T-6 By the Numbers Flashcards
Empty weight
4900 lbs
Max takeoff weight
6500 lbs
Max Shaft Horsepower
1100
oil capacity
18.5 quarts
OIL PX annunciator with PCL above idle (PSI)
40 psi
OIL PX annunciator with PCL at idle (PSI)
15 psi
turbine output shaft speed
30,000 RPM
prop operating speed
2000 RPM
ground mode at idle (N1)
60% N1
flight mode at idle (N1)
67% N1
PMU managed minimum above 10K (N1)
80% N1
ignition and boost pump deactivated during auto start (N1)
50% N1
fuel pressure switch limit, turns on BP
10 psi
manual motor after aborted start/inverted flight time limit
20 seconds
normal wing tank capacity
530 lbs
collector tank capacity
40 lbs
SPR refueled full fuel load
1100 lbs
over wing refueled full fuel load
1200 lbs
(for 2 minutes) imbalance where FUEL BAL annunciator illuminated
30 lbs
auto fuel balance tolerance
20 lbs
middle fuel probe reading
445 (+ 50) lbs
inner fuel probe reading
308 (+ 50) lbs
collector tank pressurized at ___ PSI by transfer jet pumps
1 to 1.5 psi
L or R FUEL LO annunciator illuminated
110 lbs
starter/generator output
28 VDC (300 amp)
main battery output
24 VDC (42A HR)
aux battery output
24 VDC (5 A HR)
hydraulic pressure
3000 psi
hydraulic system total capacity
1.25 gal
hydraulic reservoir capacity
0.6 gal
min hydraulic pressure to operate NW steering, gear, flaps, speed brake
1800 psi
fuel pressure supplied by engine driven low pressure fuel pump
40 psi
fuel pressure supplied by engine driven high pressure fuel pump
700 psi
max hydraulic volume allowed past the hydraulic fuse
45 cubic inches
hydraulic pressure relief valve opens
3250 to 3500 psi
EHYD PX LO annunciator illuminates
2400 (+ 150) psi
HYDR FL LO annunciator illuminates
1 qt
normal gear extension/retraction time
6 seconds
Below ___ %N1 gear warning horn sounds if A/S is below 120
87% N1
NWS range
24°
flap deflection in TO
23°
flap deflection in LDG
50°
speed brake deflection when deployed
70°
TAD active with no weight on wheels
80 knots
Below this Mach is blanked on A/S ind
0.40 Mach
stall AOA
18 units
on speed AOA
10-11 units
max endurance AOA
8.8 units
max range AOA
4.9 units
Optimum approach speed decrease rate
1 knot/100 lbs
Max velocity in level flight at sea level (thrust limited)
255 KIAS
Optimum max range AOA altitude
25,000’ MSL
Pre-stall stick shaker
5 - 10 kts (15.5 units)
Ejection seat limits
0’/0 KIAS to 35,000’/370 KIAS
Automatic seat man separation altitude
14,000’ to 16,000’ MSL
ISS BOTH rear seat ejection delay
0.37 seconds
altitude where bleed air inflow is prevented with A/C clutch engaged
<7500’ MSL
automatically maintained pressure until 18,069’ MSL (3.6 + 0.1 psid)
8000’ cockpit P/A
CKPT ALT annunciator illuminated
19,000’ cockpit P/A
CKPT PX annunciator illuminated
3.9 + 0.1 psid
DUCT TEMP annunciator illuminated
300° F
RMU cursor automatically reverts to UHF field
20 seconds
UHF/VHF memory
20 frequencies
NAV memory
10 frequencies
ELT transmission limit (battery limited)
50 hours
EADI declutters
> +30°/-20° pitch or 65° roll
Full EADI presentation reappears after unusual attitude
< +25°/-15° pitch and 60° roll
GPS self test indications
34.5 NM, 315 DTK, 130° bearing
GPS user defined waypoints
250
GPS stored flightplans
25
max waypoints per flight plan
30
flash prior to turn to next waypoint
20 seconds
CDI full scale deflection, enroute mode
ERROR!
CDI full scale deflection, approach arm
ERROR!
CDI full scale deflection, approach active
ERROR!
Approach arm
30 NM
Approach active
2 NM
FDR annunciator illuminates
80% full
AUX BAT test light will not illuminate
<50% capacity
OBOGS TEMP annunciator illuminates
200° F
NORMAL OBOGS O2 concentration, sea level to 15,000’ MSL
25% to 70%
NORMAL OBOGS O2 concentration, 15,000’ to 31,000’ MSL
45% to 95%
O2 concentration, MAX selected
94.5% (95%)
OBOGS warm-up time (after engine start)
3 minutes
OBOGS FAIL annunciator extinguishes during BIT test
baggage compartment weight limit
80 lbs
max weight of bags and pubs on glareshield
8.5 lbs
icing inhibitor mix
.5 pint/ 50 gal fuel
external power requirements
28 to 28.5 VDC/1000 to 1500 Amps
main gear tire pressure
225 +- 5 psi
nose wheel tire pressure
120 +- 5 psi
Number of static wicks
17 - 4 on each wing, 6 on elevator, 3 on rudder
sufficient battery voltage for start
23.5 VDC
Minimum main gear strut extension
2.0 inches
Minimum nose gear strut extension
2.5 inches
delay between ejections w/ISS in both
0.37 second
LOW AOA (amber donut)
10.5 units
HIGH AOA (green chevron)
18 units
PMU IOAT limit for start
121 degrees C
use HIGH IOAT START procedure
80 degrees C
time for STARTER SWITCH MANUAL to cool IOAT or clear residual fuel
20 seconds
stay clear area distance from aircraft with engine running
3 feet
minimum idle on ground (N1)
60% N1
maximum icing limits
5000 feet of light rime (probes anti ice on whenever in visible moisture)
prohibited range of stabilized prop speed on the ground
62-80% Np
idle with PMU off during overspeed gov check (N1)
67% N1
NP when at approximately 30% torque during overspeed gov check
100%
NP limit with PMU off during overspeed gov check
100 + -2%
max amps limit for T/O
ERROR!
radius for inside gear w/NWS (0.0 feet w/differential braking)
15.5 feet
radius for nose wheel w/NWS (8.3 feet w/differential braking)
18.0 feet
radius for outside gear w/NWS (8.6 feet w/differential braking)
19.6 feet
radius for wingtip w/NWS (21.0 feet w/differential braking)
33.2 feet
Torque setting to check engine instruments for T/O check
25-30% torque
degrees nose up for rotation
7-10
gusty wind T/O correction
½ gust factor (up to 10 knots)
climbout speed (160-180 KIAS for better forward visibility in climb)
140 KIAS
climbout pitch attitude
10-15 degrees NH
pitch and speed for obstacle clearance climb
15 degrees nose high and 140 KIAS
Passing through ___ feet, check OBOGS and defog
10,000 feet
increase in ITT w/defog on at any PCL setting
40 degrees C
ITT limit as controlled by PMU
820 degrees C
required pressure differential above 18,000 feet MSL
3.6 + 0.2 psi
max fuel imbalance for pre-stall, spinning and aerobatic checks
50 lbs
recommended holding speed
120 - 150 KIAS
speed on instrument approach before configuring and during missed approach
150 KIAS
speed on instrument final w/gear and flaps T/O
110 KIAS
speed on outside downwind (clean)
200 KIAS
speed on initial (USAF/USN)
200 KIAS
min speed on downwind (USAF)
120 KIAS
min speed in final turn (USAF/USN)
110 KIAS
speed on final with full flaps (USAF/USN)
100 KIAS
speed on final with T/O flaps (USAF/USN)
105 KIAS
speed on final with no flaps (USAF/USN)
110 KIAS
gusty wind threshold and touchdown speeds
½ gust factor (up to 10 knots)
normal touchdown speed (depending on flap setting)
80-95 KIAS
braking above ___ KIAS to be done with great caution
80 KIAS
check oil within ___ after landing to be max hot
30 minutes
max time to apply power to pitot/AOA heating elements on ground
10 seconds
min volume of MIL 85470 ice inhibitor to be added to fuel (½ pint/50 gal)
0.1-0.15%
max slope approved for fueling
3 degrees
time limit for LH and RH single point refueling precheck valves to shut
10 seconds
wind speed to consider hangaring A/C
80 knots
max nose wheel deflection while towing
80 degrees
max ITT for start
1000 degrees C
time for ITT to start rising after fuel flow indication during start
10 seconds
altitude/airspeed parameters for ejection seat
0/0
minimum speed to maintain while maneuvering to intercept ELP
120 KIAS
N1 with engine flameout (speeds below 8% not indicated)
0% within 5 seconds
engine out glide speed
125 KIAS
duration of emergency O2
10 minutes
consider rapid descent above this altitude if using emer O2 to prevent depletion
20,000 MSL
airstart not recommended below
2000 feet AGL
airstarts are demonstrated below
20,000 feet MSL
altitude lost during airstart procedure (at 125 KIAS glide)
1200 feet
time to complete airstart sequence
40 seconds
airstart envelope (above 15,000 feet MSL)
135-200 KIAS
airstart envelope (at or below 15,000 feet MSL)
125-200 KIAS
time for prop to unfeather after N1 reaches approximately 45%
15-20 seconds
PCL to idle for PMU off airstart (look for ITT rise w/in 10 seconds or abort)
13% N1
initial fuel flow during airstart
75- 80 PPH
amp reading after airstart
Above 30 Amps
time for starter to drain battery if generator is not reset
10 minutes
time for prop to come out of feather after prop sys CB is pulled
15-20 seconds
minimum altitude uncontrolled ejection
6000 feet AGL
___ to ___ KIAS and AOA 18+ indicate a steady state spin
120 - 135
time standby attitude indicator will provide accurate info after loss of power
9 minutes
time aux battery provides stby instruments/lighting, fire 1 and standby UHF
30 minutes
normal sustained oil pressure limits
90-120 psi
time battery will last with bus tie open
30 minutes
Electrical readings indicating generator is inoperative
25 volts and ammeter discharging
reading if battery bus fails
0 volts 0 amps
engine feed fuel pressure below ___ PSI causes boost pump to automatically engage
10 psi
max engine time with high pressure fuel pump suction feeding
10 hours
auto fuel balancing keeps fuel balance within
20 lbs
More than ____ fuel imbalance for two minutes triggers FUEL BAL light (fault in auto system)
30 lbs
level of fuel that triggers L or R FUEL LO annunciator
110 lbs (16 gallons)
EHYD PX LO light illuminates below
2400 + 150 psi
HYDR FL LO light illuminates below
1 qt
pressure hydraulic system functions at a reduced capacity & speed
1800 psi - 2880 psi
hydraulic pressure within green arc
2880-3120 psi
minimum altitude for controllability check
6000 ft AGL
minimum speed during Controllability check (or stick shaker or max deflection)
90 KIAS
add ___ KIAS to minimum controllable speed on final with structural damage
20 KIAS
touchdowns in landing configuration have been accomplished up to ___ KIAS
110 KIAS
touchdowns above ___ KIAS cause increased directional sensitivity & longer landing
100 KIAS
in environmental systems or defog duct triggers the DUCT TEMP light
300 degrees F
descend below with environmental system/pressurization failure
25,000 feet MSL
speed to attain with runaway trim
110-150 KIAS
stick pressure at approach speed with elevator trim failure at high speed cruise
10 lbs
stick pressure at approach speed with aileron trim failure at high speed cruise
5 lbs
stick pressure at approach speed with rudder trim failure at high speed cruise
20 lbs
max speed with canopy shattered/damaged/gone or CANOPY light on
150 KIAS
CKPT PX light illuminates with this pressure differential
3.9+ 0.1 psi
cabin alt triggers CKPT ALT annunciator
19,000 MSL
decompression above___ feet may trigger OBOGS light due to mode compensation
20,000 feet MSL
AGL altitude to use MOR handle to deploy parachute & separate from seat in mtns.
8,000 feet AGL
speed range for controlled ejection
125-180 KIAS
Ejection seat time to full chute
4.37 sec (FRONT)/4.00 sec (REAR)
min ejection altitude with 90 degree dive and 250 KIAS
850 feet AGL
min ejection altitude inverted (level flight) with 250 KIAS
180 feet AGL
For each 1000 ft MSL of altitude add ___to minimum ejection numbers for additional terrain clearance
Add 1%
ejection seat chart not accurate above ___
8000 feet MSL
glide speed to high key
125 KIAS
min speed until intercepting final on ELP
120 KIAS
min speed on final during ELP
110 KIAS
Above ___ knots ditch into the wind instead of parallel the swells
25
add ___ feet to high, low, and base key with engine in idle due to no feathering
500 feet
max descent rate for 125 KIAS glide, 4-6% torque, clean.
1350 fpm
high key altitude
3000 feet AGL
low key altitude
1500 feel AGL
base key altitude
600-800 feet AGL
max time inverted flight
15 seconds
max time zero G flight
5 sec
torque to set for ELP, PEL, or to simulate zero thrust
4-6%
minimum fuel to burn down to for landing with gear malfunction
100 lbs
If no rise in ITT ___ seconds after fuel flow indications, place PCL off and abort start
10
approximate idle for PMU off ground start (N1)
67% N1
PCL in idle before ___ N1 during manual start may cause engine damage/overtemp
60% N1
FUEL PX light illuminates
<10 psi fuel px
OIL PX light illuminates
<40 psi above idle or 15 psi at idle
OBOGS TEMP light illuminates
200 degrees F
MAINT FDR light illuminates
80% memory full
Maximum allowable airspeed
316 KIAS/0.67 Mach
Maximum torque for T/O
100%
Maximum torque transient for 20 seconds
131%
Maximum ITT for T/O
820° C
Maximum ITT idle
750° C
Max ITT for start (5 seconds)
1000° C
Max transient ITT (20 seconds)
870° C
Max N1
104%
Max Np, PMU off
100 + 2 %
Emergency Max Np
110%
Normal oil pressure range
90 - 120 psi
Max oil pressure during start
200 psi
Transient oil pressure range, aerobatics and spins only
40 - 130 psi
Minimum oil pressure, at idle, aerobatics and spins only (5 seconds max)
15 psi
Normal oil temperature range
10° to 105° C
Min oil temperature for start
-40° C
Acceptable oil temperature, transient power, 10 minutes max
106° - 110° C
Normal hydraulic pressure
1800 - 3000 psi
starter duty cycle
20 seconds
cooling period before second start attempt
30 seconds
cooling period before third start attempt
2 minutes
cooling period before fourth start attempt
5 minutes
cooling period before fifth start attempt
30 minutes
gear/flap extension airspeed limit
150 KIAS
Max turbulence penetration A/S
195 KIAS
Symmetric Vo (operating maneuvering speed)
227 KIAS
Asymmetric Vo 5 seconds
177 KIAS
Symmetric, clean G limits
-3.5 to 7.0 G
Symmetric, gear/flaps extended G limits
0 to 2.5 G
Asymmetric, clean G limits
-1.0 to 4.7 G
Asymmetric, gear/flaps extended G limits
0 to 2.0 G
Spins prohibited below
10,000’ MSL
Spins prohibited above
22,000’ MSL
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
Max ramp weight
6550
Max takeoff/landing weight
6500
Max zero fuel weight
5500
Max descent rate at touchdown (main tires serviced to normal landing conditions pressure 185 +- 5)
600 fpm
Max descent rate at touchdown (main tires serviced to max landing conditions pressure 225 +- 5)
780 fpm
Max crosswind
25 knots
Max tailwind for takeoff
10 knots
Aerobatics prohibited with fuel lower than
150 lbs/side
Max fuel imbalance
50 lbs
Ground ops temperature limits
-23° C (-9.4° F) to +43° C (109.4° F)
Apply equipment cooling chart
35° C (95° F)
Pressurization Safety valve opens
4.0 +- .1 psi
Canopy open wind limit
40 knots
Min / Max Pilot weight (Nude) for ejection seat
103 - 245 lbs
Min / Max Pilot weight (with equipment) for ejection seat
121- 271 lbs
Above ___ KIAS utilize half lateral stick inputs or less performing sustained elevated G rolls
180
sink rate at best glide, clean
1100 to 1300 fpm
best glide speed, gear down, flaps/SB up
105 KIAS
sink rate at best glide w/gear down
1500 fpm
Above ___ torque full right rudder and full right aileron may not prevent a left roll off at stall
60%
altitude loss during six turn, steady-state spin
4500’
nose high pitch for best spin entry
15° to 20°
time, altitude loss, and airspeed per turn, stabilized spin
2 - 3 seconds, 400’ to 500’, 120 KIAS, 18 AOA
aggravated spin attitude and turn rate
70° nose down, 280°/second turn
altitude loss for spins
500’/turn, 1500’ to 2000’ dive recovery
Recommended turbulence/t-storm penetration airspeed
180 KIAS
Approach/landing speed with ice accumulation on aircraft
VAPP + 10(min)
Windshear recovery
15° pitch/110 KIAS min/10.5 AOA max/PCL MAX
Operations in visible moisture should be avoided below what temp.
5° C/41° F (or below)
hydroplaning can occur in less than ___ of slush or water
0.1 inch
CONVERSION == MPH/1.15 = Knots
knots x 1.15 = MPH
nose tire hydroplane speed
85 knots
main tire hydroplane speed
115 knots
below ___ degrees power-up of the digital instruments may shorten instrument service life
-21° C (-6° F)
below ___ degrees remove battery
-29° C (-20° F)
CONVERSION °F = (°C x 1.8) + 32
°C = (°F - 32) x 1.8
Standard day, sea level temp
15°C (59°F)
Standard day, sea level pressure
29.921
Dry RCR
23
wet RCR
12
ice/ standing water RCR
5
Maximum brake energy absorption capability
3.96 Million Foot-lbs
Max abort speed reaction time
6 seconds (3 sec decision/3 sec application)
Airspeed increase during 6 second reaction at max abort speed
20 knots
Max crosswind
25 knots
Max crosswind, wet
10 knots
Max crosswind, ice
5 knots
Charted performance climb speed
140 KIAS
