. Maximum operating altitude of battery is 5000 metres.

82. RPM display turns red when engine RPM is above 5800.

83. Manifold Pressure (MAP) displayed in millimeter of Hg unit.

84. Tailwinds extend take off and landing length required by 18 – 28 mtrs for
every 3 Kts / 5 Kmph of increase in wind speed.

85. Vertical Fin Area 1.10 Sq metres

86. Max Ldg weight (MLW) 472.5 Kgs

87 Stall Speed Vs (Clean / Flaps Up) 43 Knots

88. Best Climb rate at 100 Kts 800 feet per minute (4.0 m/sec)

89. Max Speed VFE 25 (Flap 25°) 55 knots.

90. Engine warm up throttle to be set to 2500 rpm, till oil temperature reaches 50
deg C.

91. During taxying brake serviceability checked every 200 metres.

92. Flutter is defined as oscillation of control surfaces.

93. The undercarriage of Virus SW 80 is a robust tricycle type.

94. The wing span of Virus SW 80 is 10.5 Meter.
95. In case of battery failure, engine will continue to function, but restart will not
be possible.

96. Difference in magneto drop check is 115 maximum.

97. Engine cam shaft driven oil pump sucks engine oil from the oil tank and
forces it through oil filter to individual lubrication points.

98. Surplus oil from lubrication points accumulates at the bottom of crank case
and is forced back to oil tank blow by gases.

99 The cylinder heads of Rotax 912A is cooled by liquid water

101 Pitot tube is attached to bottom side of the right wing.
102 The propeller is driven via gearbox with integrated mechanical shock absorber
and overload clutch.
103 The fuel tank is located inside the fuselage with a fuel shut off valve inside
the cockpit.
104 Virus Microlite ac is powered by a single ROTAX 912 A, 4 cylinder
horizontally opposed 4 stroke Engine.
105 The coolant flow for cooling cylinder heads is forced by a cam shaft driven
water pump.
106 The magneto switches are of toggle type.
107 The battery of Virus SW 80 is of Lithium Phosphate (dry) type.
108. The operation range of battery is from -30 deg C to +60 deg celcius.
109. Cockpit also accommodates a wheel brake lever that controls main 38.
undercarriage brakes hydraulically.

110 Elevator trim is electrical, driving a spring mechanism through a common

switch, to reduce stick load.

111 A parachute and rocket system is installed behind right seat for emergency
rescue and its activation handle is located overhead between both pilots.

112 Nose undercarriage has a spring type shock absorber and a steerable nose
wheel.

113 The flaps offer 3 position settings viz., Position 0 (Bottom most) for fully
retracted, Position 1 (middle) for 15 degrees extended and Position 2(top) for
25 extended.

114 Minimum Sink Rate Flaps 15° is 460 feet per minute.
115 Landing roll at MTOW (SL) is 410 feet
116 Ground crew to carry out tyre check after every landing for any creep or
rubbing marks on the sides.
117 Aiming to reach end of base leg with height 500 feet and speed 55 knots.
118 Touch down, under normal wind conditions will occur at 40 knots.
119 During descent, if throttle on idle setting, ensure throttle is opened slightly for
120 short periods of time, to ensure spark plugs do not turn dirty.
121 Close throttle to idle, Allow engine to cool down for 01 minute.
123 Roll straight for a short distance to ensure nose wheel is straight before
applying brakes.
124 In case of cross country flight or cruise flight, climb at 100 Knots speed to
increase overall travelling speed.
125 Carryout weekly check for water contamination in fuel and specially for
aircrafts on ground for prolonged period.
126 In case switching off aircraft for very short duration and starting again, carry
out engine run up and mag drop check.
127 Flutter Caused by abrupt control deflections at speeds close to or in excess
of VNE
128 Touch water with the slowest possible speed, possibly from a high flare
situation in ditching
129. Ensure correct air speed 64 Kts when engine failure in flight.
130 Carburetor Icing may occur even at temperatures as high as + 10° C,
provided air is highly humid
131. In case of alternator failure, battery will support all onboard avionics
132. Aircraft tends to re-establish normal flight by itself usually after having spun
for just 90° - 180°
133. Minimum height to commence the maneuver of stall is 1500 ft AGL. Height
loss in recovery is around 200 ft.
134. Care must be taken not to exceed 70 Kts / 55 Kts during recovery from stall
with Flaps 15° / Flaps 25° in stall recovery procedure.
135. Starts at commencement of crosswind turn till commencement of turn on to
downwind.
136. Check Wing trailing edge for any damage, Flaperon movement, vertical or
horizontal play during pre- flight external checks.
137. Steep turns are to be carried out with initial speed of 100 Kts.
138. Flying in side slip turbulence may result in non-precise fuel quantity
indication.
139. Tailwinds affect take-off and landing performance by more than twice, as
much as headwind does.
140. Once rolled out on downwind, check height, speed and direction correct
and carry out downwind checks
141. Warm Up the engine during taxying so that the engine does not overheat due
to prolonged taxy. Also check brake serviceability every 200 meters.
142. Engine is required to be warmed up, at not more than 2500 RPM, till such
time working temperatures of oil is achieved.

MULTIPLE CHOICE QUESTION ( MCQ)

1. Soft grass runways tend to increase take off performance data by. ---------
(a) 15% (b) 25% (c) 20% (d) 30%

2. Spin initiation is not to be carried out below --------- ft AGL

(a) 1500 (b) 750 (c) 2500 (d) 500

3. All parts have been tested to a minimum safety factor of

(a) 1.875 (b) 1.785 (c) 1.885 (d) 1.775

4. Sink rate at 50 kts of Virus SW 80

(a) 420 f/s (b) 430 f/s (c) 440 f/t (d) 450 f/s

5. During Cruise carry out checks of engine and flight parameters every ....
(a) 10 Minuts (b) 5 minuts (c) 15 minuts (d) 7 minutes

6. Before switch off to cool down engine for ---

(a) 2 Minutes (b) 5 Minutes (c) 3 Minutes (d) 1 Minutes

7. During downwind Height 700 feet AGL / Speed --------

(a) 70-75 kts (b) 65-70 kts (c) 70-72 kts (d) 75-78 kts

8. Aircraft should be steered by using ----

(a) Elevator only (b) Flapron only (c) Rudder pedals only (d)
Flap only

9. Stall speed of aircraft in Flap 25°

(a) 35 kts (b) 40 kts (c) 34 kts (d) 38 kts

10. During rough operation of Aircraft ensure correct air speed

(a) 55 kts (b) 65 kts (c) 64 kts (d) 50kts

11. When electrical fuel pump failure, attempt to reduce power to increase
(a) Oil Pr (b) Manifold Pr (c) Fuel Pr (d) EGT

12. Max EGT Difference

(a) 40 (b) 50 (c) 30 (d) 20

13. Provision for cabin heating and windshield defrost / demist is provided for, by
utilizing hot air from the.
(a)Engine (b)Carburettor (c)Battery (d)Air filter
14. Braking of nose wheel by
(a)Electrically (b) Hydraulically
(c)Mechanically (d) Nose wheel have no brake

15. Operating temperature of virus sw-80 battery

(a)0-30degree (b)0-25degree (c)-30-60-degree (d)0-50 degree

16. Difference between both side of magneto check

(a)300rpm (b)115rpm (c)117rpm (d)120rpm

18. White band range in ASI

(a)35-50kts (b)35-70kts (c)35-80kts (d)35-90kts

19. Best climb rate at MTOW

(a)1230ft/min (b)1220ft/min (c)1222ft/min (d)1225ft/min

20. Single magneto drop check max________RPM

(a) 500 (b) 300 (c) 115 (d) 400

21.Best climb speed of Virus Aircraft

(a) 65 kts (b) 75kts (c) 76kts (d) 80 kts

22. Max useful load of Virus SW 80

(a) 197.0 (b) 197.5 (c) 195.7 (d) 179.5

23. Minimum Sink Rate Flaps 15° - 460 feet per minute
(a) 460 feet per minute (b) 460 feet per sec
(c) 460 mtr per sec (d) 460 mtr per minute

24. Recommended lateral displacement for downwind leg is ________

(a) 0.5 NM (b) .8 NM (c) .7NM (d) .4NM

25. Sufficient heights for recovery of stall

(a) 500 ft AGL (b) 1500 ft AGL (c) 2500 ft AGL (d) 450 ft AGL

26. Minimum height of aircraft to commence a one turn spin is _________

(a) 1500 ft AGL (b) 2500 ft AGL (c) 750 Ft AGL (d) 500 Ft
AGL

27. Carburettor icing may even occur as temperature as high as ________

(a) +15° (b) +10° (c) -10° (d) -15°

28. Magneto drop check at RPM

(a) 300 (b) 4000 (c) 115 (d) 5500

29. A parachute and rocket system is installed ___________.

(a) In front of right seat (b) Behind the right seat
(c) Behind the left seat (d) In front of left seat
30. Maximum wind speed for parking outdoors with tie down is________
(a) 45 kts (b) 41 kts (c) 40 kts (d) 42 kts

31. Before taxy altimeter should set in_________

(a) QFE (b) QNH
(c) QNE (d) Both a and b

32. After take of Height 300 ft, speed should ______ select flaps to Flaps 0
position
(a) 60 kts (b) 70 kts
(c) 70 kts t (d) 55 kts

33. Red band range in ASI _______

(a) 135kts (b)137kts (c)139kts (d)142kts

34. Engine performance at 5800RPM

(a) 79hp (b) 81hp (c) 85hp (d) 88hp

35. Final Approach Speed - 50 Knots with Flaps 25°

(a) 50 Knots with Flaps 25° (b) 50 Knots with Flaps
15°
(c) 43Knots with Flaps 25° (d) 38 Knots with Flaps
25°

36. X COM VHF 760 Transreceiver provides for user defined channels.
(a) 89 (b) 90 (c) 88 (d) 99
37. Fuel hoses are protected with_____ and_________.

(a) Glass and silicon rubber (b) glass and synthetic

rubber
(c) Silicon and composite (d) plastic and rubber

38. The propeller diameter is

(a) 1650 mm (b) 1660 mm

(c) 1750mm (d) 1560mm

39. Fuel Flow of Rotax 912A is dependent on values of

(a) Engine RPM (b) Manifold pressure

(c) Engine fuel consumption data (d) all of the above

40 ASI indicates speed in Knots. The speed indication turns red
when speed exceeds.

(a) 134 Kts (b) 135 Kts (c) 133 Kts (d) 136 Kts

41 The cooling system of Rotax 912A comprises of

Water cooled Cylinder Heads Ram Air cooled Cylinders

Water cooled Cylinders Ram Air cooled Cylinder heads

Water cooled Cylinder Heads water cooled Cylinders

Water cooled Cylinder Heads oil cooled Cylinders

42. _______________ controls levers makes virus SW 80, ideal for initial
as well as for advanced training.

(a) Main flight (b) primary flight (c) full dual main flight (d)
secondary flight

43 Firewall is reinforced by heat and noise insulation using glass

______________.

(a) Insulation tapes (b) flame retardant sandwich (c) metal sheets (d)
anti-flame wall

44 CDI stands for ___________________.

(a) Capacitor decreased ignition (b) capacitor diode ignition

(c) Capacitor discharge ignition (d) capacitor device ignition

45. The torque produced by the engine at 4800 RPM is __________

(a) 103Nm (b) 104Nm (c) 105Nm (d) 106Nm

46 _______________ is displayed in millimeter Hg.

(a) oil pressure (b) oil temperature

(c) coolant temperature (d) manifold pressure

47 Exhaust Gas Temperature (EGT 1 & EGT 2) displayed in deg Celsius. If EGT
rises above , displayed value becomes red with ‘HIGH’ indication.
(a) 920 deg Celsius (b) 925 deg Celsius
(c) 930 deg Celsius (d) 923 deg Celsius
(xiii) During rough engine operation or engine failure in flight ensure correct air
speed _____________

(a) 50kts (b) 54kts (c) 64kts (d) 70kts

48. Fuel recommended in virus SW 80 is __________________

(a) unleaded super grade 93 (b) unleaded super grade 94

(c) unleaded super grade 95 (d) unleaded super 95

49. Totalizer starts counting engine hours when RPM exceeds ___________

(a) 700 (b) 800 (c) 7000 (d) 8000

50 Normal circuit for virus SW 80 aircraft shall be flown at ___________ AGL at

a speed of 70-75 knots.

(a) 500 ft. (b) 600 ft. (c) 700 ft. (d) 800 ft.

51 Maximum wind speed for parking aircraft outdoors without tie down is
__________

(a) 15 kts (b) 25 kts (c) 40 kts (d) 55 kts

52. During caution range of oil temperature, it will display in

____________colour.

(a) Red (b) Yellow (c) Green (d) White

53. Provision for cabin heating and windshield defrost / demist is provided for, by
utilizing______________
(a) hot air from the engine (b) outside air
(c) option a and b (d) none of these
54. All engine & flight control operating levers are located in ______________
(a) Fuselage (b) tail plane (c) wings attachment
(d) the cabin
TRUE OR FALSE:

1. Fire extinguisher is a poly foam AFFF (Aqueous Film Forming Foam)

compound for extinction of hydrocarbon and polar solvent fires. TRUE
2. The EGT warning is also displayed when the engine is off. TRUE
3. Oil temperature displayed in deg Celsius, If oil temperature rises above
125 deg Celsius, displayed value becomes red with ‘HIGH’ warning.
TRUE
4. Engine does not comprise of a cooling fan, hence cooling of engine is
entirely dependent on ram/ moving air. TRUE
5. Maximum permitted RPM is 5500 RPM for 05 minutes. FALSE
6. The ignition system is of dual breaker less capacitor discharge. TRUE
7. After pulling the activation handle the main canopy opens in 3.2 seconds.
TRUE
8. Variometer registering flight time when speed exceeds 36 Kts for more than 05
minutes. FALSE
9. Range of tachometer is from 0 to 5800 RPM. FALSE
10. Prohibition Flying when OAT above 55 deg Celsius. TRUE
11. Magneto drop check is carried out at 4000 RPM. TRUE
12. The maximum useful load is 197.5Kg. TRUE
13. Aspect ratio of Virus SW 80 is 11:1. FALSE
14. Spinner is located in rear side of aircraft. FALSE
15. Virus SW 80 aircraft is approved for day VFR operations only. TRUE
16. Maximum wind speed for parking outdoor without tie down is 40 Kts.
FALSE
17. Maximum take-off weight is 472.5Kg. TRUE
18. Virus SW 80 Microlight Max Speed V NE 135 Knots. TRUE
19. Virus SW 80 Microlight Wing surface area is 12.29 Sq metres. FALSE

20. Restrictions Maximum wind speed for parking outdoors of Virus without
tie down is 15 Kts. TRUE
21. Flying is permitted in heavy rainfall. F
22. Green Band in ASI 43 – 108 Knots. T

23. To do taxy, after release parking brakes, open throttle to 2500 RPM. F

24. During take-off as aircraft accelerates, slowly bring control stick to 1/3rd back
and lift nose wheel off the ground. T

25. During cruise, after reaching cruise altitude establishes horizontal flight and set
engine power to cruise setting (5300 RPM). T

26. Take off & landing with flaps fully retracted is permitted . F

27. Minimum RPM (Red Line) is at 1650 F

28. Best Climb Speed - 76 Knots. T

29. Temperature displayed in PSI. F

30. Tailwinds affect take off and landing performance by more than twice, as
much as headwind does. TRUE

31. Ignition System used in virus SW 80 Dual Breakerless Capacitor

Discharge. True

32. T/O Ground roll of Virus sw 80 is 140 metres False

33. Final Approach Speed is 50 Knots with Flaps 15° False

34. In pre flight inspection Form – 700 completed in all respects and closed /
signed. True

35. Normal flight operation, Mechanical Fuel pump provides adequate oil Pr.
F

36. In icing condition set cabin heating on provided from engine. T

37. Flutter is defined as oscillation of engine. F

38. During smoke in cockpit open the door and leave it hanging freely T

39. During engine failure at take select fuel shut off valve on. F

40. Height loss in stall recovery is around 150 ft. F

41. During downwind landing light off. F

42. During switch off first magnetos off then Avionics off and master off. F

43. Prior To descent, obtain RT permission from the Ground crew. F

44. Before take off parachute safety pin should be inserted. F

45. During Magneto Drop check select any off the magneto. F

46. During starting of aircraft Starter button engage not more than 5 sec F

47. Cockpit pre flight inspection Elevator trim set to neutral position T

48. Best Lift/Drag ratio speed is 65 kts. F

49. Take and landing with Flaps fully retracted is prohibited in Virus SW 80
T

50. During electric fuel Pump failure oil pr will be indicated low. F

51. In ditching make sure that both door fully closed. F

52. During engine fire in flight keep avionics ON and Master ON as required,
on approach set both OFF. T

53. During Final Approach Speed below 55 knots, select flaps to position
‘0’ F

54. During Line up give RT call to ground crew for takeoff. F

55. Before takeoff chock fully backward. F

56. Form 700 should be completed after the flight. F

57. Aerobatic manoeuvres including full developed spin is prohibited in Virus SW

80 T

58. After landing Select Flaps to Position 15°. F

59. Tailwind does not affect take off and landing performance. F
1. Write down External Checks before stall.
(a) Check within local flying area in allotted sector
(b) Not over populated or prohibited area
(c) Away from clouds & large expanse of water
(d) Not likely to enter clouds, especially during recovery
(e) Point of reference selected for orientation.

2. Write down Actions taken when icing / Pneumatic Instrument Failure.

(a) Turn back or change altitude to exit icing conditions

(b) Maintain VFR flight
(c) Set cabin heating ON
(d) Look out for signs of icing on Pitot tube
(e) In case of pneumatic instruments failure, use GPS information for
reference
(f) Plan to land at the nearest airport
(g) Maneuvre the aircraft gently and keep flaps at Flaps ‘0’ position

3. Write down the Cockpit Pre-flight Inspection.

(a) Inside cockpit, check instruments and instrument panel for condition
(b) Check battery disconnection ring in slot
(c) All switches off
(d) Select Master Switch ON, check Gene Fail light ON
(e) Check all instruments set to initial setting
(f) Check Pitot static lines and cables are correctly connected and in position
(g) Check Main wing spar for connection, bolts & nuts in position
(h) Safety belts undamaged
(i) Avionics switch ON, check fuel quantity sufficient for sortie. Press Fuel CB
in and check fuel not leaking from gascolator.
(j) Check elevator trim travel and set to neutral
(k) Avionics & Master switch OFF
(l) Flaps handle down, check flaps for full deflection, and back to ‘0’ position
(m) Emergency Parachute Release Handle safety pin ‘IN’

4. Write down Vitals actions before take off.

(a) Check Parachute safety pin removed.

(b) Select flaps as required for take off (Flaps 1 or Flaps 2 depending on runway
available and winds)
(c) Trimmer in neutral position
(d) Choke fully forward
(e) Fuel valve open, fuel quantity adequate
(f) Landing light ON
(g) Master / Avionics / Magneto switches ON
(h) Flight instruments serviceable. Altimeter set to airfield elevation, back to
QNH, note correction
(i) Engine parameters callout
(j) Oil Pr / Oil Temp / CT 1 & 2 / EGT 1 & 2 / Fuel Qty (%)
(k) Check full and free movement of controls, no fowling or grinding noise
 (l) Check Harness tight and door closed and locked. Confirm from copilot
(m) Check wind direction and speed
(n) Note time. Give RT call for line up.

5. Write sequence of fuel flow.

The fuel flows from the tank (1) via a coarse filter (2) the safety cock (3), water
drain cock (4) and fine filter (5) to the mechanical fuel pump (6). From the pump
fuel passes on to the two carburettors. (7).

6. Fuel Pressure.

Displayed in PSI. If value drops below 2.2 PSI, it turns red with ‘LOW’
warning. If fuel pressure rises above 5.8 PSI, displayed value becomes red
alternatively with ‘HIGH’ warning.

7. Indications of Carburetor Icing.

Rough engine noises

Gradual loss of power

8. Action to be taken when Smoke in Cockpit.

(a) Avionics OFF

(b) Disconnect the battery from the circuit
(c) Land as soon as possible

9. Write down Safety checks after recovery from stall.

(a) Engine parameters within limits

(b) Orientate with point of reference
(c) RT call for ‘Operations Normal’
Spin

10. Write down Checks after Landing.

(5X3)

(a) Clear off runway. Stop aircraft.

(b) Parking brakes ON. Aircraft not moving forward.
(c) Select Flaps to position ‘0’.
(d) Landing lights OFF.
(e) Note flight time
(f) Parking Brakes OFF. Taxy to dispersal
11. Write down take off procedure.

Once cleared for takeoff by the ATC, release brakes, open throttle slowly to full
power. Check engine RPM 5300 – 5500. Engine Parameters within limits. As
aircraft starts moving forward, maintain direction with rudder pedals. Check ASI
registering. As aircraft accelerates, slowly bring control stick to 1/3rd back and
lift nose wheel off the ground. Maintain direction with rudders. Speed
approaching 40 – 43 Knots; gently pull back on stick to get airborne

12. Explain Flight Control System.

Virus SW 80 features flaperons, elevators and rudder as flying control surfaces.

Full dual main flight control levers make the airplane ideal for basic and
advanced flight training. Flight controls viz., flaps, ailerons and elevators are
connected to cabin controls using self fitting push pull tubes. Rudder is
controlled via cables connected to pedals. Elevator trim is electro-mechanical,
driving a spring mechanism, with a common cockpit switch available to both
pilots. Flaperons are installed at the training edge of each wing. Two different
control levels are used for flaps and ailerons. Lateral movement of the dual flight
control stick effects the aileron movement of the flaperon, while a flap lever
located between both seats is used for facilitating movement of flaps.

13. Write down Vital actions to be taken before takeoff.

(a) Check Parachute safety pin removed.

(b) Select flaps as required for takeoff (Flaps 1 or Flaps 2 depending on runway
available and winds)
(c) Trimmer in neutral position
(d) Choke fully forward
(e) Fuel valve open, fuel quantity adequate
(f) Landing light ON
(g) Master / Avionics / Magneto switches ON
(h) Flight instruments serviceable. Altimeter set to airfield elevation, back to
QNH, note correction
(i) Engine parameters callout
(j) Oil Pr / Oil Temp / CT 1 & 2 / EGT 1 & 2 / Fuel Qty (%)
(k) Check full and free movement of controls, no fowling or grinding noise
(l) Check Harness tight and door closed and locked. Confirm from copilot 22
(m) Check wind direction and speed
(n) Note time. Give RT call for line up.
14. Write down Switch Off procedure.

(a) Close throttle to idle. Allow engine to cool down for 01 minute
(b) Parking Brakes ON. Check aircraft not moving forward, give clearance to
Position chocks
(c) RT call
(d) Engine cool time over, select all green switches off
(e) Avionics OFF. Both magnetos OFF. Master switch OFF
(f) Fuel Pump CB OUT / Fuel shut off valve close
(g) Release parking Brakes
(h) Insert Parachute safety pin
(i) Exit aircraft and position pitot cover

15. Write down engine warm up procedure.

Engine Warm Up. Engine is required to be warmed up, at not more than 2500
RPM, till such time working temperatures of oil is achieved. Engine warm up is
to be avoided at idle RPM, as this causes spark plugs to turn dirty.

(a) Engine throttle to be set to 2500, till oil temperature reaches 50 deg C
(b) Ensure engine nose pointing into wind
(c) Ensure engine temperature & pressure with operational limits

16. Write down checks for line up.

Checks on Line Up.

(a) Throttle to idle, aircraft on brakes, aircraft not moving forward

(b) Check compass reading runway heading, note correction if any
(c) Take off path ahead and above clear
(d) Give RT call to ATC for take off

17. Write action taken when engine fire on ground. (10)

Engine Fire on Ground.

(a) Shut fuel valve OFF
(b) Come to full stop, engage starter and set throttle to full power
(c) Disconnect battery from the circuit (pull battery disconnection ring on
switch column)
(d) Master switch OFF immediately after engine has stopped
(e) Abandon the aircraft and start the fire extinguisher
Note. After fire has been extinguished DO NOT attempt to restart the
engine.
18. List out aerobatic manoeuvre Limitations in Virus SW 80.
(a) Power on / off stalls are not to be carried out below 1500 ft AGL.
(b) Power on / off lazy eights are not to be carried out below 1500 ft AGL, with
entry speed 110 Kts.
(c) Steep turns are to be carried out with initial speed of 100 Kts.
(d) Chandelle manuevres with an entry speed of 120 Kts, are not to be carried
out below 500 feet AGL.
(e) Spin initiation is not to be carried out below 2500 ft AGL and recovery to be
initiated at maximum 180 deg in actual spinning manuevre.

19. Action to be taken during smoke in cockpit.

(a) Avionics OFF

(b) Disconnect the battery from the circuit
(c) Land as soon as possible

Note In case of trouble breathing or visibility out of the cockpit has degraded
severely due to smoke, open the cabin door and leave it hanging freely. Flying
with door open, do not; under any circumstances exceed 60 Kts.

20. What are steps to be followed before Proceeding to aircraft?

(a) Pre flight briefing carried out, covering the complete sortie profile.
(b) Pre flight meals / medical completed. All participants are fully fit to fly.
(c) Authorisation Book filled in and signed.
(d) Form – 700 completed in all respects and closed / signed.

21. What are checks carried out after landing?

(a) Clear off runway. Stop aircraft.

(b) Parking brakes ON. Aircraft not moving forward.
(c) Select Flaps to position ‘0’.
(d) Landing lights OFF.
(e) Note flight time
(f) Parking Brakes OFF. Taxy to dispersal

22. What are the checks to be carried out before engine start?

(a) Check fuel quantity sufficient for duration of flight

(b) Confirm Pitot cover removed
(c) Confirm Parachute safety pin removed
(d) Engage wheel brakes and apply parking brakes
(e) Check fuel valve open, fuel CB IN, fuel pump on (by sound)
(f) In case of cold start, select choke fully open by pulling choke lever fully
back
(g) Select Avionics OFF and both magnetos ON
 (h) Check area around and propeller area clear. Take clearance from ground
crew for start
(i) Engage starter button till engine starts (not more than 10 seconds, in one
go
(j) Select Avionics switch ON (k) Check oil pressure registering and within
limits
(l) Set throttle to adjust RPM below 2500
(m) Select choke lever fully forward (Closed) while maintaining RPM
(n) Check Engine parameters normal.

23. Action to be taken when rough engine operation or engine failure in flight.

(a) Ensure correct air speed 64 Kts

(b) Start analyzing terrain below
(c) Choose most appropriate site for landing out
(d) Provided engine failed aloft, react as follows.
(e) Ensure Master switch is in ON position
(f) Magneto switches both set to ON
(g) Fuel valve open
(h) Attempt to restart the engine
(j) If unsuccessful, begin with landing out procedure immediately

24. Write down Switch Off procedure of Virus SW 80.

(a) Close throttle to idle. Allow engine to cool down for 01 minute
(b) Parking Brakes ON. Check aircraft not moving forward, give clearance to
Position chocks
(c) RT call
(d) Engine cool time over, select all green switches off
(e) Avionics OFF. Both magnetos OFF. Master switch OFF
(f) Fuel Pump CB OUT / Fuel shut off valve close
(g) Release parking Brakes
(h) Insert Parachute safety pin
(i) Exit aircraft and position Pitot cover