Cessna 208 (B) Caravan I T.T.R.
Cessna 208 (B) Caravan I T.T.R.
Cessna 208 (B) Caravan I T.T.R.
5. What is the maximum operation speed with flaps extended beyond 20 0? 125kts.
8. What is the maximum Ng for reverse thrust and time limitation? 101.6% and
1minute.
9. What is the maximum allowable SHP? 675shp, compensated for temperature and
altitude.
11. What is the minimum oil temperature for engine acceleration? 100C.
16. Where is the oil dipstick located? At rear of the engine, left side.
response.
18. What is the unusable fuel with both tanks on? 3.6 US gal.
21. What is the oxygen tank nominal pressure? 1850 psi, at 700F[210C].
22. What action would you take if the torque went over the maximum limit?
23. What is the rpm for a propeller over speed test? 1750 plus or minus 60rpm.
24. What is the purpose of the inertial separator? To prevent FOD, i.e.; moisture
particles from entering the compressor air inlet when in bypass mode.
25. Beta range is selected by? Power lever.
26. After an aborted start; wait for fuel to drain off and select motoring
procedure.
27. If oil pressure falls to 85 psi when operating above 72% Ng, what action should
28. Give the battery start cycle limitations; 30 seconds on, 60 seconds off,
29. Give the external power start cycle limitations; 20 seconds on, 120 seconds
30. Engine oil; Mil – l – 23699D. Exxon turbo oil 2382. Mobil jet oil 2.
31. Give the dry motoring run procedure; FC lever [cut-off], ignition switch
[normal], battery [on], fuel shut off [open], fuel boost switch [on], starter
switch [motor].
32. When do you check engine oil quantity? Within 10 minutes of engine shutdown
33. Where is the oil tank filler located? Rear of the engine on the left side.
34. The fuel reservoir tank is vented to; both fuel tanks.
35. Where are the fuel vents located? At the trailing edge of each wing, at the
tips.
36. The normal operation of the fuel system is; both tanks on.
37. The fuel cross feed system is; there isn’t one.
38. Where are the fuel drain valves located? Fuel tank external sump, Inboard fuel
39. The battery bus is powered; even if the battery switch is selected off.
system.
41. The electrical power is supplied by; one engine-driven starter/generator [28V,
42. Where is the external power switch located? On the left sidewall switch and CB
panel.
43. How many positions can be selected on the external power switch? 3; off-
starter-bus.
44. Engine fire in the air; power lever idle, propeller feather, fuel condition lever
45. Electrical fire in the air; batt switch off, generator trip and release, stand-by
46. Engine fire on the ground during starts; fuel condition lever cut-off, fuel boost
49. The brake fluid reservoir filling; between min. & max
50. How are brakes connected to the pedals? Through I master cylinder attached
51. Give the propeller anti-ice cycle; 90 seconds on, 90 seconds off
52. How can u tell if the oil-operated pressure switch in the propeller anti-ice
54. If the auto mode failed, how would you activate the propeller anti-ice system?
55. How many positions on the wing de-ice detector light switch? 2. [Wing light]
56. Does the propeller have to be unfeathered for the propeller anti-ice to be
57. The engine de-icing/anti-icing system is; no such system, propeller only
58. Why, in flight, must the mixing air always be in flight position? The cabin air
must be allowed to return into the mixer to get blended with hot compressor
59. What happens if the ground position is used in flight? The system may overheat
60. What is the position of the heat switch during start? It must be in the off
62. Where is the flaps indicator in relation to the flap selector? To the left of the
63. Where is the emergency power lever located? Extreme left side of pedestal,
next to throttle
64. Aileron trim is achieved by? A knob located on the pedestal above the rudder
trim wheel
65. Where is the rudder trim wheel located? On the pedestal below the aileron trim
wheel
66. Where is the elevator trim wheel located? Vertically mounted at extreme left
of the pedestal
67. Where is the fuel shut-off valve located? To the right of the aileron trim knob
on the pedestal
68. Where is the oxygen bottle located? At the top of the tail cone bulkhead
69. How do you know if the oxygen is flowing to the masks? Hoses of oxygen masks
71. Does aileron travel change with the flaps in the down position? No
72. How many & what type of trim tabs are on the wing ailerons? Two. Left wing
73. How would you counteract a runaway aileron trim? Runaway is not possible
74. The rudder trim operates against; the nose wheel steering bungee
75. How does the stall warning operate? Pneumatically operated, electrically
operated
76. Where is the engine rpm gauge? Top instrument panel, to the right of the
torque gauge
77. What are the standard tire pressures? Main [40 plus/minus 5], Nose [36
plus/minus 6]
78. The nose-wheel steering is available through; 150 either side of neutral
79. When does the fuel warning light come on? When the respective tank contains
25 US gal or less
80. What does the vacuum pump operate? The gyroscope instruments
81. The suction gauge indications at diff height should be; 30,000’: 3.0-5.5”Hg
84. What are the fuel tank contents? Total 335gal, each 167.8
87. What is the C. of G datum position? 100” forward of the front firewall
91. What is the maximum allowed time for avgas use? 150hrs
92. What is the maximum allowable time for use of a mixture of 3 parts Jet A1 to
93. Erratic operation of the generator; place switch on trip position for 3minutes
then reset
94. The maximum glide speeds with a cargo pod installed are; 95kias @ 8750lbs,
95. The maximum glide speeds without cargo pods installed are; 97kias @ 8750lbs,
97. Where are the fuel quantity indicators located? Upper portion of the
99. Fuel is pumped from the reservoir to? The reservoir manifold assembly
100. The fuel control unit meters the fuel and directs it to; the flow divider
which distributes the fuel to dual manifold, THEN to 14 fuel nozzles located in
101. What are the maximum and transient rpms? 1900 max 2090 transient
102. What are the maximum, starting & transient ITT’s? 8050C max. 8500C,
103. The fuel condition lever cut-off position shuts off; all fuel to the engine
fuel nozzles
104. The low idle positions; the control rod stop to provide an rpm of 52% Ng
105. The high idle positions; the control rod stop to provide an rpm of 65%Ng
ELECTRONICS
overheat light
4. The generator control unit [GCU] controls the operation of the; starter-
generator
5. The ground power monitor; protects the electrical system from incorrect
voltages
6. Loss of any pneumatic signal to the fuel control unit causes; the engine to drop
to idle rpm
7. When the starter switch is placed in the start position; the ignition system is
8. During the overspeed governor test the propeller rpm should not exceed; 1750
plus/minus 60rpm
ANTI-ICE/DE-ICE
approximately; 6 seconds
4. The wing, wing strut and stabilizer de-ice boots are intended to be used; after
5. When the boot press switch is moved to the auto position; one three-segment
6. When the boot press switch is moved to the manual position; all de-ice boots
inflate simultaneously
POWERPLANT
3. The power turbine is mounted on a shaft that; drives the reduction gear
4. Air inducted into the engine; enters at the rear and is exhausted at the front
5. During operations using the emergency power lever; the emergency power lever
annunciator light will illuminate when the lever is unstowed from normal
6. With the propeller control lever in the max position; the propeller speed is
governed at 1900rpm
7. Engine oil level should be; maintained to within 2 quarts of max hot or max cold
as appropriate
9. The inertial separator should be placed in the by-pass position; when flying through