MB 339 CD nice numbers

Min turn radius

Min turn radius

8,6 mt

Basic empty mass (unusable fuel + hyd fluid+ oil)

3350 kg

Max mass for TO and landings

6350 Kg (14000 lb)

Pilot training mission weight

4680kg

Compressor ratio

5,9:1

Engine power in kN

17,8

Max rpm at 100%

13760 rpm/min

Minimum engine temperature to avoid flame out

200°C

Hot relight envelope

120-200 KIAS below 20.000ft

Cold relight envelope

120-155 KIAS below 20.000ft, between 8-10%

Engine anti-ice failure, set rpm…

Below 85%

In case of ice aggregation on intakes set rpm to…

70% for 5 min

JPT LMTR Amplifier calibrated at

756°C +5/-12

Safe distance from exhaust nozzle at idle and at full

15 mt IDLE

25 mt FULL

Air for BOV is taken from

4th compressor stage

Starting system is powered by

External power or 28 V dc essential bus

GEN 1 act as starter until

23%

temperature conditions for starting with batteries or with external

-15/+45 batteries

-26/+50 external

Starting cycle

25 sec

Acceleration time from 40% to 98%

6 sec

Acceleration time from 60% to 100%

4 sec

When to release RELIGHT push button

40% or after 30 sec or peak and then decrease

Engine oil green arc

0.4-2.4 bar

Engine oil normal operations with 95%

1.7-2.4 bar

Min oil pressure in flight

0.35 bar

Min oil press on ground (IDLE)

0.7 bar

“OIL PRESS” caution legend

On if <0.4 bar

Oil system capacity

11 pint

Oil tank capacity

13.5 pint

Oil contained in tank

9.5 pint

Usable oil and unusable oil quantities

6.5 pint usable , 3 pint unusable

Max and min oil consumption allowed

1,25 to 0,9 pints per hour

Oil level must be checked within ____ from engine shut down

30 min

Battery endurance (ON and EMG, day and night)

ON :

21’ day 17’ night (+25°)

17’ day 14’ night (-18°)

EMG:

46’ day 36’ night (+25°)

39’ day 31’ night (-18°)

Gen 1 specifics

Starter until 23%

28V DC, 9kW, 300Ah

Gen 2 specifics

Starts above 40% and max above 60%

6kW 28V 200 Ah

Batteries specifics

Nichel-cadmium 25V DC, 24Ah, 20 cells

External Power specifics

28V DC, 800Ah

Inverter specifics

600V AC, single phase static inverter

“BATT HOT”

On at 66°

Back OFF at 60°

Hydraulic system nominal pressure

176+-14 bar

Hydraulic main system is linked to

LDG gear, wheel brakes, NAS, flaps, speed brake , ail servo

Hydraulic emergency system is linked to

LDG Emergency extension

EMG brakes

Minimum pressure for emergency breaking

70 bar

Safety pressure valve of the hydraulic systems opens and closes at

Opens 235 and closes at 201 bar

Solenoid operated separation valve

108 bar

Ail servo system use a pressure reduced at

146 bar

Ail servo switch back to manual mode when pressure below

61 bar

Nitrogen charge main and emergency hydraulic accumulator at

59 bar (860 psi)

Landing gear retraction and extension time in normal and emergency procedure

5 sec normal

20 sec emergency

Flashing red light in landing gear handle when

Speed below 165 kias, altitude below 10000ft and RPM below 62%

Steady red light of landing gear contro lever

Mismatch between lever position and actual gear

Nose wheel microswitch

RATS

RNAV heater

AOA heater

TTS heater

Steering

Microswitch left main gear

SERACAP

Salvo Jett

Electrovalve for hydraulic circuits separation

Retraction of gear on ground (down lock override)

Anti-ice engine

Canopy seal

Anti-skid

Pitot annunciators

Microswitch right main gear

SERA

Salvo Jett

Electrovalve for hydraulic circuits separation

Retraction of gear on ground (down lock override)

Anti-ice engine

Corner speed

280-320 kias depending on mass

Max glide distance clean configuration

150+ corrections (AOA .48)

Max steering angle

56° left and right

Excursion of flaps

0°

28°

66°

Speedbrake excursion

56° max

28° half

Fuel system transfer pressure

0,3 bar

Booster pump pressure

18 psi

“FUEL PRESS” caution legend and time of flight available without pressure

< 3 psi (0.2 bar)

15’ flight without pressure

Normal fuel transfer

41kg/min

Fuel transfer valve opens when

Fuselage tank is below 590 +20/-30

“F. TRANS” caution legend

The selected tank (pyl or tip) are non transferring regularly into fuselage tank.

Fuel contained in fuselage tank is less than 500+30/-20

“F.LOW” caution legend

Fuselage tank below 210+-20kg

“F.UNBAL” caution legend

Difference of more than 60kg for more than 12 sec

Fuel dump time

Only tip, 2 min for ¾ and 6 min for the remaining ¼

Main fuselage tank

626 kg

Tip tank quantity

803 kg

Pylon tank quantity

530 kg

Total fuel clean config

1429 kg

Total fuel quantity with pylon

1959 kg

Unusable fuel for each tip

10kg

Seat ADJ switch do not operate for more than

1 min (wait 8 minutes between operations)

Sequential ejection (who goes first and time)

Back seat 0.35 sec earlier

Altitude for controlled bail out

2000 ft AGL

Altitude for uncontrolled bail out

6000 ft AGL

Barostatic time release unit prevent automatic man seat separation:

Above 5000mt (16.500ft) and between 5000mt and 2100mt (6900 feet) if g controller unit senses more 2,25 g

Oxygen total capacity

68 lt

Oxygen operating pressure

27.5 bar reduced to 5 bar for breathing

“OXY LOW” caution legend

Less than 7+-0.7 bar

Min oxygen for local sortie

20 bar

Above 33.000ft cabin altitude regulator supplied

100% oxygen in norm position

Above 36.000 cabin altitude, regulator supplies

Oxygen with positive pressure

Explain cabin pressurization system

Sea level to 8000 = cockpit alt

8000 to 16.000 ft => 8000ft constant

16.000 to 24.000 ft => half altitude +- 500ft

Above 24.000 ft => half altitude +1000/2000 ft

Erected spin characteristics and recovery

Entry 10 kts before stalling speed, high AOA, 70° below horizon, speed increasing to 170kias

Recovery: ½ to 2/3 turn (tip empty) or 1 turn (tip full)

Altitude loss for spin recovery and pull out in any case

Less than 3000ft (4000ft inverted)

Poor visibility speed

200Kias

Tacan channels

126 X and Y

CANOPY warning light

Steady = not closed and locked

Flashing = previous condition and RPM above 90%

Min RPM to test anti-ice system

60% with both generators active

Right pitot and left pitot supply…

Right stand by instruments

Left micro air data computer

FIRE AND OVERHEAT warning lights

Above 300°C for 7 sec

“HYD PRESS” caution light

Hydraulic pressure of emergency system is less than 70 bar

Maximum temperature of wheel/brake system is attained ….

5 to 15 minutes after braking

Therefore wait 30 min before conducting any post or pre flight ops

If operating continuously under icing conditions, rpm should be…

Maintained above 55% (can fall below for a maximum of 3 minutes)

When oil press low instead of setting 85% we can set ____ to see if pressure raises to 0.35 within ____

95%

10 sec

Minimum pressure of Hydraulic Emergency Accumulator before turning engine on

59 bar