Boeing B747-400 ATA 49 Auxiliary Power Unit PDF

Boeing B747-400 Differences_to_ Revision: 1FEB2011 ATA 49 Author: RE For Training Purposes Only
LTT 2007 Auxiliary Power Unit EASA Part-66 B1 -B744_49_B1 Training Manual...

Boeing B747-400 Differences_to_ Revision: 1FEB2011 ATA 49 Author: RE For Training Purposes Only
LTT 2007 Auxiliary Power Unit EASA Part-66 B1 -B744_49_B1 Training Manual For training purposes and internal use only.
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Lufthansa Technical Training Dept HAM US Lufthansa Base Hamburg Weg beim Jäger 193 22335 Hamburg Germany Tel: +49 (0)40 5070 2520 Fax: +49 (0)40 5070 4746 E-Mail: [email protected] www.Lufthansa-Technical-Training.com Revision Identification:  The date given in the column ”Revision” on the face of  Dates and author’s ID, which may be given at the base  The LTT production process ensures that the Training this cover is binding for the complete Training Manual. of the individual pages, are for information about the Manual contains a complete set of all necessary pages latest revision of that page(s) only. in the latest finalized revision. Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 ATA 49 AIRBORNE AUXILIARY POWER PRATT & WHITNEY CANADA PWC 901A FOR TRAINING PURPOSES ONLY! FRA US/T3 ReF May 20, 2009 01/ATA_DOC Page 1 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 49−00 GENERAL INTRODUCTION Engine Dimensions (Approx.)  Exhaust Gas Temperature  Length 76.90 IN − Maximum Rated 641C  Width 43.33 IN − Maximum (Auto Shutdown) 700C  height 51.54 IN  Oil Temperature  Weight (Wet−Without Generators Installed) 889.5 LBS − Normal Operating Temp 180F (82C)  Weight (Dry−Without Generators Installed) 846.5 LBS − Maximum (A/S) Temp 275F (135C) Engine Ratings (Approx.)  Fuel Flow − 896 LB/HR  Engine Rated Speed (100%) − N1 24,625 RPM − N2 31,200 RPM  Generator Output Speed − 8,000 RPM  Maximum Shaft Horsepower − 286 SHP  Airflow − ( No Load and 60F(16C)) 254 LB/MIN − ( Max Load and 60 F(16C)) 444 LB/MIN FOR TRAINING PURPOSES ONLY!  Bleed Pressure − ( No Load and 60F(16C)) 25 PSIA − ( Max Load and 60F(16C)) 42 PSIA  Bleed Air Temperature − 380−450F (195−232C) FRA US/T3 ReF Mar 9, 2011 02|PW 901A|L1 Page 2 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 APU COMPT 317AL, 318AR FOR TRAINING PURPOSES ONLY! AUXILIARY POWER UNIT 317AR, 318AL APU COMPARTMENT Figure 1 Auxiliary Power Unit FRA US/T3 ReF Mar 9, 2011 02|PW 901A|L1 Page 3 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 AUXILIARY POWER UNIT DESCRIPTION GENERAL APU DRAIN The auxiliary power unit (APU) is a self−contained unit that provides electrical The APU drains and vents provide for removal of fuel, oil, and water from the and pneumatic power during airplane ground operations. The APU consists of APU and venting areas of undesirable pressure accumulation. Most liquids are a twin spool turbine engine, two AC electrical generators driven by the load discharged overboard through a drain mast and other discharge fittings located gearbox, and controls for safe, automatic, and continuous operation. The AC on the lower side of the fuselage. The air intake plenum and the oil filler generators supply electrical power to airplane electrical systems. In addition, scupper drain directly into the APU compartment. the APU provides bleed air to airplane pneumatic systems. The pneumatic system provides compressed air for airplane air conditioning, main engine APU ENGINE FUEL SYSTEM starting, and operation of the air−driven hydraulic pumps. The APU fuel system supplies fuel from the aircraft fuel system to the APU. The APU is located in the tail section. Access is gained to the APU by opening The APU fuel system consists of a fuel supply line extending from No. 2 (and two cowl−type doors directly below the APU. The APU is attached to a vertical no.3) main fuel tank to the APU, drain lines connected to the supply firewall, forward of the APU, and to the airplane upper structure. Vibration line shroud, a DC fuel boost pump, a fuel shutoff valve, and pressure isolator−type mounts are used between the support structure and the APU. switches to control and monitor system operation. At the APU, fuel flow is controlled by the APU controller in conjunction with the fuel metering unit The APU engine consists of two counter−rotating turbines, each driving (FMU) to provide metered fuel to the combustion chamber. a compressor/rotor assembly. Each compressor/rotor assembly consists of a shaft bolted to a single stage centrifugal impeller. The load compressor (N1) APU IGNITION AND STARTING is driven by the power turbine while the gas generator compressor (N2) is The APU ignition and starting system cranks the APU engine and ignites the driven by the high pressure turbine. The load compressor shaft transmits air−fuel mixture in the engine combustor when start is initiated. Automatic torque to the load gearbox, which then provides drive for the two electrical controls de−energize the starter motor and ignition circuits during the APU generators and a cooling air fan. An accessory gearbox is mounted beneath starting cycle. the air inlet case which provides drives for various APU accessories. The APU battery provides the 28 volts DC necessary for turning the APU AIR INLET APU starter and supplies the APU controller with power prior to engine The APU air inlet provides air to the compressor through a door located on the start. The APU battery is located in the E33 equipment rack. right side of the airplane tail cone, and an inlet duct leading to the APU air inlet APU COOLING AIR SYSTEM plenum. The door is partially open for inflight operation and fully open for The APU air systems provide cooling air for APU accessory cooling and bleed FOR TRAINING PURPOSES ONLY! on−ground operation. The door is fully closed when the APU is not operating. air for the airplane pneumatic system. A fan driven by the load gearbox supplies cooling air to the AC electrical generators, to an air cooled oil cooler and to the APU compartment for compartment cooling. Exhaust air from the accessory cooling system is then vented into the APU compartment. FRA US/T3 ReF Feb 20, 2011 04|49−00 BASIC|L2 Page 4 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 ÄÄ ÈÈ ÁÁ ÄÄÄÄ ÉÉÉÉ APU AIR INLET APU AIR INLET DOOR LEGEND : POSITION SWITCH 13_ P 1.0 INLET APU AIR INLET PRESS. SENSOR ÇÇ ÁÁ Ä ÄÄÄÄÄÄÉÉÉÉÄÄÄÄÄ Ä DOOR ACTUATOR FUEL P 3 − AIR PRESSURE T 1.0 INLET TEMP. SENSOR FLOW ÉÉ ÈÈÈ ÈÈÈÈÈÈÈ ÈÈÈÈÈÈ ÁÁ ÈÈÈÈÈÈ Ä ÄÄÄ ÉÉÉÉ Ä DIVIDER AND SERVO FUEL EGT TRIM UNIT DUMP VALVE R OIL P3 AIR PRI / SEC. È ÈÈÈ ÈÈÈÈÈÈÈ ÈÈÈÈÈÈ ÈÈ ÄÄÄ Ä Ä FILTER S/N IDENT UNIT FUEL NOZZLES E ( 14 ) È Ä T 6.0 EXHAUST OIL FILLER GAS TEMP. CAP COUPLE ( 6 ) F COOLING È ÇÇ Ä FAN I.G.V. E R È Ä È Ä È Ä N1−SPEED SENSOR Ç ÇÇÇÇ ÇÇÇ Ç È Ä GENERATOR NO.1 OIL T TANK ÇÉÉÉÉÉ ÇÇÇ Ç Ç ÈÇÇÇÇ ÇÇ Ä TO COMP. O T 1.2 SENSOR Ç ÇÉÉÉÉÉ Ç ÈÈÈ È ÈÇÇÇÇ É Ä GENERATOR NO.2 DIVERTER Ç ÉÉÉÉÉ ÇÇÇÇ É ÉÉÉÉÉ Ä VALVE RATE TO CONTROL SENSOR COMP. IGNITER RESET OIL LEVEL PLUG T 1.3 SENSOR DIVERTER ÉÉÉÉÉ Ä SENSOR VALVE D FLOW TO Ç Ç È É È ÉÉÉÉÉ ÇÇÇ Ä SENSOR OTHER MUFFLER IGNITER I PLUG Ç Ç ÇÇÇÇÇÈ ÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈ É ÈÈÈ È ÇÇÇ Ä M N IGNITION Ç Ç ÇÇÇÇÇ ÉÉ É É É ÉÉÉÉÉÉÇÇÇÇÇÇ Ä APU EXCITER BLEED AIR INLET GUIDE VANE ISOLATION CONTROL AND TO BEARINGS VALVE Ç ÇÇÇ Ç ÇÇÇÇÇ ÇÇ Ç É ÉÉÉÉ ÉÉÉÉ ÉÉÉÉÉÉ ÇÇÇÇÇÇ Ä ACTUATOR TO ÇÇÇÇ Ç Ç ÇÇ É É ÉÉÉÉÉÉÇÇÇÇÇÇ ÄÄÄÄÄÄÄ COMPARTMENT TRANSFER FUEL PUMP FUEL COOLING BLOCK A STARTER AND METERING Ç ÇÇ É ÉÉ É É ÉÉÉÉ ÉÉÉÉÉÉÇÇÇÇÇÇ FILTER ASSEMBLY UNIT 3 MAIN OIL Ç ÇÇ ÉÉ É Ä ÄÄÄÄÄÄ É ÄÄÄ ÉÉÉÉÉÉ ÄÇ Ä ÄÄÄ Ä ÇÇÇÇÇÇ Ä TEMPERATURE SENSOR AIR COOLED FOR TRAINING PURPOSES ONLY! Ç ÇÇ ÉÉ ÉÉÉ Ä ÇÇÇÇÇ É Ç ÄÄ ÄÄÄÄ Ä OIL COOLER LOW OIL ( ACOC ) PRESSURE SWITCH P Ç ÇÇ Ç ÇÇ ÉÉ ÄÄ Ä ÄÄ ÇÇÇÇÇ Ç Ä Ä OIL PUMPS ÉÉ ÄÄ ÇÇÇÇÇ ÉÉ É Ç Ä ÄÄÄÄ Ä ÄÄÄÄ ( PRESS 1 SCAVENGE 3 ) VENT AIR APU FUEL A TO TO SOV Ç ÇÇ ÉÉ ÄÄÉÉÉ ÇÇÇ ÉÉ É Ç Ä Ë COMPARTMENT EXHAUST G FUEL COOLED FROM Ç ÇÇ ÉÉ ÉÉÉÉÉÉÉÉ ÉÉÉ ÇÇÇ Ç Ä N 2 − SPEED AIRCRAFT OIL COOLER SENSOR APU SHROUD ( FCOC ) OIL M FUEL PRESS. DRAIN VALVE SYSTEM E REGUL. Ç ÇÇ Ç ÇÇ ÄÄ ÇÇÇ ÄÄÄÄÄÄÄÄÄÄÄÄÄÄ Ç Ä OIL FILTER WITH ÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ Ç Ä POP OUT IND APU Ç ÇÇ ÇÇÇÇ ÇÇÇ ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ Ç DRAIN MAST Figure 2 APU Basic Schematic FRA US/T3 ReF Feb 20, 2011 04|49−00 BASIC|L2 Page 5 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 APU BLEED AIR SYSTEM APU EXHAUST SYSTEM The diverter valve and the IGV control system are designed to limit bleed air to The exhaust system provides for sound attenuation and conducting of exhaust the pneumatic system in favor of electrical power when the unit has been gases and acts as a thermal barrier to shield the APU compartment from loaded to capacity. Bleed air not required by the airplane pneumatic system or exhaust gases. The exhaust duct directs the exhaust gases aft and upward the APU for operation is bypassed through the diverter bleed valve into the from the airplane. The exhaust system consists of a bellows and nozzle, outer exhaust duct downstream of the turbine section. APU bleed air for airplane and inner duct, acoustical liner, and seal assembly. The exhaust duct is cooled pneumatic systems incorporates an overheat detection system which can by secondary air flowing between the outer and inner duct and exiting into the provide an APU automatic shutdown to prevent structural damage resulting exhaust stream at the nozzle. from APU duct failure. APU EXHAUST GAS TEMPERATURE AND VELOCITY APU ENGINE CONTROLS High temperature will be found up to 40 feet from the exhaust nozzle of the Primary control of the APU is accomplished by the APU controller (APUC). The APU depending on wind conditions. Starts must not be attempted within range APUC is a full authority digital electronic control (FADEC) which provides for of flammable materials or fumes. A minimum of 40 feet must be clear to the unattended operation of the APU. The APUC is located in the E8 aft equipment rear of the aircraft to avoid injury to persons or damage to equipment during center. the APU operation. Other APU controls consist of switches, relays, and electronic equipment to APU LUBRICATION SYSTEM control the starting, stopping, and normal operation of the APU. The APU control components are located on the APU, the P83 equipment panel in the The lubrication system is designed to supply clean lubricating oil to E8 aft equipment center, the accessory panel for the APU battery, the P5 the bearings, gears and generator drive splines. The oil flow rate is 64 lb/min at panel, and APU remote panel (the right side of the main gear wheel well). The a constant pressure of 80 psig. The oil flow lubricates and cools the bearings APU can only be started from the P5 overhead panel. Shutdown can be and carries foreign matter to the oil filter where it is retained. The oil tank is accomplished from either the P5 overhead panel or the APU control panel. integral with the load gearbox and is of the ’hot tank’ type, which does not allow scavenge oil to cool before returning to the tank. APU ENGINE INDICATIONS APU ELECTRICAL SYSTEM APU engine operation is indicated on the status page or maintenance page of the lower EICAS display. Two APU driven 90 KVA generators are mounted on the front of the load gearbox. The generators are cooled via inlet air diverted from the Exhaust gas temperature (EGT), low pressure turbine speed (N1), high APU plenum to the generators which are enclosed for cooling air containment. pressure turbine speed (N2), and oil quantity (OIL QTY) are the only engine parameters shown on the EICAS display while the APU is operating. FOR TRAINING PURPOSES ONLY! The EICAS maintenance page can be selected via the CMCS to display either realtime or snapshot indications of the same parameters mentioned above plus the following: battery voltage (DC−V), battery charge rate (DC−A), APU serial number, total operating hours on APU, and number of starts on APU. FRA US/T3 ReF Feb 20, 2011 04|49−00 BASIC|L2 Page 6 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 GENERAL 49−00 ÄÄ ÈÈ ÁÁ ÄÄÄÄ ÉÉÉÉ APU AIR INLET APU AIR INLET DOOR LEGEND : POSITION SWITCH 13_ P 1.0 INLET APU AIR INLET PRESS. SENSOR ÇÇ ÁÁ Ä ÄÄÄÄÄÄÉÉÉÉÄÄÄÄÄ Ä DOOR ACTUATOR FUEL P 3 − AIR PRESSURE T 1.0 INLET TEMP. SENSOR FLOW ÉÉ ÈÈÈ ÈÈÈÈÈÈÈ ÈÈÈÈÈÈ ÁÁ ÈÈÈÈÈÈ Ä ÄÄÄ ÉÉÉÉ Ä DIVIDER AND SERVO FUEL EGT TRIM UNIT DUMP VALVE R OIL P3 AIR PRI / SEC. È ÈÈÈ ÈÈÈÈÈÈÈ ÈÈÈÈÈÈ ÈÈ ÄÄÄ Ä Ä FILTER S/N IDENT UNIT FUEL NOZZLES E ( 14 ) È Ä T 6.0 EXHAUST OIL FILLER GAS TEMP. CAP COUPLE ( 6 ) F COOLING È ÇÇ Ä FAN I.G.V. E R È Ä È Ä È Ä N1−SPEED SENSOR Ç ÇÇÇÇ ÇÇÇ Ç È Ä GENERATOR NO.1 OIL T TANK ÇÉÉÉÉÉ ÇÇÇ Ç Ç ÈÇÇÇÇ ÇÇ Ä TO COMP. O T 1.2 SENSOR Ç ÇÉÉÉÉÉ Ç ÈÈÈ È ÈÇÇÇÇ É Ä GENERATOR NO.2 DIVERTER Ç ÉÉÉÉÉ ÇÇÇÇ É ÉÉÉÉÉ Ä VALVE RATE TO CONTROL SENSOR COMP. IGNITER RESET OIL LEVEL PLUG T 1.3 SENSOR DIVERTER ÉÉÉÉÉ Ä SENSOR VALVE D FLOW TO Ç Ç È É È ÉÉÉÉÉ ÇÇÇ Ä SENSOR OTHER MUFFLER IGNITER I PLUG Ç Ç ÇÇÇÇÇÈ ÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈÈ É ÈÈÈ È ÇÇÇ Ä M N IGNITION Ç Ç ÇÇÇÇÇ ÉÉ É É É ÉÉÉÉÉÉÇÇÇÇÇÇ Ä APU EXCITER BLEED AIR INLET GUIDE VANE ISOLATION CONTROL AND TO BEARINGS VALVE Ç ÇÇÇ Ç ÇÇÇÇÇ ÇÇ Ç É ÉÉÉÉ ÉÉÉÉ ÉÉÉÉÉÉ ÇÇÇÇÇÇ Ä ACTUATOR TO ÇÇÇÇ Ç Ç ÇÇ É É ÉÉÉÉÉÉÇÇÇÇÇÇ ÄÄÄÄÄÄÄ COMPARTMENT TRANSFER FUEL PUMP FUEL COOLING BLOCK A STARTER AND METERING Ç ÇÇ É ÉÉ É É ÉÉÉÉ ÉÉÉÉÉÉÇÇÇÇÇÇ FILTER ASSEMBLY UNIT 3 MAIN OIL Ç ÇÇ ÉÉ É Ä ÄÄÄÄÄÄ É ÄÄÄ ÉÉÉÉÉÉ ÄÇ Ä ÄÄÄ Ä ÇÇÇÇÇÇ Ä TEMPERATURE SENSOR AIR COOLED FOR TRAINING PURPOSES ONLY! Ç ÇÇ ÉÉ ÉÉÉ Ä ÇÇÇÇÇ É Ç ÄÄ ÄÄÄÄ Ä OIL COOLER LOW OIL ( ACOC ) PRESSURE SWITCH P Ç ÇÇ Ç ÇÇ ÉÉ ÄÄ Ä ÄÄ ÇÇÇÇÇ Ç Ä Ä OIL PUMPS ÉÉ ÄÄ ÇÇÇÇÇ ÉÉ É Ç Ä ÄÄÄÄ Ä ÄÄÄÄ ( PRESS 1 SCAVENGE 3 ) VENT AIR APU FUEL A TO TO SOV Ç ÇÇ ÉÉ ÄÄÉÉÉ ÇÇÇ ÉÉ É Ç Ä Ë COMPARTMENT EXHAUST G FUEL COOLED FROM Ç ÇÇ ÉÉ ÉÉÉÉÉÉÉÉ ÉÉÉ ÇÇÇ Ç Ä N 2 − SPEED AIRCRAFT OIL COOLER SENSOR APU SHROUD ( FCOC ) OIL M FUEL PRESS. DRAIN VALVE SYSTEM E REGUL. Ç ÇÇ Ç ÇÇ ÄÄ ÇÇÇ ÄÄÄÄÄÄÄÄÄÄÄÄÄÄ Ç Ä OIL FILTER WITH ÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ Ç Ä POP OUT IND APU Ç ÇÇ ÇÇÇÇ ÇÇÇ ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ Ç DRAIN MAST Figure 3 APU Basic Schematic FRA US/T3 ReF Feb 20, 2011 04|49−00 BASIC|L2 Page 7 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 CONTROL SYSTEM - APU 49−61 APU CONTROL DESCRIPTION APU CONTROLLER REMOVAL AND INSTALLATION (b) P83 Panel, E8 Aft Equipment Center This procedure gives the tasks to remove and install the APU controller. 1) APU PRIMARY CONT 2) APU START DLH 001−099 ( D−ABVA AND ON ) The APU controller is in the aft equipment center, E8. The aft CAUTION: YOU MUST CAREFULLY DO THE STEPS IN THE TASK equipment center is behind the sidewall panel, outboard of the lower mattress, BELOW TO REMOVE THE APU CONTROLLER. A FAILURE in the crew rest area, and above door five. You can get access to the TO DO THE STEPS CORRECTLY CAN CAUSE DAMAGE TO APU controller through the sidewall panel. THE EQUIPMENT. DLH 101−199 ( D−ABTA AND ON ) (7) Do this task to remove the APU controller from the aft equipment center, E8: ”ESDS Shelf−Mounted Component Removal” (Ref 20−41−02/201). The APU controller is in the aft equipment center, E8. The aft equipment center is above the aft left side of the coat closet in the APU CONTROLLER INSTALLATION airplane cabin. You can get access to the APU controller through the ceiling panel above the coat closet. Procedure (1) Make sure you set the switches on the back of the APU controller set to APU CONTROLLER REMOVAL these positions: Procedure (a) MIN ECS switch − E (b) MAX ECS switch − E (1) Make sure the APU control switch on the P5 panel is OFF and attach a (c) DUCT PRESS − A DO−NOT−OPERATE tag. (d) MES switch − D (2) Move the enable switch for the CMC ground test on the P461 panel to ENABLE. CAUTION: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL THE APU CONTROLLER. A FAILURE (3) Show the APU maintenance page on the EICAS (Ref 45−10−00/201). TO DO THE STEPS CORRECTLY CAN CAUSE DAMAGE TO (a) Look at the APU maintenance page and write down the data THE EQUIPMENT. that follows: 1) The total number of hours that the APU operated. (2) Do this task to install the APU controller in the aft equipment center, E8: 2) The total number of APU starts. ”ESDS Shelf−Mounted Component Installation” (Ref 20−41−02/201). 3) The APU serial number. (3) Remove the DO−NOT−CLOSE tags and close these circuit breakers: FOR TRAINING PURPOSES ONLY! (4) Move the enable switch for the CMC ground test on the P461 panel to (a) P83 Panel, E8 Aft Equipment Center NORMAL. 1) APU PRIMARY CONT 2) APU START (5) Move the remote enable switch for the ground test in the Main Electronic Equipment bay to NORMAL. (b) P6 Main Power Distribution Panel 1) 6K18 APU ALTN CONT (6) Open these circuit breakers and attach DO−NOT−CLOSE tags: (a) P6 Main Power Distribution Panel (4) Do this task: ”APU Ground Test” (Ref 49−11−00/501). 1) 6K18 APU ALTN CONT (5) Remove the DO−NOT−OPERATE tag from the APU control switch on the P5 panel. FRA US/T3 ReF Feb 20, 2011 04|APUC CHANGE|L2 Page 8 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 CONTROL SYSTEM - APU 49−61 B C D SERIAL NO. 112 A E OPER HOURS 3126 S1 APU STARTS 1254 B C D A E S2 PART OF THE B C D APU MAINTENANCE PAGE A E ELECTRONIC EQUIPMENT RACK, E8 (AFT EQUIPMENT CENTER) S3 APU B C D CONTROLLER A E S4 BACK FACE OF THE APU CONTROLLER PLACKARD FOR TRAINING PURPOSES ONLY! RECORD APU HOURS AND CYCLES BEFORE DOOR REMOVING UNIT 5L VOR HERAUSZIEHEN ( REF ) DES GERäTES APU APU STUNDEN/CYCLES CONTROLLER ABLESEN. ( APUC ) INSTRUCTION NOTE : EO 0118644 ELECTRONIC EQUIPMENT RACK, E8 FROM 18.12.1991 (AFT EQUIPMENT CENTER) Figure 4 APU Controller Removal and Installation FRA US/T3 ReF Feb 20, 2011 04|APUC CHANGE|L2 Page 9 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 CONTROL SYSTEM - APU 49−61 CIRCUIT BREAKER 16 17 18 R 359 PANEL 5 5 5 L AIR / GND − RELAY R 686 P6 − 2 APU DUCT OVERHEAT LATCH ENG ENG PARK R 7176 RELAY 3 4 BRAKE APU INLET DOOR RELAY R 8310 R 7188 APU GENERATOR APU START RELAY AVAILAIBLE RELAY 2 1 /2 2 1 /2 7 1 /2 K P 83 1 2 APU ALTN ENG 4 CONT CB : APU START R 7852 CB : APU PRIMARY CONTROL R 8077 CB : PACK 1 CLOSED RELAY APU INLET DOOR R 8078 PACK 3 CLOSED RELAY R 8079 APU BLEED VALVE CLOSED CB : RELAY APU DUCT OVERHEAT CB : R 7715 FOR TRAINING PURPOSES ONLY! OUTFLOW VALVE LH APU 95% N1 RELAY CB : APU DUCT OVERHEAT OUTFLOW VALVE RH RESET SWITCH R 460 APU DUCT OVERHEAT DOOR CLOSED RELAY INDICATOR LIGHT R 461 DOOR OPEN RELEAY PANEL P − 83 Figure 5 CIRCUIT BREAKER PANEL P83 AND P 6−2 FRA US/T3 ReF May 20, 2009 05|APUC|L2 Page 10 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 CONTROL SYSTEM - APU 49−61 APU STATIC INVERTER APU BATTERY CHARGER E8 RACK AFT EQUIPMENT CENTER FOR TRAINING PURPOSES ONLY! APU E33 RACK BATTERY Figure 6 APU Battery, Static Inverter and Battery Charger FRA US/T3 ReF May 20, 2009 05|APUC|L2 Page 11 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 SYSTEM - APU EICAS INDICATING 49−71 EICAS APU MAINTENANCE PAGE SYSTEM DESCRIPTION General The APU maintenance page on EICAS shows the APU data. The APU data comes from the APU controller (APUC). When the APU is off and the GROUND TEST switch is in the NORM position, no data will show on the APU maintenance page. When the APU is off and the GROUND TEST switch is in the ENABLE position, the APU maintenance page will show some data. When you operate the APU, the maintenance page shows all of the APU data. If the APU has a problem, the EFIS/EICAS interface unit (EIU) will get a snapshot of the APU data at the time of the problem. FOR TRAINING PURPOSES ONLY! FRA US/T3 ReF Feb 20, 2011 02| 95% RPM + 2 sec. T.D. FRA US/T3 ReF Feb 20, 2011 03INDICATION|L3 Page 14 Lufthansa Technical Training AIRBORNE AUXILIARY POWER B747−400 SYSTEM - APU EICAS INDICATING 49−71 OP MODE: shows the ECS ope