(c)
Removescrew securing bus bar to circuit breaker.
(d)
Removescrew securing wire to circuit breaker.
(e)
Removelocknust securing circuit breaker to support bracket. Remove circuit breaker from bracket.
10. Installation of Screw Connect Type Circuit Breakers
WARNING: ENSURE THAT BATTERY MASTER SWITCH AND THE GENERATOR SWITCHESARE IN THE OFF POSITION WHEN WORKING ON THE CIRCUIT BREAKER PANEL.
(a)
Place circuit breaker into support bracket. Secure with locknut.
(b)
Attach wire to circuit breaker terminal with screw.
(c)
Attach bus bar to circuit breaker terminal with screw.
(d)
Postion support bracket to panel assembly with screws.
(e)
Position cover panel and secure with screws.
EFFECTIVITY:
040-999
Jan 10/9024-60-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoadDistribution(continued)
Circuit Breaker Terminal -Screw Attachment
0 Insulator Plate Electroluminescent Panel Insulator / AC Bus Mounting Hardware
MountingPlate -forAC Circuit Breakers Breaker Locknutand Washer
LeftAuxiliaryCircuitBreakerPanel
CircuitBreakerInstallation Figure402
EFFECTIVITY:
040-999
24-60-00 Jan10/907
24-60-PAGE
PIPER AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DCElectricalLoad Distribution (continued)
CHART 4 BREAKERFUNCTION-LEFT BREAKER PANEL (Sheet 1 of 3)
USED CIRCUIT BREAKER CIRCUIT
ON CODE BREAKER VALUE (AMPS) PROTECTED
FUEL PUMP 10 Left Engine Electric Fuel Pump
INVERTER NO. 2 15 Number 2 dc to ac Power Inverter
FUEL TEMP SENSE 5 Fuel Temperature Monitor
FUEL FLOW 5 Left Engine Fuel Flow Indicating
FUEL PRESS 5 Left Engine Fuel Pressure IndicatingSystem
OIL PRESS 3 Left Engine Oil Pressure Indicating System
OIL TEMP 3 Left Engine Oil Temperature IndicatingSystem
OIL COOLER 5 Left Engine Oil Cooler Door
TORQUE METER 3 Left Engine Torque Indicating System
BLEED AIR CONT 3 Left Engine Bleed Air Valve
PROP DEICE 30 Left Propeller Deicer and Deice Timer
Left Propeller Inboard Heating Element
Left Propeller Outboard Heating Element
AIR INTAKE DEICE 30 Left Engine Air Intake Parting Strip
Left Engine Lip Deicer Shed Area I
Left Engine Lip Deicer Shed Area II
ICE VANE CONT 7.5 Left Engine Ice Deflector Door, Relays, and
Indicator
HTG RESET 5 Left Hydraulic ToppingGeneratorReset
Switchesand Solenoid
IGNITION 5 Left Engine Ignitor
Left engine Ignition Monitor Relay
Left Engine Automatic Ignition Torque Switch
START CONT 5 Left Engine Start Contactor
ITT 5 Left Engine InterturbineTemperatureSystem
EMER PRESS 3 EmergencyCabinPressureValve
SPK AMPLI 3 SpeakerAmplifier
MAP LIGHTS 5 Left and Right Cockpit Map Lights
No Smoking Light
Fasten Seat Belt Light
PublicAddress Chime Amplifier
BETA SOL 3 Leftand Right Engine Lock Pitch Solenoids
PRESS CONT 5 Cabin Door Solenoid Valve Vacuum Relief
Solenoid
EFFECTIVITY:
040-999
Jan10/9024-60-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer) MAINTENANCEMANUAL
A. DC Electrical Load Distribution (continued)
CHART 4 BREAKERFUNCTION-LEFTBREAKERPANEL (Sheet2 of 3)
USED ON CODE CIRCUIT BREAKER BREAKER VALUE(AMPS) CIRCUIT PROTECTED
B LEFTPITOTHEAT
B L. WINDSHIELD HEAT
B L. WINDSHIELD CONT
B FUELQUANTITY
B SURFACEDEICE
B PANELLIGHTSLEFT
B PANELLIGHTS CENTEF
B PANELLIGHTSRIGHT
A LOGO LIGHTS
B LANDING LIGHT
B TAXILIGHT
B POSITIONLIGHTS
B STROBELIGHTS
B GEAR POS IND
B GEARWARN
B INVERTERNO.2
B ELECTTRIM
B PHONE AMP 1
B LEFTALTIMETERENC
B ANNUNMALF
B ANNUN
B L. GEN RESET
B R. GEN RESET
B VOLTAGECONT
B VOLTAGECONT
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：夏延飞机维护手册 Cheyenne IIIA PA-42-720 AMM 1(84)
