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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-skid
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
Note 
Flashcard (41)