EC130 B4 Systems Flashcards
Main rotor hub
Starflex semi-rigid, bearingless hub without a drag damper.
Laminated glass resin star.
Modular fail safe design
Anti-vibration device/Rotor hub vibration absorber: A weight suspended by 3 springs absorbs lateral vibrations.
Main rotor blades
Fiberglass roving spar, glass fabric skin, foam core. Stainless steel cuff (leading edge)
Glass fiber spar box structure inside with foam core.
Main Rotor Mast
Tilted 2 degrees forward. Mast casing attached by 4 suspension bars. Includes servo actuators.
Main Gearbox
Modular design attached by flexible bidirectional suspension.
2 reduction gear stages (bevel gear drive, epicycles gear train)
EBCAU
Engine Back Up Control Ancillary Unit
Controls backup fuel metering valve in case of FADEC or stepper motor failure
Fuel Capacity
144 US gal
Fuel system
Fuel level and separate low fuel sensor in fuel tank.
Primer pump in fuel tank — through Fuel cutoff — Low pressure pump — Filter including bypass and FUEL FILT clogging detector — FUEL P detector <0.5 bar — High pressure pump — Engine
Fuel flow control
Dual channel FADEC powered helicopter 28V system and by N1 driven FADEC alternator. (Even momentary loss of normal DC power causes GOV light and disables idle mode)
Duel stepper motor fuel control with separate “Resolver” that senses position.
EBCAU separate fuel control for back up automatically set to neutral position during normal operation.
Electrical system
15ah battery in tail boom.
28V electrical system
Electrical Master Box in aft cargo
Systems control unit in lower console.
ASU under floor
3 modules of the main rotor gearbox
Top to bottom:
Epicyclic module
Bevel module
Oil module
Engine Modules
5 modules
1: Driveshaft/Power Shaft
2: Axial compressor and accesory gearbox.
3: Centrifugal compressor and N1 turbine.
4. Nf turbine
5: Reduction gearbox
Tail boom
Semi monocoque. Circular frames covered with skin.
Horizontal stabilizer
Asymmetrical airfoil. Attached with Murphy-proof attachment. Trim strip on top
Landing gear
Skid type. Supports the helicopter and damps out vibration. 3 point mustache shape with elastomer fittings reduces possibility of ground resonance.
Articulated Coupling
-To maintain MRG/engine distance constant.
-To align the driveshaft.
-To absorb engine overturning torque.
-To support the engine.
Main Rotor Gearbox Suspension
4 suspension bars suspend and support the MRG. Flexible suspension supports the base with laminated pads that deform in shear but not in compression.
A block will hold the gearbox in place even if a laminated pad is destroyed.
Spherical Thrust Bearing
Flexible in torsion, flapping.
Rigid in compression.
Frequency Adaptor
Deforms in shear.
Provides damping to adjust oscillation amplitude and natural frequency
Rotor RPM Monitoring
Magnetic rate sensor and slotted wheel on rotor mast feeds info to Rotor RPM Gauge, and the ASU for aural warnings.
Vibration Absorbers
Rotor hub: 3 springs suspend a weight to absorb vibrations in the horizontal plane.
“Cabin Resonators”: Weight in floor attached to flexible steel blade that are tuned to counteract vibrations in the vertical plane.
Vibration Absorbers
Rotor hub: 3 springs suspend a weight to absorb vibrations in the horizontal plane.
“Cabin Resonators”: Weight in floor attached to flexible steel blade that are tuned to counteract vibrations in the vertical plane.
Tail Rotor Drive
Engine rear power takeoff > Forward driveshaft > Intermediate driveshaft > Rear driveshaft > Tail Rotor gearbox
4 flexible couplings between shafts
5 ball bearing support assemblies
TR Gearbox
Dual spiral Bevel reduction gears.
Splash lubricated.
Electronic magnetic chip detector
Fenestron blades
Connected by TT bar which absorbs centrifugal force.
Boss weights reduce pedal pressures.
Hub is balanced with washers
Hydraulics
LH upper system MGB driven.
RH lower system MGB belt driven.
Pumps move fluid from reservoirs through manifold then to servocontrols.
Servocontrols
Tandem cylinder design with double distributor valve provides redundancy in case of loss of hydraulic circuit or jamming of distributor valve.
RH upper servo equipped with overload sensor “LIMIT” light with 0.5 second delay.
Jamming of distributor valve causes “SERVO” light
Engine fire detection
Two 200 degree detectors front of engine
One 400 degree detector towards rear of engine.
Contact in detector breaks due to high temps
PCB 1 displays ENG FIRE and gong
Torque measurement
Transmission shaft teeth measured in comparison to reference shaft teeth. Torsion of the shaft is calculated by a phonic sensor.
NG sensor location
Part of the FADEC alternator
