BOOK TWO, BLOCK TWO: POWERPLANTS

Question 1

P3C: HAZARDS AROUND ENGINE AREA

Answer 1

PROP ARCS, PROPELLER JET BLAST, ANTI-COLLISION LIGHTS INDICATE RUNNING ENGINES

Question 2

P8A: HAZARDS AND AREAS AROUND THE ENGINE

Answer 2

INLET SUCTION AREAS, ENGINE EXHAUST AREAS

Question 3

P3C:ENGINES

Answer 3

EQUIPED WITH FOUR T56-A-14 TURBOPROP POWERPLANT ASSEMBLIES.

Question 4

P3C:ENGINES;ENGINE POWER LEVER SYSTEM

Answer 4

ENGINES AND PROPELLERS ARE CONTROLED BY MANUAL ACTUATION OF THE ENGINE POWER LEVERS. THE ENGINE POWER LEVER SYSTEM CONSISTS OF FOUR INDEPENDENT SUBSYSTEMS, ONE FOR EACH ENGINE. THE BASIC ELEMENT OF EACH SUBSYSTEM IS A PAIR OF ENGINE POWER LEVERS, ONE EACH FOR THE PILOT AND CO-PILOT. THE FOUR LEVERS ARE INSTALLED AS A GROUP ON THE TOP OF THE CENTER CONSOLE AT THE LEFT END OF THE FLIGHT STATION AND THE COPILOT LEVERS ARE GROUPED SIMILARLY AT THE RIGHT END. CORRESPONDING PILOT AND CO-PILOT LEVERS ARE COUPLED BY THE TORQUE TUBE SO THAT MOVEMENT OF EITHER LEVER RESULTS IN IDENTICAL MOVEMENT OF ITS COUNTERPART. THE LEVER FOR ANY ENGINE CAN BE MOVED WITHOUT MOVING THOSE FOR OTHER ENGINES.

Question 5

P8A: EGINES

Answer 5

POWERED BY TWO CFM56-7B ENGINES. THE ENGINE IS A DUAL-ROTOR, AXIAL-FLOW TURBO FAN THE N1 ROTOR CONSISTS OF A FAN, A LOW-PRESSURE TURBINE. THE N2 ROTOR CONSISTS OF A HIGH-PRESSURE TURBINE.

Question 6

P8A: EGINES;ENGINE POWER LEVER SYSTEM

Answer 6

EACH ENGINE HAD INDIVIDUAL FLIGHT DECK CONTROLS .THRUST IS SET BY POSITIONING THE THRUST LEVERS. THE THRUST LEVERS ARE POSITIONED AUTOMATICALLY BY THE AUTOTHROTTLE SYSTEM OR MANUALLY BY THE FLIGHT CREW. THE FORWARD THRUST LEVERS CONTROL FORWARD THRUST FROM IDLE TO MAXIMUM. THE REVERSE THRUST LEVERS CONTROL FORWARD THRUST FROM IDLE TO MAXIMUM REVERSE.

Question 7

PROPELLERS:PC3

Answer 7

A VARIABLE PITCH, CONSTANT SPEED, HYDROMATIC PROPELLER ASSEMBLY IS MOUNTED ON EACH POWERPLANT ASSEMBLY.

Question 8

PROPELLERS:PC3

Answer 8

FOUR BLADES, BLADE PITCH CHANGING MECHANISM IN CONJUCTION WITH THE FUEL CONTROL ASSEMBLIES MAINTAINS A CONSTANT RPM OF THE ENGINE. FOR GROUND IDLE AND REVERSE THE PROPELLER BLADE CAN BE POSITIONED TO PROVIDE ZERO OR NEGATIVE THRUST. THE PROPELLER CAN ALSO “FEATHER”, MEANING THE BLADES ARE LAID FLAT WITH THE AIRSTREAM TO MINIMIZE DRAG IN THE EVENT THE ENGINE IS SHUTDOWN INFLIGHT.

Question 9

FUEL TANKS:P3C

Answer 9

THE WING FUEL TANKS ARE NUMBERED FROM LEFT TO RIGHT (FACING FORWARD) AND IDENTIFIED AS NO.1, NO.2, NO.3, AND NO.4 FUEL TANKS. THE AUXILLARY FUEL TANK IS IDENTIFIED AS NUMBER 5. EACH TANK CAN SUPPLY FUEL TO ITS RESPECTIVE ENGINE OR FUEL CAN BE SUPPLIED FROM ANY WING TANK TO ANY ENGINE THROUGH A CROSS FEED SYSTEM. WHEN THE APU IS RUNNIG FUEL IS NORMALLY SUPPLIED FROMM MAIN TANK NO.2.

Question 10

FUEL TANKS;P8A

Answer 10

FUEL TANKS ARE DIVIDED INTO FIVE FUEL TANK GROUPS (MAIN1, MAIN2, CENTER, FORWARD TANK GROUP, AND AFT TANK GROUP) AND TWO SURGE TANKS. EACH TANK CAN SUPPLY FUEL TO ITS RESPECTIVE ENGINE OR FUEL CAN BE SUPPLIED FROM ANY TANK TO ANY ENGINE THROUGH A CROSS FEED SYSTEM.

Question 11

FUEL SYSTEM:P3C; CONTENTS

Answer 11

FOUR INTEGRAL WING TANKS (1-4), EACH FEEDING FUEL TO THEIR RESPECTIVE ENGINE AND AN AUXILIARY FUSELAGE TANK (5). THE AUXILIARY FUSELAGE FUEL TANK CONSISTS OF TWO SEPERATE INTERCONNECTED FUEL TANKS, ONE OF WHCIH IS THE INTEGRAL WING CENTER SECTION FUEL TANK ANF THE OTHER A BLADDER CELL FUEL TANK IN THE FUSELAGE. FUEL IS TRANSFERRED FROM THE AUXILARY FUEL TANK TO THE ENGINE FEED FUEL TANKS PROVIDING ADDITIONAL FUEL FOR ENGINE FEED.

Question 12

FUEL SYSTEM: P3C; FUELING

Answer 12

NORMALLY, AIRCRAFT FUELING IS ACCOMPLISHED BY CENTER POINT PRESSURE FUELING. IF PRESSURE FUELING EQUIPMENT IS NOT AVAILABLE, THE WING FUEL TANKS CAN BE FUEL THROUGH OVERWING FUEL CAPS. THE PRESSURE FUELING SYSTEM IS DESIGNED TO FILL ALL FUEL TANSK AT THE TWO PRESSURE FUELING NOZZLE ADAPTERS. THESE ADAPTERS ARE LCOATED ADJACENT TO EACH OTHER JUST FORWARD OF THE FLAPS IN THE AFT INBOARD SECTION OF THE RIGHT WING.

Question 13

FUEL SYSTEM:P3C; FUEL CAPACITY

Answer 13

THE TOTAL FUEL CAPACITY OF THE P3C IS 9200 GALLONS.

Question 14

FUEL SYSTEM:P8A

Answer 14

FUEL FEED SYSTEM, ENGINE FUEL FEED AND INTEGRATED DRIVE GENERATOR COOLING SYSTEM (IDG), CONSIST OF FUEL TANKS, BOOST PUMPS, FUEL LINES AND FITTINGS, AND SHUTOFF VALVES TO CONVEY AND CONTROL THE FLOW OF FUEL FROM THE TANKS TO THE ENGINES AND THE APU AT THE PROPER PRESSURE AND FLOW RATES. THE INLETS FOR THESE PUMPS ARE LOCATED SO AS TO MAXIMIZE THE USEABLE IN THE HIGH-SPEED CRUISE REGIME.

Question 15

OBIGGS

Answer 15

ONBOARD INERT GAS GENERATING SYSTEM (OBIGGS) FOR THE P8A PROVIEDS NITROGEN-ENRICHED AIR (NEA) TO THE CENTER, WING AND AUXILIARY FUEL TANKS TO PROTECT AGAINST BALLISTIC THREATS. NEA KEEPS THE TANKS AT OR BELOW A 9% OXYGEN LEVEL THROUGH THE ENTIRE DESIGN FLIGHT PROFILE.

Question 16

FUEL SYSTEM:P8A; AERIAL REFUELING

Answer 16

AREIAL REFUELING CAPABLE. A STANDARD MILITARY AIRCRAFT REFUELING RECEIVER KNOW AS THE UNIVERSAL AERIAL REFUELING RECEPTACLE SLIPWAY INSTALLATION (UARRSI) IS INSTALLED IN THEH CROWN OF THE AIRCRAFT. THE RECEPTACLE DOOR AFT EDGE DROPS DOWN TO EXPOSE THE RECEIVER. A BOOM FROM THE TANKER IS THEN INSERTED INTO THE RECEIVER TO TRANSFER FUEL. A DUAL WALL FUEL MAINFOLD LEADS FROM THE UARRSI TO THE CENTER TANK THROUGH THE UPPER LOBE OF THE AIRCRAFT . LIGHTS ON BOTH SIDES OF THE SLIPWAY PROVIDE ILLUMINATION FOR NIGHTTIME REFUELING.

Question 17

FUEL SYSTEM:P8A;CAPACITY

Answer 17

TOTAL CAPACITY IS 10,856

Question 18

BLEED AIR:P3C

Answer 18

THE ENGINE INSTALLATIONS INCLUDE AN ENGINE BLEED AIR SYSTEM THAT PROVIDES HEATED AND PRESSURIZED AIR FROM THE COMPRESSOR FOR BOMB BAY HEATING, ENGINE ANTI-ICE, WING DE-ICE, OIL COOLER AUGMENTATION AND CROSS BLEED ENGINE STARTING. ENGINE ANTI-ICE IN CONJUNCTION WITH WING DE-ICE, EMPANAGE DE-ICE (ELECTRICAL)PROPELLER DE-ICE (ELECTRICAL), WINDSHIELD HEAT (ELECTRICAL), AND WINDSHIELD WIPERS MAKE THE P-3 AND ALL WEATHE RCAPABLE AIRCRAFT.

Question 19

BLEED AIR: P8A

Answer 19

ENGINE BLEED AIR THERMAL ANTI-ICING PREVENTS THE FORMATION OF ICE ON THE ENGINE COWL LIP. ENGINE ANTI-ICE OPERATION IS CONTROLLED BY INDIVIDUAL ENG ANTI-ICE SWITCHES. WING ANTI-ICE SYSTEM MAY BE OPERATED ON THE GROUND OR INFLIGHT. IT PROVIDES FOR THREE INBOARD LEADING EDGE SLATS BY USING BLEED AIR. THE WING ANTI-ICE SYSTEM DOES NOT INCLUDE THE LEADING EDGE FLAPS OR THE OUTBOARD LEADING EDGE SLATS. ENGINE ANTI-ICE IN CONJUNCTION WITH WING ANTI-ICE, EMPENAGE AND WINGTIP DE-ICE (ELECTRICAL), WINDSHIELD HEAT(ELECTRICAL), AND WINDSHIELD WIPERS MAKE THE P8A AN ALL WEATHER CAPABLE AIRCRAFT.

Question 20

AUXILIARY POWER UNIT (APU):P3C

Answer 20

CONSISTS OF COMPRESSOR, GAS TURBINE ENGINE, AND AN ENGINE-DRIVEN ELECTRICAL GENERATOR IS INSTALLED IN THE LOWER FUSELAGE COMPARTMENT JUST AFT OF THE NOSE LANDING GEAR WHEEL WELL. THE APU COMPRESSOR BLEED AIR PROVIDES THE PNEUMATIC POWER REQUIRED FOR ENGINE STARTING AND A SOURCE OF AIR FOR OPERATION OF THE IRCRAFT ENVIROMENTAL CONTROL SYSTEM. AIRCRAFT ELECTRICAL POWER FOR BOTH ON-THE-GROUND AND EMERGENCY INFLIGHT OPERATIONS IS PROVIDED BY THE GENERATOR.

Question 21

APU:P8A

Answer 21

SELF-CONTAINED GAS TURBINE ENGINE INSTALLED WITHIN A FIREPROOF COMPARTMENT LOCATED IN THE TAIL OF THE AIRCRAFT. THE APU SUPPLIES BLEED AIR FOR ENGINE STARTING OR THE AIR CONDITIONING, AND THE APU STARTER GENERATOR PROVIDES AC POWER. THE APU STARTS AND OPERATES INFLIGHT UP TO THE AIRCRAFT MAXIMUM CERTFIED ALTITUDE. THE APU SUPPLIES BLEED AIR FOR BOTH AIR CONDITIONING ON THE GROUND OR IN FLIGHT.