T-6 By the Numbers

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Anonymous
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254581
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T-6 By the Numbers
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2013-12-31 15:24:15
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T-6 Texan Info
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  1. Empty Weight
    4900 lbs
  2. Max takeoff/landing weight
    6500 lbs
  3. Rated Horsepower (shaft)
    1100 HP
  4. Torque
    2900 ft-lbs
  5. Thrust (at sea level)
    2750 lbs
  6. Propeller is low pitch
    15°
  7. Prop is feathered (coarse pitch is between 15-86
    86°
  8. Oil capacity
    18.5 quarts
  9. Red OIL PX annunciator lit, when PCL above idle
    <40 psi
  10. Red OIL PX annunciator lit, with PCL idle
    <15 psi
  11. Amber OIL PX lit when PCL at idle
    15-40 psi
  12. Amber OIL PX lit when PCL above idle
    40-90 psi for >10 sec
  13. Turbine output shaft speed
    30,000 RPM
  14. Prop operating speed
    2000 RPM
  15. Ground mode idle
    60% N1
  16. Flight mode idle
    67% N1
  17. PMU managed minimum idle when above 10,000 ft
    80% N1
  18. ignition and boost pump deactivated during auto start
    50% N1
  19. Boost pump comes on
    10 psi
  20. manual motor after aborted start
    20 seconds
  21. normal wing tank capacity
    530 lbs
  22. collector tank capacity
    40 lbs
  23. Single point refueling fill level
    1100 lbs
  24. if refueled with over the wing (gravity) refueling
    1200 lbs
  25. FUEL BAL annunciator
    30 lbs for >2 minutes
  26. EDM keeps fuel balance within this amount
    20 lbs
  27. Outer probe provides readings til fuel drops below this level
    445 (+/- 50) lbs
  28. Middle probe provides readings til fuel drops below this level
    308 (+/- 50) lbs
  29. collector tank pressurized by transfer jet pumps
    1-1.5 psi
  30. L/R FUEL LO annunciator illuminated
    110 lbs
  31. Starter/Generator output
    28 VDC 300 amps
  32. main battery output
    24 VDC 42 ampere-hour
  33. auxiliary battery output
    24 VDC 5 ampere-hour
  34. PMA output (sent to PMU which then converts)
    32 VAC
  35. Hydraulic system total capacity
    5 quarts (1.25 gal)
  36. Hydraulic reservoir capacity
    0.6 gallons
  37. minimum pressure required to operate NWS, flaps, gear, and speed brake
    1800 psi
  38. Engine driven low pressure pump provides
    40 psi
  39. Engine driven high pressure pump
    700 psi
  40. Max amount of fluid hydraulic fuse allows to leak if leak is over*
    0.5 qt (20-30 CI), .25 GPM
  41. Normal Hydraulic Pressure
    3000 (+/- 120) psi
  42. hydraulic pressure relief valve opens
    3250-3500 psi
  43. EHYD PX LO annunciator illuminates
    2400 (+/- 150) psi
  44. HYDR FL LO annunciator illuminates
    <1 qt in reservoir
  45. normal gear extension/retraction time
    6 seconds
  46. Gear warning horn sounds if aspd less than 120 knots
    <87% N1
  47. NWS range (80 degrees if just castoring)
    24°
  48. Flap deflection (T/O)
    23°
  49. Flap deflection (LDG)
    50°
  50. Speed brake deflection when deployed
    70°
  51. TAD active with no Weight on Wheels
    80 knots
  52. Mach window is blanked on Aspd indicator
    <0.40 Mach
  53. Stall AOA
    18 units AOA
  54. on speed AOA
    10-11 units AOA
  55. on speed AOA
    1.3Vs (stall speed)
  56. max endurance (diamond)
    8.8 units AOA
  57. max range (triangle)
    4.9 units AOA
  58. Optimum approach speed decrease rate
    1 knot/100 lbs fuel used
  59. Optimum max range AOA altitude
    25,000' MSL
  60. Stall warning (stick shaker)
    5-10 knots (15.5 units AOA)
  61. Prop diameter
    97 inches
  62. Wingspan
    33' 5"
  63. Nose to tail
    33' 4"
  64. Horizontal stab width
    11' 4"
  65. Ground to top of vertical stab
    10' 8"
  66. (ITT) PMU aborts the start
    >940° for 2 seconds >870° for 4 seconds >840° for 14 seconds
  67. PMU goes offline, won't reset if temp does not decrease below 121
    121°C IOAT
  68. PMU defaults to 121, amber dashes for IOAT, no ITT pointer, EDM FAIL
    96°C IOAT
  69. Firewall shutoff handle pull
    2-2.5"
  70. max time inverted for fuel
    15 seconds
  71. minimum required from generator to charge the battery
    25 VDC
  72. do not connect external power
    22 VDC
  73. Standby attitude indicator if all power is lost
    (+/-) 6° for 9 minutes
  74. Ejection seat limits
    0'/0 KIAS-35,000'/370 KIAS
  75. Automatic seat/man separation
    10,000'-18,000'
  76. ISS Both front seat delay after rear seat fires for spacing
    0.37 seconds
  77. Bleed air inflow prevented with A/C clutch engaged
    <7500' MSL
  78. automatically maintained until 18,069' MSL (3.6 +/- 0.2 psi)
    8000' cockpit press altitude
  79. CKPT ALT annunciator illuminated
    19,000' cockpit press altitude
  80. CKPT PX annunciator illuminated
    ΔP exceeds 3.9-4.0
  81. DUCT TEMP annunciator illuminated. Sensors are located near the  rear distribution valve and upstream of the defog valve
    300° F
  82. RMU cursor automatically reverts to UHF field
    20 seconds
  83. UHF/VHF memory can hold
    20 frequencies
  84. NAV memory
    10 frequencies
  85. ELT transmission limit (battery)
    50 hours
  86. EADI declutters
    >+30°/-20° pitch or 65° bank
  87. EADI presentation reappears
    <+25°/-15° pitch or 60° bank
  88. NACWS display stays activated after trigger is released
    7 seconds
  89. NACWS landing mode
    1.5 NM range
  90. NACWS vertical separation alert (enroute mode)
    (+/-) 2700'
  91. NACWS vertical separation alert (landing mode)
    (+/-) 500'
  92. NACWS rectangle with digits (alt above or below)
    within 300'
  93. NACWS up/down pointing triangle with digits (alt above or below)
    between 400' to 900'
  94. NACWS up/down pointing triangle with no digits
    between 1000' to 2700'
  95. GPS self test indications
    34.5NM, 315DTK, 130° bearing
  96. GPS user defined waypoints
    up to 250
  97. GPS stored flight plans
    25
  98. waypoints per flight plan
    30
  99. CDI full scale deflection (enroute mode)
    (+/-) 5 NM
  100. CDI full scale deflection (approach arm mode) APR ARM
    (+/-) 1.0 NM
  101. CDI full scale deflection (approach active mode) APR ACT
    (+/-) 0.3 NM
  102. APR ARM (GPS)
    30 NM
  103. APR ACT (GPS)
    2 NM
  104. FDR MAINT annunciator illuminates
    80% full
  105. Aux bat test light will not illuminate
    <50% capacity
  106. OBOGS TEMP annunciator illuminates
    200° F
  107. Normal O2 concentration sea level to 15,000' MSL
    25%-70%
  108. Normal O2 concentration 15,000'-31,000' MSL
    45%-95%
  109. O2 concentration if MAX selected (also max concentration)
    0.95
  110. OBOGS warmup time after engine start
    3 minutes
  111. OBOGS FAIL annunciator inhibited during built in test
    3 minutes
  112. baggage compartment weight limit
    80 lbs
  113. icing inhibitor mix (this mix is 0.13% by volume) 0.10%-0.15% acceptable
    .5 pints per 50 gal fuel
  114. External power minimums (offstation 24.0-29.5 acceptable)
    28-28.5VDC1000 Amps for 5 seconds500 Amps for 2 minutes300 Amps continuously
  115. Main Gear tire pressure (or 225 +/- 5 for USN and sometimes USAF)
    185 +/- 5 psi
  116. Nose wheel tire pressure
    120 +/- 5 psi
  117. Windscreen and front transparency designed to take this hit
    4lb bird at 270 knots
  118. Takes to pull CFS handle
    15-25 pounds
  119. Altitude sensing device opens chute (for high altitude ejections)
    14,000 to 16,000'
  120. black band on Emergency Oxygen bottle
    1800-2500 psi
  121. 1800psi is minimum at 70° correct what for diff temp?
    3.5 psi/degree F over/under 70
  122. delay after ejection handle is pulled for PIRD to retract
    .17 seconds
  123. ISS both front seat total time after handle is pulled (.17 PIRD+.37 delay)
    .54 seconds
  124. SSK automatically drops seat kit after seat/man separation
    4-6 seconds
  125. G suit pressure relief valve opens
    7 psi
  126. Evap blower assembly capability
    350 CFM
  127. ELT transmission frequencies
    121.5 and 406 MHz
  128. miles range for EHSI inner circle (double for outer)
    2.5,5,10,20,40,80,120,160,500
  129. When you push ARC button on EHSI panel
    85° Arc
  130. 1 dot on VOR
  131. 1 dot on localizer
    0.25°*localizer width
  132. On EHSI causes HDG flag to appear when in SLVD
    error>10° for 5 minutes
  133. oil must be serviced after engine shutdown
    30 minutes
  134. best results for checking oil after shutdown
    15-20 minutes
  135. 17 static wicks
    4 on each wing, 3 rudder, 6 elevator
  136. minimum battery voltage required for battery start
    23.5 VDC
  137. minimum battery voltage required to connect external power
    22 VDC
  138. minimum main gear strut extension
    2.0 inches
  139. minimum nose gear strut extension
    2.5 inches
  140. Delay after rear seat ejects before front seat ejects
    0.37 seconds
  141. LOW AOA test switch (amber donut illuminates)
    10.5 units
  142. HIGH AOA test switch (green chevron illuminates)
    18 units
  143. Use High IOAT start procedure
    80° C
  144. time for starter switch MANUAL to cool IOAT or clear fuel after abort
    20 seconds
  145. minimum idle on ground
    60% N1
  146. Prohibited range of stabilized prop speed on ground (resonance)
    62-80% Np
  147. Np limit with PMU OFF during overspeed governor check
    100 +/- 2%
  148. Max Amps for takeoff
    Positive 50 Amps
  149. Radius for inside gear w/ NWS (0.0' with differential braking)
    15.5 feet
  150. Radius for nose wheel w/ NWS (8.3' with differential braking)
    18.0 feet
  151. Radius for outside gear w/ NWS (8.6' with differential braking)
    19.6 feet
  152. Radius of wingtip with NWS (21.0' with differential braking)
    33.2 feet
  153. setting to check engine instruments for T/O check
    25-30% torque
  154. 7-10° NH
    7-10° NH
  155. delay T/O behind and larger aircraft or helicopter for wake turbulence
    2 minutes
  156. add to rotation, threshold, and touchdown speeds
    1/2 gust factor up to 10 KIAS
  157. Climbout speed (160-180 for better forward visibility)
    140-180 KIAS
  158. OBOGS and Defog (Climb check)
    10,000'
  159. increase in ITT with defog on at any PCL setting
    40°C
  160. ITT limit as controlled by PMU
    820°C
  161. required pressure differential above 18,000' MSL
    3.6 +/- 0.2 psi
  162. max fuel imbalance for pre-stall, spinning, and aerobatics checks
    50 lbs
  163. speed and descent rate for enroute descent, 8000-11000 fpm acceptable with idle and speed brake
    200-250 KIAS, 4000 fpm
  164. recommended holding speed
    120-150 KIAS
  165. penetration descent parameters
    2000-4000 fpm 200-250 KIAS
  166. speed on instrument approach before configuring and during missed approach
    150 KIAS
  167. speed on instrument final configured flaps T/O
    110 KIAS
  168. speed on outside downwind (clean)
    200 KIAS
  169. speed on initial (USAF/USN)
    200 KIAS
  170. min speed on downwind (USAF)
    120 KIAS
  171. min speed in final turn (USAF/USN)
    110 KIAS
  172. speed on final with flaps LDG
    100 KIAS
  173. speed on final with flaps T/O
    105 KIAS
  174. speed on final with no flaps
    110 KIAS
  175. normal touchdown speed depending on flap setting
    75-105 KIAS
  176. braking above to be done with extreme caution
    80 KIAS
  177. check oil within after landing (should be MAX HOT), 15-20 minutes most accurate
    30 minutes
  178. max time to apply power to pitot/AOA heating elements on ground
    10 seconds
  179. time after touchdown that N1 transitions from flight idle to ground idle
    4 seconds
  180. min volume of MIL 85470 ice inhibitor to be added to fuel .5 pint/50 gal
    0.10 to 0.15%
  181. max slope approved for fueling
  182. time limit for LH and RH single point refueling precheck valves to shut
    10 seconds
  183. if wind is expected over this, consider hangaring aircraft
    80 knots
  184. max nose wheel deflection when towing (each side)
    80°
  185. Max ITT for start
    1000° C
  186. time for ITT to start rising after fuel flow
    10 seconds
  187. min speed to maintain while maneuvering to intercept ELP final (110 KIAS on final)
    120 KIAS
  188. N1 with engine flameout (speeds below 8% not indicated)
    0% within 5 seconds
  189. duration of Emer O2
    10 minutes
  190. airstart not recommended
    2000 ft AGL
  191. Airstarts have not been demonstrated above this
    20,000 ft MSL
  192. altitude lost during airstart
    1200 ft
  193. time to complete airstart sequence
    40 seconds
  194. target airspeed for airstart over 15,000' MSL
    135-200 KIAS
  195. target airspeed for airstart below 15,000' MSL
    125-200 KIAS
  196. time for prop to unfeather after N1 reaches 45%
    15-20 seconds
  197. PCL to idle for PMU off airstart (look for ITT rise w/in 10 seconds or abort
    13% N1
  198. initial fuel flow during airstart
    75-80 PPH
  199. expect to see this after airstart
    Above 30 amps
  200. time for starter to drain battery if left in manual
    10 minutes
  201. time for prop to unfeather after PROP SYS circuit breaker is pulled
    15-20 seconds
  202. indicates steady state spin
    120-135 KIAS and AOA>18
  203. time standby attitude indicator will provide accurate (+/- 6°) indications
    9 minutes
  204. time AUX bat provides power for SLUF
    30 minutes
  205. GEN considered inop
    <25 volts and ammeter discharge
  206. reading if BAT BUS fails
    0VDC and 0 Amps
  207. If fuel px falls below this boost pump comes on (If BP not on FUEL PX annunciator will illuminate)
    10 psi
  208. Max time with high pressure pump suction feeding
    10 hours
  209. Auto balance keeps wings within this limit
    20 lbs
  210. R/L FUEL LO annunciator
    110lbs 16 gallons
  211. Hydraulics can still function but slower and at reduced capacity
    1800-2880 psi
  212. min altitude for controllability check (if practical…)
    6000' AGL
  213. min speed during controllability check (or stick shaker, or max deflection)
    90 KIAS
  214. add to min controllable airspeed until on final
    20 KIAS
  215. landings have been demonstrated up to this speed (130 KIAS with flaps up)
    110 KIAS Flaps LDG
  216. add to high key, low key, and base key if PEL is accomplished at IDLE
    500'
  217. Touchdowns above this cause increased directional sensitivity and long landings
    100 KIAS
  218. Descend below with environment system/pressurization failure
    25,000' MSL
  219. Speed to attain with runaway trim
    110-150 KIAS
  220. stick pressure at approach speed with elevator trim failure at high speed cruise
    10 lbs
  221. stick pressure at approach speed with aileron trim failure at high speed cruise
    5 lbs
  222. stick pressure at approach speed with rudder trim failure at high speed cruise
    20 lbs
  223. Max speed with canopy shattered/damaged/unlocked
    150 KIAS
  224. Decompression above may trigger transient OBOGS FAIL as OBOGS transitions to providing oxygen at higher altitudes
    20,000' MSL
  225. Recommended min altitude for ejection (controlled)
    2,000' AGL
  226. Recommended min altitude for ejection (uncontrolled)
    6,000' AGL
  227. If terrain is above this altitude use MOR handle to deploy parachute
    >8,000' AGL
  228. Speed range for controlled ejection
    125-180 KIAS
  229. time til full chute for front seat ISS in BOTH (271 lb pilot 250 KIAS)
    4.37 seconds
  230. time til full chute rear seat ISS BOTH (271 lb pilot 250 KIAS)
    4.0 seconds
  231. Glide speed to High Key
    125 KIAS
  232. Min speed on ELP until intercepting final
    120 KIAS
  233. Min speed on ELP final
    110 KIAS
  234. ditch into the wind instead of parallel to the swells
    Wind >25 Knots
  235. VSI reading during glide @ 125 KIAS
    1350-1500 fpm
  236. High Key
    2500-3000' AGL
  237. Low Key
    1500' AGL
  238. Base Key
    600-800' AGL
  239. torque to set for ELP/PEL/to simulate zero thrust w/ feathered prop
    4-6%
  240. Min fuel to burn down to when landing with gear malfunction
    100lbs
  241. Maximum allowable airspeed (Vmo) <18,769' MSL
    VMO=316
  242. Vmo Above 18,769' MSL Vmo
    0.67 Mach
  243. Max torque for takeoff
    100%
  244. max torque transient for 20 seconds
    131%
  245. Maximum ITT for Takeoff
    820° C
  246. Maximum ITT idle
    750° C
  247. Maximum ITT for start (5 seconds)
    1000° C
  248. maximum transient ITT 20 seconds
    870° C
  249. Max N1
    104%
  250. Max Np (PMU off)
    100 +/- 2%
  251. Emergency Max Np
    110%
  252. Normal Oil pressure range
    90-120 psi
  253. max oil pressure during start
    200 psi
  254. transient oil pressure range during aerobatics and spins only
    40-130 psi
  255. Minimum oil pressure, at idle, aerobatics and spins only (5 seconds max)
    15 psi
  256. Normal oil temperature range
    10°-105° C
  257. Minimum oil temperature for start
    -40°C
  258. acceptable oil temperature, transient power, 10 minutes max
    106°-110°C
  259. Normal hydraulic pressure
    2880-3120 psi
  260. Starter duty cycle
    20 seconds
  261. cooling period before 2nd start attempt
    30 seconds
  262. cooling period before 3rd start attempt
    2 minutes
  263. cooling period before 4th start attempt
    5 minutes
  264. cooling period before duty cycle is reset
    30 minutes
  265. Gear/flap extension limit
    150 KIAS
  266. max turbulence airspeed
    195 KIAS
  267. recommended turbulence penetration speed
    180 KIAS
  268. Symmetric Vo (any full or abrupt control movements may damage control system
    227 KIAS
  269. Full rudder deflection limit
    150 KIAS
  270. Symmetric G limit clean
    7.0 to -3.5 gs
  271. Asymmetric G limit clean
    0 to +2.5 gs
  272. Symmetric G limit configured
    4.7gs to -1.0 gs
  273. Asymmetric G limit configured
    0 to +2.0 gs
  274. spins below prohibited due to PMU scheduling
    <10,000' Pressure Altitude
  275. spins above prohibited
    >22,000' Pressure Altitude
  276. either pilot and gear is over 260 lbs, if combined crew weight is over 500, if fuel exceeds 1100 lbs, and if baggage compartment is over 10 lbs.
    Check CG when
  277. Max ramp weight
    6550 lbs
  278. Max zero fuel weight
    5500 lbs
  279. Max rate of descent at touchdown when main gear are serviced to 185 +/- 5 psi
    600 fpm/3.7 Gs
  280. Max rate of descent at touchdown when main gear are serviced to 225 +/- 5 psi
    780 fpm/ 5.1 Gs
  281. Max crosswind dry
    25 knots
  282. Max crosswind wet
    10 knots
  283. Max crosswind icy/standing water
    5 knots
  284. Max tailwind for takeoffMax tailwind for takeoff
    10 knots
  285. aerobatics are prohibited
    <150 lbs per side
  286. max fuel imbalance
    50 lbs
  287. Max time for high pressure pump to suction feed (w/ no boost or low pressure pump)
    10 hours
  288. max ground ops temperature limitations
    -23°C to +43°C
  289. Apply equipment cooling chart page 5-14
    35°C
  290. Cockpit ΔP turns red and overpressurization safety valve opens
    4.0 psi
  291. Canopy wind limit
    40 knots
  292. Nude bodyweight range for ejection seat MKUS16LA
    103 lbs to 245 lbs
  293. Crew (with flight gear) weight range for ejection seat
    121 lbs to 271 lbs
  294. amount of feedback force (pitch axis) from bobweight
    9-12 lbs/G
  295. utilize half laeral stick inputs or less performing sustained G rolls
    >180 KIAS
  296. Best glide speed with gear down
    105 KIAS
  297. approximate VSI during glide with gear down
    1500 fpm
  298. Full right rudder and aileron may not prevent a left torque roll at stall
    >60% torque at low airspeeds
  299. altitude lost during 6 turn steady state spin
    4500'
  300. Best pitch for spin entry
    15°-20° NH
  301. Per turn of a spin
    2-3 seconds, 400-500' loss
  302. aggravated spin
    70° nose down, 280° per second
  303. planned altitude lost for spinning
    500' per turn, 1500-2000' dive
  304. windshear T/O and approach
    add up to 10 knots for
  305. Must be added to approach speed with icing accumulation
    10 knots
  306. operations in visible moisture should be avoided
    5°C and below
  307. with icing accumulation
    max of 30° bank and 0-2 gs
  308. hydroplaning can occur
    <0.1" of water
  309. maximum temperature of the transparency when heating for deicing
    150° F
  310. Nose wheel tire can hydroplane
    >85 knots
  311. Main gear can hydroplane
    >115 knots
  312. Power-up of digital instruments may shorten instrument service life
    If temp is below 21°C
  313. Ground power unit recommended for starts below this temp
    -18°C
  314. duration and diameter of microbursts
    2-5 minutes and 2 miles diameter
  315. severe windshear
    Airspeed change >15 knots; vertical speed change >500 fpm
  316. Standard day temp at sea level
    15°C (59°F)
  317. Standard day pressure at sea level
    29.921 inHg
  318. Dry runway
    23 RCR
  319. Wet runway
    12 RCR
  320. Icy/Standing water runway
    5 RCR
  321. Maximum brake energy absorption capability
    3.96 Million Ft-lbs
  322. Abort reaction time (3 sec decision, 3 sec application)
    6 seconds
  323. airspeed increase during 6 second abort time
    20 knots
  324. decrease in range with each 10 knots of headwind while gliding
    5%
  325. Max performance climb
    140 KIAS

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