AW139
Max 17 Seats
MTOW with ”basic” version is 6 400 kg
(supplement 50 for 6 800 and supplement 90 for 7 000 kg)
Engines Pratt and Whitney PT6C-67C
228 kg then tanks are separate
Hydraulic system 4 pumps, one electrically driven only for flight control checks on
ground.
Safe OEI - Minimum 50 KIAS, positive ROC at acceptable power levels and sufficient
clearance from ground/obstacles.
The structure is a Semi-Monocoque structure.
Engine has 4 stage axial compressors, and one stage centrifugal compressor.
167 KIAS VNE
3 hydraulic pumps and 1 electrical one.
The main battery or the external power unit feeds the starter. The AUX battery sends
power to the essential buss and the other components.
The cockpit canopy is made of Kevlar
6 emergency exit in the cabin (two pr. sliding door).
The Engine has 14 fuel nozzles, 7 duplex and 7 simplex.
60 knots windspeed limitation rotor start/stop
Rotor start/stop in windspeed above 33 knots must be recorded in the logbook.
ENGINE
Pratt and Whitney PT6C-67C
Four axial compression stages and one centrifugal stage.
The engine has 14 fuel nossels (7 simplex and 7 duplex)
Exhaust is 57° up LH or RH configuration.
Two spark igniters per engine, only used during starting.
Oil lubricated system, Oil tank is integrated with the engine.
ITT is monitored at station 5, at the gas generator outlet, between the compressor and
power turbine.
Engine starting
ITT Maximum 870° C
ITT start 2 sec 1000°C
ITT start max 5 sec 950°C
ITT Start max 870°C 10 second
Start and IGN disengages at 49% NG.
With both engine at idle they are stabilized at 65% +/- 1% NF.
At 102% NR VNE 90 knots.
102% NR mandatory in Category A
Torque limiter on for OEI training
The NF / TQ sensor is located on the output section of the engine.
5 Engine Bearings (Nr. 1 and 5 ball bearings. Nr. 2,3 and 4 roller bearings)
BIG arrow in checklist means that it has to be done first flight of the day.
Compressor bleed valve prevents the compressor to stalls at low compressor
speeds.
The purpose of piccolo holes is dumping 2.8 air into engine inlet during low rpm to
prevent compressor stall.
The system has three scavenge pumps and one pressure pump.
One engine chip detector on each engine, It is NO way to burn the engine chip.
Engine Oil pressure low CAS when below 4,2 bar (resets above 4,7 bar). Only Low
pressure sensor.
The purpose of the Ecology Fuel Accumulator is to prevent fuel nozzle cooking after
shutdown, it stores the remaining fuel in the nozzles to be stored instead of spit it out on
the ground.
How is the fuel flow controlled during normal flight? By the EEC.
When does the EEC overspeed activate? 111% NF active and 109% NF deactivate .
2 spark igniters 4 and 8 o clock
Engine starter must be disengaged by 49% Ng (Start and ignition).
When should an engine start be aborted?
• light up is not within 10 seconds of ENG MODE to IDLE
• abnormal noise heard
• ITT increases beyond engine limits (HOT START caution illuminated)
• engine hangs (stagnation in NG below 54%)
• the main rotor has not begun to rotate when the gas generator (NG) reaches 40%
• engine starter fails to disengage by 49% NG.
Electrical power during start up is supported by the essential bus.
FIRE PROTECTION
If you receive a overpressure in the bottle or discharge it manually, the green “guard” on
the side of the helicopter will be pushed out. NO indication will be shown in the cockpit,
only “MAINTENANCE” when on ground (WOW switch)
There is one fire element gas expansion pr. engine
Smoke detector in the baggage department is a photoelectric device. It senses the
amount of light emitter by an LED source.
Fire wire filled with helium in the engine compartment
BAG fire test:
• BAG FIRE light, on fire panel
• Audio
• Master Warning
• CAS BAG FIRE
Engine fire Test:
• ENG 1(2) fire on fire panel
• Audio
• FIRE light near engine switches
• Throttles in roof lights up (ECL)
• Master Caution WARNING
• CAS 1 ENG FIRE AND 1 ENG FIRE DET
There are two portable fire extinguishers are Halon 1301 and pressurized with nitrogen.
Engine Bay fire on ground vs Engine exhaust fire after shutdown?
Main Rotor, Main Rotor Drive System, Tail Rotor, Tail Rotor Drive System, Flight
Controls
The NR sensor has three coil connector. 2 coils to 1 and 2 EEC and 1 coil to MAU.
The elastomeric bearing permits the blade to lead-lag, flap and for pitch change
movements (Flight control)
The lead-lag damper is filled with oil.
[ROTOR LOW] “ROTOR LOW - ROTOR LOW” (Priority number 1 aural warning)
ROTOR HIGH] “ROTOR HIGH - ROTOR HIGH” (Priority number 3 aural warning)
[NR MISCOMPARE] when discpenecy pf 3% between EEC Nr data and backup analog
sensor.
The MGB can be run without oil for 30 minutes.
CAS messages for [MBG OIL LOW], [IGB OIL LOW] and [TBG OIL LOW] will only be
shown on ground when Nr is below 2%.
MGB has 3 chip detectors (2 in sump and 1 in the collector tray of the mast bearing).
(Total 5 in the aircraft (2 MGB sump, 1 MGB mast, 1 IGB and 1 TGB)
Allowed to burn chips 3 times.
Can the oil pressure be monitored in the TGB? No
Where is the NF torque sensor located? On the output housing of the engine.
How is the MGB cooled? It's cooled by an oil cooler via the MGB system and ram air.
How many free wheeling units are there and where are they located? 2, located on the
MBG input modules.
What is the purpose of the anti flail? (Tail boom) It will prevent damage to the hydraulic
lines and structure.
The MGB oil low level waring can be tested: On ground with NR <2%.
Where are the MGB lubrication switches located? On the MGB input models.
How many main rotor blades? 5
How is the lead lag damper on the main rotor? Oil damper
During an autorotation, how does is the indicators show? Wider than normal.
Which hyd system power the rotor brake? It has its own system
When will the rotor brake caliper move down? Weight of wheels and engine to idle or
flight.
When the rotor is at a full stop, the brake pressure must be increased by pumping to a
pressure of 40bars. This will guarantee a brake operation of 8 hours.
Landing gear limitations - Flight manual, section 1 Limitations.
How many wheels? 5
How can the nose wheel be unlocked in flight? It can’t.
How is the landing gear locked down? It's locked down mechanically.
When ever the landing gear are in fully up positions they are held up by hydraulic
pressure system number 2.
What is the indication in the landing gear panel when the gear is up? The panel is black.
Two hydraulic system - fully independent and electrically connected.
Hydraulic system nr.1 supply power to 3 main rotor servo actuators and to the
emergency landing gear function.
Can you switch off one hydraulic system when you have no pressure on the other one?
No.
Hydraulic system nr. 2 uses pump nr. 2 and 4.
Hydraulic system nr.1 uses pump nr.1 and 3. Nr. 3 is electrical and only used on ground
for flight controls check.
What happens at the different levels when the hyd system nr. 2 reservoir has a leak?
• 50% UTIL SOV 2 = closed —> landing gear free fall - [HYD UTIL PRESS]….
• 28% UTIL SOV 2 = open —> landing gear circuit repressurized.
TRSOV = closed [2 SERVO].
• 22% [2 HYD MIN].
UTIL SOV 2 = closed —> landing gear free fall
[HYD UTIL PRESS].
TRSOV = closed
[2 SERVO].
How is the TRSOV closed? Only automatically.
How are the starter generators cooled? Air cooled by a fan mounted at the end the
starter-generator.
If you want to start the engine nr. 2 first you have to put the Bus Tie switch on.
Each generator is controlled buy the GCU (generator control unit).
During normal operation how is he battery charged?
Main battery via GEN 1 and AUX battery via GEN 2.
What is the minimum Volt to start? 23V
With EXT. PWR on the generators does not come online before the EXT PWR is
disconnected.
With the Bus Tie in AUTO, is it open or closed with both generators online? Open.
When is the non essential busses online? With both generators online or
EXT PWR connected.
In between the two fuel tanks there is an interconnection.
What is the fuel quality below the interconnection flange? 228kg.
What is the purpose of the booster pumps? Feed the engine during normal
operation and during start.
How many fuel probe sensors are the fuel tanks provided with?
4, 2 main probes and 2 secondary probes.
With the X-FEED selectors in normal and one boost pump fail the X-FEED opens
automatically.
Usable FUEL 1588 L
Unusable FUEL 20 L, 10 L / 8kg per tank
Minimum AFCS configuration for IFR flight..............2 AP in ATT mode Intentional ATT
MODE de-selection during IFR flight is prohibited.
How is pitch control on tailrotor – push pull rods and linear activators.
What is missing on the left hand side compared to right hand side collective – rpm
selector and governor switches.
How many trim motors in the 4 axis autopilot – 4 – 2 cyclic 1 collective 1 pedal/yaw.
Which statement regarding trim motors and linear activators is correct – linear activators
will operate whenever the respective autopilot is engaged regardless of force trim
switches ATT/SAS mode, etc.
What does CPL light mean – flight director coupled to the autopilot.
What is the minimum AFCS configuration for IFR flight – 2 AP in ATT mode.
What is the minimum speed to engage ALT-A after takeoff – 60kt.
Which autopilot controls the trim motors for flight controls – the autopilot trim master ->
the first Autopilot engaged.
1P trim fail caution – fail of pitch trim while AP1 has priority - QRH p40.
Where are the MAU located – front long nose – baggage com short nose.
What will you lose when MAU1 fail – AP1 and Flight Director 1.
Which system does not have a synoptic page on mfd – fuel system.
What statement is correct about CAS – warning red, caution amber, advisory green, mx
white.
What statement is correct about the CAS – all cas messages can be scrolled out of view
except warning.
Where are flux valves located – on the aircraft tail section.
What does the amber AHRS1 message on PFD mean – both PFDs are using
information from AHRS1 (only when AHRS1 selected on RCP).
What does the amber arrow on top of the copilot display unit 1 indicate – at least one on
side flight director parameter is invalid (Flight Director Failure – emg checklist –
S34-28).
What does the amber RAD on either PFD mean – rad alt miscompare (+-10ft)
MAUs receive heading information from the AHRS and ESIS (standby instrument
system).
What does the amber ALT caution on the altitude tape on the left side mean? –
miscompare in ALT +- 150ft - Page 3-177.
When does the pitot heater caution come visible - when temp is 4 or below and pitot
heat is off.
How are the windscreen vipers activated – panel (fast/slow-single/dual) + pushbutton on
cyclic.
What is the time limit PI 101-110 TO power - 5 min.
What is the maximum PI one engine inoperative
• 140% Max Continuous
• 141-160 % 2,5 min
• 176% Max transient 5s
Max windspeed for rotor start and stop – 60kt – has to be recorded above 33kt.