AIRCRAFT TECHNICAL EXAMINATION
CESSNA CUTLASS 172RG
1980 MODEL 172RG SERIAL NO. 172RG0498 REGISTRATION ZS-PRF
BY
SAMUEL SIDEA
DURBAN 2008-12-10
AIRCRAFT TEHCNICAL EXAMINATION – CESSNA CUTLASS 172RG 1.
The engine is rated at 180 hp at 2700 rpm.
2.
Minimum fuel pressure is 0.5 psi.
3.
Minimum oil pressure is 25 psi.
4.
The unusable fuel in each tank is 2 gallons.
5.
Maximum takeoff weight is 2650 lbs.
6.
Maximum weight in baggage compartment is 200 lbs.
7.
Fuel capacity is 66 US gallons.
8.
Operation on left or right tank is limited to level flight.
9.
For takeoff and landing select fuel cock to BOTH.
10. The manoeuvre speed at 2650 lbs is 106 kts. 11. Approach speed for precautionary landing is 65 kts. 12. The auxiliary fuel pump is used to maintain a minimum pressure of 0.5 psi. 13. If gear motor continues to run after retraction pull gear pump circuit breaker. 14. Total loss of hydraulic fluid means that gear cannot be lowered. 15. In the event of an excessive charge rate being indicated the alternator must be switched off and circuit breakers pulled out. 16. If a discharge is indicated on the ammeter turn OFF Avionics Power Switch, check alternator circuit breaker is in, then turn OFF both sections of Master Switch, then turn them ON again. 17. The static vents are located both sides of he fuselage. 18. Priming engine before start is done by a manual primer. 19. Auxiliary fuel pump must be on to check pressure rise then OFF before takeoff. 20. Auxiliary fuel pump should be used when fuel pressure falls below 0.5 psi. 21. Magneto drop allowed on run up is 150 rpm with 50 rpm between mags. 22. On checking mags with switch selected to right and no drop in rpm is detected the left magneto is faulty. 23. Landing gear is operated by an electrically driven hydraulic pack. 24. The landing gear position lits are interchangeable and may be pressed to test. 25. Inadvertant retraction on the ground is prevented by a squat switch in nose oleo. 26. The emergency hand pump is located on floor between front seats. 27. The gear warning horn will sound when MP less than 12”, or gear UP and 20° flap DOWN.
AIRCRAFT TECHNICAL EXAMINATION – CESSNA C172RG
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28. Minimum oil for engine operation is 5 US quarts. 29. In the event of loss of oil pressure the propeller will move into fine pitch. 30. Filling the fuel tanks to the bottom of the filler collar gives a quantity of 24 gallons and 2 gallons unusable each side. 31. When refuelling the fuel selector should be on LEFT or RIGHT. 32. In cruising flight LEFT or RIGHT should be used. 33. If a fuel tank is completely exhausted in flight select BOTH for remainder of flight. 34. The electrical system is 28 volt DC. 35. The alternator switch is the left half of battery master switch. 36. The ammeter indicates number of amps from alternator to battery or battery to aircraft electrical system. 37. The suction gage should normally indicate 4.5 – 5.4 inches. 38. The engine oil capacity is 9 US quarts. 39. The wing loading is 15.2 lbs/sq.ft. 40. The power loading is 14.7 lbs/hp. 41. The wing span of the aircraft is 36 feet. 42. The engine has 4 cylinders. 43. Total fuel capacity is 66 US gallons. 44. When the nose wheel is raised during takeoff the power pack may operate and restore system pressure. 45. The cowl flaps should be OPEN during the climb. 46. The indicated stall speed at most rearward C of G at 2650 lbs, 10° flap and 30° bank is 45 kts. 47. The ground roll during short field takeoff given weight of 2500 lbs, 3000 feet at 10°C is 1170 feet. 48. The fuel consumption at 10 000 feet pressure altitude using standard temperature and MP 20” at 2600 rpm is 9.4 US gallons per hour. 49. Calculate the mass and C of G for the aircraft, carrying a pilot plus two pax, 10 kg baggage and 44 US gallons usable fuel. Assume pilot and pax each weigh 70 kg.
AIRCRAFT TECHNICAL EXAMINATION – CESSNA C172RG
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ITEM
WEIGHT (lbs)
ARM (in.)
MOM/1000 (lbs/in.)
1624
37.9
61.6
264
48.0
12.7
Front seats(Pilot + pax – 70 kg each)
308
37.0
11.4
Rear seats (1 pax – 70 kg)
154
73.0
11.2
Baggage Area 1 (10 kg)
22
95.0
2.1
BASIC EMPTY WEIGHT Usable Fuel (at 6 lb/gal) Reduced Fuel (44 gal)
RAMP WEIGHT AND MOMENT
2372
99.0
-8
- 0.4
Fuel for engine start, taxi and runup TAKEOFF WEIGHT AND MOMENT
2364
41.7
98.6
50. Using the above data calculate mass and C of G on landing after a 250 nm flight at 6000 feet (65% power on a standard day). Performance at 6000 feet at 65% power on standard day Fuel consumption: 8.8 GPH Speed
128 KTAS
Distance flown:
250 nm
-----------------------------------------------------------------------------------------------------------Fuel used: Fuel remaining:
250 nm / 128 = 1 hr 57 min x 8.8 gal
= 17.19 US gal
17.19 US gal x 6 lbs/gal
= 103 lbs
264 – 8 (start, taxi, runup) – 103 (flight) = 153 lbs
ITEM
WEIGHT (lbs)
ARM (in.)
MOM/1000 (lbs/in.)
TAKEOFF WEIGHT AND MOMENT
2364
41.7
98.6
- Fuel used
103
48.0
4.9
LANDING WEIGHT AND MOMENT
2261
41.4
93.7
51. The battery is located aft of the rear cabin wall.
AIRCRAFT TECHNICAL EXAMINATION – CESSNA C172RG
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52. Emergency gear selection requires Master Switch ON, select gear DOWN, gear circuit breakers IN, extend hand pump and pump perpendicular to handle until resistance becomes heavy. 53. The fuel system has 11 fuel drains. 54. In the event of failure of the vacuum pump the AH and DI will cease to function and the suction gage will read zero. 55. The fuel consumption at 65% power, standard temperature, 2300 rap at 6000 feet is 8.8 GPH. 56. The exterior power socket is located behind a door on the left hand side of fuselage behind baggage compartment. 57. The flaps are operated electrically. 58. The VNE is 164 kts. 59. The VA at 2250 lbs is 98 kts. 60. Flaps may be extended 10° at 130 kts. 61. Landing gear may be extended up to 140 kts. 62. In the event of a cabin fire the air vents should be closed (unless there is excessive smoke in the cabin). 63. If the static source becomes blocked, select alternate static source. 64. If the low voltage light illuminates during flight, Avionics Switch OFF, Alternator circuit breakers IN, Master Switch OFF, Master Switch ON. 65. In the event that suction is lost in flight the DI will be unusable and the Turn Co-ordinator may be used. 66. If the engine driven fuel pump fails: - gravity flow will provide sufficient fuel for level and descending flight - in the climbing attitude or whenever the fuel pressure drops to 0.5 psi the electric pump should be turned ON. 67. The demonstrated crosswind component is 15 kts. 68. The stalling speed at 2650 lb, 30° bank with the most rearward C of G and flaps up is 49 KIAS. 69. The range at 65% power at 3000 feet and 2650 lb is 767 nm. 70. The endurance at 2650 lbs, 65% power, 4000 feet is 4.1 hours. 71. Venting of the fuel tanks is by connecting line from right to left tank to vent pipe beneath left wing and right filler cap vent. 72. Fuel selection during manoeuvres should be on BOTH.
AIRCRAFT TECHNICAL EXAMINATION – CESSNA C172RG
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73. The 28 volt DC electrical system incorporates a 60 amp. Alternator. 74. The emergency gear pump is located between the seats. 75. Filling the tank to the bottom of the fuel filler collar indicates a reduced fuel load of 24 US gallons with 22 US gallons usable.
AIRCRAFT TECHNICAL EXAMINATION – CESSNA C172RG
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