Post on 26-Nov-2015
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 1 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 2 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 3 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 4 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 5 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 6 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 7 of 8
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
Eurocopter AS350 - D, B, BA, B1, B2, B3 Intro and Structure
Page 8 of 8
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.