T-6 By the Numbers Flashcards
1
Q
Empty weight
A
4900 lbs
2
Q
Max takeoff weight
A
6500 lbs
3
Q
Max Shaft Horsepower
A
1100
4
Q
oil capacity
A
18.5 quarts
5
Q
OIL PX annunciator with PCL above idle (PSI)
A
40 psi
6
Q
OIL PX annunciator with PCL at idle (PSI)
A
15 psi
7
Q
turbine output shaft speed
A
30,000 RPM
8
Q
prop operating speed
A
2000 RPM
9
Q
ground mode at idle (N1)
A
60% N1
10
Q
flight mode at idle (N1)
A
67% N1
11
Q
PMU managed minimum above 10K (N1)
A
80% N1
12
Q
ignition and boost pump deactivated during auto start (N1)
A
50% N1
13
Q
fuel pressure switch limit, turns on BP
A
10 psi
14
Q
manual motor after aborted start/inverted flight time limit
A
20 seconds
15
Q
normal wing tank capacity
A
530 lbs
16
Q
collector tank capacity
A
40 lbs
17
Q
SPR refueled full fuel load
A
1100 lbs
18
Q
over wing refueled full fuel load
A
1200 lbs
19
Q
(for 2 minutes) imbalance where FUEL BAL annunciator illuminated
A
30 lbs
20
Q
auto fuel balance tolerance
A
20 lbs
21
Q
middle fuel probe reading
A
445 (+ 50) lbs
22
Q
inner fuel probe reading
A
308 (+ 50) lbs
23
Q
collector tank pressurized at ___ PSI by transfer jet pumps
A
1 to 1.5 psi
24
Q
L or R FUEL LO annunciator illuminated
A
110 lbs
25
starter/generator output
28 VDC (300 amp)
26
main battery output
24 VDC (42A HR)
27
aux battery output
24 VDC (5 A HR)
28
hydraulic pressure
3000 psi
29
hydraulic system total capacity
1.25 gal
30
hydraulic reservoir capacity
0.6 gal
31
min hydraulic pressure to operate NW steering, gear, flaps, speed brake
1800 psi
32
fuel pressure supplied by engine driven low pressure fuel pump
40 psi
33
fuel pressure supplied by engine driven high pressure fuel pump
700 psi
34
max hydraulic volume allowed past the hydraulic fuse
45 cubic inches
35
hydraulic pressure relief valve opens
3250 to 3500 psi
36
EHYD PX LO annunciator illuminates
2400 (+ 150) psi
37
HYDR FL LO annunciator illuminates
1 qt
38
normal gear extension/retraction time
6 seconds
39
Below ___ %N1 gear warning horn sounds if A/S is below 120
87% N1
40
NWS range
24°
41
flap deflection in TO
23°
42
flap deflection in LDG
50°
43
speed brake deflection when deployed
70°
44
TAD active with no weight on wheels
80 knots
45
Below this Mach is blanked on A/S ind
0.40 Mach
46
stall AOA
18 units
47
on speed AOA
10-11 units
48
max endurance AOA
8.8 units
49
max range AOA
4.9 units
50
Optimum approach speed decrease rate
1 knot/100 lbs
51
Max velocity in level flight at sea level (thrust limited)
255 KIAS
52
Optimum max range AOA altitude
25,000' MSL
53
Pre-stall stick shaker
5 - 10 kts (15.5 units)
54
Ejection seat limits
0'/0 KIAS to 35,000'/370 KIAS
55
Automatic seat man separation altitude
14,000' to 16,000' MSL
56
ISS BOTH rear seat ejection delay
0.37 seconds
57
altitude where bleed air inflow is prevented with A/C clutch engaged
<7500' MSL
58
automatically maintained pressure until 18,069' MSL (3.6 + 0.1 psid)
8000' cockpit P/A
59
CKPT ALT annunciator illuminated
19,000' cockpit P/A
60
CKPT PX annunciator illuminated
3.9 + 0.1 psid
61
DUCT TEMP annunciator illuminated
300° F
62
RMU cursor automatically reverts to UHF field
20 seconds
63
UHF/VHF memory
20 frequencies
64
NAV memory
10 frequencies
65
ELT transmission limit (battery limited)
50 hours
66
EADI declutters
> +30°/-20° pitch or 65° roll
67
Full EADI presentation reappears after unusual attitude
< +25°/-15° pitch and 60° roll
68
GPS self test indications
34.5 NM, 315 DTK, 130° bearing
69
GPS user defined waypoints
250
70
GPS stored flightplans
25
71
max waypoints per flight plan
30
72
flash prior to turn to next waypoint
20 seconds
73
CDI full scale deflection, enroute mode
#ERROR!
74
CDI full scale deflection, approach arm
#ERROR!
75
CDI full scale deflection, approach active
#ERROR!
76
Approach arm
30 NM
77
Approach active
2 NM
78
FDR annunciator illuminates
80% full
79
AUX BAT test light will not illuminate
<50% capacity
80
OBOGS TEMP annunciator illuminates
200° F
81
NORMAL OBOGS O2 concentration, sea level to 15,000' MSL
25% to 70%
82
NORMAL OBOGS O2 concentration, 15,000' to 31,000' MSL
45% to 95%
83
O2 concentration, MAX selected
94.5% (95%)
84
OBOGS warm-up time (after engine start)
3 minutes
85
OBOGS FAIL annunciator extinguishes during BIT test
86
baggage compartment weight limit
80 lbs
87
max weight of bags and pubs on glareshield
8.5 lbs
88
icing inhibitor mix
.5 pint/ 50 gal fuel
89
external power requirements
28 to 28.5 VDC/1000 to 1500 Amps
90
main gear tire pressure
225 +- 5 psi
91
nose wheel tire pressure
120 +- 5 psi
92
Number of static wicks
17 - 4 on each wing, 6 on elevator, 3 on rudder
93
sufficient battery voltage for start
23.5 VDC
94
Minimum main gear strut extension
2.0 inches
95
Minimum nose gear strut extension
2.5 inches
96
delay between ejections w/ISS in both
0.37 second
97
LOW AOA (amber donut)
10.5 units
98
HIGH AOA (green chevron)
18 units
99
PMU IOAT limit for start
121 degrees C
100
use HIGH IOAT START procedure
80 degrees C
101
time for STARTER SWITCH MANUAL to cool IOAT or clear residual fuel
20 seconds
102
stay clear area distance from aircraft with engine running
3 feet
103
minimum idle on ground (N1)
60% N1
104
maximum icing limits
5000 feet of light rime (probes anti ice on whenever in visible moisture)
105
prohibited range of stabilized prop speed on the ground
62-80% Np
106
idle with PMU off during overspeed gov check (N1)
67% N1
107
NP when at approximately 30% torque during overspeed gov check
100%
108
NP limit with PMU off during overspeed gov check
100 + -2%
109
max amps limit for T/O
#ERROR!
110
radius for inside gear w/NWS (0.0 feet w/differential braking)
15.5 feet
111
radius for nose wheel w/NWS (8.3 feet w/differential braking)
18.0 feet
112
radius for outside gear w/NWS (8.6 feet w/differential braking)
19.6 feet
113
radius for wingtip w/NWS (21.0 feet w/differential braking)
33.2 feet
114
Torque setting to check engine instruments for T/O check
25-30% torque
115
degrees nose up for rotation
7-10
116
gusty wind T/O correction
½ gust factor (up to 10 knots)
117
climbout speed (160-180 KIAS for better forward visibility in climb)
140 KIAS
118
climbout pitch attitude
10-15 degrees NH
119
pitch and speed for obstacle clearance climb
15 degrees nose high and 140 KIAS
120
Passing through ___ feet, check OBOGS and defog
10,000 feet
121
increase in ITT w/defog on at any PCL setting
40 degrees C
122
ITT limit as controlled by PMU
820 degrees C
123
required pressure differential above 18,000 feet MSL
3.6 + 0.2 psi
124
max fuel imbalance for pre-stall, spinning and aerobatic checks
50 lbs
125
recommended holding speed
120 - 150 KIAS
126
speed on instrument approach before configuring and during missed approach
150 KIAS
127
speed on instrument final w/gear and flaps T/O
110 KIAS
128
speed on outside downwind (clean)
200 KIAS
129
speed on initial (USAF/USN)
200 KIAS
130
min speed on downwind (USAF)
120 KIAS
131
min speed in final turn (USAF/USN)
110 KIAS
132
speed on final with full flaps (USAF/USN)
100 KIAS
133
speed on final with T/O flaps (USAF/USN)
105 KIAS
134
speed on final with no flaps (USAF/USN)
110 KIAS
135
gusty wind threshold and touchdown speeds
½ gust factor (up to 10 knots)
136
normal touchdown speed (depending on flap setting)
80-95 KIAS
137
braking above ___ KIAS to be done with great caution
80 KIAS
138
check oil within ___ after landing to be max hot
30 minutes
139
max time to apply power to pitot/AOA heating elements on ground
10 seconds
140
min volume of MIL 85470 ice inhibitor to be added to fuel (½ pint/50 gal)
0.1-0.15%
141
max slope approved for fueling
3 degrees
142
time limit for LH and RH single point refueling precheck valves to shut
10 seconds
143
wind speed to consider hangaring A/C
80 knots
144
max nose wheel deflection while towing
80 degrees
145
max ITT for start
1000 degrees C
146
time for ITT to start rising after fuel flow indication during start
10 seconds
147
altitude/airspeed parameters for ejection seat
0/0
148
minimum speed to maintain while maneuvering to intercept ELP
120 KIAS
149
N1 with engine flameout (speeds below 8% not indicated)
0% within 5 seconds
150
engine out glide speed
125 KIAS
151
duration of emergency O2
10 minutes
152
consider rapid descent above this altitude if using emer O2 to prevent depletion
20,000 MSL
153
airstart not recommended below
2000 feet AGL
154
airstarts are demonstrated below
20,000 feet MSL
155
altitude lost during airstart procedure (at 125 KIAS glide)
1200 feet
156
time to complete airstart sequence
40 seconds
157
airstart envelope (above 15,000 feet MSL)
135-200 KIAS
158
airstart envelope (at or below 15,000 feet MSL)
125-200 KIAS
159
time for prop to unfeather after N1 reaches approximately 45%
15-20 seconds
160
PCL to idle for PMU off airstart (look for ITT rise w/in 10 seconds or abort)
13% N1
161
initial fuel flow during airstart
75- 80 PPH
162
amp reading after airstart
Above 30 Amps
163
time for starter to drain battery if generator is not reset
10 minutes
164
time for prop to come out of feather after prop sys CB is pulled
15-20 seconds
165
minimum altitude uncontrolled ejection
6000 feet AGL
166
___ to ___ KIAS and AOA 18+ indicate a steady state spin
120 - 135
167
time standby attitude indicator will provide accurate info after loss of power
9 minutes
168
time aux battery provides stby instruments/lighting, fire 1 and standby UHF
30 minutes
169
normal sustained oil pressure limits
90-120 psi
170
time battery will last with bus tie open
30 minutes
171
Electrical readings indicating generator is inoperative
25 volts and ammeter discharging
172
reading if battery bus fails
0 volts 0 amps
173
engine feed fuel pressure below ___ PSI causes boost pump to automatically engage
10 psi
174
max engine time with high pressure fuel pump suction feeding
10 hours
175
auto fuel balancing keeps fuel balance within
20 lbs
176
More than ____ fuel imbalance for two minutes triggers FUEL BAL light (fault in auto system)
30 lbs
177
level of fuel that triggers L or R FUEL LO annunciator
110 lbs (16 gallons)
178
EHYD PX LO light illuminates below
2400 + 150 psi
179
HYDR FL LO light illuminates below
1 qt
180
pressure hydraulic system functions at a reduced capacity & speed
1800 psi - 2880 psi
181
hydraulic pressure within green arc
2880-3120 psi
182
minimum altitude for controllability check
6000 ft AGL
183
minimum speed during Controllability check (or stick shaker or max deflection)
90 KIAS
184
add ___ KIAS to minimum controllable speed on final with structural damage
20 KIAS
185
touchdowns in landing configuration have been accomplished up to ___ KIAS
110 KIAS
186
touchdowns above ___ KIAS cause increased directional sensitivity & longer landing
100 KIAS
187
in environmental systems or defog duct triggers the DUCT TEMP light
300 degrees F
188
descend below with environmental system/pressurization failure
25,000 feet MSL
189
speed to attain with runaway trim
110-150 KIAS
190
stick pressure at approach speed with elevator trim failure at high speed cruise
10 lbs
191
stick pressure at approach speed with aileron trim failure at high speed cruise
5 lbs
192
stick pressure at approach speed with rudder trim failure at high speed cruise
20 lbs
193
max speed with canopy shattered/damaged/gone or CANOPY light on
150 KIAS
194
CKPT PX light illuminates with this pressure differential
3.9+ 0.1 psi
195
cabin alt triggers CKPT ALT annunciator
19,000 MSL
196
decompression above___ feet may trigger OBOGS light due to mode compensation
20,000 feet MSL
197
AGL altitude to use MOR handle to deploy parachute & separate from seat in mtns.
8,000 feet AGL
198
speed range for controlled ejection
125-180 KIAS
199
Ejection seat time to full chute
4.37 sec (FRONT)/4.00 sec (REAR)
200
min ejection altitude with 90 degree dive and 250 KIAS
850 feet AGL
201
min ejection altitude inverted (level flight) with 250 KIAS
180 feet AGL
202
For each 1000 ft MSL of altitude add ___to minimum ejection numbers for additional terrain clearance
Add 1%
203
ejection seat chart not accurate above ___
8000 feet MSL
204
glide speed to high key
125 KIAS
205
min speed until intercepting final on ELP
120 KIAS
206
min speed on final during ELP
110 KIAS
207
Above ___ knots ditch into the wind instead of parallel the swells
25
208
add ___ feet to high, low, and base key with engine in idle due to no feathering
500 feet
209
max descent rate for 125 KIAS glide, 4-6% torque, clean.
1350 fpm
210
high key altitude
3000 feet AGL
211
low key altitude
1500 feel AGL
212
base key altitude
600-800 feet AGL
213
max time inverted flight
15 seconds
214
max time zero G flight
5 sec
215
torque to set for ELP, PEL, or to simulate zero thrust
4-6%
216
minimum fuel to burn down to for landing with gear malfunction
100 lbs
217
If no rise in ITT ___ seconds after fuel flow indications, place PCL off and abort start
10
218
approximate idle for PMU off ground start (N1)
67% N1
219
PCL in idle before ___ N1 during manual start may cause engine damage/overtemp
60% N1
220
FUEL PX light illuminates
<10 psi fuel px
221
OIL PX light illuminates
<40 psi above idle or 15 psi at idle
222
OBOGS TEMP light illuminates
200 degrees F
223
MAINT FDR light illuminates
80% memory full
224
Maximum allowable airspeed
316 KIAS/0.67 Mach
225
Maximum torque for T/O
100%
226
Maximum torque transient for 20 seconds
131%
227
Maximum ITT for T/O
820° C
228
Maximum ITT idle
750° C
229
Max ITT for start (5 seconds)
1000° C
230
Max transient ITT (20 seconds)
870° C
231
Max N1
104%
232
Max Np, PMU off
100 + 2 %
233
Emergency Max Np
110%
234
Normal oil pressure range
90 - 120 psi
235
Max oil pressure during start
200 psi
236
Transient oil pressure range, aerobatics and spins only
40 - 130 psi
237
Minimum oil pressure, at idle, aerobatics and spins only (5 seconds max)
15 psi
238
Normal oil temperature range
10° to 105° C
239
Min oil temperature for start
-40° C
240
Acceptable oil temperature, transient power, 10 minutes max
106° - 110° C
241
Normal hydraulic pressure
1800 - 3000 psi
242
starter duty cycle
20 seconds
243
cooling period before second start attempt
30 seconds
244
cooling period before third start attempt
2 minutes
245
cooling period before fourth start attempt
5 minutes
246
cooling period before fifth start attempt
30 minutes
247
gear/flap extension airspeed limit
150 KIAS
248
Max turbulence penetration A/S
195 KIAS
249
Symmetric Vo (operating maneuvering speed)
227 KIAS
250
Asymmetric Vo 5 seconds
177 KIAS
251
Symmetric, clean G limits
-3.5 to 7.0 G
252
Symmetric, gear/flaps extended G limits
0 to 2.5 G
253
Asymmetric, clean G limits
-1.0 to 4.7 G
254
Asymmetric, gear/flaps extended G limits
0 to 2.0 G
255
Spins prohibited below
10,000' MSL
256
Spins prohibited above
22,000' MSL
257
Check CG when:
1) Rear pilot exceeds 260 lbs
2) Combined crew weight exceeds 500 lbs
3) Fuel exceeds 1100 lbs
4) Baggage compartment is used
258
Max ramp weight
6550
259
Max takeoff/landing weight
6500
260
Max zero fuel weight
5500
261
Max descent rate at touchdown (main tires serviced to normal landing conditions pressure 185 +- 5)
600 fpm
262
Max descent rate at touchdown (main tires serviced to max landing conditions pressure 225 +- 5)
780 fpm
263
Max crosswind
25 knots
264
Max tailwind for takeoff
10 knots
265
Aerobatics prohibited with fuel lower than
150 lbs/side
266
Max fuel imbalance
50 lbs
267
Ground ops temperature limits
-23° C (-9.4° F) to +43° C (109.4° F)
268
Apply equipment cooling chart
35° C (95° F)
269
Pressurization Safety valve opens
4.0 +- .1 psi
270
Canopy open wind limit
40 knots
271
Min / Max Pilot weight (Nude) for ejection seat
103 - 245 lbs
272
Min / Max Pilot weight (with equipment) for ejection seat
121- 271 lbs
273
Above ___ KIAS utilize half lateral stick inputs or less performing sustained elevated G rolls
180
274
sink rate at best glide, clean
1100 to 1300 fpm
275
best glide speed, gear down, flaps/SB up
105 KIAS
276
sink rate at best glide w/gear down
1500 fpm
277
Above ___ torque full right rudder and full right aileron may not prevent a left roll off at stall
60%
278
altitude loss during six turn, steady-state spin
4500'
279
nose high pitch for best spin entry
15° to 20°
280
time, altitude loss, and airspeed per turn, stabilized spin
2 - 3 seconds, 400' to 500', 120 KIAS, 18 AOA
281
aggravated spin attitude and turn rate
70° nose down, 280°/second turn
282
altitude loss for spins
500'/turn, 1500' to 2000' dive recovery
283
Recommended turbulence/t-storm penetration airspeed
180 KIAS
284
Approach/landing speed with ice accumulation on aircraft
VAPP + 10(min)
285
Windshear recovery
15° pitch/110 KIAS min/10.5 AOA max/PCL MAX
286
Operations in visible moisture should be avoided below what temp.
5° C/41° F (or below)
287
hydroplaning can occur in less than ___ of slush or water
0.1 inch
288
CONVERSION == MPH/1.15 = Knots
knots x 1.15 = MPH
289
nose tire hydroplane speed
85 knots
290
main tire hydroplane speed
115 knots
291
below ___ degrees power-up of the digital instruments may shorten instrument service life
-21° C (-6° F)
292
below ___ degrees remove battery
-29° C (-20° F)
293
CONVERSION °F = (°C x 1.8) + 32
°C = (°F - 32) x 1.8
294
Standard day, sea level temp
15°C (59°F)
295
Standard day, sea level pressure
29.921
296
Dry RCR
23
297
wet RCR
12
298
ice/ standing water RCR
5
299
Maximum brake energy absorption capability
3.96 Million Foot-lbs
300
Max abort speed reaction time
6 seconds (3 sec decision/3 sec application)
301
Airspeed increase during 6 second reaction at max abort speed
20 knots
302
Max crosswind
25 knots
303
Max crosswind, wet
10 knots
304
Max crosswind, ice
5 knots
305
Charted performance climb speed
140 KIAS
