Transcript
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
ATA CHAPTER 73 ENGINE FUEL AND CONTROL 73-10 DISTRIBUTION
2
OPERATION ............................................................................................................................................ 2 Fuel System ........................................................................................................................................... 2 Fuel Filter/Heater Unit .......................................................................................................................... 4 Fuel Manifold Assy & Nozzles............................................................................................................. 7 Fuel Drain Ejector Tank........................................................................................................................ 8 OPERATION ............................................................................................................................................ 8
73-20 CONTROLLING
9
Hydro - Mechanical Fuel Control Unit (Hmu)..................................................................................... 9 Hmu Eec Mode.................................................................................................................................... 10 Hmu Manual Mode ............................................................................................................................. 12 Fault Detection System ....................................................................................................................... 13 EEC Features & TSC Features............................................................................................................ 15 EEC SAFETY FEATURES ................................................................................................................ 15 TSC FEATURES ................................................................................................................................ 15 Auto-Feather System........................................................................................................................... 16 NH Overspeed Test: ............................................................................................................................ 18 Engine Trim:........................................................................................................................................ 18
73-30 INDICATING
19
FUEL FLOW AND TEMPERATURE................................................................................................... 19 FUNCTIONAL DESCRIPTION ............................................................................................................ 19 OPERATION .......................................................................................................................................... 19 Fuel Flow Primary EICAS Page ......................................................................................................... 21 FUEL FILTER / PRESSURE.................................................................................................................. 22 FUNCTIONAL DESCRIPTION ............................................................................................................ 22 OPERATION .......................................................................................................................................... 22 Fuel -Flow / -Used / -Temperature / -Pressure and HP Filter on Fuel Page ....................................... 23 Fuel Flow on Engine Page................................................................................................................... 24 LP Fuel Filter on System Maintenance Page ...................................................................................... 25 Fuel Flow on RMU Page 2.................................................................................................................. 26
INDEX
27
LIST OF ILLUSTRATIONS
27
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-1 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
73-10 DISTRIBUTION OPERATION Fuel System
Fig. 1 Fuel System Fuel is pumped from the aircraft fuel tanks, to the engine fuel inlet, by either the electrical fuel booster pumps or by the ejector pumps. Fuel is introduced into the engine fuel system at the fuel heater unit. This unit consists of a filter and a fin type heater in two integral housings. The filter housing contains a bypass valve to ensure an adequate fuel flow in the event of blockage and an indicator to wam of impending blockage. The heater housing is divided into two circuits. RGB lubricating oil flows through one circuit to transfer heat to the fuel, which flows through the other circuit. A themnal sensor in the fuel circuit operates a valve to regulate the oil flow in order to maintain proper fuel temperature. The outlet port incorporates a switch to operate a low pressure waming and a retum port for the fuel drain tank. Fuel transfers to the fuel pump by an extemal transfer tube. The pump is a positive displacement type. The inlet contains a screen which, when blocked, lifts from it's seat to allow the fuel to bypass. The fuel passes through the inlet screen and is pumped through the outlet filter by a single stage gear type pump. The outlet filter has a bypass valve to divert the fuel flow in the event of filter blockage and an indicator to wam of impending blockage.
Page: 73-2 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
To maintain fuel inlet pressure, an amount of fuel is retumed from the HMU to the inlet side of the pump through an ejector nozzle positioned ahead of the main inlet. Fuel is routed between the HMU and the pump by intemal passages which are sealed by prefommed packings. The hydromechanical metering unit (HMU) divides the high pressure fuel between the motive flow, metered flow and bypass flow circuits. The motive flow circuit is used to drive airframe ejectors and purge the fuel drain tank. The metered flow circuit provides fuel to the fuel nozzles. The bypass flow circuit retums excess fuel back to the fuel pump inlet. An airframe supplied fuel flow meter measures the amount of fuel flowing through the metered flow circuit. The flow divider splits metered fuel flow into the primary and the secondary circuits with the engine running. During shut down the dump valve purges remaining fuel, trapped within the manifolds, to the fuel drain tank. The primary and secondary fuel manifolds carries fuel to the 14 fuel nozzles and in the event of a defective packing, drains fuel leakage. The fuel nozzles delivers fuel to the combustion chamber. The fuel drain tank contains fuel from the previous engine shut down and will be purged, during the next engine run, into the low pressure fuel system at the fuel heater unit . Types of fuel and additives Ref.: SB20004 Use of AVGAS limited to 150 hours/TBO Hours on AVGAS = Amount of AVGAS / average fuel consumption
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-3 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
Fuel Filter/Heater Unit
Fig. 2 Fuel Filter/Heater Unit Purpose: Construction:
Operation:
Filter:
Impending bypass switch:
Page: 73-4 Issue: 08/95 ETM/ETX
Pre-heat the fuel to prevent ice crystal formation Consists of a low pressure fuel filter, an impending bypass indicator, a bypass valve (ref. fuel system), a heat exchanger, a thermal sensor and an oil flow control valve The heater housing has two circuits: lubricating oil and fuel. Heat transfers from oil to fuel. A thermal sensor in the fuel circuit operates an oil flow control valve to maintain the required fuel temperature. Fuel out temp. below 10°C = full oil flow, max. heating Fuel out temp. above 10°C = reduction of heat transfer Fuel out temp. above 32°C = full bypass, no heating 70 microns Cleanable Buble Point test Activates at 1.5 psid Field replaceable Bypass valve: Opens at 3 psid - FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
Fuel Pump
Fig. 3 Fuel Pump Purpose: Provide high pressure fuel flow to the mechanical control unit to meet engine fuel requirements at any operating conditions Description: Single stage gear type pump driven by the HP rotor through the accessory gearbox. The pump incorporates a 74 micron inlet strainer with integral bypass feature, a set of spur gears and a 10 micron outlet filter. The outlet filter is equiped with a bypass valve and an impending bypass switch. 100% NH = 3740 PPH (TYPICAL) Operation: Rotation of the pump gears draw the low pressure fuel through the inlet strainer. Restricton in the system causes the fuel to pressurize and flow through the outlet filter out to the hydromechanical fuel control (HMU). When blockage of the pump inlet strainer causes a pressure drop of 1.3 psid, the strainer lift off its seat and allow fuel to bypass the strainer. When blockage of the pump outlet filter causes a pressure drop of 25 psid, the impending bypass switch sends a warning signal. When the pressure drop reaches 50 psid the bypass valve opens and send unfiltered fuel to the HMU. Bypass fuel from the mechanical fuel control is returned to the inlet of the pump, through an ejector nozzle, to help maintain the inlet pressure to the pump gears. Inlet strainer: Outlet filter:
Effectivity: 328-100 Mod.10
cleanable (ELECTROSONIC) cleanable (ULTRASONIC) buble point test Buble point test:
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Page: 73-5 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
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Flow Divider Valve
Fig. 4 Flow Divider Valve Purpose:
Divides flow between primary and secondary fuel manifolds and dumps fuel from the manifolds on shutdown Construction: Two concentric valves spring loaded to dump position Dump position: Purge fuel manifolds and nozzles from any remaining fuel Prevents contamination of nozzles Fuel returns to engine Primary flow position: 10 psi closes dump side of primary valve Opens flow to primary manifolds 10 nozzles begin to flow Primary and secondary flow position: 310 psi opens secondary valve Opens flow to secondary manifolds 14 additional nozzles begin to flow Page: 73-6 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
Fuel Manifold Assy & Nozzles
Fig. 5 Fuel Manifold Assy & Nozzles Purpose: Construction:
Atomize and deliver fuel to the combustion chamber. Primary - secondary adapters Primary flow through center orifice Secondary flow through annular orifice Locating pin on adapter
Secondary adapters Secondary flow only Locating pin on gas generator case Positions # 1-4-8-12 Drain manifold Prevents fuel from leaking on the gas generator case Collects fuel manifold leakage and drains it overboard
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-7 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
Fuel Drain Ejector Tank
Fig. 6 Fuel Drain Ejector Tank Purpose:
Collect engine drain fuel and return it to the fuel heater upstream of the fuel pump.
Construction:
Tank Float Valve Lever Non- return valve Ejector pump
OPERATION Fuel drained from the nozzles raises the tank fuel level and the float rises. During its movement, the float body lifts the lever which unseats the valve from the plug orifice. The fuel pressure, acting on the upper end of the orifice, together with a small depression produced by the annulus at the orifice lower end, causes a pressure drop inside the plug orifice. The pressure drop unseats the non-return valve, permitting fuel to flow to the ejector pump. The fuel then is drawn by the ejector pump venturi action and returned to the engine low pressure fuel system.
Page: 73-8 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
73-20 CONTROLLING Hydro - Mechanical Fuel Control Unit (Hmu)
Fig. 7 Hydro - Mechanical Fuel Control Unit (Hmu) Features: Provides metered flow for engine requirements Provides motiv flow for airframe ejector boost pomps Limits min / max fuel flow Limits acceleration and deceleration rate Back up Nh speed control (manual mode)
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-9 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
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Hmu Eec Mode
Fig. 8 Hmu EEC Mode Motive flow valve: High pressure relief valve: Power lever valve: Potentiometer: P3 servo: Page: 73-10 Issue: 08/95 ETM/ETX
Opens to send fuel to airframe ejector boost pumps when supply pressure exceeds bypass pressure by 270 PSID. Opens at 1350 PSID to relieve excess pressure in HMU. Manually controls metering orifice A1 for "manual mode", and rotates potentiometer for "EEC mode". Connected to power lever valve, it reads position of lever and transmits (PLA) signal to EEC. Regulates Wf/P3. Travels up and down to control fuel flow. - FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
Pressure regulating valve: Torque motor: Enrichment solenoid:
Min. pressurizing valve: Cut-off valve:
TRAINING MANUAL LINE /BASE MAINTENANCE
UP Towards min. WF stop (90 PPH). Closes windows A2 and A3. DOWN Towards Max. WF stop (1350 PPH)Opens windows at A2 and A3. Maintains pressure differential of 23 PSID between supply pressure and regulator pressure. EEC controls torque motor. Increase current Torque motor valve opens. Decrease current Torque motor valve closes. Enriches or de-enriches HMU manual schedule. EEC on - De-enriched - Solenoid up.- Energized EEC off - Enriched - Solenoid down.- De-energized Maintains a minimum pressure of 110 PSID in HMU before allowing fuel flow to the engine. Shuts off flow to the engine, by forcing min pressurizing valve to close.
Note: EEC OFF BELOW 25% NH.
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-11 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
Hmu Manual Mode
Fig. 9 Hmu Manual Mode Manual mode: EEC off, torque motor de-energizes and closes. Enrichment solenoid de-energizes and moves down. Fixed fuel flow circuit then flows to Most Selector pushing it to the left and continuing to the pressure regulating valve. Differential pressure is now controlled via window A1 in the power lever valve. Enrichment solenoid: Up when EEC is on, blocking fixed fuel flow circuit to PRV, and allowing regulator pressure to control PRV via torque motor. Should the enrichment solenoid stay up (de-enriched) during a reversion to manual mode at take-off power, the engine would decelerate to min. flow. To prevent this, the solenoid is enriched (down) during take-off allowing the Most Selector to regulate the flow to the pressure regulating valve between the higher of two pressures. As the aircraft climbs to higher altitudes and the EEC lowers the fuel flow in an effort to maintain NH constant, it becomes possible for the Most Selector to switch from EEC regulator pressure to manual fixed fuel flow pressure. When this happens the EEC can no longer reduce the fuel to control NH since authority has been switched to the manual schedule. Therefore, the enrichment solenoid must be deenriched (up) after take-off. Page: 73-12 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
Fault Detection System
Fig. 10 Fault Detection System The control software contains various fault detection routines which allow the EEC to identify and accommodate system faults. The built-in-test infomms the pilot of the fault by setting the fault indicator. EEC hardware faults are detected by self test routines executed upon control initiation and at regular intervals during nommal operation. Sensor and input signal processing faults are detected by comparison of the input data with normal operating range and rate of change limits. Discrete switch input faults are identified by comparison logical input and output combinations. The engine is controlled by the EEC (automatic mode) or by the pilot (manual mode) and a reversion from automatic to manual occurs under anyone of the following conditions: - EEC detects a fault within itself - EEC detects a fault in one of several components providing input pilot selection The ENG MANUAL light illuminates whenever a reversion has taken place. The EEC FAULT light illuminates when a fault has been detected within the EEC or within the HMU PLA system
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-13 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
There are two types of reversion to manual: latching and non-latching. Latching fault: - Once corrected, does not automatically result in the EEC resuming functioning - The EEC must be pilot reset by cycling the 28 volts reset breaker or the ENG MANUAL switch Non-latching fault: - Once corrected, results in the EEC resetting itself (ENG MANUAL light OFF) • Example: Loss of Nh signal when CLA is in feather • EEC resets itself at engine start-up when Nh is > 25% Minor fault: - Fault affecting accuracy but not integrity of control system Major fault: - Fault affection integrity of control system - Always revert to manual Fail fixed: - Ensures no power loss during reversion to manual when a minor is fault detected - Available when PLA and CLA are in the take-off range Operation: During takeoff, upon detection of a minor fault the EEC will freeze the torque motor current at the level it was an instant before detection of the fault. The EEC will then revert to manual but there will be no power loss if fault occurred in steady state.
Page: 73-14 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
EEC Features & TSC Features
Fig. 11 EEC Features & TSC Features EEC FEATURES Command the handling bleed valve. Keeps NH constant during cruise through various ambient conditions. Controls accel and decel rate based on Nh. NP fuel governing functions Maintain minimum NP at low power. Schedule NP as a funciton of PLA in reverse. Limits maximum NP in reverse. EEC SAFETY FEATURES NH overspeed protection at 103%. -> EEC switches off. NP > 100% or NP accelerating faster than a predetermined rate, EEC will reduce fuel flow to control NP within 105%. -> Feature enabled when NP > 80%. TSC FEATURES Torque output to cockpit Auto-feather logic Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-15 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
Auto-Feather System
Fig. 12 Auto-Feather System Purpose: Components: Arming:
Trigger:
Disarming:
Page: 73-16 Issue: 08/95 ETM/ETX
Detect an engine failure and signal airframe to feather the failed engine propeller. System is used during take off only TSC reads torque from sensor and manages auto-feather logic\ Auto-feather switch ON Both PLA's in TO range Both torque > 50.4% (+- 5.1%) "Ammed" light ON One engine torque < 19.4% (+-5.1%) Other engine torque > 50.4% (+-5.1%) 0.5 second later "Armed" light OFF, propeller feathers, auxiliary pump activates and local NP fuel goveming is cancelled Auto-feather switch OFF or One PLA < TO range or Both PLA's < TO range or Both engine torque < 50.4% (+- 5.1%) or Auto-feather triggered
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT Test:
TRAINING MANUAL LINE /BASE MAINTENANCE
Both engines Nnning CLA at MAXIMUM rpm PLA's at flight idle Auto-feather switch ON A/F test switch 1 and 2 ON "Armed" light ON Release one A/F switch 0.5 second later "Arrned" light off, propeller feathers, auxiliary pump activates and local NP fuel goveming is cancelled
Governing PLA: Position of PLA represents a certain NH speed. The EEC will vary fuel flow to maintain NH as required by a schedule of a rating chart.
Cancel NP(T) Governing: -When feathering propeller NP(T) fuel governing feature must be cancelled to avoid an overtorque, since EEC would otherwise try and maintain a minimum NP. NP(T) fuel governing is cancelled whenever prop is feathered by 1. Auto-feather 2. Condition lever selecting electrical feather 3. Manual selecting feather (OHP) or 4. NPT falls below 6000 RPM (NP<30%.
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-17 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
NH Overspeed Test:
TRIM TEST
NH OVSP TEST ENG LH FI TEST
LH
ENG RH 1
PLA FI
MADC
2
OFF PLA FI SSEC DISABLE Fig. 13 LH Engine Test Panel Checks EEC's 103% overspeed protection without running engine at high NH. When NH overspeed test switch is on, it resets limit to 60% NH. Engine Trim:
4
3
4
3
ACTR GO
TEST TAB LOCK AUX PUMP
RH
LH ENG-TRIM
ENG LH
ENG RH
Fig. 14 RH Engine Test Panel Purpose:
1. To establish power loss when EEC reverts to manual. 2. To eliminate throttle staggers.
Procedure: Run engine with EEC's off. Trim switches in minimum position. Set power as recommended by MM Remove power lever stagger by moving both power levers to mid position of stagger. EEC on and adjust trim selectors to bring both engines to an equal power as recommended, by MM.
Page: 73-18 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
73-30 INDICATING FUEL FLOW AND TEMPERATURE FUNCTIONAL DESCRIPTION The system indicates the fuel flow rate (consumption) and also the fuel temperature of the LH (RH) engine. The signals supplied by the fuel flow transmitter and the fuel temperature sensor are indicated on the EICAS display. The fuel flow transmitter is located on the right side of the engine next to the ignition exciters. The fuel temperature sensor is located on the left side of the engine on the fuel heater valve (fuel outlet). The fuel flow and temperature indication system consists of the following main components: - Fuel flow transmitter - Fuel temperature sensor - EICAS on the central displays.
OPERATION Fuel supplied to the engine flows through the fuel flow transmitter. The transmitter is driven by a turbine driver which generates torque and thus turns the measuring unit. The fuel flow rate output-signal from the transmitter is proportional to the time displacement between two sinus pulse signals. This generated signal is supplied for indication processing to the DAU 1 (DAU 2). Subsequently the EICAS display indicates the fuel flow rate (FF) in LBS / HR (or KG / H). The indicating range is between 0 and 1 200 LBS / HR. The fuel temperature sensor supplies resistance signals which correspond to the temperature of the fuel which is present at the sensor. The signal supplied to the DAU 1 (DAU 2) is indicated on the EICAS display in 0C. The indicating range between - 600C and 990 C (+/20 C).
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-19 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
EICAS Indication
MFD PAGE Indication FUEL PAGE digital
Fault or Condition Fuel temperature indicating LH / RH
- 600 to + 990 C
white amber FUEL PAGE digital / white
Fuel flow indicating LH / RH
0 to 1200 LBS / HR
FF LH / RH ENGINE PAGE digital / white
Fuel flow indicating LH / RH
0 to 1200 LBS / HR
FF LH / RH Fuel flow indicating LH / RH
digital / white 0 to 1200 LBS / HR
FF LH / RH
Page: 73-20 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
Fuel Flow Primary EICAS Page
Honeywell
97.0
97.0 TQ
80.2
80.2
WSHLD HEAT FAIL PUSHER NO ICE CHECK DU 5 GPWS FAIL AIR COND ON TONE GEN 1-2 FAIL END
NP
800
800 ITT
80.3
80.3
CAB ALT V/S
2000 FT 0 FPM NU
NH
500 2870
OIL TEMP OIL PRSS FF LBS / HR FQ LBS
ND 500 2870
0°
0°
MAIN CAPT REF SYSTEM DATA
COPY
AHRS
F/O SYSTEM
MSG
Fig. 15 Fuel Flow Primary EICAS Page
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-21 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
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FUEL FILTER / PRESSURE FUNCTIONAL DESCRIPTION The system monitors the fuel pressure and also the fuel heater inlet (low pressure) and fuel pump outlet (high pressure) filter for clogging. The signals supplied by the low fuel pressure switch or by the HP- or LP - fuel warning switches are indicated on the EICAS display. The low fuel pressure switch is located on the left side on the fuel heater. The fuel warning switches are also located on the left side. The HP-fuel warning switch is installed on the fuel pump outlet filter and the LP fuel warning switch on the fuel heater inlet filter. The pressure indication system consists of the following components: -
Low fuel pressure switch HP-fuel warning switch LP-fuel warning switch EICAS on the central display
OPERATION If the fuel heater inlet filter or fuel pump outlet filter is clogged, the HP-fuel warning switch or LP-fuel warning switch installed in the bypass circuit connects ground to the DAU 1 (DAU 2). The EICAS subsequently displays caution messages. If the fuel pressure below the minimum value (< 40 +/- 3kPa) the low-fuel pressure switch connects ground to the DAU 1 (DAU 2) and the EICAS displays caution messages. CAS FIELD Indication AMBER
MFD PAGE Indication
Fault or Condition Low fuel pressure condition LH /RH
ENGINE Page AMBER
Low fuel pressure condition LH /RH
L / R FUEL PRSS LOW
PRSS LOW (LH) (RH)
FUEL Page AMBER
Low fuel pressure condition LH /RH
PRSS LOW (LH) (RH)
AMBER
Fuel filter (HP) clogged
FUEL FILT
BYPASS FUEL Page AMBER
HP - fuel filter LH RH clogged
HP FILTER (RH) (RH)
SYS MAINT AMBER
LP - fuel filter LH RH clogged
L R LP FILTER
Page: 73-22 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
Fuel -Flow / -Used / -Temperature / -Pressure and HP Filter on Fuel Page Honeywell
500 FF LBS/HR 500 123 USED LBS 123
LH ENG 30 °C
RH ENG 31 °C
HP FILTER
HP FILTER APU
PRSS LOW FAIL
PRSS LOW FAIL
X-FEED FAIL ELPMP OFF JETPMP ON
185
ELPMP OFF JETPMP ON
1280
1405
LBS 2870
TOTAL QTY 5740
PRESEL QTY TANK TEMP.
1280
1405
–24
185
2870 LBS
LBS °C
SYSTEM 1/3 FLIGHT HYDR CONTROL
ENGINE
FUEL
NEXT
Fig. 16 Fuel -Flow / -Used / -Temperature / -Pressure and HP Filter on Fuel Page
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-23 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
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Fuel Flow on Engine Page Honeywell
100.0 %
TQ
100.0 %
80.2 %
NP
80.2 %
800 °C
ITT
800 °C
ALTITUDE
80.3 %
NH
80.3 %
MAX TQ
80.4 %
NL
80.4 %
TQ OF DAY OAT A
95 °C
OIL TEMP
95 °C
60 PSI
OIL PRSS
61 PSI
500
FF LBS/HR
FUEL
25000 FT
ALLOW M MODE
- 9 °C
100 %
CRZ
500
FUEL
SYSTEM 1/3 FLIGHT HYDR CONTROL
ENGINE
FUEL
NEXT
Fig. 17 Fuel Flow on Engine Page
Page: 73-24 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
LP Fuel Filter on System Maintenance Page Honeywell
FUEL L TRANSFER MON 021292 R TRANSFER MON 021292
FLIGHT CONTROLS ELECTR
L LP FILTER R LP FILTER CPCS BACKUP INSTRUMENTS
APU OVERTEMP EGT OVERCURRENT ECU OIL TEMP HIGH
OXYGEN QTY ACCURACY
ENGINE
ICE PROTECT L SWDW TEMP R SWDW TEMP L FWDW TEMP R FWDW TEMP
L MAIN OIL FILT R MAIN OIL FILT L SCAV OIL FILT R SCAV OIL FILT L RGB CHIPS DETECT R RGB CHIPS DETECT L ENG CHIPS DETECT R ENG CHIPS DETECT
HYDRAULICS PROXI MAINT
SYSTEM 3/3 CPCS/ OXYGEN
DOORS
SYS MAINT
SENSOR DATA
NEXT
Fig. 18 LP Fuel Filter on System Maintenance Page Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-25 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
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Fuel Flow on RMU Page 2 Honeywell
600 FF 600 85 OIL TEMP 84 61 OIL PRS 61 CPCS AUTO FAIL PITOT S HEAT FAIL L AOA FAIL R AOA FAIL BATT 1 FAIL BATT 2 FAIL RUDDER LIMITED PAGE 1 TUNE SQ
DIM
1/2
STO
ID
PGE
TST
DME
Fig. 19 Fuel Flow on RMU Page 2
Page: 73-26 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
Dornier 328 DORNIER LUFTFAHRT
TRAINING MANUAL LINE /BASE MAINTENANCE
INDEX Auto-Feather System 16 CONTROLLING 9 DISTRIBUTION 2 EEC Features & TSC Features 15 EEC SAFETY FEATURES 15 Fault Detection System 13 Fuel Drain Ejector Tank 8 Fuel Filter / Pressure 22 Fuel Filter/Heater Unit 4 Fuel -Flow / -Used / -Temperature / -Pressure and HP Filter on Fuel Page 23 Fuel Flow and Temperature 19
Fuel Flow on Engine Page 24 Fuel Flow on RMU Page 2 26 Fuel Flow Primary EICAS Page 21 Fuel Manifold Assy & Nozzles 7 Fuel System 2 Hmu Eec Mode 10 Hmu Manual Mode 12 Hydro - Mechanical Fuel Control Unit (Hmu) 9 INDICATING 19 LP Fuel Filter on System Maintenance Page 25 TSC FEATURES 15
LIST OF ILLUSTRATIONS Fig. 1 Fuel System ..................................................................................................................................................................................................2 Fig. 2 Fuel Filter/Heater Unit .................................................................................................................................................................................4 Fig. 3 Fuel Pump ....................................................................................................................................................................................................5 Fig. 4 Flow Divider Valve......................................................................................................................................................................................6 Fig. 5 Fuel Manifold Assy & Nozzles....................................................................................................................................................................7 Fig. 6 Fuel Drain Ejector Tank...............................................................................................................................................................................8 Fig. 7 Hydro - Mechanical Fuel Control Unit (Hmu)............................................................................................................................................9 Fig. 8 Hmu EEC Mode.........................................................................................................................................................................................10 Fig. 9 Hmu Manual Mode ....................................................................................................................................................................................12 Fig. 10 Fault Detection System ............................................................................................................................................................................13 Fig. 11 EEC Features & TSC Features.................................................................................................................................................................15 Fig. 12 Auto-Feather System................................................................................................................................................................................16 Fig. 13 LH Engine Test Panel ..............................................................................................................................................................................18 Fig. 14 RH Engine Test Panel ..............................................................................................................................................................................18 Fig. 15 Fuel Flow Primary EICAS Page ..............................................................................................................................................................21 Fig. 16 Fuel -Flow / -Used / -Temperature / -Pressure and HP Filter on Fuel Page ............................................................................................23 Fig. 17 Fuel Flow on Engine Page .......................................................................................................................................................................24 Fig. 18 LP Fuel Filter on System Maintenance Page ...........................................................................................................................................25 Fig. 19 Fuel Flow on RMU Page 2 ......................................................................................................................................................................26
Effectivity: 328-100 Mod.10
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Page: 73-27 Issue: 08/95 ETM/ETX
Dornier 328 TRAINING MANUAL
DORNIER LUFTFAHRT
LINE /BASE MAINTENANCE
Page: 73-28 Issue: 08/95 ETM/ETX
- FOR TRAINING PURPOSES ONLY TM-Engine Fuel & Control
Effectivity: 328-100 Mod.10
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End of ATA Chapter 73 Engine Fuel and Control
