By the numbers Flashcards
(318 cards)
1
Q
Empty weight
A
4900 lbs
2
Q
Max T/O gross weight
A
6500 lbs
3
Q
Max shaft horsepower
A
1100 SHP
4
Q
Shaft-torque at 100% indicated torque
A
2900 ft-lbs
5
Q
Pounds of thrust at sea level, zero airspeed
A
2750 lbs
6
Q
Propeller in low pitch (degrees from reference plane)
A
15 deg
7
Q
Propeller feathered (degrees from reference plane)
A
86 deg
8
Q
Altitude which 100% torque is available from seal level
A
12000’-16000’ MSL
9
Q
Oil capacity
A
18.5 quarts
10
Q
Time within which oil level must be serviced after shutdown
A
30 min
11
Q
Time within which oil readings are most accurate
A
15-20 min
12
Q
Level up to which the Oil Px indicator may read with engine shutdown (due to oil px tx design)
A
4 psi
13
Q
Red OIL PX annunciator with PCL above idle
A
40 psi or less
14
Q
Red OIL PX annunciator with PCL idle
A
15 psi or less
15
Q
Amber OIL PX annunciator with PCL above idle
A
40-90 psi for 10 sec or more
16
Q
Amber OIL PX annunciator with PCL idle
A
15-40 psi
17
Q
Red and amber OIL PX annunciators with PCL idle
A
15-40 psi for 5 sec or more
18
Q
Power turbine output shaft speed
A
30,000 RPM
19
Q
Propeller operating speed (100% Np)
A
2,000 RPM
20
Q
Prop size (aluminum)
A
97 in
21
Q
Mechanical overspeed governor limit with PMU functioning below 2120 RPM (%Np)
A
106% Np
22
Q
Mechanical overspeed governor limit with PMU not functioning/off at or below 2000 RPM
A
100% +/- 2% Np
23
Q
Ground mode at idle
A
60-61% N1
24
Q
Flight mode at idle
A
67% N1
25
Np at idle above 10000' PA MSL
80% Np
26
Voltage supplied to the PMU by the PMA
32 VAC
27
PMU automatically switches to 28 VDC battery bus
less than 40-50% Np
28
PMU auto abort start attempt if light-off has not occurred
10 sec
29
PMU will abort auto start attempt
940C for 2 sec
870C for 4 sec
840C for 19 sec
30
PMU will go offline (amber dashes in IOAT and ITT counters, removal ITT pointers, PMU FAIL)
>121C
31
N1 acceleration rate at which PMU will abort auto start attempt
<50%
32
Starter and igniters are deenergized during auto start
50% N1
33
PCL may be advanced to IDLE during auto start
60% N1 or greater
34
Max power increase with PMU off (low altitude cold conditions)
280 SHP
35
Maximum power decrease with PMU off
550 SHP
36
Time after Weight-on-Wheels activation for PMU status to illuminate for non-serious fault conditions
1 min
37
Firewall shutoff handle pull distance
2-2.5 in
38
Force required to pull CFS handle (both interior handle and exterior handle)
15-25 lbs
39
Usable fuel through single point refueling (530 lbs each side, 40 lbs collector tank)
1100 lbs
40
Usable fuel through over-the-wing refueling (580 lbs each side, 40 lbs collector tank)
1200 lbs
41
Ramp slope at which fuel is vented overboard through px relief valve
>1%
42
Difference between tanks which the fuel auto-balance system maintains
<20 lbs
43
Amount and time for auto-fuel balancing
>20 lbs for 30 sec
44
FUEL BAL illuminates and auto-balance shuts off
30 lbs within 2 min
45
Red FUEL PX annunciator illuminates
<10 psi
46
Amber L FUEL LO and R FUEL LO annunciators illuminate
110 lbs
47
Number of fuel probes
7
48
Outboard fuel probes read to
445 +/- 50 lbs
49
Middle fuel probes read
308 +/- 50 lbs
50
Inboard fuel probes read
20 lbs
51
Max time provided by fuel system for inverted flight
15 sec
52
Starter/Generator
28 VDC, 300 A
53
Battery
24 VDC, 42 AHr
54
Aux battery
24 VDC, 5 AHr
55
Min volts supplied by generator required to charge the battery
25 VDC or greater
56
Battery volts at which external power should not be connected
22 VDC or less
57
Time provided by battery to power all items on the battery bus
~30 min
58
Number of hydraulic master cylinders for brake system
2
59
Hydraulic system fluid capacity
5 quarts
60
Pressure relief valve for primary hydraulic system
3250-3500 psi
61
Normal hydraulic pressure
3000 +/- 120 psi
62
Min hydraulic pressure needed to power components
1800 psi
63
Amber HYDR FL LO annunciator illuminates for primary Hydr system
<1 quart
64
Amber EHYD FL LO annunciator illuminates for emergency accumulator
2400 +/- 150 psi
65
Restricted flow rate to emergency hydr accumulator
> 0.25 GPM
66
Hydraulic fluid loss limit by the hydraulic fuse
20-30 cu-in (0.5 qts)
67
Normal gear extension/retraction
6 sec
68
PCL mid range position
87% N1
69
Nose wheel turn limits (degrees)
+/- 80 (160 total)
70
Takeoff flaps extension (degrees)
23
71
Landing flaps extension (degrees)
50
72
Speed brake extension (degrees)
70
73
Aileron travel limits (degrees)
20 up/11 down
74
Aileron trim travel limits (degrees)
+/-6
75
Ground adjustable aileron trim tab travel limits (degrees)
20 up/8 down
76
Elevator travel limits (degrees)
18 up/ 16 down
77
Elevator trim tab travel limits (degrees)
5.5 up/22 down
78
Rudder travel limits (degrees)
24 left/right
79
Rudder trim tab travel limits (degrees)
9 left/right
80
Rudder pedal adjustment forward to aft
7 in
81
After TO trim is set, TAD provides further trim reaching this speed and Weight-Off-Wheels
80 KIAS
82
Standby attitude indicator accuracy with complete power loss
6 deg for 9 min
83
Mach information is blank below
0.40 Mach
84
Standby airspeed indicator range
6-35 (x10) Mach
85
Accelerometer deisplay range
-6 to +10 G
86
Accelerometer tolerance
+/- 0.25 G
87
Allowable difference between accelerometers in front and rear cockpit
<1 G
88
Stall AoA
18 units
89
Stick shaker activated by AoA computer
15-16 units
90
Normal approach speed AoA (1.3 times stall speed)
10-11 units
91
Max endurance AoA (white diamond)
8.8 units
92
Max range AoA (white triangle)
4.9 units
93
Optimum approach airspeed (amber donut) for gear down, flaps LDG, 3 deg approach
100 KIAS
94
Optimum approach speed decrease versus fuel used
1 knot for 100 lbs
95
Stick shaker above stall speed
5-10 knots
96
Windscreen and front transparency bird strike limits
4 lbs/270 KIAS
97
Gap below canopy when propped open using the canopy prop strut for minimal ventilation
~4 in
98
Tire Wear Criteria Main Gear Local
Red cord visible
99
Tire Wear Criteria Main Gear out and back or cross country
Main gear >3 cords visible
100
Tire Wear Criteria Nose Gear any sortie
Worn to bottom of center tread groove
101
Ops Weather Recall Recovery Airspeed
250 KIAS
102
Major injury rate of ejection seat defined as low risk
5-10%
103
Ejection seat capable of providing safe ejection
0-35000' MSL, 0-370 KIAS
104
Ejection seat/pilot separation and parachute deployment delay (MSL)
14000'-16000' MSL
105
Altitude of mountainous terrain over which the MOR handle should be used
8000' MSL
106
Emergency oxygen system supply (or until seap separation)
10 min
107
Minimum emergency oxygen cylinder pressure at 70F
1800 psi
108
Black band on emergency oxygen cylinder
1800-2500 psi
109
Change in min pressure for each degree above/below 70F
+/- 3.5 psi
110
Timer to allow shoulder harness activation
0.17 sec
111
Front seat ejection delay with ISS BOTH
0.37 sec
112
SSK lowered after seat/pilot separation
4-6 sec
113
Length of nylon lowering line for the SSK
12 ft
114
Inflow valve (bleed air) automatically closed with A/C on (regardless of position of BLEED AIR INFLOW switch)
7500 MSL
115
Amber DUCT TEMP annunciator (ECS)
300F or greater
116
Anti-G system safety valve pressure relief level
>7 psig
117
Temperature range that is maintained with the TEMP CONTROL set to AUTO
60-90F
118
Heat exchanger bypass valve is moved to full close (ECS)
>165F
119
Time for closing of defog valve
up to 40 sec
120
Reduction in climb performance that can be observed for flaps UP with DEFOG ON and PCL retarded to keep ITT within limits
up to 47%
121
Voltage applied to dump solenoid (required power to close)
28 VDC
122
Altitude at which 3.6 +/- 0.2 pressure differential is reached
18069' MSL
123
Cockpit pressure altitude at 31000' MSL
16600'
124
Amber CKPT ALT annunciator
19000'
125
Red CKPT PX annunciator
3.9 - 4.0 psi
126
EVAP BLOWER flow rate at HI setting
350 cu-ft-per-min
127
RMU cursor automatically reverts to top field after
20 sec
128
RMU direct tuning and transponder memory recall (press and hold)
>3 sec
129
UHF/VHF & backup UHF memory capacity
20 frequencies
130
NAV memory capacity
10 frequencies
131
ELT transmission duration (battery powered)
50 hrs
132
EADI unusual attitude declutter
> +30, -20, 65 bank
133
EADI unusual attitude recovery (red chevrons)
40-90 deg
134
Time it normally takes for attitude/heading display error (precession) to correct while straight and level
<1 min
135
Time it normally takes for attitude/heading display error (precession) to correct while straight and level in extreme cases
2 min
136
Heading error during normal SLVD operation that will cause HDG flag on EHSI
>10 deg for 5 min
137
EHSI VOR CDI 1 dot
5 deg
138
EHSI localizer and glideslope 1 dot (width of localizer glideslope)
0.25 x width of localizer
139
EHSI GPS EN ROUTE, APR ARM, APR ACT 1 dot
2.5, 0.5, 0.15 NM
140
NACWS upward/downward pointing triangle WITH vertical separation displayed
+/- 400-900'
141
NACWS upward/downward pointing triangle WITHOUT vertical separation displayed
+/- 1000-2700'
142
NACWS rectangle
+/- 300' or less
143
TAS normal mode range
+/- 2700'
144
TAS above mode range
+8700' to -2700'
145
TAS below mode range
+2700' to -8700'
146
TAS tracking range/altitude
40NM, 10000'
147
of GPS flight plans
25
148
GPS waypoints per flight plan
30
149
GPS will flash prior to beginning of turn anticipation for waypoint
20 sec
150
Extension of kneeboard lights that interfere with ejection envelope in FCP/RCP respectively
0.568in/0.102in
151
IDARS memory level when Green FDR MAINT illuminates
80%
152
Aux bat capacity when light does not illuminate during aux bat test
<50%
153
Aural tones are inaudible during engine start at
greater than 50% N1
154
OBOGS warmup time when OBOGS FAIL light will be inhibited
3 min
155
Amber OBOGs TEMP annunciator
200F or greater
156
O2 concentration in NORMAL from sea level to 15000' MSL
25-70%
157
O2 concentration in NORMAL from 15000' to 31000' MSL
45-95%
158
O2 concentration in MAX
95%
159
Time of O2 concentration dropped below normal for OBOGS FAIL
~20-30 sec
160
Max weight in baggage compartment
80 lbs
161
External power voltage requirement
28.0-28.5 VDC
162
External power continuous current requirement
300 A
163
Acceptable external power voltage limits for off-station engine starts
24.0-29.5 VDC
164
Main gear tire pressure (max)
225 +/- 5 lbs
165
Main gear tire pressure
185 +/- 5 lbs
166
Nose wheel tire pressure
120 +/- 5 lbs
167
Wind speed at which aircraft should be moved to hangar
>80 knots
168
Engine oil fully serviced
4.5 Gal
169
Hydraulic fluid fully serviced
1.25 Gal
170
Brake fluid fully serviced
0.5 pint
171
Air conditioning refrigerant fully serviced
3.1 lbs
172
Main gear min strut extension
2 in
173
Nose gear min strut extension
2.5 in
174
PMU defaults to 121C for all PMU functions (including IOAT display)
>96C
175
PMU flags IOAT signal, loses ability to calculate ITT, goes offline
>121C
176
Idle with PMU off
60-70% N1
177
Time which ST READY light should be illuminated before starting the engine
3 sec
178
Wingtip turn radius using NWS
33.2 ft
179
Wingtip turn radius using differential breaking
21.0 ft
180
Static runup torque setting
25-30%
181
Climb airspeed
140-180 KIAS
182
Min time before taking off behind large aircraft or helicopter
2 min
183
Rotation nose high (degrees)
7-10
184
Increase in ITT with canopy defog on
40C
185
PMU may reduce power to maintain ITT below____
820C
186
Recommended enroute descent rate
200-250 kts & 4000 fpm
187
Airspeed and slip deflection for alleviating icing accumulation on rudder centering spring
less than or equal to 170 KIAS or less & one ball
188
Recommended holding speed in clean configuration but no slower than maximum endurance AOA
120-150 KIAS
189
Time it takes for N1 to switch from flight to ground idle
4 sec
190
Anticipate increased brake sensitivity above
80 KIAS
191
Climb angle for zoom to eject
20 deg
192
Altitude gained during zoom to eject
200 ft
193
Zoom (above 150 KIAS)
2G/20 deg
194
Push over during zoom (20 KIAS lead point)
0 to +0.5 G
195
Zoom capability at 200 KIAS
600-900 ft
196
Zoom capability at 250 KIAS
1170-1550 ft
197
Useable torque (creates thrust)
>6%
198
Indicated N1 reads 0%
<8% N1
199
Altitude and time to complete the starting sequence before attaining useable power
1200 ft, 40 sec
200
Air start envelope from sea level to 15000' (airspeed)
125-200 KIAS
201
Air start envelope from 15001'-20000' (airspeed)
135-200 KIAS
202
Abort airstart if no ITT rise after fuel flow indications within
10 sec
203
Abort airstart if no N1 rise within
5 sec
204
For airstart, after N1 reaches airborne IDLE, set PCL as required
67% N1
205
Increased ITT during airstart with bleed air inflow switch in NORM or HI
40C
206
Amperage reading after airstart
>30 amps
207
Time it takes for starter to drain batter if left in MANUAL
10 min
208
Initial fuel flow during airstart
75-80 PPH
209
Time it takes for prop to feather after pulling prop sys circuit breaker
15-20 sec
210
Usual duration of fluctuations during prop sleeve touchdown
<20 sec
211
Np considered stable if below 40% with no upward change for
3 sec
212
Oil pressure <5 psi and OIL PX annunciator
check OIL TRX circuit breaker
213
Generator inoperative indications
<25 VDC and (-) amps
214
Volts which generator and batt bus will remain powered until bus tie closed and gen inop
16 VDC
215
Volts which EADI and EHSI will go offline with gen inop and bus tie closed
22 VDC
216
Required time of power interruption for resetting AHRS via circuit breaker
>0.5 sec
217
Time needed for the aircraft to be straight and level during AHRS alignment
30 sec
218
Engine operation with high pressure suction feeding total time
10 hrs
219
Min speed for controllability check
90 KIAS or stick shaker
220
Max touchdown speed at which landings with flaps LDG have been accomplished
110 KIAS
221
Max touchdown speed at which landing with flaps UP have been accomplished
130 KIAS
222
Time to wait for resetting AHRS/TAD circuit breaker
15 sec or less
223
Rapid decompression may result in transient OBOGS FAIL at (altitude)
20000' MSL
224
Time it takes from ejection handle being pulled to full chute (+0.37 for FCP when ISS BOTH)
4 sec
225
Min recommended uncontrolled ejection
6000' AGL
226
Min recommended controlled ejection
2000' AGL
227
Max sink rate for ejection
10,000 fpm
228
Do not attempt battery powered ground start
<23.5 V
229
Do not connect external power (battery volts)
<22.0 V
230
AOA green arc (on approach)
10-11 units
231
AOA red arc (stall)
18 units
232
Max N1
104%
233
Generator limitation (amps inflight)
+50 to -2 amps
234
Generator limitation (volts ground/inflight)
28.0-28.5 V
235
Battery power degraded when generator less than
25.0 V
236
Max IOAT for start
80C
237
Propeller overspeed limit
110% Np
238
Max operating speed is 316 KIAS up to this altitude and 0.67 Mach above this altitude
18769' MSL
239
Max airspeed through turbulence
195 KIAS
240
Recommened airspeed through turbulent air
180 KIAS
241
Operating maneuvering speed (Vo)
227 KIAS
242
Full rudder deflection above this airspeed exceeds the limits for the rudder control system
>150 KIAS
243
G-meter tolerances
+0.25G to -0.25G
244
Max time inverted
15 sec
245
Max time intentional zero-G
5 sec
246
Max bank angle change for uncoordinated rolling maneuver at -1G
180 deg
247
Solo or rear pilot weight with gear, check CG limits
>260 lbs
248
Combined crew weight with gear, check CG limits
>500 lbs
249
Overwing refueling, check CG limits
>1100 lbs
250
Baggage weight, check CG limits
>10 lbs
251
Max ramp weight
6550 lbs
252
Max TO/LDG weight
6500 lbs
253
Max rate of descent at touchdown when main tires serviced to normal landing conditions px (185 +/-5 lbs)
600 fpm (3.7 Gs)
254
Max zero fuel weight
5500 lbs
255
Max rate of descent at touchdown when main tires serviced to maximum landing conditions px (225 +/- 5 lbs)
780 fpm (5.1 Gs)
256
Max crosswind component for flaps LDG takeoff
10 knots
257
Approved fuels in the T-6 (see also N-25 in checklist)
JP-4, JP-5, JP-8/JP-8+100, Jet-A/Jet A+100, Jet A-1, Jet B
258
Maneuver limitation with ice accumulation
30 deg bank/0 to +2 Gs
259
Final approach speed must be increased by with ice accumulation
10 KIAS
260
Ground operation ambient temp limits
-23 to 43C
261
Cockpit Delta P changes to red and over pressurization safety valve opens
4.0 psi
262
Ejection seat weight limitations with gear
121 to 271 lbs
263
Ejection seat weight limitations nude
103 to 245 lbs
264
Pitch force during maneuvering flight conditions at aft centers of gravity
9lbs per G
265
Pitch force during maneuvering flight conditions at forward centers of gravity
12 lbs per G
266
Best glide airspeed in clean configuration (sink rate of 1350 fpm)
125 KIAS
267
Best glide airspeed with gear down and flaps up (sink rate of 1500 fpm)
105 KIAS
268
Min airspeed above stall at which the stick shaker activates in both cockpits
5 knots
269
Airspeed margin above stall for the artificial stall warning during power-off, unaccelerated conditions
5-10 knots
270
Airspeed above stall which natural light aerodynamic buffeting typically occurs (all configurations)
3 knots
271
Full rudder and right aileron may not prevent a left roll-off at stall above (torque setting)
60%
272
Do not sustain heavy buffeting during an accelerated stall above (G's)
3 G's
273
Altitude loss during a typical steady-state six turn spin
4500'
274
Nose high attitude above which spin entry may result in low oil pressure and engine damage
50 deg
275
Duration per turn for an erect spin
2-3 sec
276
Altitude loss between each turn for an erect spin
400-500 ft
277
Airspeed (stabilized) during an erect spin
120-135 KIAS
278
Airspeed reading during an inverted spin
40 KIAS
279
Airspeed or vertical speed changes considered to be windshear (knots/fpm)
15 knots or 500 fpm
280
Typical duration of a microburst
2-5 min
281
Typical diameter of a microburst
2 mi
282
Vertical speed which microburst downdrafts can exceed
6000 fpm
283
Max temp for heating the canopy transparency when deicing
150F
284
Time within which the aircraft must be thoroughly rinsed after exposure to deicing agent
48 hrs
285
Outside air temp where icing may occur
<= 5C
286
Amount to increase approach speed under ice accumulation conditions
10 knots
287
Amount of slush or water in which hydroplaning may occur
less than 0.1 in
288
Airspeed at which hydroplaning on the nose tire may occur (normal tire pressure)
85 knots or greater
289
Airspeed at which hydroplaning on the main tires may occur (normal tire pressure)
115 knots or greater
290
Preheating is recommended prior to engine start (outside air temp)
< -29C
291
Limit of higher amp draws observed during engine starts in extremely cold temperatures
-50A
292
External power is recommended for engine start (outside air temp)
< -18C
293
Initial power up of digital instruments may shorten instrument service life below (temp)
-21C
294
Standard day density of JP-8 fuel
6.8 lbs/gal
295
Critical altitude (alt at which 100% torque is no longer available with PCL MAX)
16000' MSL
296
Max Climb Power is the PCL setting which yields an ITT ____ below observed max power ITT at critical altitude; not to exceed 807C.
13C
297
Max Cruise Power is the PCL setting which yields ITT ____ below observed max power ITT at critical altitude; not to exceed 780C
40C
298
RCR range (2 being min braking friction coefficient)
2-26
299
RCR Dry
23
300
RCR Wet
12
301
RCR Icy
5
302
Max design energy absorption capability of the brakes
3.96 million ft-lbs
303
Total abort reaction time to first recognize and select idle power (3 sec) and then apply brakes (3 sec)
6 sec
304
Increase in speed during the 6 sec abort period
20 knots
305
Amount of gust factor to increase TO/LDG speeds with gusty winds
50% up to 10 knots
306
Amount to add to charted takeoff distance for a Formation Wing Takeoff (assuming lead power setting of no less than 85%)
1000'
307
Drag Index for Landing Gear Retracted, Flaps Retracted (gear UP, flaps UP)
0
308
Drag Index for Landing Gear Extended, Flaps Retracted (gear DOWN, flaps UP)
20
309
Drag Index for Landing Gear Extended, Flaps LDG (gear UP, flaps LDG)
80
310
Amount to decrease Diversion range by for every 10 knots of headwind with Drag Index of 0
5%
311
Amount to decrease Diversion range by for every 10 knots of headwind with Drag Index of 20
7%
312
Amount to decrease Diversion range by for every 10 knots of headwind with Drag Index of 80
8%
313
Enroute descent rate (set power and configuration as required)
4000 fpm (attain 220 KIAS)
314
Max range descent rate (set power as required)
1500 fpm (attain 180 KIAS)
315
Penetration descent airspeed (IDLE power, gear and flaps retracted, speed brake extended)
250 KIAS/0.67 IMN max
316
Rapid descent airspeed (IDLE power, gear and flaps retracted, speed brake extended)
316 KIAS/0.67 IMN max
317
Time and fuel allowances for a normal go-around
5 min and 60 lbs of fuel
318
Assumed delay from touchdown to initiation of braking for the calculation of Landing Distance
2 sec
