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BOMBARDIER SD3-60 Maintenance Manual

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30-00-00
AMM
General
1.
Ice and rain protection for the aircraft on the ground is provided by protective covers, described in
Chapter 10, Parking and Mooring, and by techniques described in Cold Weather Protection in
Chapter 12, Servicing.
Operationally the aircraft is protected by the following systems:
- Aerofoil de-icing.
- Engine air intake anti-icing.
- Pitot and static anti-icing.
- Windshield ice and rain protection.
- Five Bade Propeller anti-icing.
- Six Blade Propeller anti-icing.
- Ice detection system.
Flight compartment side window de-misting is covered in Chapter 21, Air Conditioning.
EFFECTIVITY: All
SD3-60 AIRCRAFT MAINTENANCE MANUAL
ICE AND RAIN PROTECTION - GENERAL
2.0.0.0
Refer to 30-11-00,
pb1.
Refer to 30-20-00,
Refer to 30-31-00,
Refer to 30-40-00,
Refer to 30-61-00,
Refer to 30-62-00,
Refer to 30-80-00,
pb1.
pb1.
pb1.
pb1.
pb1.
pb1.
30-00-00
z
Page 1
Jun 30/01

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Summary of Contents for BOMBARDIER SD3-60

  • Page 1 SD3-60 AIRCRAFT MAINTENANCE MANUAL ICE AND RAIN PROTECTION - GENERAL 30-00-00 2.0.0.0 General Ice and rain protection for the aircraft on the ground is provided by protective covers, described in Chapter 10, Parking and Mooring, and by techniques described in Cold Weather Protection in Chapter 12, Servicing.
  • Page 2 SD3-60 AIRCRAFT MAINTENANCE MANUAL AEROFOIL DE-ICING - DESCRIPTION & OPERATION 30-11-00 3.0.0.0 Description A. General Refer to Figure The pneumatic power source to operate the system is derived from interstage P2.5 compressor bleed points on each engine. The pneumatic de-icer consists of a smooth rubber fabric blanket containing small span wise de-icing tubes and is bonded to the aerofoil leading edge with cement.
  • Page 3 SD3-60 AIRCRAFT MAINTENANCE MANUAL E. System Indication (1) Shut-Off Valves The 'open' - 'closed' indication of the Shut-Off Valves is signalled via an integral set of microswitches which operate in response to the solenoid valve movement. Position indication is afforded by indicator modules on panel 4P (immediately above control switches).
  • Page 4 SD3-60 AIRCRAFT MAINTENANCE MANUAL Aerofoil De-icing Figure 1 30-11-00 EFFECTIVITY: All Page 3 Apr 24/03...
  • Page 5 SD3-60 AIRCRAFT MAINTENANCE MANUAL A time delay relay routes the pressure switch output to the SYS P indication, and is set to approximately 60 seconds to avoid any nuisance warnings during the landing flare, where lower boot inflation pressures would be expected.
  • Page 6 SD3-60 AIRCRAFT MAINTENANCE MANUAL AEROFOIL DE-ICING - MAINTENANCE PRACTICES 30-11-00 4.0.0.0 Adjustment/Test A. Function the system (1) Start engines (2) Check that C/B Nos. 94 and 244 on respective distribution panels 1D and 2D are closed. (3) On panel 4P perform the following:- (a) Check that WINGS &...
  • Page 7 SD3-60 AIRCRAFT MAINTENANCE MANUAL CHECK VALVES (ENGINE AIR BLEED LINES) - MAINTENANCE PRACTICES 30-11-01 5.0.0.0 Adjustment/Test For convenience of maintenance, the testing of the high pressure switch and relief valve NOTE: are carried out in the same procedure. A. Function check the valves Special tools and equipment: Regulated air pressure supply (0-100 p.s.i.)
  • Page 8 SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) a continuing increase in pressure (to compensate for relief valve loss) will cause the high pressure switch to illuminate the DUCT PRESSure light on panel 4P. before reaching 24 p.s.i. Check that on a falling pressure of 22 p.s.i. the high pressure switch 'breaks', NOTE: extinguishing the DUCT PRESSure light.
  • Page 9 SD3-60 AIRCRAFT MAINTENANCE MANUAL RELIEF VALVE - MAINTENANCE PRACTICES 30-11-06 6.0.0.0 Adjustment/Test A. Function check the relief valve. For convenience of maintenance, the relief valve is functioned during check valves (engine air bleed lines) test. Refer to 30-11-01, pb201. 30-11-06...
  • Page 10 SD3-60 AIRCRAFT MAINTENANCE MANUAL LOW PRESSURE SWITCHES - MAINTENANCE PRACTICES 30-11-11 7.0.0.0 Adjustment/Test A. Function check the pressure switches Special tools and equipment: Regulated air pressure supply. Refer to 12-09-03, pb301. Provide electrical power. (2) Check that C/B Nos 94 and 244 on respective distribution panels 1D and 2D are closed.
  • Page 11 SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) Open C/B No. 116 on distribution panel 2D (de-energising the right engine oil pressure relay, thus permitting the bleed air - DUCT PRESSure light on panel 4P to illuminate under the influence of the right duct pressure switch, with engine stopped).
  • Page 12 SD3-60 AIRCRAFT MAINTENANCE MANUAL HIGH PRESSURE SWITCH - MAINTENANCE PRACTICES 30-11-16 8.0.0.0 Adjustment/Test A. Function check the pressure switch. For convenience of maintenance, the high pressure switch is functioned during check valves (engine air bleed lines) test. Refer to 30-11-01, pb201.
  • Page 13 SD3-60 AIRCRAFT MAINTENANCE MANUAL TRANSISTORISED TIMER - MAINTENANCE PRACTICES 30-11-21 9.0.0.0 Adjustment/Test A. Function check the timer The timer will be proved functional by the satisfactory completion of the system function test. Refer to 30-11-00, pb201. 30-11-21 EFFECTIVITY: All Page 201...
  • Page 14 SD3-60 AIRCRAFT MAINTENANCE MANUAL EJECTOR FLOW CONTROL VALVES - MAINTENANCE PRACTICES 30-11-26 10.0.0.0 Adjustment/Test A. Function check the valves The valves will be proved functional by the satisfactory completion of the system function test. Refer to 30-11-00, pb201. 30-11-26 EFFECTIVITY: All...
  • Page 15 SD3-60 AIRCRAFT MAINTENANCE MANUAL CYCLE INDICATOR SWITCHES (BOOT FUNCTION) - MAINTENANCE PRACTICES 30-11-31 11.0.0.0 Adjustment/Test A. Function check the switches. The switches will be proved functional by the satisfactory completion of the system function test. Refer to 30-11-00, pb201. 30-11-31...
  • Page 16 SD3-60 AIRCRAFT MAINTENANCE MANUAL BOOT DE-ICERS - MAINTENANCE PRACTICES 30-11-36 12.0.0.0 Servicing A. General An average life of approximately 5 years can be expected if the following precautions are observed:- (1) Inspect the de-icers regularly and repair all damage promptly.
  • Page 17 SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) Age Master may be applied by brushing, swabbing or rolling. Plastic or rubber gloves should be used with the swab method to prevent staining of the skin. Spraying is not recommended to avoid loss of vital components needed for a protective agent to penetrate rubber.
  • Page 18 SD3-60 AIRCRAFT MAINTENANCE MANUAL D. Adhesion reduction (1) ICEX application FAILURE TO FOLLOW DIRECTIONS COULD RESULT IN BODILY INJURY OR WARNING: DEATH. HARMFUL VAPOURS MAY CAUSE SKIN AND EYE IRRITATION. USE ONLY IN A WELL VENTILATED AREA. TO AVOID PROLONGED OR REPEATED SKIN CONTACT, USE RUBBER OR NEOPRENE GLOVES (INDUSTRIAL/ ALKALINE RESISTANT TYPE).
  • Page 19 SD3-60 AIRCRAFT MAINTENANCE MANUAL ICEX may be applied immediately before flight. However, DO NOT apply ICEX over Agemaster No. 1 that has not cured for at least 24 hours. Removal/Installation CEMENT AND SOLVENT VAPOURS ARE TOXIC AND EXTREMELY FLAMMABLE. USE WARNING: ONLY IN A WELL VENTILATED AREA AWAY FROM SPARKS OR FLAMES.
  • Page 20 SD3-60 AIRCRAFT MAINTENANCE MANUAL (3) It is permissible to install De-icers on alodined or anodized surfaces. If zinc chromate primer is unaffected by scrubbing with the cleaning solvent, it does NOTE: not have to be completely removed to facilitate De-icer installation as long as adequate adhesion is obtained (see para 3.A).
  • Page 21 SD3-60 AIRCRAFT MAINTENANCE MANUAL E. Mounting De-icer Refer to Figure 203. It is recommended that associated hoses are newly replaced before installing de-icer NOTE: boots. (1) Pull the end of the hose through the connection hole in the aerofoil. Where there is more than one hose, be sure each hose end is brought out through its proper hole to avoid improper inflation sequence.
  • Page 22 SD3-60 AIRCRAFT MAINTENANCE MANUAL De-icer loose from bonded area. Allow to dry thoroughly before continuing with application. Re-apply cement if any has pulled loose. (6) Installing Remainder of De-icer After the De-icer is fastened in place along its centreline, begin to reactivate the cement on either the upper or lower surface.
  • Page 23 SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) Brush coat one coat of Thixon P-10 primer over bare clean metal and 1300L cement up to the edge of de-icer (do not apply primer over de-icer). Let Thixon P-10 dry a minimum of 30 minutes.
  • Page 24 SD3-60 AIRCRAFT MAINTENANCE MANUAL Filler and sealer application for neoprene de-icer Figure 201 30-11-36 EFFECTIVITY: All Page 209 Jun 30/01...
  • Page 25 SD3-60 AIRCRAFT MAINTENANCE MANUAL Filler and sealer application for estane de-icer Figure 202 30-11-36 EFFECTIVITY: All Page 210 Jun 30/01...
  • Page 26 SD3-60 AIRCRAFT MAINTENANCE MANUAL Illustrated Instructions Figure 203 30-11-36 EFFECTIVITY: All Page 211 Jun 30/01...
  • Page 27 SD3-60 AIRCRAFT MAINTENANCE MANUAL (c) If a force of five pounds per inch of width can be exerted under these conditions, the installation shall be considered to be satisfactory. Remember, the width increases as the corner peels back. (d) Re-cement the corner following the installation procedure.
  • Page 28 SD3-60 AIRCRAFT MAINTENANCE MANUAL (10) Shut off pneumatic supply, leaving connected to the system. (11) Ensure all water, if present, is removed from the affected de-icer boot, this will entail slitting the boot section containing water not greater than 1/2 inch.
  • Page 29 SD3-60 AIRCRAFT MAINTENANCE MANUAL (5) Wipe buffed surface with a dry, lint-free cloth. (6) For Neoprene De-Icers: (a) Brush on one coat of number 4 cement P/N 74-451-20 to de-icer surface and allow to dry. (7) For Estane De-Icers: (a) Apply one even coat of 74-451-98 cement to the de-icer surface and allow to dry.
  • Page 30 SD3-60 AIRCRAFT MAINTENANCE MANUAL Winterisation of Pneumatic De-icers Prior to initiating the following procedure, ensure the pneumatic system has been leak NOTE: tested as detailed in para 3.B and functioned. Refer to 30-11-00, pb201. This will ensure the integrity of the pneumatic de-icing system.
  • Page 31 SD3-60 AIRCRAFT MAINTENANCE MANUAL (8) Shut off de-icing system and remove the shop air from the test point. (9) Replace all panels removed in step (1) used to gain access to the ejector flow control valves. It is recommended that each ejector flow control valve be lubricated with a light NOTE: viscosity silicone oil, approx.
  • Page 32 SD3-60 AIRCRAFT MAINTENANCE MANUAL PRESSURE REGULATORS - MAINTENANCE PRACTICES 30-11-41 13.0.0.0 Adjustment/Test A. Function check the pressure regulators. Refer to 6-30-00, pb1. Open access panel 312 TZ in the aft baggage compartment rear bulkhead. (2) Install a pressure gauge 0-50 p.s.i. at the aerofoil de-icing test point.
  • Page 33 SD3-60 AIRCRAFT MAINTENANCE MANUAL WATER SEPARATOR - MAINTENANCE PRACTICES 30-11-46 14.0.0.0 Adjustment/Test A. Function test the water separator. (1) For convenience of maintenance, the water separator is function tested during pressure regulator test by checking for airflow at the overboard drain.
  • Page 34 SD3-60 AIRCRAFT MAINTENANCE MANUAL PRESSURE SWITCH AND TIME DELAY RELAY - MAINTENANCE PRACTICES 30-11-51 15.0.0.0 Adjustment/Test A. Function check the pressure switch and time delay relay. (1) Jack the aircraft. Refer to 7-10-00, pb201. (2) Provide electrical power. Refer to 12-09-03, pb301.
  • Page 35 SD3-60 AIRCRAFT MAINTENANCE MANUAL BOOT EJECTOR VALVE ANTI-ICING - DESCRIPTION & OPERATION 30-12-00 16.0.0.0 General The five boot de-icer ejector valves (two left wing, two right wing and one tail) are provided with electrically heated muffs, each rated at 1.5 amps.
  • Page 36 SD3-60 AIRCRAFT MAINTENANCE MANUAL BOOT EJECTOR VALVE ANTI-ICING - MAINTENANCE PRACTICES 30-12-00 17.0.0.0 Adjustment/Test A. Function check heater muffs (1) Hinge down flight compartment roof panel 4P Refer to 12-09-03, pb301. Provide electrical power. (3) Close C/B Nos. 87 and 237 on respective distribution panels 1D and 2D...
  • Page 37 SD3-60 AIRCRAFT MAINTENANCE MANUAL ENGINE AIR INTAKE ANTI-ICING - GENERAL 30-20-00 18.0.0.0 General The aircraft is provided with an engine air intake anti-icing system, details of which appear in the following sections. A. Engine air intake anti-icing (Pre mod A8170).
  • Page 38 SD3-60 AIRCRAFT MAINTENANCE MANUAL ENGINE AIR INTAKE ANTI-ICING - DESCRIPTION & OPERATION 31-21-10 19.0.0.0 (PRE MOD A8170) Description A. General A Dunlop AC1192 heater mat is installed on the lip of each air intake cowl and is operationally controlled within the temperature range 70°C to 80°C.
  • Page 39 SD3-60 AIRCRAFT MAINTENANCE MANUAL Should the lip temperature reach 80°C the temperature sensor will signal the thermal controller to de-energise the remote control circuit breaker, thus interrupting the heater supply. The absence of flow through the current sensing relay will cause the contacts to open, extinguishing the ON caption on panel 4P.
  • Page 40 SD3-60 AIRCRAFT MAINTENANCE MANUAL ENGINE AIR INTAKE ANTI-ICING - MAINTENANCE PRACTICES (PRE MOD A8170) 30-21-10 20.0.0.0 Adjustment/Test A. Function test the system Equipment required : Avometer (1) Gain access to the engine air intake heater terminal blocks by lowering air intake cowl 420BB on each engine.
  • Page 41 SD3-60 AIRCRAFT MAINTENANCE MANUAL (10) Select left INTAKES switch ON and check that indicator cycles ON and OFF. Allow two cycles only before selecting switch OFF. (11) Select left INTAKES switch ON and ensure that ON indication is illuminated. Momentarily apply a 28V DC feed at A1TB2 terminal 3 (left engine) and check that system trips off i.e.
  • Page 42 SD3-60 AIRCRAFT MAINTENANCE MANUAL ENGINE AIR INTAKE ANTI-ICING - DESCRIPTION & OPERATION 30-21-20 21.0.0.0 (POST MOD A8170 OR POST SERVICE BULLETIN SD360-30-17) Description A. General A Dunlop AC1192 heater mat is installed on the lip of each air intake cowl and is operationally controlled within the temperature range 70°C to 80°C.
  • Page 43 SD3-60 AIRCRAFT MAINTENANCE MANUAL Should the temperature reach 80°C, the temperature sensor will signal the control unit to de- energize the slave relay, thereby breaking the supply to the coil of the control contactor. The absence of flow of current through the current sensing relay will cause its contacts to open, extinguishing the ON indication on panel 4P.
  • Page 44 SD3-60 AIRCRAFT MAINTENANCE MANUAL ENGINE AIR INTAKE ANTI-ICING - MAINTENANCE PRACTICES 30-21-20 22.0.0.0 (POST MOD A8170 OR POST SERVICE BULLETIN SD360-30-17) Adjustment/Test A. Function test the system Equipment required: Avometer 28V DC Power Supply (1) Gain access to the engine air intake heater terminal blocks by lowering air intake cowl 420BB on each engine.
  • Page 45 SD3-60 AIRCRAFT MAINTENANCE MANUAL (10) Select the left INTAKES switch to ON and ensure that the ON indication is illuminated. Momentarily apply a 28V DC feed at A1TB2 terminal 3 (left engine) and check that system trips off i.e. indication is extinguished.
  • Page 46 SD3-60 AIRCRAFT MAINTENANCE MANUAL INTAKE INERTIAL ANTI-ICING - DESCRIPTION & OPERATION 30-22-00 23.0.0.0 Description A. General An electrical actuator functioned arrangement within each engines air intake cowl is operationally deployed to prevent ice and snow particles from clogging/entering the compressor inlet screen.
  • Page 47 SD3-60 AIRCRAFT MAINTENANCE MANUAL C. Power supplies Actuator power supplies are derived from the 28V dc left and right General Services busbars via C/B Nos 24 and 174 on respective distribution panels 1D and 2D. Drag limiting relay control supply is taken from the propeller autofeathering circuitry.
  • Page 48 SD3-60 AIRCRAFT MAINTENANCE MANUAL If the ANTI-ICE VANES switch is in the OFF (NORM caption illuminated) position at this time, 28V dc is routed to the CWP, via the energised relay(s) illuminating the associated segment of the VANE L / VANE R annunciator.
  • Page 49 SD3-60 AIRCRAFT MAINTENANCE MANUAL Intake Inertial Anti-icing Figure 1 30-22-00 EFFECTIVITY: All Page 4 Apr 24/03...
  • Page 50 SD3-60 AIRCRAFT MAINTENANCE MANUAL INTAKE INERTIAL ANTI-ICING - MAINTENANCE PRACTICES 30-22-00 24.0.0.0 Adjustment/Test A. Rig the aft intake vane Refer to Figure 201. Rigging is carried out with the linear actuator disconnected. (1) Check by manual operation, that the aft vane moves freely throughout its range of travel and seals off the rear of the duct when fully closed i.e.
  • Page 51 SD3-60 AIRCRAFT MAINTENANCE MANUAL C. Rig the forward intake vane. Refer to 12-09-03, pb301. Energise the left or right 28V D.C. general services busbar as applicable. (2) Close circuit breaker No. 24 on panel 1D (left intake) or circuit breaker No. 174 on panel 2D (right intake) as appropriate.
  • Page 52 SD3-60 AIRCRAFT MAINTENANCE MANUAL Intake Inertial Anti-icing - Rigging Figure 201 30-22-00 EFFECTIVITY: All Page 203 Apr 24/03...
  • Page 53 SD3-60 AIRCRAFT MAINTENANCE MANUAL (5) Check auto-deployment function (drag limiting) as follows:- Both intake arrangements may be checked simultaneously as undernoted. NOTE: (a) Ensure autofeather system C/B Nos.20 and 170 on respective distribution panels 1D and 2D are closed. (b) With both systems selected OFF and NORMAL displayed, hold the AUTO FEATHER test switches on panel 11P at TEST, checking:- NORMAL indications are extinguished i.e.
  • Page 54 SD3-60 AIRCRAFT MAINTENANCE MANUAL PITOT/STATIC ANTI ICING SYSTEM - DESCRIPTION & OPERATION 30-31-00 25.0.0.0 Description A. General Anti-icing protection for the pitot heads and static vents of the Pitot/Static system (Refer to 34- 11-00, pb1.) is afforded by 28V d.c. heater elements within each unit.
  • Page 55 SD3-60 AIRCRAFT MAINTENANCE MANUAL PITOT/STATIC ANTI-ICING SYSTEM - MAINTENANCE PRACTICES 30-31-00 26.0.0.0 Adjustment/Test A. Function check (1) Select both PITOT/STATIC/STALL switches OFF. (2) Energise LEFT and RIGHT 28V D.C. MAIN and ESSENTIAL SERVICES busbars from an external supply. (3) Ensure that circuit breaker Nos.21 and 22 (panel 1D) and 171 and 172 (panel 2D) are closed.
  • Page 56 SD3-60 AIRCRAFT MAINTENANCE MANUAL WINDSHIELDS - GENERAL 30-40-00 27.0.0.0 General Weather protection for the pilots windshield consists of: A. Electrically heated windshield. Refer to 30-41-00, pb1. B. Windshield wipers. Refer to 30-42-00, pb1. C. A rain repellent system. Refer to 30-43-00, pb1.
  • Page 57 SD3-60 AIRCRAFT MAINTENANCE MANUAL HEATED WINDSHIELD - DESCRIPTION & OPERATION 30-41-00 28.0.0.0 General Both forward facing windshield panels are provided with controlled electrical heat for ice prevention. The heat output from each is regulated by individual thermal controllers, operating in conjunction with associated control switches, indicators and supply (normal and overheat) relays.
  • Page 58 SD3-60 AIRCRAFT MAINTENANCE MANUAL The associated switch/indicator module will illuminate NORMal only during heat transmission i.e. until the supply is automatically switched off by the thermal controller (normal relay open) when a windshield temperature of 39°C is sensed. The normal channel relay will close to restore the heating circuit when the windshield temperature falls to 31°C.
  • Page 59 SD3-60 AIRCRAFT MAINTENANCE MANUAL HEATED WINDSHIELD - MAINTENANCE PRACTICES 30-41-00 29.0.0.0 Removal/Installation A. Remove a windscreen (1) Isolate power supply to windshield by opening CB112 and CB113 (left) or CB248 and CB249 (right) as appropriate, on distribution panels 1D or 2D respectively.
  • Page 60 SD3-60 AIRCRAFT MAINTENANCE MANUAL Adjustment/Test A. Function check The following operations presume a left windshield being function checked. For right NOTE: windshield function check, substitute right for left, and CB248 and CB249 on panel 2D for CB112 and CB113 on panel 1D.
  • Page 61 SD3-60 AIRCRAFT MAINTENANCE MANUAL (4) Should either of the thermistors exceed the set limits, a check should be carried out of the 'SPARE' thermistor (terminals S1 and S2) which, if satisfactory, may replace the damaged thermistor. Temperature Sensors - Ambient Temperature/Resistance...
  • Page 62 SD3-60 AIRCRAFT MAINTENANCE MANUAL WINDSHIELD WIPERS - DESCRIPTION & OPERATION 30-42-00 30.0.0.0 Description A. General Two independent electro-mechanical type wiper installations are provided; one at each pilots position. Each installation essentially is comprised of a motor coupled to a converter, drive arm and blade assembly.
  • Page 63 SD3-60 AIRCRAFT MAINTENANCE MANUAL Power Supplies Windshield wipers operate from the 28V DC Essential Services busbars; supplies are respectively taken for left and right hand wipers via 10 amp circuit breakers CB39 on panel 1D and CB189 on panel 2D.
  • Page 64 SD3-60 AIRCRAFT MAINTENANCE MANUAL Windshield Wipers Figure 1 30-42-00 EFFECTIVITY: All Page 3 Jun 30/01...
  • Page 65 SD3-60 AIRCRAFT MAINTENANCE MANUAL WINDSHIELD WIPERS - MAINTENANCE PRACTICES 30-42-00 31.0.0.0 Removal/Installation A. Remove converter (1) Unlock and remove bolt securing the drive arm assembly to the converter shaft. Remove the drive arm assembly complete with wiper blade. If the same wiper and drive arm assembly is to be refitted carefully mark the arm in NOTE: relation to the converter shaft.
  • Page 66 SD3-60 AIRCRAFT MAINTENANCE MANUAL (7) Re-connect electrical plug to motor and secure. (8) Close circuit breaker CB39 on panel 1D (left hand) or circuit breaker CB189 on panel 2D (right hand). (9) Replace drive arm assembly on splined end of converter shaft and secure with bolt, ensuring that any locating marks relating to the relationship of the converter shaft to the drive arm assembly position are re-aligned.
  • Page 67 SD3-60 AIRCRAFT MAINTENANCE MANUAL (5) Re-connect the earth lead from the motor to the terminal post on stringer 25 (E59 left hand or E58 right hand). (6) Re-connect electrical plug to motor and secure. (7) Close circuit breaker CB39 on panel 1D (left hand) or circuit breaker CB189 on panel 2D (right hand).
  • Page 68 SD3-60 AIRCRAFT MAINTENANCE MANUAL DO NOT OPERATE WINDSHIELD WIPERS OVER DRY GLASS. CAUTION: DO NOT ALLOW ARM TO SLAP SIDE PILLAR. (8) Operate windshield wiper over the windshield (wetted) for minimum period of 30 seconds, observing that it wipes over the desired area. Stop and park the wipers a few times to ensure that they stop at the PARK position each time.
  • Page 69 SD3-60 AIRCRAFT MAINTENANCE MANUAL RAIN REPELLENT SYSTEM - DESCRIPTION & OPERATION 30-43-00 32.0.0.0 Description A. General This system is installed to dispense a rain repellent fluid to the aircraft windshield. It is intended for use when the aircraft is operating under conditions of medium to heavy rainfall to provide considerably clearer vision than is possible by the use of windshield wipers.
  • Page 70 SD3-60 AIRCRAFT MAINTENANCE MANUAL E. Power supplies The two 28V dc supplies, one for each windshield are taken from the ESSENTIAL SERVICES busbar via circuit breakers on panel 1D and 2D. The left windshield is supplied via circuit breaker No.246 on panel 2D from the RIGHT ESSENTIAL SERVICES busbar, and the right windshield via circuit breaker No.46 on panel 1D from the LEFT ESSENTIAL...
  • Page 71 SD3-60 AIRCRAFT MAINTENANCE MANUAL Rain Repellent System - General Arrangement Figure 1 30-43-00 EFFECTIVITY: All Page 3 Jun 30/01...
  • Page 72 SD3-60 AIRCRAFT MAINTENANCE MANUAL RAIN REPELLENT SYSTEM - TROUBLE SHOOTING 30-43-00 33.0.0.0 Trouble shooting Refer to Table 101. The possible faults most likely to be encountered in this system are listed, together with the probable causes and the remedial actions. It is assumed that a 28V dc supply is available at the circuit fuses and a canister containing fluid and pressure is correctly fitted.
  • Page 73 SD3-60 AIRCRAFT MAINTENANCE MANUAL THIS PAGE LEFT BLANK INTENTIONALLY 30-43-00 EFFECTIVITY: All Page 102 Jun 30/01...
  • Page 74 SD3-60 AIRCRAFT MAINTENANCE MANUAL RAIN REPELLENT SYSTEM - MAINTENANCE PRACTICES 30-43-00 34.0.0.0 General When servicing this equipment it is essential to prevent the ingress of dirt, swarf or water. As the fluid is of a highly hygroscopic nature the presence of even small quantities of water can cause gelling of the fluid and the formation of gritty deposits in the system.
  • Page 75 SD3-60 AIRCRAFT MAINTENANCE MANUAL Remove a solenoid valve Before removing a faulty solenoid valve the electrical circuit should be rendered 'dead' by opening the appropriate circuit breaker and the pressure should be removed from the system by unscrewing the canister from its adapter socket. The valve is then removed by withdrawing the electrical socket, unscrewing the 'inlet' pipe connector and disconnecting the outlet port from the nozzle assembly.
  • Page 76 SD3-60 AIRCRAFT MAINTENANCE MANUAL C. Operate a push-button switch, at the same time listening for a simultaneous click from the associated solenoid valve, indicating that it has opened. A second click from the solenoid valve should immediately follow the first, indicating that the valve has closed and that the time delay relay has operated correctly.
  • Page 77 SD3-60 AIRCRAFT MAINTENANCE MANUAL PROPELLER ANTI-ICING (FIVE-BLADED PROPELLERS) - DESCRIPTION & OPERATION 30-61-00 35.0.0.0 Six-bladed propeller anti-icing (aircraft equipped with PT6A-67R engines). Refer to 30-62- NOTE: pb1. Description A. General Refer to Figure This installation is a B.F. Goodrich 'HotProp' 2-cycle de-icing system and comprises a...
  • Page 78 SD3-60 AIRCRAFT MAINTENANCE MANUAL D. Indication Cycle indication of current flow to the propeller heaters is provided via current sensing relays in each heating circuit signalling the ON caption situated above each control switch (panel 4P). Operation With the appropriate power supplies made available for left and right operation and the control...
  • Page 79 SD3-60 AIRCRAFT MAINTENANCE MANUAL Propeller Anti-icing - Installation Figure 1 30-61-00 EFFECTIVITY: All Page 3 Jun 30/01...
  • Page 80 SD3-60 AIRCRAFT MAINTENANCE MANUAL PROPELLER ANTI-ICING (FIVE-BLADED PROPELLERS) - MAINTENANCE PRACTICES 30-61-00 36.0.0.0 Six-bladed propeller anti-icing (aircraft equipped with PT6A-67R engines). Refer to 30-62- NOTE: pb201. Adjustment/Test A. Function check Equipment required: Avometer (1) Remove spinners from both propellers. (2) Remove connectors at brush block assemblies 'HA8' on left engine.
  • Page 81 SD3-60 AIRCRAFT MAINTENANCE MANUAL (13) Ensure that PROP HEAT and PROP HEAT CONTROL circuit breakers 7 & 8 and 157 and 158 on panels 1D and 2D are closed. (14) Select PROPELLERS heat switches - left to ON and right to TFR.
  • Page 82 SD3-60 AIRCRAFT MAINTENANCE MANUAL BRUSH BLOCK (FIVE-BLADED PROPELLERS) - MAINTENANCE PRACTICES 30-61-01 37.0.0.0 Six-bladed propeller anti-icing (aircraft equipped with PT6A-67R engines). Refer to 30-62- NOTE: pb201. Removal/Installation A. Remove a brush block. (1) Open circuit breakers Nos 7 and 8 on left distribution panel 1D and circuit breakers Nos 157 and 158 on right distribution panel 2D.
  • Page 83 SD3-60 AIRCRAFT MAINTENANCE MANUAL Brush Projection Figure 201 30-61-01 EFFECTIVITY: All Page 202 Jun 30/01...
  • Page 84 SD3-60 AIRCRAFT MAINTENANCE MANUAL Cleaning/Painting DAMAGE TO THE PROPELLER ANTI-ICING SYSTEM CAN OCCUR IF GREASE OR WARNING: OIL/CARBON DUST DEPOSITS ARE ALLOWED TO FORM ON THE BRUSH BLOCK AND ASSOCIATED SLIP RINGS. A. Clean the brush block and slip rings.
  • Page 85 SD3-60 AIRCRAFT MAINTENANCE MANUAL PROPELLER ANTI-ICING (SIX-BLADED PROPELLERS) - DESCRIPTION & OPERATION 30-62-00 38.0.0.0 Five-bladed propeller anti-icing (aircraft equipped with PT6A-65R or -65AR engines). NOTE: Refer to 30-61-00, pb1. Description A. General The propellers are each electrically de-iced in two alternate blade group sequences by B.F.
  • Page 86 SD3-60 AIRCRAFT MAINTENANCE MANUAL Panel 41C Panel 42C Component Circuit Ident Circuit Ident Contractors (4) (2) Panel 29C and 30C: The panels are respectively positioned on the left and right rear face of the step at fuselage frame station 74. The propeller de-icing associated equipment located on each...
  • Page 87 SD3-60 AIRCRAFT MAINTENANCE MANUAL Function (b) Activates timer in the 'fast stepping' checking sequence in the 10 sec. mode when; engine is stopped, mode switch is set to NORM, timer switch is at ON and the associated PRESS- TO-TEST switch/indicator is pushed repeatedly to step advance the timer through the mode sequence.
  • Page 88 SD3-60 AIRCRAFT MAINTENANCE MANUAL If the ambient temperature rises above 30°C, the thermostat contacts make, so energizing the associated LOW FUEL and OIL PRESSURE WARNING relay, and breaking the supply to the propeller heaters. F. Brush Block and Sliprings The electrical connections to the heaters of each propeller are made by two brush blocks and a propeller mounted slipring assembly.
  • Page 89 SD3-60 AIRCRAFT MAINTENANCE MANUAL (4) Test switch/cycle indicators The PUSH-TO-TEST/cycle indicator is positioned above each timer switch. The switch action is momentary press and enables the associated timer to be 'fast- stepped' through its cycling sequence when; the engine is stopped and the timer is selected ON.
  • Page 90 SD3-60 AIRCRAFT MAINTENANCE MANUAL B. Operation - both timers functional With engines running (related oil pressure relays de-energized) selection of both timer switches on panel 4P to ON will activate the timers in the 10 seconds or 20 second heating phase sequence as respectively determined by the NORM or BELOW-10 setting of the mode switch.
  • Page 91 SD3-60 AIRCRAFT MAINTENANCE MANUAL To confirm that timer logic, heaters and control circuitry are serviceable, the mode switch is set to NORM, one timer switch to ON and the opposite to TFR. The PUSH-TO-TEST switch/ indicator for the ON timer is then sequence pressed (for approx. 3 seconds) and released (for not more than 5 seconds, otherwise stepping action will be lost) until the following illuminating displays on the functioning timers switch/indicator are achieved;...
  • Page 92 SD3-60 AIRCRAFT MAINTENANCE MANUAL PROPELLER ANTI-ICING (SIX-BLADED PROPELLERS) - MAINTENANCE PRACTICES 30-62-00 39.0.0.0 Five-bladed propeller anti-icing (aircraft equipped with PT6A-65R or -65AR engines). NOTE: Refer to 30-61-00, pb201. Adjustment/Test A. Check heater mat group resistances, Equipment required: Avometer (1) Remove spinners from both propellers.
  • Page 93 SD3-60 AIRCRAFT MAINTENANCE MANUAL (c) Sequence press and release the left PUSH-TO-TEST switch/indicator as necessary and check that the indicator displays: ON lower, ON upper, ON lower, ON upper (followed by one 'no indication' press before ON lower (new cycle) resumes; release switch.
  • Page 94 SD3-60 AIRCRAFT MAINTENANCE MANUAL BRUSH BLOCKS (SIX-BLADED PROPELLERS) - MAINTENANCE PRACTICES 30-62-01 40.0.0.0 Removal/Installation A. Remove a brush block module. (1) Open C/B Nos 7&8 on panel 1D and 157&158 on panel 2D. Refer to 6-30-00, pb1. Gain access to the brush block assemblies by lowering the intake cowl and removing panel 420AB.
  • Page 95 SD3-60 AIRCRAFT MAINTENANCE MANUAL (6) Close access panels. Cleaning DAMAGE TO THE PROPELLER ANTI-ICING SYSTEM CAN OCCUR IF GREASE OR WARNING: OIL/CARBON DUST DEPOSITS ARE ALLOWED TO FORM ON THE BRUSH BLOCKS AND SLIPRINGS. A. Clean the brush blocks and sliprings Perform the following at each engine in turn:- (1) Remove both brush block assemblies (refer to para 1.A.).
  • Page 96 SD3-60 AIRCRAFT MAINTENANCE MANUAL Brush Projection Figure 201 30-62-01 EFFECTIVITY: All Page 203 Jun 30/01...
  • Page 97 SD3-60 AIRCRAFT MAINTENANCE MANUAL ICE DETECTION - GENERAL 30-80-00 41.0.0.0 General Detection of ice is by a rotary ice detector. Refer to 30-81-00, pb1. The presence of ice can be confirmed by a visual inspection of the leading edges. In darkness this is facilitated by the use of a spotlight.
  • Page 98 SD3-60 AIRCRAFT MAINTENANCE MANUAL ICE DETECTION SYSTEM - DESCRIPTION & OPERATION 30-81-00 42.0.0.0 General A Lucas Aerospace Limited Mk.3 rotary ice detector unit is mounted on the bottom of the nose fuselage at Stn. -5.50 and 7.3 in. to the left of the aircraft centreline.
  • Page 99 SD3-60 AIRCRAFT MAINTENANCE MANUAL ICE DETECTION SYSTEM - MAINTENANCE PRACTICES 30-81-00 43.0.0.0 Removal/Installation Refer to Figure 201. DO NOT DISTURB EXTERNAL BOLTS, NUTS OR SCREWS, OTHER THAN THE FOUR CAUTION: STRUCTURAL ATTACHMENT BOLTS, OR REMOVE SWITCH END COVER, OR ELSE THE ADJUSTMENT OF THE DETECTOR MAY BE SERIOUSLY IMPAIRED.
  • Page 100 SD3-60 AIRCRAFT MAINTENANCE MANUAL Ice Detector Unit - Installation Figure 201 30-81-00 EFFECTIVITY: All Page 202 Jun 30/01...
  • Page 101 SD3-60 AIRCRAFT MAINTENANCE MANUAL Torque testing Figure 202 30-81-00 EFFECTIVITY: All Page 203 Jun 30/01...
  • Page 102 SD3-60 AIRCRAFT MAINTENANCE MANUAL Refer to Figure 202. Insert the blade of a torque test indicator into the slot in the end face of the rotor and, with slight thumb pressure, apply a torque load. Check that the ICE warning light on the CWP is illuminated.