24 ELECTRICAL DC ELECTRICAL SYSTEM DESCRIPTION
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- Albert Joseph
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1 24 ELECTRICAL DC ELECTRICAL SYSTEM DESCRIPTION The Direct Current electrical system provides power to most equipment through an electrical bus system. The power may be supplied from one of three sources: 1.) BATTERY, AIRCRAFT STORAGE 2.) GENERATOR, ENGINE DRIVEN 3.) EXTERNAL POWER All three sources can power the main bus which can then power four additional buses, Secondary, Engine, Avionics and Service buses. The aircraft battery and external power can also supply power to the start box. The aircraft battery and generator can power the hot battery bus. DESCRIPTION OF COMPONENTS BATTERY, AIRCRAFT STORAGE (FIGURE 24-1) A 24 volt Gill G6381E lead acid storage battery is located in the right hand nose section and is vented to the atmosphere to preclude the build up of hydrogen gas. The battery is connected to the electrical system via the battery relay. The primary purpose of the battery is for engine starting and an emergency source of electrical power. The battery, when fully charged, has sufficient capacity (70amps/30min.) to power all installed equipment for 30 minutes. This time may be extended if non-essential equipment is turned off. The battery capacity for one hour is 43 amps. BATTERY MINDER FEMALE PLUG (FIGURE 24-1) This plug allows the aircraft battery to be connected to a Battery Minder that maintains the battery while the aircraft is not in use. The plug is wired through the battery relay and will automatically disconnect the battery minder when the battery relay is activated. The plug is located just inside the battery disconnect access door on the floor of the nose baggage compartment. December 14, 2011 Copyright 2011 by L29 Support, Inc
2 BATTERY RELAY (FIGURE 24-1) The battery relay is located in the right hand nose section and is used to connect the battery to the main bus and the start box. BUS CONTROL RELAYS (FIGURE 24-1) Bus control relays are used to facilitate remote control of the bus power and are located under the main circuit breaker panel. These relays are powered by the main bus through bus control circuit breaker (A6). CURRENT LIMITERS (FIGURE 24-1) Current limiters are installed to protect the electrical system, one each just prior to the shunts. They are located under the electrical control panel. DIFFERENTIAL MINIMUM RELAY (FIGURE 24-1) The differential minimum relay is used to connect and disconnect the generator from the electrical system. The relay will close and connect the generator to the electrical system if the generator switch is selected ON and 1) external power is not connected and 2) the generator voltage is above that of the main bus and 3) the overvoltage relay is not sensing an overvoltage condition and 4) a reverse current condition is not sensed. The differential minimum relay will open removing the generator from the electrical system when any of the above conditions are not met. EMERGENCY BUS POWER (FIGURE 24-1) This provides a means to bypass the bus control relays and supply power directly from the main bus. EXTERNAL POWER RECEPTACLE (FIGURE 24-1) The purpose of the receptacle is to allow the aircraft electrical system to be powered from an external power source. The receptacle is located on the aft left fuselage. EXTERNAL POWER RELAY (FIGURE 24-1) The external power relay is used to connect external power from the external power receptacle to the electrical system. The external power relay is located on the left side of the engine mount. December 14, 2011 Copyright 2011 by L29 Support, Inc
3 FIGURE 24-1 December 14, 2011 Copyright 2011 by L29 Support, Inc
4 FILTER (FIGURE 24-1) A filter is used to reduce or eliminate high frequency interferences caused by the generator when producing electrical power. GENERATOR, ENGINE DRIVEN (FIGURE 24-1) An engine driven generator, capable of producing 105 amps at 28VDC, is utilized to power all installed electrical equipment and recharge the aircraft storage battery. Generator cooling is accomplished by ram air and an internal fan. HOT BATTERY BUS (FIGURE 24-1) The hot battery bus is powered whenever the battery is connected or when the battery relay is closed and the generator is online and supplying power. Refer to page for list of equipment powered from this bus. IMPULSE SENDER (FIGURE 24-1) The impulse sender is used to make the GEN annunciator light flash. MAIN BUS (FIGURE 24-1) The main bus is powered through one of two current limiters located under the electrical control panel. When the battery switch is turned on the main bus may be powered by the battery, generator or external power. Refer to page for list of equipment powered from this bus. MAIN POWER RELAY (FIGURE 24-1) The main power relay is used to automatically disconnect both the battery and the generator from the electrical system when an external power source is connected by opening the battery and differential relays. OVER VOLTAGE RELAY (FIGURE 24-1) The overvoltage relay protects the electrical system from voltage that exceeds the maximum allowable. If the voltage spikes the overvoltage relay signals the differential relay to open, disconnecting the generator from the rest of the electrical system. REGULATOR (FIGURE 24-1) A carbon voltage regulator is used to stabilize the output voltage of the generator under fluctuating loads and variable engine speeds. December 14, 2011 Copyright 2011 by L29 Support, Inc
5 SHUNTS (FIGURE 24-1) Shunts are placed in series with the battery and generator feeds so that the current flow can be measured. Current information, supplied through the source control relay may be read on the analog amp/voltmeter. The shunts are located below the electrical control panel. SIGNALING RELAY (FIGURE 24-1) The signaling relay is used to indicate a difference in voltage between the aircraft battery and the generator. When the voltage of the generator is lower than the battery the signaling relay sends a signal to the impulse sender and illuminates the GEN light in both annunciators. SOURCE CONTROL RELAY (FIGURE 24-2) The source control relay is used to provide the selected information to the analog amp/voltmeter. The relay is controlled by the source selector switch, located next to the analog amp/voltmeter. FIGURE 24-2 STABILIZING TRANSFORMER (FIGURE 24-1) A stabilizing transformer is used to prevent spikes in the voltage as a result of turning on and off electrical equipment. December 14, 2011 Copyright 2011 by L29 Support, Inc
6 STANDBY POWER (FIGURE 24-3) Standby power is a means to supply power to Comm 1 and the GPS without powering up the normal electrical system. FIGURE 24-3 STANDBY POWER RELAY (FIGURE 24-3) The relay, when activated, allows Comm 1 and the GPS to be powered from the hot battery bus rather than from the avionics bus. The relay will automatically deactivate and switch power back to the avionics bus when the main bus is powered. START BOX (FIGURE 24-1) The start box is used to sequence the starter and ignition for engine starts. The start box is discussed in greater detail in the engine section. December 14, 2011 Copyright 2011 by L29 Support, Inc
7 CONTROLS AND INDICATORS ELECTRICAL CONTROL PANEL The electrical control panel is located in the front cockpit on the forward portion of the right console. FIGURE ) BATTERY SWICTH (BATT) The Battery Switch is a locking type switch, pull to change. When the switch is positioned to ON (see exception one) it closes the circuit between circuit breaker N1 (hot battery bus) and the battery relay coil, through the main power relay. This energizes the coil pulling the relay contacts closed connecting the battery to the normal electrical system. Exception one: external power has priority over the other two power sources. When external power is connected to the aircraft it automatically activates the main power relay and prevents the battery or differential relays from closing. Positioning the BATT switch to ON energizes the coil in the external power relay, instead of the battery relay, allowing the external power to connect December 14, 2011 Copyright 2011 by L29 Support, Inc
8 to the normal electrical system. When external power is disconnected the main power relay de-energizes and allows the battery and differential relays to operate normally. 2.) GENERATOR SWITCH (GEN) The generator switch is a locking type switch, pull to change. Selecting the generator switch ON closes the circuit between the overvoltage relay and the differential relay. This allows the differential minimum relay to energize and close if: 1) external power is not connected and 2) the generator voltage is above that of the main bus and 3) the overvoltage relay is not sensing an overvoltage condition and 4) a reverse current condition is not sensed. 3.) EXTERNAL POWER INDICATOR LIGHT (EXT PWR) Illumination of the ON light indicates external power is connected and the main power relay is activated. Pushing the EXT PWR indicator tests all the indicator lights in the electrical control panel, source selector switch and the standby power switch. 4.) DIGITAL VOLTMETER A digital voltmeter is located on the electrical control panel and is powered by the main bus through the bus sensing circuit breaker (A5). The voltmeter indicates the voltage of the main bus only. 5.) BUS SELECTOR SWITCHES AND BUS SENSING The bus selector switches are illuminated push button switches located on the electrical control panel. They are identified as Secondary (SEC), Engine (ENG), Avionics (AVI) and Service (SER). Pushing the switches in will energize their respective bus control relay, pulling the relay contacts closed connecting the bus to the main bus. Pushing the switches again will de-energize their respective bus control relays opening the contacts and disconnecting power from the respective bus. The switches will illuminate OFF anytime their respective bus is not powered and the main bus is, regardless of switch position. The bus sensing circuits are powered by the main bus through the bus sensing circuit breaker (A5). Refer to page for a list of equipment powered from these buses. December 14, 2011 Copyright 2011 by L29 Support, Inc
9 ANALOG AMP/VOLTMETER & SOURCE SELECTOR SWITCH The analog amp/voltmeter and the source selector switch are located on the lower right of the front instrument panel, figure FIGURE 24-5 The meter indicates amps on the lower scale from -40 to Voltage can also be read on the meter s upper scale from 0 to 30 if the button, located on the lower portion of the indicator, is pushed and held in. An illuminated selector switch, located to the lower right of the analog amp/voltmeter, is labeled SOURCE and may be used to select and display the battery or generator information on the amp/voltmeter. The normal indication is lights out ; this will display the generator information. When the selector switch is pushed in BATT will illuminate and the amp/voltmeter will display the battery information. Pushing the switch again will return it to lights out condition and the generator information will be displayed. The meter and wiring are protected by fuses located next to the shunts under the electrical control panel. ANNUNCIATOR LIGHT, GEN (FIGURE 24-6) When the voltage of the generator is lower than the battery the signaling relay sends a signal to the impulse sender and illuminates the GEN light in both annunciator panels. This is also an indication that the differential relay is open and the generator is offline. FIGURE 24-6 December 14, 2011 Copyright 2011 by L29 Support, Inc
10 CIRCUIT POTECTION (FIGURE 24-7&8) Electrical circuits are protected with resettable circuit breakers. When a current demand in a circuit reaches its limit the circuit breaker will open. The button indicator will pop up to expose a white band. Circuit breakers should not be reset in flight and must cool before attempting a reset. The main circuit breaker panel is located on the aft right console in the front cockpit (figure 24-7). The circuit breakers are assigned an alphanumeric number. Row A is the most inboard row and progress outboard to rows B, C & D respectively. The first circuit breaker in each row starts with the number 1 and progress to higher numbers proceeding right. FIGURE 24-7 The hot battery bus circuit breaker panel is located on the floor of the nose baggage compartment under a clear plastic door (figure 24-8). FIGURE 24-8 EMERGENCY BUS POWER (FIGURE 24-7) These guarded toggle type circuit breakers are used to power their respective buses, from the main bus, during certain abnormal or emergency procedures. They are located on the main circuit breaker panel. To activate, break the copper safety wire, lift the red guard and place the switch up to ON. This will bypass the bus control relays and supply power directly from the main bus. If December 14, 2011 Copyright 2011 by L29 Support, Inc
11 the bus is powered the OFF light in the bus selector switch will extinguish. OVERVOLTAGE RELAY The overvoltage relay protects the electrical system from voltage that exceeds the maximum allowable. If the voltage spikes the overvoltage relay signals the differential relay to open, removing and isolating the generator from the rest of the electrical system. The operation of the overvoltage relay is automatic; however the relay may be manually reset. Cycling the generator switch, OFF to ON, will reset the overvoltage relay which will allow the generator to be reconnected to the electrical system if the generator voltage is within limits. STANDBY POWER (FIGURE 24-8) Standby power may be used to supply power to COMM 1 and the GPS without powering up the normal electrical system. The standby power switch is an illuminated push button momentary switch used to energize the standby power relay. The switch is located on the right console and the normal indication is lights out. To activate, push the switch in and release. The blue ON light will illuminate when standby power is on. Standby power will automatically shut off anytime the main bus is powered so to shut off the standby power turn the BATT switch to ON (then OFF if electrical power is no longer required). FIGURE 24-8 December 14, 2011 Copyright 2011 by L29 Support, Inc
12 VOLTAGE ADJUSTMENT (FIGURE 24-9) A voltage fine adjustment knob is installed on the left aft console in the front cockpit. Turning the knob clockwise increases the voltage and counter-clockwise decreases the voltage. The range of adjustment is from 26.5 & 28.5VDC. This adjustment is intended as a maintenance function and no pilot inputs are required. FIGURE 24-9 December 14, 2011 Copyright 2011 by L29 Support, Inc
13 CIRCUIT BREAKERS, ALPHABETICAL The main circuit breaker panel is located on the aft right console in the front cockpit. The circuit breakers are assigned an alphanumeric number. Row A is the most inboard row and progress outboard to rows B, C & D respectively. The first circuit breaker in each row starts with the number 1 and progress to higher numbers proceeding right. Circuit breakers starting with the letter N are located in the nose section under a clear plastic door on the floor of the nose baggage compartment. System or Item (Abv.) Air Conditioning (A/C) Altimeter, Encoding, Front (ALT1) Altimeter, Encoding, Blind (ALT2) Annunciator (ANN) Annunciator/Switch Navigation (MD41) Argus 7000, Front (ARG1) Argus 7000 Rear (ARG2) Attitude Gyro System (ATT) Audio Control Panel No.1 (ACP1) Avionics Cooling Fan #1 (FAN1) Avionics Cooling Fan #2 (FAN2) Battery Relay (BATT) Beacon (BCN) Bus Sensing (BUSS) Bus Control (BUSC) Canopy Jettison (CJET) Communications No.1 (COM1) Communications No.2 (COM2) Defrost Blower (DEF) Directional Gyro System (DG) Engine Instruments, Front (ENG1) Engine Instruments, Rear (ENG2) Extraction Blower (EXT) Fire Extinguisher (FIRE & ENG1) Flap Actuator (FLAP) Flood Lights Front Cockpit (FLGT) Flood Lights Rear Cockpit (FDL2) Fuel Pump, Electric (FPMP) Fuel Quantity (ENG1) C/B Number B1 C7 C8 A4 C6 C10 C11 B6 C3 C12 C13 N1 D9 A5 A6 A2 N3 & C1 C2 D1 B7 B14 B15 D2 N2 & B14 B4 A7 B8 B13 B14 December 14, 2011 Copyright 2011 by L29 Support, Inc
14 System or Item (Abv.) C/B Number Generator Signal Flasher (GENF) A3 GPS Navigation (GPS) N4 & C5 Horizontal Stabilizer Trim (STAB) A1 Ignition System (ING) B11 Ignition System (ING) B12 Instrument Lights (INST) D11 KNS80 (KNS8) C4 Landing Gear Actuator (LAND) B3 Landing Light Power (LLGT) A9 Landing Light Control (LCTR) D5 LDGR & FLAP Indicators (IND) B5 Navigation Lights (NAV) D7 Pitot Heat, Left (PHTL) B2 Pitot Heat, Right (PHTR) D4 Priority Switch (ENG2) B15 Radio Lights (RAD) D10 Recirculation Blower (REC) D3 Standby Power N4 & A6 Smoke System, Control (SCTR) D13 Smoke System, Power (SPWR) D12 Start Box (ENG1) B14 Strobe Lights (STRB) D8 Taxi Light (TAXI) D6 Temperature, OAT/Cabin (TEMP) D14 Transponder (XPDR) C9 Turn & Bank Front (T&B1) A8 Turn & Bank, Rear (T&B2) B9 VOR/LOC/GS/DME Navigation (KNS80) C4 December 14, 2011 Copyright 2011 by L29 Support, Inc
15 CIRCUIT BREAKERS BY BUS The main circuit breaker panel is located on the aft right console in the front cockpit. The circuit breakers are assigned an alphanumeric number. Row A is the most inboard row and progress outboard to rows B, C & D respectively. The first circuit breaker in each row starts with the number 1 and progress to higher numbers proceeding right. If the amperage is depicted as one value, it is the circuit breaker rating. If the amperage is depicted as two values, the first value is the actual load and the second is the circuit breaker rating. Values with an (*) are considered an intermittent load. If more than one item is powered thru a circuit breaker the addition items are listed under the main item. HOT BATTERY BUS (NOSE SECTION) C/B System or Item (Abv.) Amp N1. Battery Relay (BATT).4/2 N2. Fire Extinguisher (FIRE) 5* N3. Comm. No.1 (COM1) 1(Rec)/5*(Xmit)/10 N4. GPS Navigation (GPS).5*/2 Standby Power MAIN BUS C/B System or Item (Abv.) Amp A1. Horizontal Stabilizer Trim (STAB) 10* A2. Canopy Jettison (CJET) 5* A3. Generator Signal Flasher (GENF) 5* A4. Annunciator (ANN) 5* A5. Bus Sensing (BUSS).2/2 A6. Bus Control (BUSC) 1.4/5 Standby Power A7. Flood Lights Front Cockpit (FLGT) 1.2/5 A8. Turn & Bank Front (T&B1).4/2 A9. Landing Light Power (LLGT) 21.4/30 December 14, 2011 Copyright 2011 by L29 Support, Inc
16 SECONDARY BUS C/B System or Item (Abv.) Amp B1. Air Conditioning (A/C) 5* B2. Pitot Heat, Left (PHTL) 6.4/10 B3. Landing Gear Actuator (LAND) 5* B4. Flap Actuator (FLAP) 5* B5. LDGR & FLAP Indicators (IND) 5 B6. Attitude Gyro System (ATT) 7.7/20 B7. Directional Gyro System (DG) 7.7/20 B8. Flood Lights Rear Cockpit (FDL2) 1.2/5 B9. Turn & Bank, Rear (T&B2).4/2 B10 OPEN ENGINE BUS C/B System or Item (Abv.) Amp B11. Ignition System (ING) 2.4*/5 B12. Ignition System (ING) 2.4*/5 B13. Fuel Pump, Electric (FPMP) 6.8/10 B14. Engine Instruments Front (ENG1) 5 Start Box Fire Extinguishing Fuel Quantity B15. Engine Instruments Rear (ENG2) 5 Priority Switch AVIONICS C/B System or Item (Abv.) Amp C1. Comm. No.1 (COM1) 1(Rec)/5*(Xmit)/10 C2. Comm. No.2 (COM2) 1(Rec)/5*(Xmit)/10 C3. Audio Control Panel (ACP1) 1.1/5 C4. VOR/LOC/GS/DME Navigation (KNS8) 1.3/ 5 C5. GPS Navigation (GPS).5/2 C6. Annunciator/Switch Navigation (MD41).4/2 VOR Indicator, GI-106A C7. Altimeter, Encoding, Front (ALT1) 1/2 C8. Altimeter, Encoding, Blind (ALT2).5/1 C9. Transponder (XPDR).5/3 C10. Argus 7000CE, Front (ARG1).5/3 C11. Argus 7000CE, Rear (ARG2).5/3 C12. Avionics Fan (FAN1).5/2 C13 Avionics Fan (FAN2).5/2 C14 OPEN C15 OPEN December 14, 2011 Copyright 2011 by L29 Support, Inc
17 SERVICE BUS C/B System or Item (Abv.) Amp D1. Defrost Blower (DEF) 1.0/3 D2. Extraction Blower (EXT) 1.0/3 D3. Recirculation Blwr (REC) 3.4(Low)/6.5(High)/10 D4. Pitot Heat, Right (PHTR) 6.4/10 D5. Landing Light Control (LCTR) 1.7*/5 D6. Taxi Light (TAXI) 8.9/15 D7. Navigation Lights (NAV) 2.9/5 D8. Strobe Lights (STRB) 3.5/5 D9. Beacon (BCN) 1.7/3 D10. Radio Lights (RAD) 5 D11. Instrument Lights (INST) 10 D12. Smoke System Electric Pump (SPMP) 3.5*/10 D13. Smoke System Control (SCTR).8*/2 D14. Temperature (TEMP).1/1 D15 OPEN December 14, 2011 Copyright 2011 by L29 Support, Inc
18 Intentionally left blank December 14, 2011 Copyright 2011 by L29 Support, Inc
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