T-6 By the Numbers (2) Flashcards
Max ITT for start
1000* 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 included)
0% within 5 seconds
Engine out glide speed
125 KIAS
Duration of Emergency O2
10 minutes
Consider rapid descent above this altitude if using emergency O2 to prevent depletion
20,000 MSL
Glide rotates N1 below 8% (indicate 0%) if engine flamed out (oil px = 0 psi)
125 KIAS
Airstart not recommended below
2,000’ AGL
Airstarts are demonstrated below
20,000’ MSL
Altitude lost during airstart procedure (at 125 KIAS glide)
1,200’
Time to complete airstart sequence
40 seconds
Airstart envelope (at or below 15,000’ MSL)
125-200 KIAS
Airstart envelope (above 15,000’ MSL)
135-200 KIAS
Time for prop to unfeather after N1 reaches ~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
Amp reading after airstart
> 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 ft AGL
Indications of a steady state spin
120-135 KIAS and AOA 18+
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
Torque max with CHIP or OIL PX lights illuminated
60%
Normal sustained oil pressure limits
90-120 psi
Time battery will last with but tie open
30 minutes
Generator is considered inoperative
25 volts and ammeter discharging
Reading if battery bus fails
0 volts and 0 amps
Engine fuel pressure below causes boost pump to automatically engage
Max engine time with high pressure fuel pump suction feeding
10 hours
Auto fuel balancing keeps fuel balance within
20 lbs
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 anucnicator
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 and speed
1800 - 2880 psi
Hydraulic pressure within green arc
2880-3120 psi
Minimum altitude for controllability check
6,000’ AGL
Minimum speed during controllability check (or stick shaker or max deflection)
90 KIAS
Add to minimum controllable speed on final with structural change
20 KIAS
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* - 1-5*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 limit
150 KIAS
Max turbulence penetration airspeed
195 KIAS
Symmetric Vo
227 KIAS
Asymmetric Vo 5 seconds (Intentional zero g limit)
177 KIAS
Symmetric, clean
+7.0 to -3.5 Gs
Symmetric, gear/flaps extended
+2.5 to 0 Gs
Asymmetric, clean
+4.9 to -1.0 Gs
Asymmetric, gear/flaps extended
+2.0 to 0 Gs
Spins prohibited
below 10,000’ MSL
Spins prohibited
above 22,000’ MSL
When do you check CG
- 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 lbs
Max takeoff/landing weight
6500 lbs
Max zero fuel weight
5500 lbs
Max descent rate at touchdown
780 fpm
Max crosswinds
25 knots
Max tailwind for takeoff
10 knots
Aerobatics prohibited
Max fuel imbalance
50 lbs
High pressure fuel pump only limit
10 hrs
Ground ops temperature limits
-24C (-9.4F) to +43C(109.4F)
Apply equipment cooling chart
35C (95F)
Pressurization safety valve opens
4.0 +/- 0.1 psi
Canopy wind limits
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
Touchdowns in landing configuration have been accomplished up to this
110 KIAS
Touchdowns above this airspeed cause increased directional sensitivity and longer landing
100 KIAS
In environmental systems or defog duct triggers the DUCT TEMP light
300* F
Descend below with environmental system/pressurization failure
25,000 ft 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 may trigger OBOGS light due to mode compensation
20,000’ MSL
Recommended minimum ejection altitude (controlled)
2,000’ AGL
Recommended minimum ejection altitude (uncontrolled)
6,000’ AGL
Use MOR handle to deploy parachute & separate from seat in mountains
> 8,000’ AGL
Speed range for controlled ejection
125-180 KIAS
Ejection seat time to full chute (based on ISS BOTH, 271 lb pilot, 250 KIAS)
4.37 sec (Front)/4.00 sec (REAR)
Min altitude/airspeed for successful ejection with up to a 10,000 fpm sink rate
0/0
Min ejection altitude with 90 degree dive and 250 KIAS
850’ AGL
Min ejection altitude inverted (level flight) with 250 KIAS
180’ AGL
Additional terrain clearance to above numbers for each 1,000’ MSL of altitude
Add 1%
Ejection seat chart not accurate above
8,000’ MSL
Glide airspeed to high key
125 KIAS
Min speed until intercepting final on ELP
120 KIAS
Min speed on final during ELP
110 KIAS
Ditch into the wind instead of parallel the swells
Above 25 knots
Add this altitude to high, low, and base key with engine in idle due to no feathering
500 ft
Max descent rate for 125 KIAS glide, 4-6% torque, clean
1350 fpm
High key altitude
3,000’ AGL
Low key altitude
1,500’ AGL
Base key altitude
600-800’ AGL
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
Set PCL to fuel flow indication (expect 70-80 pph) for PMU off ground start
13% N1 minimum
If no rise in ITT, place PCL off and abort start
10 seconds after fuel flow indications
Approximate idle for PMU off ground start
67% N1
Placing PCL in idle before _____ during manual start may cause engine damage/overtemp
60% N1
FUEL PX light illuminates when _____
OIL PX light illuminates when ______
OBOGS TEMP light illuminates when _____
> 200* F
At what fuel level triggers L/R FUEL LO indicator
110 lbs or 16 gallons (respective tank)
MAINT FDR light illuminates when
Memory is 80% full
At what do you utilize half lateral stick inputs or less performing sustained elevated G rolls
> 180 KIAS
Best glide, clean airspeed
125 KIAS
Sink rate at best glide, clean airspeed
1100-1300 fpm
Best glide, gear down, flaps/speed brake up airspeed
105 KIAS
Sink rate at best glide w/gear down airspeed
1500 fpm
Zero thrust power setting
4-6% Torque
Full right rudder and full right aileron may not prevent a left roll off at stall
> 60% Torque
Altitude loss during six turn, steady-state spin
4,500 ft
Nose high pitch attitude for best spin entry
15-20*
Parameters per turn, a stabilized spin
2-3 seconds, 400’-500’, 120 KIAS, 18 AOA
Aggravated spin parameters
70* nose down, 280*/second turn
Altitude loss for spins
500’/turn, 1500’ to 200’ dive recovery
Recommended turbulence/t-storm penetration airspeed
180 KIAS
Windshear T/O
Vrot + (up to) 10
Wind shear approach
Vapp + (up to) 10
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
5* C/41* F (or below)
Hydroplaning can occur
MPH/1.15 =
KNOTS aka KIAS
Nose tire hydroplane
> 85 knots
Main tire hydroplane
> 115 knots
Power-up of the digital instruments may shorten instrument service life
Remove battery when temperature is below
-29* C (-20* F)
(*C x 1.8) + 32 =
*F
Standard day, sea level temperature
15* C (59* F)
Standard day, sea level pressure
29.921
Dry
23 RCR
Wet
12 RCR
Ice/Standing Water
5 RCR
Maximum brake energy absorption capability
3.96 million ft-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
Takeoff speed in gusty wind
T/O speed + 50% of gust speed (max of 10)
Charted performance climb speed
140 KIAS
Climb above this altitude may not be possible except clean configurations, 250 KIAS
15,000’ MSL
Penetration descent, idle power, clean
316 KIAS/0.67 Mach
Rapid descent, idle power, speed brake extended
316 KIAS/0.67 Mach
Enroute descent, power as required, clean
220 KIAS/4000 fpm
Max range descent, power as required, clean
180 KIAS/1500 fpm descent
Decreased range for each 10 knots of headwind, clean
5%
Gusty wind landing
Vapp/LND + 50% of gust (max of 10)
Charted landing distance glidepath
3*
