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T-34C Systems Familiarization Te

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									T-34C Systems Familiarization Test Gouge
1. The T-34 Engine is a reverse-flow type with inverted capabilities.
    It is a PT6A-25 turboprop built by Pratt and Whitney. (550 SHP,
    1315 ft-lb torque; Navy limited 425 SHP, 1015 ft-lb torque)
2. Describe the compressor section of the engine: three stage axial
    and single stage centrifugal compressor with a 7:1 ratio
3. What is P3: fuel control reference air tells FCU how much air is
    in the diffuser
4. Describe engine bleed air: comes from the diffuser and provides
    cockpit heating
5. What are the four main sections of the engine: compressor,
    combustion, turbine, exhaust
6. The combustion chamber is: annular reverse flow type
7. How many igniter plugs: 2, used only for initial start
8. What is the first turbine called: N1, or compressor
9. When RPM is at 101.5% N1 = 37,000 RPM
10. What is the second turbine called: Nf, free turbine, or power
    turbine
11. What does the engine inlet air bypass system do: prevents ice
    from reaching engine
13. A yellow can indicates what substance: oil
14. Oil system capacity: 4.4 gallons
15. What type oil pump and location: gear driven, oil tank
16. Units of measurement on dipstick: quarts
17. Dipstick indications are: hot & cold, max & min
18. What type of oil system: pressure and splash and spray
19. Oil heat exchanger heats fuel to: 70-90∞ F
20. Auxiliary oil tank capacity: 1 qt
21. PCL controls fuel flow how: has 11” rod running from cam box
    assembly to FCU
22. Internal scavenge pump location: inside accessory gearbox
23. How many scavenge oil pumps: 2
24. Oil temperature and pressure limitations:
    *Limitations ~~Temp ~~Pressure
    *Minimum ~~(-40∞ C) ~~40 psi @ idle
    *Normal ~~10-99∞ C ~~65-85 psi
    *Maximum ~~100∞ C ~~100 psi
25. Idle normal is: 62-65% but not below 60% or over 65%
26. Exciter box uses what type & strength electricity: 28VDC to
    generate 1400V P(ulsating)DC
27. Green "ignition" light on annunciator panel: exciter box is
    energized
28. How many relays does the starter have: 2, generator and auto-
    ignition
29. What does auto-ignition do: provides spark during flameout
30. "Auto-ignition" light on annunciator panel: auto-ignition system
    armed
31. When does auto-ignition engage: when torque is 300-180 ft-lb
32. Describe reduction gearbox: two stage, reduces power turbine RPM
    at 15:1 ratio
33. Where is chip detector located: reduction gearbox
34. Torque indicator system: 26V AC, mounted on reduction gearbox
    flange
35. Max torque: 1315 ft-lb (550 SHP)
36. NATOPS torque: 1015 ft-lb (425 SHP)
37. Where is the propeller tachometer generator: reduction gearbox
38. Normal max allowable RPM: 2200
39. Define blade angle: angle between the plane of rotation of the
    propeller and the chord line of the blade
40. Three known blade angles: Feather: 87.5∞, Idle: 17.5∞, Max beta:
    -5∞
41. Six parts of pitch change assembly: feathering springs, retainer
    cup, counterweights, servo piston, connecting links, beta
    feedback ring
42. Force required to keep prop at idle: high oil pressure
43. What does the PCL control: fuel flow
44. Conditions to select beta:
    a. DC power to solenoid
    b. nose landing gear strut compressed
    c. depress beta switch on PCL
45. Two ranges of PCL: beta and power
46. Two functions of condition lever: control fuel on/off, set RPM
47. Purpose of beta feedback ring: set idle and beta
48. Three positions of condition lever: fuel off, feather, and RPM
49. How many friction knob locks: one in front cockpit
50. Pitch change progression...
    ex:Fuel increase, RPM increase, less HP oil, piston moves aft,
    prop angle increases, etc.
51. Overspeed governor location: reduction gearbox
52. When does overspeed governor work: 2332 RPM
53. How does overspeed governor work: diverts high pressure oil back
    to reduction gearbox
54. At what RPM does primary prop governor fail: 2331
55. Where is fuel topping governor located: primary prop governor
56. How does fuel topping governor work: decreases Py air which
    decreases fuel flow
57. What does the torque limiter limit the engine to: 1315 ft-lb (550
    SHP)
58. What does EPL do: manually controls fuel flow
59. Primary fuel for T-34: JP-5
60. Fuel capacity: 135 gallons
61. Useable fuel: 130 gallons
62. Fuel gauge reads: lbs
63. R or L low fuels light comes on at: 90 lbs useable fuel remaining
64. Engine driven fuel boost pump: moves fuel from sump to engine
65. Fuel boost pump is mounted to and driven by: external oil
    scavenge pump on accessory gearbox
66. Indicates fuel boost pump failure: fuel press and master caution
67. Electric boost pump uses: 28 VDC
68. Fuel pressure light comes on: could be an oil scavenge pump
    problem
69. Fuel flow gauge electricity: 26 VAC
70. 3 parts of FCU: hydro pneumatic mechanical; hydro (fuel),
    pneumatic (P3), mechanical (PCL)
71. How many thermocouples: 8 bi-metallic
72. Max continuous ITT: 695∞ C
73. Will ITT temp set off fire warning light: no, infrared radiation
74. Can you dim fire warning light: no
75. Time to raise/lower gear: 4 sec
76. Landing gear strut type: shock strut
77. What is inside of strut: nitrogen and hydraulic fluid
78. How many inches showing on rear strut: 3”
79. How many inches showing on front strut: 3-5”
80. Tire inflated with: nitrogen
81. Describe 3 main safety switches on 3 struts
    Starboard: disables AOA indexer, disables “gear up” side of gear
    motor
    Port: warning light and horn actuation, NACWS test enabled
    Nose: beta enabled, rudder pedal shakers disabled
82. Where is landing light warning from: nose gear position switch
83. How many types of landing gear uplocks and what are they: 2,
    mechanical advantage and positive uplocks
84. How many types of landing gear downlocks and what are they:
    3, mechanical advantage, overcenter pivot, positive downlock.
    Nose gear does not have positive downlock.
85. Main landing gear has what kind of downlock: positive
86. What type of switch tells landing gear up/down: position switch
87. What lights indicate gear is down and locked: external data
    indicator lights
88. Only conditions to silence landing gear horn: in flight, gear up,
    PCL < 75% or in flight, gear up, PCL and EPL > 75%
89. Control lock in place, control surfaces are: elevators full down,
    rudder aligned with vertical stabilizer, ailerons neutral (both 2
    deg down)
90. Secondary flight controls: trim tabs, strakes, and ventral fins
91. Auxiliary flight controls: flaps
92. Trim controls location: forward end of left console
93. Adjust trim when: to adjust for unbalanced flight without
    exerting continuous pressure on primary flight controls
94. Trim sequence: rudder, elevator, aileron
95. Difference between R & L elevators: 9∞ (R up 4.5/L down 4.5)
96. Rudder trim type: anti-servo
97. Describe anti-servo: trim leads in direction of travel and
    provides artificial feel.
98. Aileron trim type: servo, opposite direction
99. Does right aileron trim tab move: no
100. Strakes and ventral fin purpose: limit spin rate
101. Flap extension time: 10 sec
102. Flap purpose: high lift devices
103. Max speed to use flaps: 120 KIAS
104. Flap indicator on which wing: left
105. Landing gear speeds: up = 120 KIAS, down = 150 KIAS
106. Max gross weight: ramp = 4425, takeoff/land = 4400
107. Max airspeed: 0-20,000ft = 280 KIAS, 20,000-25,000 = 245 KIAS
108. G-limits: -2.3, +4.5
109. Limit of nose gear deflection: 30∞
110. Enter/exit: left side
111. Overhead assist handle: unlocks canopy from an aft open position
112. Color of nitrogen storage bottle for canopy blow: orange
113. Nitrogen: actuates cylinder which pulls cables attached to both
    canopies pulling them back
114. How long does emergency canopy release take: 1-4 secs
115. Seat lock release: right side
116. Causes inertial reel on safety harness to restrain pilot: raped
    linear deceleration (of > +2g)
117. How many clocks: 2
118. Clocks powered: spring
119. Jet pump: mixes bleed air with outside air
120. Where does fresh air come from: accessory air inlet
121. Purpose of firewall gate valve: controls flow from jet pump
122. Cockpit heating overtemperature sensor location: in the air duct
    aft of firewall
123. Warning given when air duct temp exceeds 250∞ F: master caution
    light and bleed air
124. What action is taken when BLEED AIR annunciator fault light
    illuminates: switch environmental control to fresh air increase
125. Source of outside air to rear cockpit: scoop under plane
126. Purpose of air conditioner: remove heat from circulated cockpit
    air
127. A/C system: vapor cycle
128. A/C compressor operated: belt driven, actuated by clutch
129. A/C compressor location: left side of aircraft
130. High pressure A/C switch rated at: 380 psi
131. Low pressure A/C switch rated at 3 psi
132. Condenser blower location: front wheel well
133. Which gear uplock position switch works compressor blower: port
134. Oxygen tank capacity: 76 cubic feet, 1850 psi
135. Min oxygen for flight: 1000 psi
136. Why set oxygen switch to 100%: prevent contamination
137. Type oxygen during climb and descent: 100% and normal
138. White flow indicator: oxygen being sent to regulator
139. Switch will alter oxygen pressure: emergency control lever
140. Oxygen T-handle location: front, right, forward cockpit
141. Oxygen high-pressure relief valve location: aft, right side of
    empennage
142. Master brake cylinders: 4
143. How does the shuttle valve work: most pressure applied operates
    brakes
144. Min brake thickness: 1/10 inch
145. Which cockpit has control of parking brake: front
146. Conditions prohibit setting of parking brake: overheating or
    freezing temps
147. Trim tab purpose: relieve pressure on flight controls
148. Compliance with NATOPS is mandatory
149. What is a line connector or relay: takes a small amount of
    current to manage large amount of current
150. Battery volts needed to start aircraft: 22V
151. Battery produces: hydrogen gas
152. Two items can recharge battery: GPU and generator
153. Purpose of electrical command switch: takes control of AC and DC
    power
154. Can you give away command: no
155. Only hot wired switch: electrical take command
156. Generator power rating: 30V, 200 amps
157. What does voltmeter read: highest voltage (generator)
158. Ammeter readings: + or –
159. Three indications of external power:
    a. generator light off
    b. 28V
    c. discharge on ammeter
160. Why is GPU used: to save power during start and for maintenance
161. Power rating of starter: 28V, 800amps
162. Time limitation on starter: 40 secs, 60 secs, 40 secs, 60 secs,
    40 secs, 30 mins
163. How do you get master caution light off: fix problem or depress
    button
164. Type of light provided by utility light: spot or flood
165. Purpose of glare shield: to prevent strobe from shining in
    pilot’s eyes
166. When use Emergency audio position on mixer switch: amplifier
    failure
167. How do you manually set frequency: turn knob to manual
168. “Main” on UHF frequency: normal operation
169. “Both” on UHF frequency: normal and monitors guard frequency
170. Guard channel: 243 MHz
171. VOR antenna location: top of vertical stabilizer
172. TACAN provides on standby: bearing only
173. Systems test button: checks bearing needles, VOR, RMI needle,
    and DME
174. TACAN antenna location: bottom of fuselage, forward of ventral
    fin
175. TACAN provided in T/R: bearing and DME
176. How is DME measured: slant range nautical miles
177. How long to warm up transponder: 20 secs
178. ELT location: front cockpit left side
179. Batter life of ELT: 48 hours min
180. When selecting alt static air, which instruments are accurate:
    front cockpit only
181. Where does alternate static air come from: avionics compartment
182. Max allowable altimeter error: 75ft
183. Alt encoder location: front cockpit only
184. Which transponder does altitude encoder send information too:
    whichever has command
185. What is indication that alt encoder is not working: red “code
    off” flag is displayed
186. When does AOA indexer work: landing gear down, in flight
187. Power required by RMI: 26VAC and 28VDC
188. Flux detector location: in left wing tip
189. Describe flux detector: north knowing but unstable
190. Power required of directional gyro: 115V AC
191. Normal position of “fast slave” switch: slave
192. Required to use “fast slave”: straight and level, unaccelerated
    flight
193. Limits of attitude indicator: +/- 82∞ pitch, 360∞ roll
194. One needle width on turn indicator: _ STD rate turn
195. Two needle widths on turn indicator: STD rate turn
196. What type of power do the inverters produce: 115V & 26V AC
197. Three parts of compressor section: compressor inlet case,
    compressor, & diffuser
198. From diffuser what provides P3 & bleed air: 2 tap-offs
199. Number of spray nozzles: 10 primary & 4 secondary
200. Compressor turbine rotation: counter-clockwise
201. Purpose of compressor turbine: rotates compressor and drives
    accessory gearbox
202. Prop at max RPM, what is power turbine RPM: 33,000
203. Located between two turbines: 8 thermocouples measure ITT
204. Door allows solid particles to be separated and vented
    overboard: Engine Air Inlet Bypass
205. Accessory inlet air directs air to: engine driven accessories,
    oil cooler, cockpit, starter/generator (AOCS)
206. How are bearings lubricated: pressure
207. Accessory and reduction gearbox lubrication: pressure and spray
    and splash
208. Main oil tank location: between accessory gearbox & compressor
    inlet casing
209. Auxiliary oil tank location: bottom accessory gearbox
210. Main oil pump location: bottom part of main oil tank
211. Describe main oil pump: gear-type pump driven by a shaft from
    AGB
212. What drives internal scavenge pump: same shaft as main oil pump
213. Internal oil scavenge pump removes oil from: compressor bearings
    and AGB
214. External oil scavenge pump removes oil from: power turbine shaft
    bearings and RGB
215. Type of oil filter: metal screen
216. Oil breather location: main oil tank
217. Oil pressure transmitter location: right side AGB
218. What happens to fuel flow when exciter box operating: provides
    false reading
219. Auto-ignition sense switch location: RGB
220. Five ignition components: starter switch, 2 igniter plugs,
    ignition switch, exciter box
221. Used to retain fuel if cap is lost during flight: anti-siphoning
    flapper valve
222. In 40 gallon tank on inboard en to prevent fuel-siphoning action
    if fuel expands due to heat: siphon break valves
223. These sensors measure fuel weight in tanks: capacitance type
    fuel quantity sensors
224. Power requirement for fuel capacity system: 28V DC
225. Low fuel lights receive input from: thermistor on baffle section
    of 40-gallon tanks
226. Fuel flow transmitter location: top center of firewall
227. Sediment drains on 40 gallon tanks: snap type water sediment
    drains
228. Detects loss of fuel pressure: boost pressure sense switch
229. Fuel flow transmitter produces: 26V AC signal
230. Pressure of main fuel pump: 800 psi
231. Device limits compressor to 37,000 RPMs: FCU
232. Purpose of ITT system: provide engine-operating temp
233. Type of fire detection system: flame surveillance system
234. ITT limitations
    *Normal =400-695∞ C
    *Max continuous =695∞ C
    *Max starting =1090∞ C (925∞ C, 2 secs)
235. Firewall test sensing switch location: front cockpit only
236. Purpose of torquemeter: indication of engine power out on prop
    shaft
237. Three accessories that use torquemeter oil pressure: torque
    limiter, auto-ignition sense switch, and torque transmitter

								
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