Ec225 Tech Quiz

Front 1

Max Gross Weight of 225?

Back 1

11,000 kg

Front 2

Max Weight on the Sling?

Back 2

3,000 kg

Front 3

Max overall width of 225?

Back 3

16.2 m (Rotor Diameter)

Front 4

Max height of 225?

Back 4

4.97 m

Front 5

D Value of 225

Back 5

19.5 m

Front 6

Wheel tracking width

Back 6

3 m

Front 7

Minimum permissible weight of 225?

Back 7

6500 kg

Front 8

FADEC stands for?

Back 8

Full

Authority

Digital

Engine

Control

Front 9

On touchdown, the skid shoe will contact at....?

Back 9

12 degrees

Front 10

Total fuel capacity WITHOUT EFT's

Back 10

2297 kgs

Front 11

A blue light on a cockpit switch or panel indicates?

Back 11

Correct Position

Front 12

A system panel 'Latch' type switch that has a Yellow and White light illuminated within the switch indicates?

Back 12

The system is switched off.

Front 13

A Blue & White illuminated switch labeled GPU indicates?

Back 13

The GPU is available but NOT authorised.

Front 14

A yellow latch switch in the overhead console indicates?

Back 14

The system has failed OR is not online.

Front 15

A BLUE illuminated switch in the overhead console indicates?

Back 15

The GPU power is available AND operating the aircraft systems.

Front 16

A green light on a switch or system panel indicates?

Back 16

Normal system operation.

Front 17

In the event of CAUTION +HYD caption illuminating, the correct action to take would be:

Back 17

Check the VMS VEHICLE page for a Hyraulic systems caption or parameter, cancel the CAUTION, consult the checklist.

Front 18

The captions that can be extinguished by cancelling the amber CAUTION attention getter on the CWP are:

Back 18

HYD

FUEL

XMSN

FIRE DET

ENG

Front 19

How is the ELEC caption on the CWP extinguished?

Back 19

By selecting the failed electrical system OFF

Front 20

In the VMS, failure of EID 1, and following reconfiguration, will result?

Back 20

In EID 2 defaulting to the ENGINE page.

Front 21

Soft keys on an MFD are active...

Back 21

For those functions which they are labeled.

Front 22

To permit accurate fuel capacity computations, the correct values for fuel density that should be entered into the VMS are?

Back 22

0.79 SG & 15 degrees

Front 23

To permit an accurate calculation of the minimum VTOSS, what action must be taken by the flight crew?

Back 23

Ensure that the VMS Take-off weight is correct by checking the accuracy of:

Aircraft Empty Mass

Fuel Mass Value

Accurate Payload Mass

Front 24

A 'PING' annunciation indicates:

Back 24

MPC has been reached on the FLI

MTOP has been reached on the FLI

The Hydraulics Servos are close to 'Jack-Stall'

Front 25

A 'GONG' annunciation indicates:

Back 25

A red WARN + Red caption on the CWP

(except fire)

Front 26

Which of the AMC's is the master unit?

Back 26

AMC-01

Front 27

The AHRS units use which type of component to provide primary attitude info?

Back 27

Fiber Optic Gyroscopes

Front 28

The First Limit Indicator provides a consolidated indication of which engine parameters?

Back 28

N1

TOT

Tq

Front 29

'Safety Pitch' indication is provided on the FLI to facilitate:

Back 29

A safe operating margin for revision to single flight as the VMS will only display AEO parameters until OEI flight has been established.

Front 30

'Safety Pitch' on the FLI, when operating at 80kts corresponds to:

Back 30

OEI LO @ 100% Nr

Front 31

The APM's are provided with collective pitch setting information by which component?

Back 31

Collective pitch Trim Actuator

Front 32

Which power margins are being utilised when operating in the AMBER band on the FLI scale with AEO?

Back 32

Take-off power (5mins)

Front 33

OEI CT limit on the FLI scale is indicated by:

Back 33

The bottom of the amber band & the FADEC stop symbol

Front 34

OEI LO Limit on the NG gauge is indicated by:

Back 34

A BROKEN RED line

Front 35

The FADEC Stop (topping) is indicated on the FLI scale by?

Back 35

A RED 'Diode' symbol

Front 36

When operating in the OEI-HI power margin, the correct symbology is:

Back 36

Front 37

When operating in the OEI-LO power margin, the correct symbology is:

Back 37

Front 38

The aircraft CG datum is located?

Back 38

4.67 m FORWARD of the main rotor

Front 39

What are the boot loading limitations

Back 39

A (Top Shelf) : 250kgs

B (Tail Cone) : 50kgs

C (Main Lug) :250kgs

A+B+C =400kgs max

Front 40

Capacity of the MGB oil system is?

Back 40

24 liters

Front 41

During normal system operation the MGB standby oil pump is prevented from delivering oil to the gearbox by?

Back 41

Check Valve located on the filter assembly.

Front 42

The DOOR/COWL caption on the CWP can be cancelled by?

Back 42

Close the relevant door
Pressing the re-arm on the Door Monitoring panel

Front 43

The MGB LH Accessories gearbox drives?

Back 43

ALT 1

LH HYD Sys Pump

MGB oil cooler fan

Front 44

The MP amber caption on the VMS Vehicle page indicates?

Back 44

Pressure in the main pump line is <3.7 bar

Front 45

With the MGB Main Pump operating normally and NO other captions, illuminations of the S/B P caption on the VMS Vehicle page indicates?

Back 45

The STBY pump is delivering <2.6 bar

Front 46

The correct action to take following illumination of the red MGP P caption on the CWP is:

Back 46

Reduce to Vy & operate the EMLUB system, land within 30mins.

Front 47

Temp threshold for illumination of the AMBER MGB T on the VMS Vehicle page?

Back 47

Front 48

CHIP caption cleared on the VMS Vehicle page using the Fuzz Burner. Where has the chip been burnt from?

Back 48

The chip was on the sump chip plug on the MGB

Front 49

Following a MP caption on the VMS vehicle page the AMBER MGB T illuminates. The correct action to take is:

Back 49

Reduce to Vy and monitor the MGB temperature

Front 50

Operation of the MGB Standby Cooling System will cause?

Back 50

Some of the MGB Oil to be passed through the standby heat exchangers for cooling and then passed through the endoscopic

Front 51

The purpose of the over-pressure vent in the MGB is?

Back 51

To prevent the pressurisation of the MGB when the EMLUB system is in operation

Front 52

The EMLUB system consists of?

Back 52

11lts of glycol, injected with the assistance of P2.4 air (from the LH engine). (30mins).

Front 53

In the event of OEI, operations of the EMLUB system is?

Back 53

Not possible if the LH engine fails.

Front 54

The purpose of the heat exchanger in the EMLUB system is?

Back 54

To reduce bleed air temperature below 80 degrees

Front 55

The correct response to the illumination of the Red MGB T caption on the CWP, verified by gauge indications is?

Back 55

Front 56

Illumination of the MGB EMLUB caption on the CWP indicates?

Back 56

Failure of the EMLUB system OR the GLYCOL tank is empty

Front 57

With regards to the Rotor Brake, engine start is inhibited when:

Back 57

The rotor brake operating lever is in the 21 bar position

Front 58

The rotor brake receives hydraulic fluid pressure from:

Back 58

The LH hydraulic system

Front 59

The RB ON caption is illuminated:

Back 59

By a micro-switch at the RB puck calliper

Front 60

When must a high wind start procedure be carried out?

Back 60

When the wind speed exceeds 30kts

Front 61

During a high wind start with the Rotor Brake applied and the engine switch in the FLIGHT postion, what will occur?

Back 61

The engine will accelerate to IDLE

Front 62

The maximum NR limit for application of the rotor brake is?

Back 62

45 %

Front 63

The articulation of the MR blade sleeves is effected by?

Back 63

Laminated Spherical Thrust Bearings for ALL planes of movement

Front 64

IGB T caption will illuminate when the oil temperature in the IGB exceeds?

Back 64

110 degrees

Front 65

TGB T caption will illumunate when the oil temperature in the TGB exceeds?

Back 65

94 degrees

Front 66

Conning angle of the MR blades is limited by?

Back 66

The centrifugal coning stop

Front 67

The MR drag damping is effected by?

Back 67

Hydro-elastomeric drag damper

Front 68

Automatic rotor tuning is effected by?

Back 68

Accelerometers built into the aircraft

Front 69

The LH Nr gauge is powered by?

Back 69

The Essential & Secondry bus

Front 70

The Nr LOW and HIGH aural waring thresholds are?

Back 70

95.5%

109.5%

Front 71

Power ON max continuous Nr is?

Back 71

103.8%

Front 72

Power OFF minimum NR < 100KIAS?

Back 72

83%

Front 73

Failure of the Single Phase 26V AC Transformer is indicated by?

Back 73

0 volts indicated on the overhead panel with the rotary selector switch set to the 26V position.

A STAB caption on the Radar display.

Front 74

A short circuit on the ALT 1 distribution bus will be indicated by?

Back 74

ALT 1

BUS 1

TRU 1

Front 75

Illumination of:

TRU2,

ESS BUS,

BUS TIE and

BATT+

captions indicate?

Back 75

DC essential Bus Short Circuit.

Front 76

What electrical consumers are lost with a single alternator failure?

Back 76

None (redundancy).

Front 77

How are DC consumers supplied in the event of a short circuit on the AC Distribution Bus?

Back 77

Both ESS and SEC DC Bus Bars are supplied by the remaining TRU.

Front 78

The EMERGENCY consumers are?

Back 78

(From the Emergency Battery....)

ISIS

Ordinance Lights

Emergency Lighting

Triple Tacho

Front 79

In the event of a double Alternator Failure, what occurs in terms of load-shedding?

Back 79

PP3 (SEC BUS) load-shedding occurs automatically.

Front 80

Following a double TRU failure, indications that the Emergency DC Power Supply has come on line are?

Back 80

DC captions on the CWP extinguishes and a green FLOW light illuminates in the Emergency DC Power Supply selection switch.

Front 81

The amber TEMP caption in the overhead panel indicates?

Back 81

Battery is warm

(>10 degrees case/internal temp differential)

Front 82

The minimum voltage for a battery start is?

Back 82

25 Volts

Front 83

AHRS 1 receives a reference signal from which component?

Back 83

26C AC Transformer

Front 84

Activation of the Emergency Gang-bar deselects what?

Back 84

ALT 1 & 2

and the BAT + contactor

Front 85

The LH Hydraulic system supplies which servo's?

Back 85

Upper bodies of the MR servos

LH TR servos

Front 86

Illumination of the RH LVL caption on the VMS vehicle page indicates?

Back 86

Fluid in the reservoir has dropped to 2 liters or the socket is disconnected.

Front 87

Illumination of the APUMP caption on the VMS Vehicle page indicates

Back 87

The AUX pump has seized and an over-current is occurring (short circuit)

Front 88

The Auto-Pilot Hydraulics are lost when?

Back 88

LH LVL caption illuminates

(4 lts)

Front 89

When the landing gear is lowered, the AUX pump will run:

Back 89

AUTOMATICALLY

Front 90

In the event of a Hydraulic leek occurring at the LH Hyd Pump, how will system pressure be assured>

Back 90

It is assured by the Main Pump 2 lt standpipe and the inline check valve.

Front 91

The AA.P caption will illuminate when system pressure in the AP Hyd pack:

Back 91

<70 Bar

Front 92

What indications and actions are required when the landing gear is lowered using the emergency landing gear extension system

Back 92

3 x greens within 2 minutes. The emergency landing gear extension handle needs to be pushed down to stop the pump after 2 minutes of operation (for cooling)

Front 93

A green PUMP light on the landing gear control panel indicates?

Back 93

The pump is running

Front 94

The undercarriage red LG warning light illuminates when?

Back 94

IAS < 60kts and undercarriage is retracted.

Front 95

Minimum GS for brake application

Back 95

35 kts

Front 96

A jammed main servo rotary distributor valve is indicated by?

Back 96

There is no cockpit indication.

Front 97

In the event of control failure, the TR control safety device will

Back 97

Set the tail rotor pitch to a value corresponding to 6-6.5 FLI (spring system)

Front 98

The Smart Electro-Mechanical Actuators have how much authority of the flight controls?

Back 98

+/- 7%

Front 99

In the event of LH Hydraulic system failure, a coupled approach is possible provide:

Back 99

The SEMA's are serviceable.

Front 100

Yaw / Collective coupling is provided such that:

Back 100

Permits yaw inputs generated by collective and the pedals do not move.

Front 101

The analogue trim actuators have how much control authority?

Back 101

100 %

Front 102

In the 7 tank fuel system, the correct number of jetpumps fitted are?

Back 102

RHG x 3

LHG x 1

Front 103

Low level fuel sensors are fitted in?

Back 103

Only the longitudinal tanks (< 71 kgs / 90 lts)

Front 104

During fuel transfer operations betwen longitudinal tanks, the HIGH level indicator light will illuminate when:

Back 104

The receiving longitudinal tank is full.

Front 105

With the AUTO TRANSFER switch in the OFF position on the fuel panel, the fuel quantity indication will be?

Back 105

LH and RH group quantity.

Front 106

Maximum permitted pressure for pressure refueling is?

Back 106

3.5 Bar

Front 107

During flight if fuel does not appear to transfer from the SPONSON tanks, the probable cause is:

Back 107

The REFUEL / DEFUEL switch is not in the OFF position

Front 108

The Engine Warning Repeater in the overhead quadrant will illuminate when?

Back 108

OIL P

FADEC

FIRE

warnings illuminate

Front 109

The DIFF PWP caption on the CWP will illuminate when:

Back 109

Tq split >20%

N1 split > 6%

Engine Failure

Front 110

CHK TRQ caption will appear on the FLI scale when TQ split exceeds?

Back 110

5 %

Front 111

The engine bleed valve closes in normal operation at:

Back 111

90 %

Front 112

OIL P1 caption on the CWP will illuminate when engine oil pressure reaches?

Back 112

< 1.6 BAR

Front 113

In flight the illumination of the FADEC caption on the VMS indicates:

Back 113

Major governor failure

Front 114

Overspeed?

Back 114

117% - FADEC will shutdown engine

Front 115

Bleed valve offset mode control is effected by:

Back 115

APM's (in regards to IAS and RAD ALT)

Front 116

An engine automatic overspeed shutdown is confirmed by:

Back 116

The GOV light flashes when the starter selector is switched to shutdown

Front 117

How is Nr effected with an engine FADEC selector in the BACK UP position?

Back 117

The fuel metering is frozen, therefore Nr is regulated at 103.8%

Front 118

N1 speed signals are provided to the FADEC by?

Back 118

The engine driven Alternators

Front 119

The triple Tach derives N2 speed signals sensed from?

Back 119

Toothed wheel (F1) fixed to the Free Turbine Shaft.

Front 120

Inadvertent operation of the 2nd SHOT fore bottle during an engine fire drill will cause:

Back 120

The fire bottle of the other engine to be discharged into the engine.

Front 121

The ISIS receives air pressure information from:

Back 121

Direct from the RH pitot tube.

Front 122

Three flashing indications at the top of the FND - P R Y:

Back 122

Are instructions to the pilot to TAKE MANUAL CONTROL.

Front 123

ECL INITIAL ACTIONS:

ENGINE OVER HEAT DURING START OR SHUTDOWN

Back 123

1. Engine Control Switch - STOP

2. Crank affected engine UNTIL < 200°C

Front 124

ECL INITIAL ACTIONS:

ENGINE BAY FIRE ON GROUND

Back 124

1. IF fire is confirmed visually…..

a. Illuminated fuel shutoff valve - CONFIRM and PULL

b. Fire extinguisher (1st shot) - ACTIVATE

c. Engine control switch - STOP

d. Booster pumps - OFF

2. IF fire indications persist….

a. Fire extinguisher (2ndshot) - ACTIVATE

Front 125

ECL INITIAL ACTIONS:

ENGINE BAY FIRE IN FLIGHT

Back 125

1. Fire - CONFIRM

2. Illuminated fuel shutoff control - CONFIRM and PULL

3. Fire extinguisher (1st shot) - ACTIVATE

4. Engine control switch - STOP

5. Booster pumps (affected engine) - OFF

6. IF fire indications persist….

a. Fire extinguisher (2ndshot) - ACTIVATE

b. Start timer.

12. If the fire indications persist for more than 1 minute after step 6 -

a. LAND / DITCH IMMEDIATELY

Front 126

ECL INITIAL ACTIONS:

MGB FIRE 1 AND2

Back 126

1. LAND / DITCH IMMEDIATELY

(EMERG LANDING POWER ON)

NOTE: Only ONE MGB FIRE detection does not indicate a MGB fire. The systems run in parallel to each other an therefore TWO indication will be evident when there is a fire.

Front 127

ECL INITIAL ACTIONS:

SMOKE AND / OR FIRE IN THE CABIN OR COCKPIT

Back 127

A)ACTIONS ON THE GROUND

1. Radio call Complete

2. If the source cannot be identified and isolated:

a.General cut-out handle PULL

b.Rotor brake APPLY

c. Passengers Evacuate

B) ACTIONS IN FLIGHT

ECL

Front 128

ECL INITIAL ACTIONS:

SINGLE ENGINE FAILURE IN FLIGHT

Back 128

1. Comply with relevant profile

2. Collective Maintain NR

3. If there are fire indications - 03 ENGINE FIRE IN FLIGHT

Front 129

ECL INITIAL ACTIONS:

DUAL ENGINE FAILURE IN FLIGHT

Back 129

1. Collective - Lower immediately

Warning: NR will decay rapidly even if recovery action is taken within 1 second. Maintain collective FULLY DOWN until NR recovers

2. Auto-rotate - 80 knots

3. If time persists:

a. Both engine control switches STOP, then FLT

NOTE: The start sequence will not begin untilN1 reduces to 10%

4. Landing Gear - Down overland / Up over water

5. Parking brake - OFF

6. Nose-wheel - LOCKED

7. Floats (overwater) - ARM /INFLATE (max 6500’/85kts)

8. Radio call - Complete

9. Satellite tracking - Switched to emergency

10. If neither engine will start Conduct a power of landing / ditching.

CONSIDERATIONS:

If neither engine has started by 1000’ RADALT, switch both to STOP and booster pumps OFF

EOL - Progressive flare technique:

At about 150’ above the surface, flare20° nose-up within 2 seconds and lower the collective. For landing, set 10° nose-up and use collective as required to cushion the touchdown.

EOL – Constant pitch attitude technique:

At 300’above the surface, set 10° nose-up and lower the collective fully. For landing, at about 50’ use the collective as required to cushion the touchdown.

EOL – For both techniques:

o As the collective is raised to cushion the touchdown, the collective to-yaw interlink will increase the tail rotor pitch, causing right yaw. Correct with left pedal and control roll attitude with cyclic to minimize drift.

o Over water, try to reduce the G/S as much as possible and land with the wind 10-20° to the left.

o Over land, at heavy weights, land at 20 knots or more if surface conditions permit.

Front 130

ECL INITIAL ACTIONS:

FADEC FAILURE(MAJOR GOVERNING FAILURE)

Back 130

1. Collective - Maintain NR

2. If during takeoff - Continue takeoff

Front 131

ECL INITIAL ACTIONS:

TOTAL LOSS OF MGB OIL PRESSURE

Back 131

MGB oil pressure < 0.4 bar

1. EMLUB SHOT Press

2. Timer Start (max 30mins)

3. Airspeed Set Vy

4. If the indications were simultaneous, or if MGB EMLUB illuminates:

a. LAND / DITCH IMMEDIATELY

Front 132

Ground Clearance is

Back 132

.43 m

Front 133

Tail Skid clearance is

Back 133

1.12 m

Front 134

Max Floor Loading

Back 134

800 Kg/m sq

Front 135

Max Crosswind/Tailwind is

Back 135

Crosswind :25 kts

Tailwind :20 kts

Front 136

Max Turbulence Speed is

Back 136

135 kts

Front 137

Rotor Brake limits are

Back 137

2 x 5 mins then

15 mins break (10 mins rotors running)

Front 138

Max Braking / Landing speeds are

Back 138

Landing Speed : 40 kts

Braking Speed : 35 kts

Front 139

TAWS = Terrain Avoid Warn System is

Back 139

Enhanced

Ground
Proximity

Warning

System

Front 140

Starting Limits are

Back 140

Max Continuous : 780

Max Transient : 830 - 5 sec

Max Transient : 840 - 2 sec

Auto Shut Down : 900