De Havilland DASH8 100 Series Maintenance Manual
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De Havilland DASH8 100 Series Maintenance Manual

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**ON A/C ALL
1.

General

Engine fuel indicating associated with the engine fuel and control system consists of a fuel
low pressure warning system, a fuel flow indicating system and a fuel temperature indicating
system for each engine. The systems for each engine have like components and are identical
in operation.
Fuel Low Pressure Warning consists of a fuel low pressure switch, sensing fuel pump inlet
pressure and connected by electrical wiring to the caution lights system. Fuel flow indicating
is by means of a transmitter sensing fuel flow to the engine fuel manifold, connected by
electrical wiring to an indicator on the engine instrument panel. Fuel temperature indicating is
by means of a transmitter sensing temperature at the fuel pump inlet, connected by electrical
wiring to an indicator on the engine instrument panel.
For location of the fuel low pressure switches, and fuel flow and fuel temperature transmitter,
refer to ENGINE FUEL AND CONTROL − GENERAL, Figure 1.
Other indications associated with the fuel system are fuel quantity indicating systems, one for
each fuel tank; refer to Chapter 28.
MASTER
EFFECTIVITY: See Pageblock 73−30−00 page 1
D
S ERIES 100
AIRCRAFT MAINTENANCE MANUAL
ENGINE FUEL INDICATING − GENERAL
73−30−00
Dec 20/2004
Page 1

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Summary of Contents for De Havilland DASH8 100 Series

  • Page 1 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ENGINE FUEL INDICATING − GENERAL General Engine fuel indicating associated with the engine fuel and control system consists of a fuel low pressure warning system, a fuel flow indicating system and a fuel temperature indicating system for each engine.
  • Page 3 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FUEL LOW PRESSURE WARNING − DESCRIPTION AND OPERATION General Two identical but separate fuel low pressure warning systems, monitor input fuel pressure to the engine driven fuel pump for each engine. In the event fuel pressure falls below a pre−set minimum pressure, the system activates caution lights.
  • Page 4 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL LOW PRESSURE WARNING Figure 1 MASTER 73−31−00 EFFECTIVITY: See Pageblock 73−31−00 page 1 Page 2 Dec 20/2004...
  • Page 5 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL LOW PRESSURE WARNING Figure 2 MASTER 73−31−00 EFFECTIVITY: See Pageblock 73−31−00 page 1 Page 3 Dec 20/2004...
  • Page 7 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FUEL FLOW INDICATING − DESCRIPTION AND OPERATION General Fuel flow indicating for the engine fuel and control installation consists of two identical, but independent fuel flow indicating systems, one for each engine. Each system consists of a fuel flow transmitter connected to a fuel flow indicator.
  • Page 8 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL A test pushbutton is provided on the indicator, which when pressed, with power on, causes the indicator to move to 1050 PPH (400 ±70 KG/H), indicated by a blue dot on the face of the indicator dial and an equivalent digital display. Releasing the pushbutton causes the pointer to fall to zero and a digital display of 0.0.
  • Page 9 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL FLOW TRANSMITTER INSTALLATION Figure 1 MASTER 73−32−00 EFFECTIVITY: See Pageblock 73−32−00 page 1 Page 3 Dec 20/2004...
  • Page 10 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL FLOW (FF) INDICATING SYSTEM − SCHEMATIC Figure 2 MASTER 73−32−00 EFFECTIVITY: See Pageblock 73−32−00 page 1 Page 4 Dec 20/2004...
  • Page 11 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL FLOW KG/H x 100 INDICATOR FUEL FLOW (METRIC) 5V DC LTG (REFER TO CHAPTER 33) 28V DC L BUS FUEL FLOW IND ENGINE 1 0 TO 5V DC OUTPUT TO FLIGHT DATA RECORDER DC REF FUEL USED PULSE NOTE...
  • Page 13 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FUEL FLOW INDICATING − MAINTENANCE PRACTICES General The maintenance procedures that follow are for the: – Removal and installation of the fuel flow indicator – Removal and installation of the fuel flow transmitter –...
  • Page 14 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (c) Tighten the top right and lower left screws (3). (3) Remove the safety clips and tags and close the circuit breakers that follow: (a) On the left DC circuit breaker panel: – FUEL FLOW IND ENG 1 (C5) –...
  • Page 15 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Equipment and Materials: – Fuel resistant container, commercially available (1) Make sure that the aircraft is in the same configuration as in the removal procedure. (2) Install the fuel flow transmitter (1) as follows: (a) Put a container below the fuel flow lines (3) and (4) to collect the fuel that spills.
  • Page 16 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Indicator. 2. Electrical connector. PPH x 100 3. Screw. 4. Instrument panel. 1 0 0 Fuel Flow Indicator − Removal and Installation Figure 201 MASTER 73−32−00 EFFECTIVITY: See Pageblock 73−32−00 page 201 Page 204 Jan 15/2010...
  • Page 17 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FRONT INLET CASE REAR FLANGE (REF) LEGEND 1. Fuel flow transmitter. 2. Electrical connector. 3. Fuel line. 4. Fuel line. 5. Bolt. 6. Washer. 7. Bracket. FUEL FLOW TRANSMITTER − REMOVAL/INSTALLATION Figure 202 MASTER 73−32−00 EFFECTIVITY: See Pageblock 73−32−00 page 201 Page 205...
  • Page 18 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Adjustment/Test General (1) The maintenance procedure that follows is to make sure that the fuel flow indicators operate correctly. The test procedure includes the operational test of the fuel flow indicator. Operational Test of the Fuel Flow Indicator WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS...
  • Page 19 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FUEL TEMPERATURE INDICATING − DESCRIPTION AND OPERATION General Refer to Figure 1. The fuel temperature indicating system for the fuel feed systems of both engines consists of temperature transmitter for each engine connected by electrical wiring to a dual indicator which serves both engines.
  • Page 20 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL TEMPERATURE INDICATING SCHEMATIC Figure 1 MASTER 73−33−00 EFFECTIVITY: See Pageblock 73−33−00 page 1 Page 2 Dec 20/2004...
  • Page 21 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FUEL TEMPERATURE INDICATING − MAINTENANCE PRACTICES Removal/Installation The following maintenance procedures are approved for the removal and the installation of the fuel temperature dual indicator. Removal of the Fuel Temperature Dual Indicator Refer to Figure 201. WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 22 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT. (4) Apply electrical power to the aircraft.
  • Page 23 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Indicator. 2. Electrical connector. 3. Screw. − 4 0 − 4 0 Fuel Temperature Dual Indicator − Removal and Installation Figure 201 MASTER 73−33−00 EFFECTIVITY: Page 203 Jan 15/2009...
  • Page 25 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ENGINE INDICATING − GENERAL General Engine indicating consists of torque (TRQ), high pressure compressor rotor speed (NH), low pressure compressor rotor speed (NL), inter−turbine (ITT) temperature indicating systems for each engine. The indicators associated with these systems are located on the engine instrument panel in the flight compartment (refer to Figure 1).
  • Page 26 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENGINE INSTRUMENT PANEL Figure 1 MASTER 77−00−00 EFFECTIVITY: See Pageblock 77−00−00 page 1 Page 2 Dec 20/2004...
  • Page 27 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENGINE INDICATING − SENSING COMPONENTS ON ENGINE Figure 2 MASTER 77−00−00 EFFECTIVITY: See Pageblock 77−00−00 page 1 Page 3 Dec 20/2004...
  • Page 28 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL PRE MOD 8−1/1101 LIQUID CRYSTAL DISPLAY (LCD) HEATERS − ELECTRICAL SCHEMATIC Figure 3 MASTER 77−00−00 EFFECTIVITY: See Pageblock 77−00−00 page 1 Page 4 Dec 20/2004...
  • Page 29 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TORQUE INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. Two torque indicating systems are provided, one for each engine, to indicate the torsional deflection (torque) between the reduction gearbox input shaft and the reduction gearbox layshaft.
  • Page 30 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Range marks are a green arc 0 to 90%, a yellow arc 90 to 105%, a dashed red limit (radial) at 105% torque and solid red limit mark (radial) at 90% torque. On aircraft with SOO 8152 incorporated, range marks are a green arc 0 to 97.5%, a yellow arc 97.5 to 112.5%, a dashed red limit (radial) at 112.5% torque and solid red limit mark (radial) at 97.5% torque.
  • Page 31 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (5) Move the power levers forward until the PWR UPTRIM light on engine instrument panel comes on (power levers should be above FLT IDLE + 12 degrees). NOTE: Operation of PWR UPTRIM light confirms function of overtorque switch, relay 7712−K5 and power uptrim circuits (see Chapter 61).
  • Page 32 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL PRE MOD 8/0886 TORQUE INDICATING SYSTEM Figure 1 (Sheet 1 of 2) MASTER 77−10−00 EFFECTIVITY: See Pageblock 77−10−00 page 1 Page 4 Dec 20/2004...
  • Page 33 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL MOD 8/0886 TORQUE INDICATING SYSTEM Figure 1 (Sheet 2 of 2) MASTER 77−10−00 EFFECTIVITY: See Pageblock 77−10−00 page 1 Page 5 Dec 20/2004...
  • Page 34 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL TORQUE INDICATOR Figure 2 MASTER 77−10−00 EFFECTIVITY: See Pageblock 77−10−00 page 1 Page 6 Dec 20/2004...
  • Page 35 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL TORQUE INDICATING SYSTEM − MAINTENANCE PRACTICES Removal/Installation The procedures that follow are for the removal and installation of the torque (TRQ%) indicators. Removal of the Torque (TRQ%) Indicators WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 36 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (5) Remove all tools, equipment and unwanted materials from the work area. WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
  • Page 37 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TORQUE INDICATING (TI) CALIBRATION TEST − MAINTENANCE PRACTICES Adjustment/Test Equipment and Materials: Digital Voltmeter 0 to 10 + or − 0.001 Volts Power Supply 0 to 10 Volts (variable) Test Cable (locally manufactured) Torque Indicating (TRQ) Calibration Test (1) With dc power on, press test pushbutton on indicator.
  • Page 38 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (7) Adjust voltage applied to pins 3 and 4 to obtain readings within limits for pointer Test Point % provided in Figure 202. (8) Connect digital voltmeter at receptacle 9811−J104 pins E and F (engine No. 1) or pins G and H (engine No.
  • Page 39 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL TORQUE SYSTEM CALIBRATION CHECK DETAILS Figure 201 MASTER 77−10−11 EFFECTIVITY: See Pageblock 77−10−11 page 201 Page 203 Dec 20/2004...
  • Page 40 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL RECORDER TEST POINTER & DIGITAL OUTPUT VOLTS POINT % VOLTS (Nominal) 0.00 22.5 1.28 0.94 3.42 2.50 4.56 3.33 5.69 4.17 6.84 5.00 TOLERANCES: POINTER: + or − 0.07 Volts Digital Readout: + or − 0.03 Volts Recorder Output: + or −...
  • Page 41 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL HIGH PRESSURE COMPRESSOR ROTOR SPEED (NH) INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. A separate speed indicating system is provided for the high pressure compressor rotor of each engine.
  • Page 42 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL and permits engine ignition if required. When engine speed falls (NH < 59.5 + or − 0.5%), switch (S1) closes and the Auto Relight System is enabled. Above engine idle speed (NH > 60.8 + or − 0.5%), switch (S1) opens and igniter operation is inhibited. (Ref Chapter 74 −...
  • Page 43 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL EXTERNALLY REPLACEABLE LAMPS 2 PLACES 40 60 UNLIT BLUE DOT PRESS TO TEST AT TEST VALUE PUSH BUTTON 105.0% N SPEED INDICATOR RANGE MARKS: 10 TO 20% & 66 TO 100% GREEN 100% RED RADIAL 5V DC LIGHTING LIGHTING GROUND 28VDC L ESS BUS...
  • Page 45 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL NH INDICATING SYSTEM − MAINTENANCE PRACTICES Removal/Installation The maintenance procedures that follow are for the removal and installation of the (NH) indicators. Removal of the (NH) Indicators WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 46 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT. (6) Apply electrical power to aircraft.
  • Page 47 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL HIGH PRESSURE COMPRESSOR ROTOR SPEED (NH) INDICATING SYSTEM CALIBRATION CHECK − MAINTENANCE PRACTICES Adjustment/Test Equipment and Materials: Signal Generator (HP204C or equivalent) High Pressure Compressor Rotor Speed (NH) Indicating System Calibration Check (1) With dc power on, press test pushbutton on indicator.
  • Page 48 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL EXTERNALLY REPLACEABLE LAMPS 2 PLACES PRESS TO TEST 40 60 80 PUSH BUTTON UNLIT BLUE DOT AT TEST VALUE 105.0% NH NH SPEED INDICATOR NH SENSOR (MAGNETIC PICK−UP) 5V DC LIGHTING LIGHTING GROUND (H5) 28VDCL ESS BUS ENG 1NH IND POWER GROUND...
  • Page 49 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FREQ (HZ) RECORDER O/P (0.5 TO 5.0 VPP) INDICATION (%) (VOLTS) 18,990 4.55 15,192 3.64 11,394 2.73 7,596 1.82 3,798 0.91 TOLERANCES: POINTER + OR − 1.0% DIGITS + OR − 0.3% RECORDER + OR − 0.03 Volts NH CALIBRATION CHECK VALUES Figure 202 MASTER...
  • Page 50 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Operational and Functional Test Procedures Operational Test of the NH Speed Indicator Auto Relight System (Post ModSum 8Q100813 aircraft) (1) The procedure that follows is an operational test of the NH Speed Indicator auto relight system (Aircraft with ModSum 8Q100813).
  • Page 51 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL – Audible firing of both ignitors at Engine #1. (e) On the center console, set the PROP #1 Lever to FUEL OFF and observe the following: – No audible firing of both ignitors at Engine #1. On the ENGINE START panel, set the IGNITION #1 switch to OFF.
  • Page 52 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL CB PANEL CB NO. NAME L ESS IGN #1 L ESS NH IND #1 (3) For engine #2, close the following circuit breakers: CB PANEL CB NO. NAME R ESS IGN #2 R ESS NH IND #2 (4) Tools and Equipment (a) Commercially available multi−meter.
  • Page 53 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (o) Move engine ignition switch #1 to the "OFF" position. Check that 28 VDC cannot be measured at 9811−TB19 Pin 3C. (p) Remove all electrical power to the aircraft. (q) Move Condition Lever #1 to the "FUEL OFF" position and reconnect the following wire, 9811−TB19, 7411−10003L18 to 3C.
  • Page 54 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (o) Move engine ignition switch #2 to the "OFF" position. Check that 28 VDC cannot be measured at 9811−TB16 Pin 2A. (p) Remove all electrical power to the aircraft. (q) Move Condition Lever #2 to the "FUEL OFF" position and reconnect the following wire, 9811−TB16, 7411−20003L18 to 2A.
  • Page 55 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LOW PRESSURE COMPRESSOR ROTOR SPEED (NL) INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. The speed indicating system for the low pressure compressor rotors of both engines consists of a speed sensor for each engine connected by electrical wiring to a dual indicator which serves both engines.
  • Page 56 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENGINE LOW PRESSURE COMPRESSOR ROTOR SPEED (NL) INDICATING SYSTEM − WIRING DIAGRAM Figure 1 MASTER 77−14−00 EFFECTIVITY: See Pageblock 77−14−00 page 1 Page 2 Jun 20/2005...
  • Page 57 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENG (NL) INDICATING SYSTEM − MAINTENANCE PRACTICES Removal/Installation The procedures that follow are for the removal and installation of the engine (NL) indicators. Removal of the (NL) Indicator WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 58 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (7) On the overhead console, rotate the ENGINE PANEL lighting selector from OFF to BRT. Check that the (NL) indicator back lighting varies from off to bright. (8) Do an engine start (refer to Chapter 71−00−00). (9) Check for correct operation of the (NL) indicator(s).
  • Page 59 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL INTERTURBINE TEMPERATURE INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. The interturbine temperature (ITT) indicating system provides visual indication of operating temperature in the interturbine zone between the low pressure turbine rotor and the first stage of the power turbine rotor.
  • Page 60 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL exceeds 810 degrees C. The lamp and its associated switch are connected into test and dim unit circuits. A test pushbutton is provided in each indicator, which when pressed, with indicating system power on, causes the indicator pointer to move to 1050 degrees C, indicated by the dial, a blue dot on the face of the indicator dial and an equivalent digital display.
  • Page 61 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL INTER TURBINE TEMPERATURE (ITT) INDICATING SYSTEM Figure 1 MASTER 77−20−00 EFFECTIVITY: See Pageblock 77−20−00 page 1 Page 3 Dec 20/2004...
  • Page 63 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ITT INDICATORS − MAINTENANCE PRACTICES Removal/Installation The maintenance procedures that follow are for the removal and installation of the ITT indicators. Removal of the ITT Indicators WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 64 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT. (6) Apply electrical power to aircraft.
  • Page 65 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL INTER−TURBINE TEMPERATURE INDICATOR (ITT) CALIBRATION TEST − MAINTENANCE PRACTICES Adjustment/Test Equipment and Materials: Millivolt Generator−Pyrotest V2777 (or equivalent) Inter−Turbine Temperature Indicator (ITT) Calibration Test (1) Open and clip the following circuit breakers: (a) ENG 1 ITT IND (F5) on 28V dc left essential bus circuit breaker panel (when testing engine No.
  • Page 66 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Manual). NOTE: Check insulation resistance terminal to casing, 2 megohms minimum at 45 volts AC or DC. (12) Connect alumel and chromel leads to terminal block and torque alumel nut (large diameter) to 25 to 30 pound−inches and chromel nut (small diameter) to 20 to 25 pound−inches (refer to Figure 203).
  • Page 67 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL MILLIVOLT SETTINGS CORRECTED FOR AMB. TEMP. Figure 201 (Sheet 1 of 2) MASTER 77−20−11 EFFECTIVITY: See Pageblock 77−20−11 page 201 Page 203 Dec 20/2004...
  • Page 68 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL MILLIVOLT SETTINGS CORRECTED FOR AMB. TEMP. Figure 201 (Sheet 2 of 2) MASTER 77−20−11 EFFECTIVITY: See Pageblock 77−20−11 page 201 Page 204 Dec 20/2004...
  • Page 69 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL INTER−TURBINE TEMPERATURE (ITT) INDICATING SYSTEM CALIBRATION DETAILS Figure 202 MASTER 77−20−11 EFFECTIVITY: See Pageblock 77−20−11 page 201 Page 205 Dec 20/2004...
  • Page 70 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL INTER−TURBINE TEMPERATURE (ITT) INDICATING SYSTEM CALIBRATION DETAILS Figure 203 MASTER 77−20−11 EFFECTIVITY: See Pageblock 77−20−11 page 201 Page 206 Dec 20/2004...
  • Page 71 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ITT INPUT CHARACTERISTICS TOLERANCES INDICATIONS DEGREES C POINTER DIGITS + 9 DEG C + OR − 5 DEG C + OR − 9 DEG C + OR − 5 DEG C 1000 + OR − 9 DEG C + OR −...
  • Page 73 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL INDICATING − DESCRIPTION General Refer to Figure 1. Oil system indicating for each of the two engines is by the same type systems, consisting of oil pressure indicating, oil temperature indicating and low oil pressure warning. An oil tank is an integral part of each engine and oil level (quantity) indicating is by means of a sight glass on the left side of the engine.
  • Page 74 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL INDICATING COMPONENTS Figure 1 MASTER 79−30−00 EFFECTIVITY: See Pageblock 79−30−00 page 1 Page 2 Dec 20/2004...
  • Page 75 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL OIL PRESSURE INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. The oil pressure indicating system for each engine consists of an oil Pressure transmitter, connected by electrical wiring to the oil temperature section of a dual oil pressure and temperature indicator.
  • Page 76 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL PRESSURE INDICATING AND ELECTRICAL SCHEMATIC Figure 1 MASTER 79−32−00 EFFECTIVITY: See Pageblock 79−32−00 page 1 Page 2 Dec 20/2004...
  • Page 77 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL PRESSURE/TEMPERATURE DUAL INDICATOR − MAINTENANCE PRACTICES Removal/Installation The maintenance procedures that follow are for the removal and installation of the oil pressure/temperature dual indicator. Removal of the OIL PRESSURE/TEMPERATURE Dual Indicator WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 78 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (7) Do an engine start (Refer to Chapter 71−00−00). (8) Check for correct operation of the OIL PRESS/TEMP dual indicator. (9) Shut down the engine (Refer to Chapter 71−00−00). MASTER 79−32−00 EFFECTIVITY: Page 202 Jun 20/2005...
  • Page 79 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL OIL TEMPERATURE INDICATING SYSTEM General The oil temperature indicating system for each engine consists of an engine oil temperature transmitter, connected to the temperature side of a dual pressure and temperature indicator by electrical wiring.
  • Page 80 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL TEMPERATURE INDICATING AND ELECTRICAL SCHEMATIC Figure 1 MASTER 79−34−00 EFFECTIVITY: See Pageblock 79−34−00 page 1 Page 2 Dec 20/2004...
  • Page 81 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL TEMPERATURE BULB − MAINTENANCE PRACTICES General The maintenance procedure that follows is for the removal and the installation of the oil temperature bulb. The oil temperature bulb is screwed into an adapter adjacent to the engine oil filter.
  • Page 82 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (9) Remove all tools, equipment and unwanted materials from the work area. (10) Do the engine start procedure for the related engine (refer to AMM 71−00−00). (11) Check for the correct operation of the oil pressure/temperature dual indicator in the engine instrument panel in the flight compartment.
  • Page 83 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Oil temperature bulb. 2. Electrical connector. 3. Packing. 4. Adapter. OIL TEMPERATURE BULB − REMOVAL/INSTALLATION Figure 201 MASTER 79−34−03 EFFECTIVITY: Page 203 Jul 15/2012...
  • Page 85 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LOW OIL PRESSURE WARNING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1 and Figure 2. The low oil pressure warning system for each engine consists of an engine oil pressure low switch, which is mounted on the engine oil tank on the left side of the engine (refer to INDICATING −...
  • Page 86 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENGINE OIL PRESSURE LOW WARNING SYSTEM (PRE−MOD 8/0235 AND 8/0446) − ELECTRICAL SCHEMATIC Figure 1 MASTER 79−36−00 EFFECTIVITY: See Pageblock 79−36−00 page 1 Page 2 Dec 20/2004...
  • Page 87 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL ENGINE OIL PRESSURE LOW WARNING SYSTEM (MOD 8/0235 AND 8/0446) − ELECTRICAL SCHEMATIC Figure 2 MASTER 79−36−00 EFFECTIVITY: See Pageblock 79−36−00 page 1 Page 3 Dec 20/2004...
  • Page 89 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL PRESSURE SWITCH − MAINTENANCE PRACTICES General The maintenance procedure that follows is for the removal and the installation of the oil pressure switch. The oil pressure switch is installed on the oil tank adjacent to the sight glass. The procedure is the same for the left engine and the right engine.
  • Page 90 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (10) Do the engine shutdown for the related engine (Refer to Chapter 71−00−00). (11) Install the left side center panel 413 AL (engine No. 1) or 423 AL (engine No. 2) (Refer to Chapter 71−10−00). (12) Install the lower forward nacelle cowl (Refer to Chapter 71−10−00).
  • Page 91 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Electrical connector. 2. Oil pressure switch. 3. Tube. 4. Tube. 5. Nut. 6. Washer. 7. Screw. 8. Bracket. OIL PRESSURE SWITCH − REMOVAL/INSTALLATION Figure 201 MASTER 79−36−01 EFFECTIVITY: Page 203 Jan 15/2010...
  • Page 92 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Electrical connector. 2. Oil pressure switch. 3. Tube. 4. Tube. 5. Nut. 6. Washer. 7. Screw. 8. Bracket. OIL PRESSURE SWITCH − REMOVAL/INSTALLATION Figure 202 MASTER 79−36−01 EFFECTIVITY: Page 204 Jan 15/2010...
  • Page 93 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL OIL PRESSURE TRANSMITTER − MAINTENANCE PRACTICES General The maintenance procedure that follows is for the removal and the installation of the oil pressure transmitter. The oil pressure transmitter is installed on the oil tank adjacent to the sight glass.
  • Page 94 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (20) Remove the clamp (10) from the oil pressure transmitter (1). (21) Put the protective caps on the open ends of the oil pressure transmitter (1). Install Oil Pressure Transmitter (1) Make sure that the aircraft is in the same configuration as in the removal task. (2) Remove the protective caps from the oil pressure transmitter (1) and the tee (4).
  • Page 95 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Oil pressure transmitter. 2. Electrical connector. 3. Tube. 4. Tee. 5. Union. 6. Packing. 7. Nut. 8. Retainer. 9. Packing. 10. Clamp. 11. Screw. 12. Washer. 13. Nut. 14. Bracket. 15. Tube. 16.
  • Page 96 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Oil pressure transmitter. 2. Electrical connector. 3. Tube. 4. Tee. 5. Union. 6. Packing. 7. Nut. 8. Retainer. 9. Packing. 10. Clamp. 11. Screw. 12. Washer. 13. Nut. 14. Bracket. 15. Tube. 16.
  • Page 97 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL PROPELLER SYNCHROPHASING SYSTEM − DESCRIPTION AND OPERATION General The propeller synchrophasing control circuits provide for automatic speed and phase angle synchronizing for the propeller system and provide visual indication of circuits powered. The propeller of engine No.
  • Page 98 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL PROPELLER SYNCHROPHASING SYSTEM − ELECTRICAL SCHEMATIC Figure 1 MASTER 61−29−00 EFFECTIVITY: See Pageblock 61−29−00 page 1 Page 2 Dec 20/2004...
  • Page 99 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Operation With the SYNCHROPHASE switch selected to ON, the system is powered, indicated by the advisory light which comes on. Input signals from the pulse generator are processed by the synchrophase control box. Circuits using the signal from engine No. 1 propeller pulse generator as the reference or master signal relay a correction signal, as required to the torque motor of engine No.
  • Page 100 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL SYNCHROPHASER PULSE GENERATOR DETAILS Figure 2 MASTER 61−29−00 EFFECTIVITY: See Pageblock 61−29−00 page 1 Page 4 Dec 20/2004...
  • Page 101 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL PROPELLER RPM (NP) INDICATING SYSTEM − DESCRIPTION AND OPERATION General Refer to Figure 1. A separate speed indicating system is provided for each propeller. Each system consists of a propeller speed (NP) sensor connected by electrical wiring to a PROP RPM X100 indicator. Description and Operation Propeller Speed (NP) Sensor A propeller speed sensor is located on and supplied as part of each basic engine.
  • Page 102 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL Beta Lockout System Installed (CR873CH00011). MASTER 61−44−00 EFFECTIVITY: See Pageblock 61−44−00 page 1 Page 2 Dec 20/2004...
  • Page 103 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL PROPELLER SPEED (NP) INDICATING Figure 1 MASTER 61−44−00 EFFECTIVITY: See Pageblock 61−44−00 page 1 Page 3 Dec 20/2004...
  • Page 105 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL PROPELLER (PROP RPM) INDICATING SYSTEM − MAINTENANCE PRACTICES Removal/Installation The following maintenance procedures are approved for the removal and the installation of the propeller (PROP RPM) indicators. Removal of the Propeller (PROP RPM) Indicator WARNING: REMOVE ALL ELECTRICAL POWER FROM THE AIRCRAFT BEFORE YOU DO MAINTENANCE.
  • Page 106 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL (6) Remove all tools, equipment and unwanted materials from the work area. WARNING: MAKE SURE THAT ALL PERSONS IN THE AREA OF THE AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
  • Page 107 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL readings at appropriate indicator for pointer and digital indications are within tolerances provided in Figure 201. (8) Connect digital voltmeter at receptacle 9811−J104 pins J and K engine (No. 1) or pins L and M (engine No. 2) and repeat step (7) to obtain digital readings for indicator and voltage output to Flight Data Recorder (FDR) within limits of Figure 201.
  • Page 108 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL FREQUENCY (HZ) INDICATOR (RPM) FLIGHT DATA 0.5 TO 5.0 VOLTS PINTER and RECORDER PEAK TO PEAK DIGITAL (VOLTS) 3,400 1500 5.00 2,720 1200 4.00 1,813 2.67 1.33 0.67 NP CALIBRATION CHECK VALUES Figure 201 MASTER 61−44−00 EFFECTIVITY: See Pageblock 61−44−00 page 201...
  • Page 109 S ERIES 100 AIRCRAFT MAINTENANCE MANUAL NP INDICATING SYSTEM CALIBRATION DETAILS Figure 202 MASTER 61−44−00 EFFECTIVITY: See Pageblock 61−44−00 page 201 Page 205 Jun 20/2005...

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