AS350is

Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure

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AS350 SeriesSeating Capacity 4-6 standard, 7 with dual front seatExternal load up to 1.4 TonsSAR Hoist installationEMS up to 2 stretchers

Pilot/CoPilot doors with pocket doorsSliding Rear door is option L/H & R/H

Vertical Fins

Body Structure with Fuel Cell located under main XMSN

Cargo DoorsR/H & L/H

Skid gear mounted on dampers

Tail Boom

Tail Guard

Canopy

Air intake for MGB/Engine oil Coolers

MGB Cowlings RH & LH sides

T/R Driveshaft CoversEngine Cowl

HorizontalStabilizer


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Family Publication DescriptionOperating Flight Manual (PMV) RFM

Master Service Recommendations (PRE) Inspection Intervals andSchedules

Maintenance Description and Operation Manual (MDF)

Wiring Diagrams and Fault Isolation Manuals (MCS/MFI)

Standard Practices Manual (MTC) Standard repair, Maintenance & checking procedures

Maintenance (MET), Repair (MRR) andStorage (MST) Manuals

Difference maintenance levelOperations

Identification Catalogs Illustrated Parts, Tools, Additional Supply Parts, Tools and Materials

Service Bulletins Helicopter publication supplements Directives for operators

Service Letters Temporary supplements Topics of Interest (blue hatch – note as important)

Engine Publications Maintenance Manual, Parts/Tool Catalogue, Service Bulletins

Equipment Publications

Equipment Description and Maintenance Manual (MCM)

Publications• 3 Families• Operating• Maintenance• Identification


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System DescriptionMain Rotor Hub (MRH) Starflex semi-rigid bearingless hub without a drag damper. Modular, fail

safe,Greaseless

Main Rotor Blades Spar made of fiberglass roving, glass fabric skin. and foam core. Fail safe design

Main Rotor Mast Removable sub-assemblies. Mast casing attached by 4 suspension bars which lift the helicopter. Includes servo actuators

Main Gear Box (MGB) Modular design attached by flexible bidirectional suspension. There are 2 reduction gear stages – 1. bevel gear drive, 2. Epicyclic gear train. Pressure lubrication with oil cooling system, rotor brake and hydraulic pump drive.

Tail Rotor (TR) Two blade hingeless seesaw rotor with glass roving spar. Pitch change through spar twisting. Greaseless fail safe design.

Tail Rotor Gearbox (TGB) Angle reduction gear with splash lubrication

Engine Powered by LTS 101 in D (super D) models. Powered by Arriel 1 (B, BA, B1, B2) and Arriel 2 (B3)

ARRIEL 1 AND 2 LYCOMING LTS 101


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Overall Length Rotors Turning - 42.45ft (12.94m)Rotor Diameter - 35 ft (10.69m)

Fuselage Length - 35.80 ft (10.93m)

T/R Diameter- 6.10 ft (1.86m)

OverallHeight - 10.93 ft (3.33m)

Low skids

Skids - 7.48 ft (2.28m)

Horizontal - Stab8.29 ft (2.53m)

Widest Part

Fin Height - 10.70 ft (3.26m)

Low skids


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X YZ

133.8” (3.4m) Rotor Hub Axis tilted

2 deg forward

102.3”(2.6m)

Fwd CG Limit Aft CG Limit

Airframe Reference Points and special configurations

Helicopter Datum ReferencesX – Longitudinal 133.8” fwdY – Lateral 102.3” above cabin floor datumZ - Vertical

Hoist the helicopter from here after removal of the M/R blades

Mooring points for high wind are here - L/H and R/H sides

Ground handling wheels attachhere


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Instrument Panel Console and Controls

Collective Controls

ExtPwrBAT

Fuel Pump

GenGen

ResetCrank

MasterSW

W/LTTest

A/ColPosLts

HydTest

Horn

PitotInst.Lts 1

InstLts 2

StrobeLt

TaxiLt

LandingLt

StandbyHorizon

FlowMeter

Sand Filter

ConfWS

Wiper

InvertAtt.Ind

Gyro Compas

TrimRlse

Pitch Trim

RollTrim

FloatArm

Sling Hoist FlareFloatFiring

AS350 uses fusesLocated on 31α and 32α panels

Blue and Red switches are normally in the same place

Hyd. cutoff Button

Hyd. cutoff Button

Swivel Light on/off

Swivel Light Control

Twist gripFriction

VEMD scroll switch

Push button forautomatic Governor locking

Securing Stud (collective full down

The B3 has 2 additional switches anda twist grip throttle

B

B3

BA, B1, B2


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Instrument Panel D, B, BA, B1, B2

Instrument Panel B3 with VEMD

Caution Panel – Bleed Valve is for B, BA Models only

Caution Panel – The B3 incorporates a VEMD for monitor-ing of engine instruments and other pa-rameters.

In addition the aural warning is sounded for First Limit (FLI) and NR max as well as NR min and Hydraulics

HYD GENMGB P

MGB T BAT

HORN F. FILT FUEL BAT T

DOORS ENG CHIPFIRE

PITOT BLEED V

CHIP TGB MGB CHIP ENG P FUEL P

FUEL ------ GENE PITOTMGB TEMP

ENG CHIP

ENG PENG FIRE

FUEL P

------ BATT HORN DOORMGB CHIP

MGB P

BAT TEMP

FUEL FILT

------ ------TWT GRIP

GOVTGB CHIP

GOV HYDR


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Click the cursor over thecaution panel to see necessary actions

Doors

One or both baggage hold side doors unlocked

• Reduce airspeed 120kts max.• Check visually if possible that doors are closed.• If one or both doors are open or it is not possible to check, land if possible or continue flight at reduced speed.• Maintain low sink rate and flat profile landing approach.

Hyd - Failure

Servo-Control system failure - Press < 30 bar.The pressure stored in the accumulators allows sufficient time to slow the aircraft with hydraulic assistance. Warning of the pressure drop is confirmed by the horn.

• Reduce collective and airspeed to 40-60 kts.• Disengage the collective pitch hydraulic pressure switch. (Isolate servos).• Make a flat approach over a clear area and make a run on landing with slight fwd speed (walking pace).• If failure occurs in a hover, land normally

Note - There is no yaw servo accumulator on the D, B, BA. The B1 and B2 are as follows

The yaw servo-control has a load compensator and a hydraulic accumulator. which remains pressurized indefinitely after a hydraulic pump failure or after hydraulic power cut-off via the collective lever hydraulic power release control. The accumulator may be depressurized by pressing the HYD. TEST pushbutton. Do not press the HYD. TEST push button: this would cause inmediate depressurization of the accumulator and the resulting control loads could be heavy.

Horn

Alarm Horn not set.

• Set the horn by pressing the push button on the center console• The horn will sound under the following circumstances:

₋ Hyd caption light - Pressure < 30 bars ₋ NR between 250-335(250-360 on BA,

B1 and B2) ₋ NR > 410 intermittent (B1, B2)

Chip TGB

Metal particles detected in TGB.

• Continue flight avoiding prolonged hovering.

Gen

DC. power supply failure. If voltmeter shows > 24v or ammeter not zero, Gen is working.

• Test the D.C. voltage.• Check the position of the push-button.• Attempt to reset after mod 1686.• If unsuccessful:• Shed the least essential GEN consumer circuits; continue flight, according to circumstances, keeping a close check on voltage (22 volts minimum). -Maximum flight time on battery : • Day: 50 min.

₋ Items - Battery, Fuel pump, VHF, Radio- Nav

• Night: 20 min. ₋ Items - Day + Inst. Lts 1+2, Horizon, Pos

lts, Anti-Col.• Land as soon as practicable. See altitude limits after booster pumps have been switched off.

Fuel Filter

Fuel filter clogging (impending bypass). P1-P2 differential > 206mb

• Reduce Power

• If light goes out, continue flight at reduced power

• If light remains on, land as soon as possible.

F. FILT

F. FILT

Engine Chip

Metal particles in engine oil system

• Land as soon as possible.• For Turbomeca engines it is prohibited to takeoff again until necessary maintenance inspections have been performed.

MGB Chip

Metal particles in MGB.

• Reduce power. • Monitor MGB.P. and MGBT. lights on caution panel.

• If MGB P light illuminates reduce power and land as soon as possible. The MGB has been bench tested to 45 mins at zero pressure with a min. power setting in level flight at 55 kts.

• If MGB T light illuminates press the CAP test panel switch to check the MGB P light.• If the light does not illuminate land as soon as possible (same as MGB P light), otherwise land and check the MGB oil level - if normal fly to the nearest base.

MGB P

MGB T

MGB Oil Pressure

Main Gear Box oil minimum pressure.

• Reduce power and land as soon as possible. The MGB has been bench tested to 45 mins at zero pressure with a min. power setting in level flight at 55 kts.

Fire

Engine Fire.

• Fire during start ₋ Fuel Flow Control - Close ₋ Fuel Shut Off - Close ₋ Boost Pump - Off ₋ Ventilate (crank) 10 secs ₋ Battery - off ₋ Extiguish fire with available equipment

• Fire in flight ₋ Enter autorotation ₋ Fuel Shut off - Close ₋ Boost Pump - Off ₋ Master Switch - Off ₋

Note: Thinking pilots will (time and circumstnances allowing), look for signs of fire eg. smoke trail, smell. Condensation and false failures are not uncommon

MGB Oil Temperature

Main gear Box maximum oil temperature.

• If MGB T light illuminates press the CAP test panel switch to check the MGB P light.

₋ If the light does not illuminate land as soon as possible (same as MGB P light),

₋ otherwise land and check the MGB oil level - if normal fly to the nearest base.

MGB P

MGB T

Pitot

Pitot heating system is not on.

• Check the push button is on (center console)• Keep watch on IAS readings.

Engine Oil Pressure

Engine Oil pressure alarm

• Reduce power.• Check engine oil pressure - If pressure is low or zero

₋ read torquemete : ₋ If reading very low shut down engine ₋ If reading correct land immediately ₋ If both pressure and torquemeter

readings are correct, land as soon as ₋ possible.

Fuel Quantity

Fuel quantity is below 15.8 US glas (60 litres)

• Avoid large attitude changes• Remaining usable fuel:

₋ D, B, BA - 25 mins approx ₋ B1, B2 - 18 mins approx

Battery

Battery disconnected from the DC circuit. Battery not charging

• Check push button - on (center console)• Keep a watch on voltage• Continue flight according to circumstances

Battery Temperature

Battery maximum temperature

• Isolate the battery by switching the battery off (center console)• Land as soon as possible.

Note: AS350 series helicopter may be fitted witha lead acid batery in which case the Battery Temperature monitoring is disabled (unnecessary) and placarded accordingly.

Bleed Valve

This is an indicator light only for the B and BA versions.

• The Bleed valve indicator light will normally illuminate (bleed valve open) when NG < 93% approx and extinguish (bleed valve closed) when NG > 96% approx.

Anomalies

Bleed Valve light on (bleed valve remains open)

₋ Increase fuel consumption ₋ limited power (especially at higher

altitude)

Bleed Valve light off (bleed valve closed - jammed)

₋ Increased possibility of surging

Note: In all cases avoid sudden power variations.

BLEED V

BLEED V

Fuel Pressure

Fuel pressure < 0.2 bar (B1, and B2 have dual boost pumps - failure can occur in one or both)

• Check Fuel Boost Pump(s) switch is on• Check fuel contents and fuses (if poss.)• Check fuel pressure:

₋ If failure is confirmed ₋ Do not continue flight longer than

necessary. It is prohibited to takeoff with inoperative fuel boost pump(s)

• FUEL P. > 0.2 bar on either or both. ₋ If pressure is normal: ₋ one pump is faulty (B1, B2), or system

is faulty - flight may be continued.• Pressure Zero, pump(s) are faulty:

₋ flight may be continued at an altitude lower than 5000 ft (1524m ).

• Low Pressure: ₋ Press CAP test and check Fuel F. light ₋ If light does not illuminate - continue

flight otherwise land as soon as possible.

AS350is

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