T-6 By The Numbers - Ch. 1 W/ Change 4

Front 1

Empty weight

Back 1

4900 lbs

Front 2

Max. takeoff gross weight

Back 2

6500 lbs

Front 3

Max. shaft horsepower

Back 3

1100

Front 4

Shaft torque at 100% indicated torque

Back 4

2900

Front 5

Pounds of thrust at sea level, zero airspeed

Back 5

2750

Front 6

Propeller in low pitch (degrees from the reference plane)

Back 6

15º

Front 7

Propeller feathered (degrees from the reference plane)

Back 7

86º

Front 8

Altitude which 100% torque is available to (from sea level)

Back 8

12,000–16,000ft MSL

Front 9

Oil capacity

Back 9

18.5 quarts

Front 10

Time which oil level must be serviced within

Back 10

30 min.

Front 11

Time which oil readings are most accurate

Back 11

15-20 min.

Front 12

Red OIL PX annunciator with PCL above idle

Back 12

≤40 psi

Front 13

Red OIL PX annunciator with PCL idle

Back 13

≤15 psi

Front 14

Amber OIL PX annunciator with PCL above idle

Back 14

40-90 psi (≥10 sec)

Front 15

Amber OIL PX annunciator with PCL idle

Back 15

15-40 psi

Front 16

Red and amber OIL PX annunciator with PCL idle

Back 16

15-40 psi (≥5 sec)

Front 17

Power turbine output shaft speed

Back 17

30,000 RPM

Front 18

Propeller operating speed (100% Np)

Back 18

2000 RPM

Front 19

Propeller size (aluminum)

Back 19

97 inch

Front 20

Mechanical overspeed governor limit with PMU functioning

Back 20

106% Np

Front 21

Mechanical overspeed governor with PMU not functioning/off

Back 21

100∓2% Np

Front 22

Ground mode at idle

Back 22

60% N1

Front 23

Flight mode at idle

Back 23

67% N1

Front 24

Np at idle above 10,000ft MSL

Back 24

80% Np

Front 25

PMU automatically switches to 28 VDC battery bus

Back 25

< 40-50% Np

Front 26

PMU auto abort start attempt if light-off has not occurred

Back 26

10 sec.

Front 27

PMU will abort auto start attempt

Back 27

940ºC for 2 sec.
870ºC for 4 sec.
840ºC for 19 sec.

Front 28

PMU will go offline (amber dashes in IOAT and ITT counters, removal of ITT pointers, PMU FAIL)

Back 28

> 121ºC

Front 29

N1 acceleration rate at which PMU will abort auto start attempt

Back 29

< 50%

Front 30

Starter and igniters are deenergized during auto start

Back 30

50% N1

Front 31

PCL may be advanced to idle during auto start

Back 31

≥ 60% N1

Front 32

Maximum increase in power with PMU off (low altitude cold conditions)

Back 32

280 shp

Front 33

Maximum decrease in power with PMU off

Back 33

550 shp

Front 34

Usable fuel through single point refueling

Back 34

1100 lbs

Front 35

Additional fuel available through over-the-wing refueling

Back 35

100 lbs

Front 36

Ramp slope at which fuel is vented overboard through pressure relief valve

Back 36

> 1%

Front 37

Amount and time for auto fuel balancing system

Back 37

20 lbs for 30 sec.

Front 38

FUEL BAL annunciator illuminates and auto balance system shuts off

Back 38

30 lbs within 2 min.

Front 39

Red FUEL PX annunciator is activated

Back 39

< 10 psi

Front 40

Amber L FUEL LO and R FUEL LO annunciators are activated

Back 40

110 lbs

Front 41

Number of fuel probes (three in each wing tank, one in the collector tank)

Back 41

7

Front 42

Fuel level outer fuel probes reads to

Back 42

445 ∓50 lbs

Front 43

Fuel level middle fuel probes reads to

Back 43

308 ∓50 lbs

Front 44

Fuel level inner fuel probes read to

Back 44

20 lbs

Front 45

Minimum time provided by the fuel system for inverted flight

Back 45

15 sec.

Front 46

Starter/generator

Back 46

28 volts, 300 amps

Front 47

Battery

Back 47

24 volts, 42 amps

Front 48

Minimum volts required to charge the battery

Back 48

≥ 25 volts

Front 49

Auxiliary battery

Back 49

24 volts, 5 amps

Front 50

Battery volts at which external power should not be connected

Back 50

≤ 22 volts

Front 51

Time provided by the battery to power all items on the battery bus

Back 51

30 min.

Front 52

Number of hydraulic master cylinders for brake system

Back 52

2

Front 53

Hydraulic system fluid capacity

Back 53

5 quarts

Front 54

Pressure relief valve for primary hydraulic system

Back 54

3250 to 3500 psi

Front 55

Normal hydraulic pressure

Back 55

3000 ∓120 psi

Front 56

Minimum hydraulic pressure needed to power components

Back 56

< 1800 psi

Front 57

Amber HYDR FL LO annunciator illuminates for primary hydraulic reservoir

Back 57

< 1 quart

Front 58

Amber EHYD PX LO annunciator illuminates for the emergency accumulator

Back 58

2400 ∓150 psi

Front 59

Restricted flow rate to the emergency accumulator

Back 59

> .25 GPM

Front 60

Hydraulic fluid loss limit by the hydraulic fuse

Back 60

0.5 quarts

Front 61

Normal gear extension/retraction

Back 61

6 sec.

Front 62

PCL mid-range position

Back 62

87% N1

Front 63

Nose wheel turn limits (160º total)

Back 63

80º

Front 64

Takeoff flaps extension

Back 64

23º

Front 65

Landing flaps extension

Back 65

50º

Front 66

Speed brake extension

Back 66

70º

Front 67

Aileron travel limits

Back 67

20º up / 11º down

Front 68

Elevator travel limits

Back 68

18º up / 16º down

Front 69

Rudder travel limits

Back 69

24º left/right

Front 70

TAD provides further trim in addition to weight off wheels

Back 70

80 KIAS

Front 71

Standby attitude indicator accuracy with complete power loss

Back 71

6º for 9 min.

Front 72

Accelerometer display range

Back 72

-6 to +10 G

Front 73

Accelerometer tolerance

Back 73

∓0.25 G

Front 74

Allowable difference between accelerometers in front and rear cockpit (notice maintenance if higher)

Back 74

< 1G

Front 75

Stall AOA

Back 75

18 units

Front 76

Normal approach speed AOA (1.3 times stall speed)

Back 76

10-11 units

Front 77

Maximum endurance AOA (white diamond)

Back 77

8.8 units

Front 78

Maximum range AOA (white triangle)

Back 78

4.9 units

Front 79

Optimum approach airspeed (amber doughnut)

Back 79

100 KIAS

Front 80

Optimum approach speed decrease versus fuel used

Back 80

1 knot for 100 lbs

Front 81

Stick shaker above stall speed

Back 81

5-10 knots

Front 82

Stick shaker AOA

Back 82

15.5 units

Front 83

Windscreen and front transparency bird strike limits

Back 83

4 lbs / 270 KIAS

Front 84

Ejection seat capability

Back 84

35,000’ / 370 KIAS

Front 85

Ejection seat/pilot separation and parachute deployment delay

Back 85

14,000-16,000’ MSL

Front 86

Seat/pilot separation pending completion of TCTO 13A5-69-504/TD ACB 1037

Back 86

10,000-18,000’ MSL

Front 87

Altitude for mountainous terrain which the MOR handle should be used

Back 87

8,000’ MSL

Front 88

Emergency oxygen system supply

Back 88

10 min.

Front 89

Minimum emergency oxygen cylinder pressure at 70ºF

Back 89

1800 psi

Front 90

Change in pressure with temperature above/below 70ºF

Back 90

3.5 psi

Front 91

Front seat ejection delay with ISS BOTH

Back 91

0.37 sec.

Front 92

SSK lowered after seat/pilot separation

Back 92

4-6 sec.

Front 93

Inflow valve (bleed air) automatically closed with A/C on

Back 93

< 7,500’ MSL

Front 94

Amber DUCT TEMP annunciator (ECS)

Back 94

≥ 300ºF

Front 95

G-suit safety valve

Back 95

> 7 psig

Front 96

Temperature range that is maintained with the TEMP CONTROL set to auto

Back 96

60ºF to 90ºF

Front 97

Heat exchanger bypass valve is moved to full close (ECS)

Back 97

> 165ºF

Front 98

Closing of the defog valve

Back 98

40 sec.

Front 99

Altitude which 3.60.2 pressure differential is reached

Back 99

18,069’ MSL

Front 100

Cockpit pressure altitude at 31,000’ MSL

Back 100

16,600ft

Front 101

Amber CKPT ALT annunciator

Back 101

19,000ft

Front 102

Cockpit differential pressure after 18,069ft

Back 102

3.9∓0.2

Front 103

Red CKPT PX annunciator

Back 103

3.9 to 4.0

Front 104

Fresh air valve is automatically closed

Back 104

8,000ft pressure altitude

Front 105

RMU cursor automatically reverts to the top field

Back 105

20 sec.

Front 106

RMU direct tuning and transponder memory recall

Back 106

> 3 sec.

Front 107

UHF/VHF & UHF backup memory capacity

Back 107

20 frequencies

Front 108

NAV memory capacity

Back 108

10 frequencies

Front 109

ELT transmission duration (battery powered)

Back 109

50 hrs

Front 110

EADI unusual attitude declutter

Back 110

>+30º, -20º, 65º bank

Front 111

EADI unusual attitude recovery (red chevrons)

Back 111

30-90º

Front 112

EHSI VOR CDI 1 dot

Back 112

5º

Front 113

EHSI localizer & glideslope 1 dot (width of localizer/glideslope)

Back 113

0.25º x width of localizer

Front 114

EHSI GPS EN ROUTE, APR ARM, APR ACT 1 dot

Back 114

2.5, 0.5, 0.15 NM

Front 115

NACWS upward/downward pointing triangle with vertical separation displayed

Back 115

∓400-900ft

Front 116

NACWS upward/downward pointing triangle

Back 116

∓1000-2700ft

Front 117

NACWS rectangle

Back 117

≤∓300ft

Front 118

TAS normal mode range

Back 118

∓2700ft

Front 119

TAS above/below mode range

Back 119

∓2700-8700ft

Front 120

TAS tracking range/altitude

Back 120

40 NM / 10,000ft

Front 121

GPS flight plans

Back 121

25

Front 122

GPS waypoints per flight plan

Back 122

30

Front 123

GPS will flash prior to beginning of turn anticipation for waypoint

Back 123

20 sec.

Front 124

IDARS memory level when Green FDR MAINT illuminates

Back 124

80%

Front 125

Aux bat capacity when light does not illuminate during aux bat test

Back 125

< 50%

Front 126

Aural tones are inaudible during engine start

Back 126

< 50% N1

Front 127

OBOGS warm-up time when OBOGS fail light will be inhibited

Back 127

3 min.

Front 128

Amber OBOGS TEMP annunciator

Back 128

≥ 200ºF

Front 129

Oxygen concentration in NORMAL from sea level to 15,000’ MSL

Back 129

25-70%

Front 130

Oxygen concentration in NORMAL from 15,000’ to 31,000’ MSL

Back 130

45-95%

Front 131

Oxygen concentration in MAX

Back 131

95%

Front 132

Maximum weight in baggage compartment

Back 132

80 lbs

Front 133

Time that oil level must be serviced within after engine shutdown

Back 133

30 min.

Front 134

Time that provides the most accurate oil level readings after engine shutdown

Back 134

15-20 min.

Front 135

Main gear tire pressure (max)

Back 135

225∓5

Front 136

Main gear tire pressure

Back 136

185∓5

Front 137

Nose wheel tire pressure

Back 137

120∓5

Front 138

Acceptable external power voltage limits for off-station engine starts

Back 138

24.0 to 29.5 VDC

Front 139

Wind speed which aircraft should be moved to hanger

Back 139

> 80 knots