T-6 By The Numbers

By Connie Reynolds,2014-12-12 01:15
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T-6 By The Numbers

    T6 By The Numbers


    4900 lbs Empty weight

    6500 lbs Max takeoff weight

    1100 Max Shaft Horsepower

    18 quarts oil capacity

    40 psi OIL PX annunciator with PCL above idle 15 psi OIL PX annunciator with PCL at idle 30,000 RPM turbine output shaft speed

    2000 RMP prop operating speed

    60% N1 ground mode at idle

    67% N1 flight mode at idle

    80% N1 PMU managed minimum above 10K

    50% N1 ignition and boost pump deactivated during auto start 10 psi fuel pressure switch limit, turns on BP 20 seconds manual motor after aborted start/inverted flight limit 530 lbs normal wing tank capacity

    40 lbs collector tank capacity

    1100 lbs SPR refueled full fuel load

    1200 lbs over wing refueled full fuel load

    30 lbs (for 2 minutes) imbalance where FUEL BAL annunciator illuminated

    20 lbs auto fuel balance

    445 (+ 50) lbs middle fuel probe

    308 (+ 50) lbs inner fuel probe

    1 to 1.5 psi collector tank pressurized by transfer jet pumps 110 lbs L or R FUEL LO annunciator illuminated 28 VDC (300 amp) starter/generator output

    24 VDC (40A HR) main battery output

    24 VDC (5 A HR) aux battery output

    3000 psi hydraulic pressure

    1.25 gal hydraulic system total capacity

    0.6 gal hydraulic reservoir capacity

    1800 psi min hydraulic pressure to operate NW steering, gear, flaps, speed brake

    40 psi fuel pressure supplied by engine driven low pressure fuel pump

    700 psi fuel pressure supplied by engine driven high pressure fuel pump

    45 cubic inches max hydraulic volume allowed past the hydraulic fuse 3250 to 3500 psi hydraulic pressure relief valve opens 2400 (+ 150) psi EHYD PX LO annunciator illuminates

    1 qt HYDR FL LO annunciator illuminates

    6 seconds normal gear extension/retraction time 87% N1 gear warning horn sounds if A/S is below 120 24; NWS range

    23; flap deflection in TO

    50; flap deflection in LDG

    70; speed brake deflection when deployed 80 knots TAD active with no weight on wheels 0.40 Mach Below this Mach is blanked on A/S ind 18 AOA stall

    10 to 11 AOA on speed

1.3 VS on speed AOA

    8.8 AOA max endurance

    4.9 AOA max range

    1 knot/100 lbs Optimum approach speed decrease rate 25,000’ MSL Optimum max range AOA altitude

    5 - 10 kts (15.5 units) Pre-stall stick shaker

    0’/0 KIAS to 35,000’/370 KIAS Ejection seat limits

    10,000 to 18,000’ MSL Automatic seat man separation 0.37 seconds ISS BOTH rear seat ejection delay

    <7500’ MSL Bleed air inflow prevented with A/C clutch engaged 8000’ cockpit P/A automatically maintained until 18,069’ MSL (3.6 + 0.1 psid)

    19,000’ cockpit P/A CKPT ALT annunciator illuminated

    3.9 + 0.1 psid CKPT PX annunciator illuminated

    300; F DUCT TEMP annunciator illuminated

    20 seconds RMU cursor automatically reverts to UHF field 20 frequencies UHF/VHF memory

    10 frequencies NAV memory

    50 hours ELT transmission limit (battery limited) > +30;/-20; pitch or 65; roll EADI declutters

    < +25;/-15; pitch and 60; roll Full EADI presentation reappears after unusual attitude

    7 seconds NACWS display time limit after trigger is released 1.5 NM range NACWS landing mode

    + 2700’ NACWS vertical separation alert (enroute mode) + 500’ NACWS vertical separation alert (landing mode) < + 300’ NACWS rectangle with digits

    > + 400’ to 900’ NACWS upward/downward pointing triangle with digits > + 1000’ to 2700’ NACWS upward/downward pointing triangle with no digits 34.5 NM, 315 DTK, 130; bearing GPS self test indications

    250 GPS user defined waypoints

    25 GPS stored flightplans

    30 max waypoints per flight plan

    20 seconds flash prior to turn to next waypoint + 5 NM CDI full scale deflection, enroute mode + 1 NM CDI full scale deflection, approach arm + 0.3 NM CDI full scale deflection, approach active 30 NM Approach arm

    2 NM Approach active

    80% full FDR annunciator illuminates

    <50% capacity AUX BAT test light will not illuminate 200; F OBOGS TEMP annunciator illuminates 25% to 70% NORMAL O2 concentration, sea level to 15,000’ MSL

    45% to 95% NORMAL O2 concentration, 15,000’ to 31,000’ MSL

    95% O2 concentration, MAX selected

    3 minutes OBOGS warm-up time (after engine start) < 2 minutes OBOGS FAIL annunciator extinguishes during BIT test 80 lbs baggage compartment weight limit

    .5 pint/ 50 gal fuel icing inhibitor mix

    28 to 28.5 VDC/1000 to 1500 Amps external power requirements 225 + 5 psi main gear tire pressure

    120 + 5 psi nose wheel tire pressure


    17 Static wicks 4 on each wing, 9 on elevator

    23.5 VDC sufficient battery voltage for start

    2.0 inches Minimum main gear strut extension

    2.5 inches Minimum nose gear strut extension

    0.37 second delay between ejections w/ISS in both

    10.5 units LOW AOA (amber donut)

    18 units HIGH AOA (green chevron)

    121 degrees C PMU limit for start

    80 degrees C use HIGH IOAT START procedure

    130 degrees C max ITT for auto start

    20 seconds time for STARTER SWITCH MANUAL to cool IOAT or clear residual fuel 3 feet stay clear area from aircraft with engine running 60% N minimum idle on ground 1

    62 80% N prohibited range of stabilized prop speed on the ground P

    67% N idle with PMU off during overspeed gov check 1

    100% N at approximately 30% torque during overspeed gov check P

    100 + 2% N limit with PMU off during overspeed gov check P

    +50 amps max amps limit for T/O

    15.5 feet radius for inside gear w/NWS 0.0 feet w/differential braking

     radius for nose wheel w/NWS 8.3 feet w/differential braking 18.0 feet

    19.6 feet radius for outside gear w/NWS 8.6 feet w/differential braking 33.2 feet radius for wingtip w/NWS 21.0 feet w/differential braking 25-30% torque setting to check engine instruments for T/O check 8-10 degrees nose up for rotation

    ? gust factor (up to 10 knots) gusty wind T/O

    140 KIAS climbout speed (160-180 KIAS for better forward visibility in climb) 10-15 degrees NH climbout pitch attitude

    15 degrees nose high and 140 KIAS pitch and speed for obstacle clearance climb 10,000 feet check OBOGS and defog

    40 degrees C increase in ITT w/defog on at any PCL setting 820 degrees C ITT limit as controlled by PMU

    3.6 + 0.1 psi required pressure differential above 18,000 feet MSL 50 lbs max fuel imbalance for pre-stall, spinning and aerobatic checks 200-250 KIAS and 4000 fpm power and descent rate desired for enroute descent

    (8,000 11,000 fpm acceptable with idle/speed brake) 120 150 KIAS recommended holding speed

    2000 4000 fpm and 200-250 KIAS (penetration descent parameters) 150 KIAS speed on instrument approach before configuring and during missed approach

    110 KIAS speed on instrument final w/gear and flaps T/O 200 KIAS speed on outside downwind (clean)

    200 KIAS speed on initial (USAF/USN)

    120 KIAS min speed on downwind (USAF)

    110 KIAS min speed in final turn (USAF/USN)

    100 KIAS speed on final with full flaps (USAF/USN)

    105 KIAS speed on final with T/O flaps (USAF/USN)

    110 KIAS speed on final with no flaps (USAF/USN)

    ? gust factor (up to 10 knots) gusty wind threshold and touchdown speeds 80-95 KIAS normal touchdown speed (depending on flap setting) 80 KIAS braking above to be done with great caution

    30 minutes check oil within after landing to be max hot 10 seconds max time to apply power to pitot/AOA heating elements on ground

    0.1-0.15% min volume of MIL 85470 ice inhibitor to be added to fuel (? pint/50 gal) 3 degrees max slope approved for fueling

    10 seconds time limit for LH and RH single point refueling precheck valves to shut 28-28.5 VDC /1000 amps for 5 sec/500 amps for 2 min/300 amps continuous ground power required

    225+5 psi main gear tire pressure

    120+5 psi nose gear pressure

    80 knots wind speed to consider hangaring A/C

    80 degrees max nose wheel deflection while towing


1000 degrees C max ITT for start

    10 seconds time for ITT to start rising after fuel flow indication during start 0/0 altitude/airspeed parameters for ejection seat

    120 KIAS minimum speed to maintain while maneuvering to intercept ELP 0% within 5 seconds N with engine flameout (speeds below 8% not indicated) 1

    125 KIAS engine out glide speed 2 10 minutes duration of emergency O 220,000 MSL consider rapid descent above this altitude if using emer O to prevent depletion

    125 KIAS glide rotates N below 8% (indicate 0%) if engine flamed out (oil px = 0 psi) 1

    2000 feet AGL airstart not recommended below

    20,000 feet MSL airstarts are demonstrated below

    1200 feet altitude lost during airstart procedure (at 125 KIAS glide) 40 seconds time to complete airstart sequence

    135-200 KIAS airstart envelope (above 15,000 feet MSL)

    125-200 KIAS airstart envelope (at or below 15,000 feet MSL)

    15-20 seconds time for prop to unfeather after N reaches approximately 45% 1

    13% N PCL to idle for PMU off airstart (look for ITT rise w/in 10 seconds or abort) 1

    75- 80 initial fuel flow during airstart

     amp reading after airstart Above 30 Amps

    10 minutes time for starter to drain battery if generator is not reset 15-20 seconds time for prop to come out of feather after prop sys CB is pulled 6000 feet AGL minimum altitude uncontrolled ejection

    120 135 KIAS and AOA 18+ indicate a steady state spin

    9 minutes time standby attitude indicator will provide accurate info after loss of power 30 minutes time aux battery provides stby instruments/lighting, fire 1 and standby UHF 60% torque max with CHIP or OIL PX lights illuminated

    90-120 psi normal sustained oil pressure limits

    30 minutes time battery will last with bus tie open

    25 volts and ammeter discharging generator is considered inoperative

    0 volts 0 amps reading if battery bus fails

    10 psi engine feed fuel pressure below causes boost pump to automatically engage 10 hours max engine time with high pressure fuel pump suction feeding 20 lbs auto fuel balancing keeps fuel balance within

    30 lbs fuel imbalance for two minutes triggers FUEL BAL light (fault in auto system) 110 lbs (16 gallons) level of fuel that triggers L or R FUEL LO annunciator 2400 + 150 psi EHYD PX LO light illuminates below

    1 qt HYDR FL LO light illuminates below

    1800 psi - 2880 psi pressure hydraulic system functions at a reduced capacity & speed 2880-3120 psi hydraulic pressure w/in green arc

    6000 ft AGL minimum altitude for controllability check

    90 KIAS minimum speed during controllability check (or stick shaker or max deflection) 20 KIAS add to minimum controllable speed on final with structural damage

    110 KIAS touchdowns in landing configuration have been accomplished up to this 100 KIAS touchdowns above this cause increased directional sensitivity & longer landing 300 degrees F in environmental systems or defog duct triggers the DUCT TEMP light 25,000 feet MSL descend below with environmental system/pressurization failure 110-150 KIAS speed to attain with runaway trim

    10 lbs stick pressure at approach speed with elevator trim failure at high speed cruise 5 lbs stick pressure at approach speed with aileron trim failure at high speed cruise 20 lbs stick pressure at approach speed with rudder trim failure at high speed cruise 150 KIAS max speed with canopy shattered/damaged/gone or CANOPY light on 3.9+ 0.1 psi CKPT PX light illuminates with this pressure differential 19,000 MSL cabin alt triggers CKPT ALT annunciator

    20,000 feet MSL decompression above may trigger OBOGS light due to mode compensation 2000 feet AGL recommended minimum ejection altitude (controlled)

    6000 feet AGL recommended minimum ejection altitude (uncontrolled)

    >8,000 feet AGL Use MOR handle to deploy parachute & separate from seat in mtns. 125-180 KIAS speed range for controlled ejection

    4.37 sec (FRONT)/4.00 sec (REAR) Ejection seat time to full chute

    (based on ISS BOTH, 271 pound pilots, 250 KIAS) 0/0 min altitude/airspeed for successful ejection with up to a 10,000 fpm sink rate 850 feet AGL min ejection altitude with 90 degree dive and 250 KIAS 180 feet AGL min ejection altitude inverted (level flight) with 250 KIAS Add 1% additional terrain clearance to above numbers for each 1000 ft MSL of altitude 8000 feet MSL ejection seat chart not accurate above

    125 KIAS glide to high key

    120 KIAS min speed until intercepting final on ELP

    110 KIAS min speed on final during ELP

    Above 25 knots ditch into the wind instead of parallel the swells

    500 feet add to high, low, and base key with engine in idle due to no feathering 1350 fpm max descent rate for 125 KIAS glide, 4-6% torque, clean. 3000 feet AGL high key

    1500 feel AGL low key

    600-800 feet AGL base key

    4-6% torque to set for ELP, PEL, or to simulate zero thrust 100 lbs minimum fuel to burn down to for landing with gear malfunction 13% Nminimum set PCL to fuel flow indication (expect 70-80 pph) for PMU off ground start 1

    10 seconds after fuel flow indications if no rise in ITT, place PCL off and abort start 67% N approximate idle for PMU off ground start 1

    60% N placing PCL in idle before during manual start may cause eng damage/overtemp 1

    <10 psi fuel px FUEL PX light illuminates

    <40 psi above idle or 15 psi at idle OIL PX light illuminates

    200 degrees F OBOGS TEMP light illuminates

    110 lbs or 16 gallons (respective tank) fuel level which triggers L/R FUEL LO

    80% memory full MAINT FDR light illuminates


    316 KIAS/0.67 Mach Maximum allowable airspeed

    100% Maximum torque for T/O

    131% Maximum torque transient for 20 seconds 820; C Maximum ITT for T/O

    750; C Maximum ITT idle

    1000; C Max ITT for start (5 seconds)

    870; C Max transient ITT (20 seconds)

    104% Max N1

    100 + 2 % Max Np, PMU off

    110% Emergency Max Np

    90 - 120 psi Normal oil pressure range

    200 psi Max oil pressure during start

    40 - 130 psi Transient oil pressure range, aerobatics and spins only

    15 psi Minimum oil pressure, at t idle, aerobatics and spins only (5 seconds max)

    10; to 105; C Normal oil temperature range

    -40; C Min oil temperature for start

    106; - 110; C Acceptable oil temperature, transient power, 10 minutes max

    1800 - 3000 psi Normal hydraulic pressure

    20 seconds starter duty cycle

    30 seconds cooling period before second start attempt

     cooling period before third start attempt 2 minutes

    5 minutes cooling period before fourth start attempt 30 minutes cooling period before fifth start attempt 150 KIAS gear/flap extension limit

    195 KIAS Max turbulence penetration A/S

    227 KIAS Symmetric Vo

    177 KIAS Asymmetric Vo 5 seconds Intentional zero g limit +7.0 to -3.5 G Symmetric, clean

    +2.5 to 0 G Symmetric, gear/flaps extended

    +4.9 to -1.0 G Asymmetric, clean

    +2.0 to 0 G Asymmetric, gear/flaps extended <10,000’ MSL Spins prohibited

    >22,000’ MSL Spins prohibited

    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 6550 Max ramp weight

    6500 Max takeoff/landing weight

    5500 Max zero fuel weight

    780 fpm Max descent rate at touchdown

    25 knots Max crosswind

    10 knots Max tailwind for takeoff

    <150 lbs/side Aerobatics prohibited

    50 lbs Max fuel imbalance

    10 hrs High pressure fuel pump only limit -23; C (-9.4; F) to +43; C (109.4; F) Ground ops temperature limits 35; C (95; F) Apply equipment cooling chart

    4.0 + .1 psi Pressurization Safety valve opens 40 knots Canopy wind limit

    103 - 245 lbs Min / Max Pilot weight (Nude) for ejection seat 121- 271 lbs Min / Max Pilot weight (with equipment) for ejection seat


    >180 KIAS utilize half lateral stick inputs or less performing sustained elevated G rolls

    125 KIAS best glide, clean

    1100 to 1300 fpm sink rate at best glide, clean

    105 KIAS best glide, gear down, flaps/SB up

    1500 fpm sink rate at best glide w/gear down

    4 to 6% torque zero thrust power setting

    >60% torque full right rudder and full right aileron may not prevent a left roll off at stall

    4500’ altitude loss during six turn, steady-state spin 15; to 20; nose high pitch for best spin entry

    2 - 3 seconds, 400’ to 500’, 120 KIAS, 18 AOA per turn, stabilized spin 70; nose down, 280;/second turn aggravated spin

    500’/turn, 1500’ to 200’ dive recovery altitude loss for spins


    180 KIAS Recommended turbulence/t storm penetration airspeed V + (up to)10 Windshear T/O ROT

    V + (up to) 10 Windshear approach APP

    V + 10(min) Approach/landing speed with ice accumulation on aircraft APP

    15; pitch/110 KIAS min/10.5 AOA max/PCL MAX Windshear recovery

    5; C/41; F (or below) Operations in visible moisture should be avoided <0.1 inch of slush or water hydroplaning can occur

    MPH 1.15 = Knots

    >85 knots nose tire hydroplane

    >115 knots main tire hydroplane

    <-21; C (-6; F) Power-up of the digital instruments may shorten instrument service life

    -29; C (-20; F) Remove battery


    ;F = (;C 1.8) + 32

    15;C (59;F) Standard day, sea level

    29.921 Standard day, sea level

    23 RCR Dry

    12 RCR Wet

    5 RCR Ice/Standing Water

    3.96 Million Foot-lbs Maximum brake energy absorption capability 6 seconds (3 sec decision/3 sec application) Max abort speed reaction time 20 knots Airspeed increase during 6 second reaction at max abort speed

    25 knots Max crosswind

    10 knots Max crosswind, wet

    5 knots Max crosswind, ice

    T/O speed + 50% of gust (max of 10) Takeoff speed in gusty winds 140 KIAS Charted performance climb speed

    15,000’ MSL Climb above this altitude may not be possible except clean configurations 250

    KIAS/0.67 Mach Penetration descent, idle power, clean 316 KIAS/0.67 Mach Rapid descent, idle power, speed brake extended 220 KIAS/4000 fpm Enroute descent, power as required, clean 180 KIAS/1500 fpm descent Max range descent, power as required, clean 5% Decreased range for each 10 knots of headwind, clean V/LND + 50% of gust(max of 10) Gusty wind landing APP

    3; Charted landing distance glidepath

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