CARAVAN C208 SERIES
PILOT TRAINING MANUAL
© 2016 FlyRight, Inc.
For Training Purposes Only
This document is subject to revison. The document is current when training is completed. There is no revision
process for this document after completion of training, therefore, it’s content is subject to change without your
knowledge.
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
AIRCRAFT NAME
PILOT TRAINING MANUAL
REVISION LOG
This pilot training manual is current as of the date in the table below, and is a complete manual based on the
PTM with revised pages as listed:
For Training Purposes Only
Revised: April 12, 2017
Revision
Date
Revision December 7, 2016
12/07/2016
Revision February 15, 2017
02/15/2017
Revision April 12, 2017
04/12/2017
iii
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
AIRCRAFT NAME
This page intentionally left blank.
For Training Purposes Only
Revised: April 12, 2017
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3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
TABLE OF CONTENTS
AIRCRAFT GENERAL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-1
INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
AIRCRAFT GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
TURNING RADIUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2
GENERAL ARRANGEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3
COCKPIT LAYOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
PREFLIGHT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
TIEDOWNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
EMERGENCY EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
PILOT OPERATING HANDBOOK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
APPROVED ENGINE FUEL AND OIL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-10
FUEL QUANTITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-10
ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1
GENERATOR CONTROL UNIT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
GROUND POWER MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
BATTERY SWITCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
STARTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
IGNITION SWITCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
GENERATOR SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
AVIONICS POWER SWITCHES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
EXTERNAL POWER SWITCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
STANDBY ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4
CIRCUIT BREAKERS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4
VOLT/AMMETER AND SELECTOR SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
ANNUNCIATOR LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
GROUND SERVICE PLUG RECEPTACLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6
INDICATORS AND ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8
TYPICAL ELECTRICAL SYSTEM DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10
LIGHTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-1
EXTERIOR LIGHTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
INTERIOR LIGHTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5
NORMAL OPERATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7
MASTER WARNING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
For Training Purposes Only
5HYLVHG$SULO
v
7DEOHRI&RQWHQWV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
ANNUNCIATOR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
INDICATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3
FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-6
INDICATORS AND ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8
NORMAL OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10
AUXILIARY POWER UNIT OVERVIEW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-1
POWERPLANT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7-1
POWERPLANT DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1
PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-12
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-15
INDICATORS AND ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-19
NORMAL OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22
POWER PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23
POWERPLANT INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-25
FIRE DETECTION SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
FIRE DETECTION LOOP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
CONTROL BOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
ALARM MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
EMERGENCY PORTABLE FIRE EXTINGUISHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
INDICATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2
PNEUMATICS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-1
VACUUM SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-1
PNEUMATICS SYSTEM DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-3
INDICATORS AND ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-4
NORMAL OPERATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-6
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-6
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-6
ICE AND RAIN PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-1
WING, WING STRUT, MAIN LANDING GEAR LEG,
CARGO POD NOSECAP AND STABILIZER DEICE BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . 10-1
For Training Purposes Only
Revised: April 12, 2017
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Table of Contents
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
PROPELLER ANTI-ICE BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-3
WINDSHIELD ANTI-ICE PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-4
PITOT/STATIC HEAT SYSTEMS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-4
STANDBY ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-4
WING INSPECTION LIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-5
WINDSHIELD ICE DETECTOR LIGHT (IF INSTALLED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-5
LOW AIRSPEED AWARENESS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-6
AIRSPEED REMINDER BUG (IF INSTALLED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-6
STALL WARNING SYSTEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-6
INERTIAL SEPARATOR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-6
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-7
INDICATORS AND ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-9
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-11
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-13
AIR CONDITIONING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .11-1
OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1
AIR CONDITIONER (OPTIONAL) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1
COCKPIT WINDOW VENTILATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1
CABIN HEAT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1
VENTILATION CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-4
CABIN HEATING, VENTILATING AND DEFROSTING SYSTEM
(PASSENGER VERSION) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-6
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-7
NORMAL OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-11
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-11
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-11
PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12-1
HYDRAULIC POWER SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13-1
LANDING GEAR AND BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .14-1
LANDING GEAR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-1
BRAKE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-1
NORMAL BRAKE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-2
NOSE WHEEL STEERING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-2
PARKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-3
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-4
NORMAL OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-6
EMERGENCY OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-6
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-6
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15-1
AILERON AND SPOILER FLIGHT CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-1
ELEVATOR CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-1
RUDDER SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-1
For Training Purposes Only
5HYLVHG$SULO
vii
7DEOHRI&RQWHQWV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
FLAP CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-2
FLIGHT CONTROL STALL WARNING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-2
TRIM SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-3
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-4
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-9
AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .16-1
COMMUNICATION & NAVIGATION RADIOS: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-1
ATTITUDE INSTRUMENTATION: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-3
PITOT STATIC SYSTEM OVERVIEW AND INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . 16-4
OAT GAUGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-6
KNI-415 RADAR ALTIMETER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-7
NAVIGATION PRESENTATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-7
AUTOPILOT AND FLIGHT DIRECTOR OPERATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-11
KT-71 TRANSPONDER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-13
WEATHER RADAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-14
AIRCRAFT AND AVIONICS PROTECTIVE DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-16
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-17
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-17
GARMIN 400W SERIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-19
OXYGEN SYSTEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .17-1
OXYGEN MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-1
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-3
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-3
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-3
PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-4
CONTROLS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-7
MANEUVERS AND PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .18-1
NORMAL OR SHORT FIELD (OBSTACLE CLEARANCE) TAKEOFF . . . . . . . . . . . . . . . . . . . 18-2
REJECTED TAKEOFF / ENGINE FAILURE DURING TAKEOFF ROLL . . . . . . . . . . . . . . . . . 18-3
STALL RECOVERY PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-4
APPROACH TO STALL: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-5
ENROUTE CONFIGURATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-5
APPROACH TO STALL: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-6
LANDING CONFIGURATION (STRAIGHT AHEAD OR APPROACH TURN) . . . . . . . . . . . . . 18-6
APPROACH TO STALL: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-7
TAKEOFF CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-7
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-8
<1000 FEET AGL, STRAIGHT AHEAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-8
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-9
>1000 FEET AGL, TURNBACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-9
LANDING PATTERN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-10
INSTRUMENT APPROACH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-11
(PRECISION OR NON-PRECISION) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-11
For Training Purposes Only
Revised: April 12, 2017
viii
Table of Contents
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
BALKED LANDING (GO-AROUND) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-12
EMERGENCY DESCENT PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-13
UNUSUAL ATTITUDE RECOVERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-14
NOSE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-14
UNUSUAL ATTITUDE RECOVERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-15
NOSE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-15
STEEP TURNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-16
COCKPIT FLOWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-17
BEFORE STARTING ENGINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-18
STARTING ENGINE (START FLOW) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-20
STARTING ENGINE (AFTER START FLOW) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-22
BEFORE TAKEOFF (1 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-24
BEFORE TAKEOFF (2 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-26
AFTER SYSTEMS CHECKS COMPLETE & AVIONICS SET . . . . . . . . . . . . . . . . . . . . . . . . . . 18-26
BEFORE LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-28
AFTER LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-30
SHUTDOWN AND SECURING AIRPLANE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18-32
WEIGHT AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .19-1
INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-1
AIRPLANE WEIGHING PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-1
WEIGHT AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-2
CREW AND PASSENGER LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-4
BAGGAGE/CARGO LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-5
AIRPLANE WEIGHING FORM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-10
SAMPLE WEIGHT AND BALANCE RECORD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-11
WEIGHT AND BALANCE RECORD (LOADING MANIFEST)
(1 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-12
WEIGHT AND BALANCE RECORD (LOADING MANIFEST)
(2 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-13
CABIN INTERNAL DIMENSIONS (CARGO VERSION) (1 OF 2) . . . . . . . . . . . . . . . . . . . . . . . 19-14
CABIN INTERNAL DIMENSIONS (CARGO VERSION) (2 OF 2) . . . . . . . . . . . . . . . . . . . . . . . 19-15
CARGO BARRIER AND BARRIER NETS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-16
CARGO TIR DOWN ATTACHMENTS (1 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-17
CARGO TIE-DOWN ATTACHMENTS (2 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-18
CABIN INTERNAL LOADING ARRANGEMENTS (CARGO VERSION)
(1 OF 4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-19
CABIN INTERNAL LOADING ARRANGEMENTS (CARGO VERSION)
(2 OF 4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-20
CABIN INTERNAL LOADING ARRANGEMENTS (CARGO VERSION)
(3 OF 4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-21
CABIN INTERNAL LOADING ARRANGEMENTS (CARGO VERSION)
(4 OF 4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-22
CARGO POD LOADING ARRANGEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-23
CARGO POD MEASUREMENTS AND MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-24
TYPICAL CARGO RESTRAINT METHODS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-25
For Training Purposes Only
5HYLVHG$SULO
ix
7DEOHRI&RQWHQWV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
SAMPLE LOADING PROBLEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-26
CENTER OF GRAVITY MOMENT ENVELOPE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-27
CENTER OF GRAVITY LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19-28
PLANNING AND PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20-1
USE OF PERFORMANCE CHARTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-1
SAMPLE PROBLEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-1
TAKEOFF AND LANDING DATA (TOLD) CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-4
FIGURE 20-1. AIRSPEED CALIBRATION (SHEET 1 OF 2). . . . . . . . . . . . . . . . . . . . . . . . . . . 20-5
FIGURE 20-1. AIRSPEED CALIBRATION (SHEET 2 OF 2). . . . . . . . . . . . . . . . . . . . . . . . . . . 20-6
FIGURE 20-2. ALTIMETER CORRECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-7
FIGURE 20-3. PRESSURE CONVERSION:
INCHES OF MERCURY TO MILIBARS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-8
FIGURE 20-4. TEMPERATURE CONVERSION CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-9
FIGURE 20-5. ISA CONVERSION AND OPERATING
TEMPERATURE LIMITS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10
FIGURE 20-6. STALL SPEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-11
FIGURE 20-7. WIND COMPONENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-12
FIGURE 20-8. MAXIMUM ENGINE TORQUE FOR TAKEOFF . . . . . . . . . . . . . . . . . . . . . . . . 20-13
FIGURE 20-9. TAKEOFF DISTANCE
(SHEET 1 OF 2; SHEET 2 OF 2 NOT SHOWN.) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-14
FIGURE 20-10. RANGE PROFILE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-15
FIGURE 20-11. CRUISE PERFORMANCE
(SHEET 7 OF 13; OTHERS NOT SHOWN.) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-16
FIGURE 20-12. TIME, FUEL AND DISTANCE TO CLIMB
(SHEET 1 OF 2; SHEET 2 NOT SHOWN.) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-17
FIGURE 20-13. TIME, FUEL AND DISTANCE TO DESCEND . . . . . . . . . . . . . . . . . . . . . . . . . 20-18
FIGURE 20-14. LANDING DISTANCE (SHEET 1 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20
FIGURE 20-14. LANDING DISTANCE (SHEET 2 OF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-21
FIGURE 20-15. SAMPLE TAKEOFF AND LANDING DATA (TOLD) CARD . . . . . . . . . . . . . . 20-22
AIRCRAFT MANUALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GOS-1-1
PILOTS OPERATING HANDBOOK AND FAA APPROVED FLIGHT MANUAL. . . . . . . . . . . . GOS-1-1
ADDITIONAL EQUIPMENT MANUALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-1-1
MASTER MINIMUM EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-1-2
MAINTENANCE MANUALS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-1-2
LIMITATIONS & SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GOS-3-1
AIRSPEED LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-2
AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-2
POWER PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-3
POWERPLANT INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-5
MISCELLANEOUS INSTRUMENT ITEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-6
PREFLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-6
VISUAL AND TACTILE CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-6
WEIGHT LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-7
CENTER OF GRAVITY LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-7
For Training Purposes Only
Revised: April 12, 2017
x
Table of Contents
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
MANEUVER LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-7
FLIGHT LOAD FACTOR LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-8
FLIGHT CREW LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-8
MASTER MINIMUM EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-8
FUEL LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-9
MAXIMUM OPERATING ALTITUDE LIMIT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-11
OUTSIDE AIR TEMPERATURE LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-11
MAXIMUM PASSENGER SEATING LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-11
OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-11
PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-3-12
HANDLING, SERVICE AND MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GOS-5-1
INTRODUCTION TO SERVICING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-1
PUBLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-1
GROUND HANDLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-2
JACKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-4
LEVELING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-5
SERVICING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-5
SERVICE DIFFICULTY REPORT SUMMARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GOS-5-8
For Training Purposes Only
5HYLVHG$SULO
xi
7DEOHRI&RQWHQWV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
Page intentionally left blank.
For Training Purposes Only
Revised: April 12, 2017
xii
Table of Contents
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
DLOHURQVVSRLOHUVDQGHOHYDWRUDQGUXGGHUEUDNHSHGDOV
for the rudder.
AIRCRAFT GENERAL
The aircraft is equipped with one Pratt & Whitney of
&DQDGD 37$$ WXUERSURS HQJLQH FDSDEOH RI
producing 675 SHP. The engine is equipped with a
WKUHHEODGHGFRQVWDQWVSHHGIXOOIHDWKHULQJUHYHUVLQJ
propeller.
INTRODUCTION
W
elcome to the Cessna Model 208B Grand
&DUDYDQ 6LQFH FHUWL¿FDWLRQ LQ &HVVQD¶V
single-engine aircraft has earned its place in the freight
DQG SDVVHQJHU ZRUOG DV D XWLOLWDULDQ UREXVW DLUFUDIW
7KH*UDQG&DUDYDQZDVLQWHQGHGWREHDUHSODFHPHQW
IRULWVVPDOOHUFRXQWHUSDUWWKH&HVVQD&DUDYDQ
While this training manual provides an understanding
of the systems and operations of the Cessna Model
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or equipment not covered in this manual. It is imperative
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+DQGERRN7KLVPDQXDOZLOOGHVFULEHWKHV\VWHPVDQG
HTXLSPHQW IRXQG RQ PDQ\ DLUFUDIW +RZHYHU WKHUH
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Training Manual.
DIMENSIONS
Pivot Point
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ERWKWKHFDUJRYHUVLRQDQGWKHSDVVHQJHUYHUVLRQRIWKH
0RGHO % 6+3 6RPH HTXLSPHQW GLႇHUHQFHV
H[LVWEHWZHHQWKHVHYHUVLRQVDQGVSHFL¿FYHUVLRQVDUH
LGHQWL¿HGWKURXJKXVHRIWKHWHUPV³&DUJR9HUVLRQ´DQG
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information applies to all airplanes.
Pivot Point
20’ - 6”
52’ - 1”
100” (Hartzell)
106” (McCauley)
2.5’ - 14.75”
AIRCRAFT GENERAL
11’ - 8”
The Cessna Model 208B Grand Caravan series are
high-wing monoplane aircraft of aluminum construction
with wing struts. They are an extremely versatile aircraft
SURYLGLQJPDQ\EHQH¿WVIRUWKHLURSHUDWRUV7KH&HVVQD
0RGHO % *UDQG &DUDYDQ VHULHV KDV D ODUJH FDELQ
for passenger comfort and generous cargo space.
The empennage consists of a conventional vertical
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The control surfaces are manually operated through
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NOTE: CABIN-SIDE WINDOWS
AND THE RIGHT HAND
AFTER PASSENGER DOOR
ARE NOT INSTALLED ON
THE CARGO VERSION.
PASSENGER VERSION
15’ - 5 1/2”
MAX
CARGO VERSION
13’ - 3.5”
41’ - 7”
For Training Purposes Only
Revised: February 15, 2017
1-1
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
The principle dimensions for the Cessna Model 208B
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WINGSPAN . . . . . . . . . . . . . . . . . . . . . . . 52 FEET 1 INCH
AIRCRAFT LENGTH . . . . . . . . . . . . . . )((7,1&+(6
TAIL HEIGHT . . . . . . . . . . . . . 15 FEET 5 ½ INCHES MAX
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RADIUS FOR NOSE WHEEL . . . . . . )((7,1&+(6
RADIUS FOR OUTSIDE WHEEL. . . . . 13 FEET 3 INCHES
RADIUS FOR WINGTIP . . . . . . . . . . )((7ǫ,1&+(6
ZLWKVWUREHOLJKW It is important to note that the Cessna Model 208B
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6. $QG $LUSODQHV WKUX QRW
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TURNING RADIUS
RADIUS FOR WINGTIP . . . . . . . . . . . . . . . . . . 33.65 FEET
ZLWKVWUREHOLJKWV )RU $LUSODQHV WKUX ,QFRUSRUDWLQJ
The turning radius of the Model 208B varies depending 6. DQG 2Q WKUX RQ ZKHWKHU DLUFUDIW LQFRUSRUDWLQJ 6. DUH ,QFRUSRUDWLQJ 6. DQG $LUSODQHV included. Below is the minimum turning radius data and On.
67.30’ (with Strobe Lights)
65’4 - 7/8” (with Strobe Lights)
33.65’ (with Strobe Lights)
32’8 - 5/8” (with Strobe Lights)
14’10”
PIVOT POINT
13’3”
NOTE:
NOTE:
MINIMUM TURNING
RADIUS WITH INBOARD
WHEEL BRAKE LOCKED,
FULL RUDDER AND
POWER.
MINIMUM TURNING
RADIUS WITH INBOARD
WHEEL BRAKE LOCKED,
FULL RUDDER AND
POWER.
For Airplanes 2080001 thru 0403 Incorporating SK208-164. 2080404
and On, 208B0001 thru 1223 Incorporating SK208-164, and Airplanes
208B1224 and On.
For Airplanes 2080001 thru 0403 not Incorporating SK208-164. and
Airplanes 208B0001 thru 1223 not Incorporating SK208-164.
For Training Purposes Only
Revised: February 15, 2017
1-2
AS-01 Aircraft Overview
PLACE SEATING
ER STAGGERED)
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
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GENERAL ARRANGEMENT
CABIN CONFIGURATIONS
CABIN ENTRY DIMENSIONS
100.0
100.0
CABIN HEIGHT MEASUREMENTS
* 135.5
(133.5 - 146.5)
173.9
1
* 135.5
(133.5 - 146.5)
2
3
4
5
6
8
7
245.9
11
10
9
CARGO DOOR (LEFT SIDE)
PASS. DOOR (RIGHT SIDE)
AFT WALL
8
7
CREW DOOR
(1 EACH SIDE)
6
51”
54”
52”
46”
10
9
245.9
261.9
5
3
209.9
225.9
CARGO BARRIER/NETS
(IF INSTALLED FOR
CARGO MISSION)
2
4
173.9
189.9
209.9
1
11
CARGO DOOR (LEFT SIDE)
CARGO BARRIER/NETS
AFT WALL
ZONE
6
** 344.0
10 OR 11 - PLACE SEATING
(COMMUTER SIDE BY SIDE)
CREW DOOR
(1 EACH SIDE)
ZONE
6
** 344.0
* 135.5
(133.5 - 146.5)
1
52”
46”
CABIN WIDTH MEASUREMENTS
* 135.5
(133.5 - 146.5)
2
54”
10 OR 11 - PLACE SEATING
(COMMUTER STAGGERED)
100.0
100.0
51”
1
* MAX. CABIN BREADTH
** CABIN FLOOR
2
173.9
3
4
173.9
3
4
209.9
5
6
209.9
5
6
245.9
7
8
245.9
7
8
281.9
9
10
281.9
9
10
*62”
** 54”
53”
*64” *53”
** 59 1/2” ** 51”
*46”
** 42”
DOOR OPENING DIMENSIONS
** 344.0
ZONE
6
10 - PLACE SEATING
(COMMUTER)
** 344.0
ZONE
6
WIDTH (MID/
OVERALL)
WIDTH
(BOTTOM)
CREW DOORS
LQ
LQ
LQ
CARGO DOOR
LQ
LQ
LQ
PASSENGER
DOOR
LQ
LQ
LQ
DOOR OPENING DIMENSIONS (CONTINUED)
10 - PLACE SEATING
(UTILITY)
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For Training Purposes Only
Revised: February 15, 2017
WIDTH (TOP)
1-3
HEIGHT
(FRONT)
HEIGHT
(MID/
OVERALL)
HEIGHT
(REAR)
CREW DOORS
LQ
LQ
LQ
CARGO DOOR
50 in
50 in
50 in
PASSENGER
DOOR
50 in
50 in
50 in
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
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crew entry provides a means of overriding the outside
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PASSENGER ENTRY DOORS (PASSENGER
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CABIN LIGHTING
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BAGGAGE COMPARTMENT
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anchor plates provided in the airplane
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loading details.
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the airplane is equipped with special seating for this
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DOORS AND EXITS
CREW ENTRY DOORS
The left door for
crew entry has a
conventional exterior
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window. The right
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a conventional interior
For Training Purposes Only
Revised: February 15, 2017
The
entry
door
for
passengers consists of an
upper and lower section.
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section swings upward
and the lower section
drops down providing
integral steps to aid in
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airplane. The upper door
section incorporates a
conventional exterior door
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an interior door handle
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receptacle. The lower door
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from either inside or outside
the airplane. This handle is
designed so that when the
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to the OPEN position. The
lower door also contains
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and a doorlowering device.
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safety feature so that if the upper door is not properly
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The aircraft is equipped with an automatic door lift with
telescoping gas springs to raise the door to the full up
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automatically from their stowed positions.
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
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the upper door section just forward of the exterior door
handle operates in conjunction with the interior door
handle. It is used whenever it is desired to open the
door from outside the airplane while the interior door
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WARNING:
DO NOT USE THE OUTSIDE KEY LOCK TO LOCK
THE DOOR PRIOR TO FLIGHT. THE DOOR COULD
NOT BE OPENED FROM THE INSIDE IF IT WERE
NEEDED AS AN EMERGENCY EXIT.
WEIGHTS
WARNING:
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DO NOT USE THE OUTSIDE KEY LOCK TO LOCK
THE DOOR PRIOR TO FLIGHT. THE DOOR COULD
NOT BE OPENED FROM THE INSIDE IF IT WERE
NEEDED AS AN EMERGENCY EXIT.
COCKPIT ARRANGEMENT
CARGO DOORS
A two-piece cargo door is installed on the left side
of the airplane just aft of the wing trailing edge. The
cargo door is divided into an upper and a lower section.
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the lower section swings forward to create a large
opening in the side of the fuselage which facilitates the
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of the cargo door incorporates a conventional exterior
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emergency door release and an interior door handle
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also incorporates two telescoping door lifts which
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A cargo door open warning system is provided as a
safety feature so that if the upper door is not properly
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The handle is designed so that when the upper door
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position.
For Training Purposes Only
Revised: February 15, 2017
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control to either pilot. Dual rudder pedals under the
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1-5
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
COCKPIT LAYOUT
s FLAP MOTOR
STBY
DOWN
NORM
UP
STBY
FAN/OPEN
OPEN/FAN
OFF
1000
1500
500
2000
0
USE NO
OIL
CLOSE
PSI
uy
CLOSE
OXYGEN
SUPPLY PRESSURE
MADE IN USA
ON
OFF
OFF
RIG
HT
FT
LE
FUEL TANK
SELECTORS
ON
165
GAL
ON
165
GAL
40
60
20
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT : 200 LBS
0
0
80
20
-20
-20
100
40
-40
-40
-60
120
60
C
140
F
N 33 60
15 12
E 120 160
E
6
S 210 240 W 300 330
-ANNUN PANELLAMP
NIGHT
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
STARTER
ENERGIZED
5
IGNITION
ON
10
BATTERY
OVERHEAT
WINDSHIELD
ANTI-ICE
15
4
20
0
OFF
2
1
3
4
ITT
C° X 100
16
40
5
6
7
20
FT-LB
X100
DE-ICE
PRESSURE
12
8
TORQUE
0
DOOR
WARNING
TEST
FUEL SELECT
OFF
120
60
Ng
8
°
80
1
8
2
7
2
3
1
110
4
FUEL FLOW
4
10
-40
5
2
1
E
0
PPH X 100
5
6
FUEL
3
55
°C
100
6
4
2
E
8
4
7
8
10
FUEL 12
B ASE D
4
5
6
4
2
E
2
1
E
10
11
6
7
FUEL
3
9
14
16
G A QTY 0
L LO N S X 1
8
8
10
FUEL 12
14
16
G A QTY 0
L LO N S X 1
L BS X 1 0 0
0
3
6
140
PSI
40
0
9
0
9
10
11
OIL
85
%RPM
20
ST LIM
1090
PROP
RPM X 100
25
OFF
TEST
ENGINE
FIRE
VOLTAGE
LOW
MAX
TORQUE
1865
1970
1970
1970
RPM
1900
1800
1700
1600
BELOW
ICING
MIN SPEED
120 KIAS MINIMUM IN ICING FLAPS UP EXCEPT 110 KIAS IF CLIMBING TO EXIT ICING
FIRE
DETECT
9
10
11
L B S X 1 00
O N 6. 7L BS/ GAL
BA SED
ON 6. 7LBS/GAL
5
MAX WT. MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
AIR
MKR
FD
240
10
10
10
10
20
BC
20K
25K
30K
O
P
TEL
1 NAV 2
DME
MKR
ADF
AUTO
COM 1
HF
OFF
8888888888 8888888888
COM 2
INT
EXT
USE
STBY
KK 165 TSO
PHONE
TRIM
000 000 00
V
FPL
AIRSPEED
KNOTS
100 FEET
40
60
MP 240
H
ALTITUDE
40 60
20
20
10
10
10
10
29.8
29.9
SET
OTH
PULL
CLRIDENT ENT
30.0
CAL
160
8.8.8.8
KR 87 TSO
V
100
PULL
FOR
QUICK
ER
EC T
140
120
VOL
PUSH
VOL/ ID
ADF
BFO
FRQ
FLT
SGT
ET
RST
OFF
/VLOC
IDT
8
/
NAV
30
12
30
8.8.8.8
GND
TST
SBY
OFF
ON
ALT
N
33
15
21
OBS
NAV
30
VP
Wx
WxA
RNG
RNG
S
2
1
3
33
R
GND
TST
SBY
OFF
ON
ALT
KT 71 TSO
2 MIN TURN
ELEC
24
24
6
XPDR1
PUSH
21
3
NAV
FR
2
15
ALT
RNG
VACUUM
VENT
PULL ON
VERTICAL
SPEED
.5
3
0
12
-50
1
8.8.8.8
8.8.8
L
IDT
FT / MIN
X 1000
.5
S
8.8.8
BRT
Wx
BRT
WxA
12
N
GEN
200
12
30
25
30
OBS
KT 71 TSO
TO
E
E
W
N
A
V
GS
3
0
E
VERTICAL
SPEED
.5
6
GS
3
33
2
1
3
6
W
NRST
N
N
33
GS
W
21
E
150
6
S
24
100
15
20
NAV
NRST
COM
VOLTS
0
USR
8.8.8
D
N2
BENDIX/KING
15
10
5
INT
ALT
ADF
PUSH
VOL/ SQ
200
180
NAV
80
APT
VOR
NBD
PULL
MSG
OBS
TEST
C
PWR
HLD
N1
OFF
100
SUCTION
IN HG
AMPS
50
VENT
PULL ON
CRSR
STBY/RAD
USE
COMM
OFF ON
MIC KMA 24 TSO
C
7
2
1 COM 2
3
BENDIX/KING
120
6
15K
A
HI
LO
W
5
4
3
A
O
M
30.0
ENCODING
80
140
30
AMPS
YD
24
10
PROP ANTI-ICE
AP
GS
29.8
29.9
60
5
160
0
ALT
40
MPH
MPH
6
180
4
QUARTZ
7
ARM
CPLD
20
40
KNOTS
200
3
8
20
2
9
NAV
HGD APPR
DH
AIRSPEED
21
CLOCK
10
ICE DET
P/TEST
1
KLN 89B TSO
GPS
FT / MIN
X 1000
15
12
11
BENDIX/KING
SPEAKER
MPH
N720FX
1
S
2
XPDR2
BATT
VOLT
MAP
VP
+
FREE
CW
GPS
WAYPOINT
GPS
Approach
-
ARM
ACTV MSG
TAXI/
RECOG
ON
RIGHT
LDG
STROBE
NAV
BCN
L
TRK
RNG
HSt NAV
ALT HSt
DH
CONTINUED FLIGHT AFTER
ENCOUNTERING MODERATE OR
GREATER ICING CONDITIONS IS
PROHIBITED. ONE OR MORE OF THE
FOLLOWING DEFINES MODERATE ICING
CONDITIONS FOR THIS AIRPLANE.
GPS
LIGHTS
LEFT
LDG
OVERSPEED
GOVERNOR
PUSH TO TEST
NAV
MAP
2
X 100 FEET
INDICATED AIRSPEED IN LEVEL CRUISE
FLIGHT AT CONSTANT POWER
DECREASED BY 20 KNOTS
PHONE
NAV
3
20
ENGINE TORQUE REQUIRED TO
MAINTAIN AIRSPEED INCREASES BY 400
FT LBS
10
TRK
GAIN
4
15
AIRSPEED OF 120 KIAS CANNOT BE
MAINTAINED IN LEVEL FLIGHT
2 MIN TURN
ELEC
TRK
TRK
1
RADAR ALT
R
PULL STAB OFF
MIC
5
DN
TEST
GAIN
PULL STAB OFF
KFC - 150
ON
UP
FD
ALT
HDG
ALT
HDG
NAV
APR
BC
AP
ENG
APR
BC
AP
ENG
AN ACCCRETION OF 1/4 INCH OF ICE IS
OBSERVED ON THE WING STRUT
DN
PHONE
SMOKE
NO
SMOKE ON
BELT
SEAT
BELT
KFC - 150
CABIN
UP
CABIN
LIGHTS BRT
L FLT PANEL
L FLOOD
MIC
INERTIAL SEPERATOR
BYPASS - PULL
NORMAL -PUSH
R FLT PANEL
R FLOOD
STALL
HEAT
WING
LIGHT
NAV
WARNING
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI TAKEOFF AND LANDING. FAILURE
TO PROPERLY LATCH SEAT AND HEED ALL
SAFETY INSTRUCTIONS CAN RESULT IN BODILY
INJURY OR DEATH
BOOT
PRESS
PROP
W/S
ON
FD
WARNING
ASSURE THAT ALL CONTAMINANTS, INCLUDING
WATER, ARE REMOVED FROM FUEL AND FUEL
SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE
CONTAMINANT FREE FUEL AND HEED ALL SAFETY
INSTRUCTIONS AND OWNER ADVISORIES PRIOR
TO FLIGHT CAN RESULT IN BODILY INJURY OR
DEATH
DEICE / ANTI-ICE
PITOT/STATIC
HEAT
AUTO
OFF
LWR PANEL/
PED/OVHD
CW/CKT BKR
OFF
CABIN HEAT
ENG INST
AIR CONDITIONING
AC FANS
RADIO
LEFT
MANUAL
MANUAL
AFT
COOL
ALT STATIC AMP
PULL ON
PARKING
BRAKE
PULL
RIGHT
TEMP
HOT
HIGH
MIXING AIR
GRD-PULL
FLT-PUSH
BLEED AIR HEAT
ON
AFT CABIN-PULL
FWD CABIN-PUSH
DEFROST-PULL
FWD CABIN-PUSH
OFF
LOW
VENTILATE
RUDDER LOCK
PULL
DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE
AIRCRAFT.
2605070-9
UP
TRIM
DN
TRIM
UP
10°
NOSE
DOWN
Cessna
Cessna
Caravan I
Caravan I
20°
NOSE
UP
MAP LIGHT
LO
MAX
HI
CAUTION
USE BETA AND REVERSE ONLY
WITH ENGINE RUNNING AND
PROPELLER OUT OF FEATHER
AILERON TRIM
L
FUEL SHUTOFF
PULL OFF
R
NOSE
L
RUD TRIM
NOSE
R
CABIN HEAT
FIREWALL SHUTOFF
PULL - OFF
BUS
1
PWR
STBY
PWR
FLAP
MOTOR
STBY
FLAP
MOTOR
IGN
30
40
10
10
5
BUS
2
PWR
STBY
PWR
LEFT
VENT
BLWR
RIGHT AUX FUEL RIGHT ANNUN STALL AIR
VENT FUEL CONT TURN/ PANEL WARN COND
BLWR PUMP HEATER BANK
CONT
10
10
5
FUEL
TOTAL
LEFT
FUEL
QTY
OIL
TEMP
BLEED
AIR
HEAT
AFT
VENT
BLWR
5
5
5
30
40
BUS
1
PWR
FIRE
DET
30
5
BUS
2
PWR
ITT
GAGE
30
5
START LEFT ANNUN GEN GEN
CONT TURN/ PANEL CONT FIELD
BANK
5
5
5
5
15
10
ON
BUS
LEFT
W/S
W/S
PITOT ANTI-ICE ANTI-ICE
HEAT
CONT
STARTER
OFF
OFF
FUEL
FLOW
5
15
20
5
RIGHT AIR PROP DE-ICE RIGHT PROP PROP
FUEL SPEED 0-SPEED BOOT PITOT ANTI-ICE ANTI-ICE
QTY WARN TEST
HEAT
CONT
5
5
5
5
15
30
ON
RESET
ON
NORM
TRIP
5
OFF
FUEL
BOOST
GENERATOR
BUS
1
PWR
LEFT STROBE BEACON MAP INST WING SEAT
LGD LIGHT LIGHT LIGHT LIGHT ICE DET BELT
LIGHT
LIGHT
30
10
5
10
BUS
2
PWR
RIGHT
LDG
LIGHT
TAXI
LIGHT
NAV
LIGHT
30
10
15
10
2
5
TORQ
IND
ON
5
RADIO RH
FLOOD ATT
LIGHT GYRO
5
5
DG
RMI
AUD/
MKR
A/P
FD
ELEV
TRIM
10
5
5
5
5
5
10
5
COM/NAV
2
XPDR
2
ADF
2
DME
RNAV
RADIO
ALT
AVN
FAN
AUDIO
AMP
5
5
5
HF
XMT
HF
RCVR
5
30
For Training Purposes Only
5HYLVHG$SULO
GPS/
LORAN
10
5
HF
XMT
MOTOR
IGNITION
STARTER
1
ADF
1
HSI
2
NORM
STBY PWR
5
XPDR
1
10
START
OFF
OFF
ENC
ALT
COM/NAV
1
FUEL
SEL
WARN
ON
5
30
AVIONICS
STBY
PWR
AVIONICS
BUS TIE
ON
OFF
2
30
AVIONICS
RADAR RADAR RADAR STM
CONT
R-T GRAPHICS SCP
5
5
1-6
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
L EFT STATIONARY PANEL
UPPER STATIONARY PANEL
TORQUE
1865
1970
1970
1970
N720FX
10
5
IGNITION
4
20
0
3
4
40
5
6
7
20
FT-LB
X100
2
1
ITT
C° X 100
16
8
°
0
9
11
2
3
10
6
3
1
110
4
FUEL FLOW
4
10
°C
100
2
1
E
0
-40
5
PPH X 100
5
6
FUEL
3
55
PSI
40
1
8
7
2
140
OIL
85
80
0
9
PROP
RPM X 100
25
120
60
Ng
%RPM
20
ST LIM
1090
OFF
15
OFF
12
8
TORQUE
0
CT
6
4
2
E
8
4
7
8
10
FUEL 12
5
2
1
E
10
11
6
4
2
E
0
B ASE D
8
7
8
10
FUEL 12
9
14
16
10
11
G A QTY 0
L LO N S X 1
L BS X 1 0 0
4
6
FUEL
3
9
14
16
G A QTY 0
L LO N S X 1
LB S X 1 00
O N 6. 7L BS/ GAL
BA SED
O N 6. 7LBS/GAL
5
12
11
2
3
9
8
RIGHT FLIGHT CONTROL PANEL
4
QUARTZ
7
10
1
CLOCK
10
ICE DET
P/TEST
5
6
20
30
5
4
3
AMPS
20K
25K
30K
6
15K
200
7
AIRSPEED
KNOTS
100 FEET
40
60
2
M 240
PH
180
8
ALTITUDE
40 60
PH
PROP ANTI-ICE
20
20
10
10
10
10
M
0
29.8
29.9
80
SUCTION
IN HG
30.0
160
100
PULL
FOR
QUICK
ER
EC T
140
120
AMPS
50
VENT
PULL ON
10
5
100
15
VOLTS
20
150
N
25
30
L
2
1
3
6
VERTICAL
SPEED
.5
W
-50
33
R
30
GEN
200
24
VACUUM
2 MIN TURN
ELEC
21
VOLT
12
BATT
3
0
E
ALT
FT / MIN
X 1000
15
0
1
2
S
PUSH
ANTI-ICE CONTROL
CENTER RADIO PANEL
SED ON 6. 7LB
5
DEICE / ANTI-ICE
PITOT/STATIC
HEAT
STALL
HEAT
WING
LIGHT
BOOT
PRESS
PROP
W/S
ON
MKR
A
O
M
AUTO
BENDIX/KING
SPEAKER
HI
TEL
LO
1 COM 2
1 NAV 2
DME
MKR
ADF
AUTO
8888888888 8888888888
COM 2
INT
EXT
KLN 89B TSO
GPS
USE
STBY
KK 165 TSO
PHONE
OFF
COM 1
HF
OFF
NAV
OFF ON
MIC KMA 24 TSO
OFF
CRSR
STBY/RAD
USE
COMM
APT
VOR
NBD
PULL
MSG
OBS
TEST
INT
USR
ALT
NAV
FPL
NRST
CAL
SET
OTH
PULL
CLRIDENT ENT
3
ADF
8.8.8
C
C
PWR
PUSH
VOL/ SQ
MANUAL
MANUAL
D
V
KR 87 TSO
V
PUSH
VOL/ ID
ALT STATIC AMP
PULL ON
8.8.8.8
VOL
ADF
BFO
FRQ
SGT
FLT
ET
RST
OFF
/VLOC
COM
IDT
/
NRST
OBS
8.8.8
8.8.8.8
8.8.8
8.8.8.8
GND
TST
SBY
OFF
ON
ALT
KT 71 TSO
LEFT FLIGHT CONTROL PANEL
BRT
IDT
MAX WT. MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
FD
20
ARM
ALT
CPLD
GS
BC
A
O
P
RNG
RNG
29.8
29.9
60
ON
ALT
MAP
VP
TRK
RNG
XPDR2
NAV
MAP
TRK
TRK
30.0
10
10
000 000 00
ENCODING
160
80
140
GND
TST
SBY
OFF
KT 71 TSO
TRIM
PH
10
M
H
MP
180
HLD
N1
120
VP
Wx
WxA
XPDR1
AP
YD
20
10
40
NAV
HGD APPR
DH
40
KNOTS
240
RNG
AIR
AIRSPEED
200
Wx
BRT
WxA
N2
OFF
BENDIX/KING
100
NAV
BENDIX/KING
TRK
GAIN
PULL STAB OFF
NAV
30
W
30
W
33
21
CW
GPS
Approach
ARM
1
GPS
WAYPOINT
ACTV MSG
FR
2
FD
ALT
HDG
NAV
APR
BC
AP
ENG
S
HSt NAV
ALT HSt
GPS
CONTINUED FLIGHT AFTER
ENCOUNTERING MODERATE OR
GREATER ICING CONDITIONS IS
PROHIBITED. ONE OR MORE OF THE
FOLLOWING DEFINES MODERATE ICING
CONDITIONS FOR THIS AIRPLANE.
3
R
INDICATED AIRSPEED IN LEVEL CRUISE
FLIGHT AT CONSTANT POWER
DECREASED BY 20 KNOTS
DH
1
2
RADAR ALT
X 100 FEET
3
20
ENGINE TORQUE REQUIRED TO
MAINTAIN AIRSPEED INCREASES BY 400
FT LBS
2 MIN TURN
ELEC
PULL STAB OFF
KFC - 150
24
.5
15
FREE
GAIN
12
-
DN
UP
FT / MIN
X 1000
OBS
+
TO
DN
NAV
L
N
A
V
GS
3
0
12
30
24
VERTICAL
SPEED
.5
E
W
GS
S
33
2
1
3
E
E
6
N
6
12
24
N
NAV
33
GS
21
21
15
S
3
6
15
N
AIRSPEED OF 120 KIAS CANNOT BE
MAINTAINED IN LEVEL FLIGHT
4
15
10
5
TEST
AN ACCCRETION OF 1/4 INCH OF ICE IS
OBSERVED ON THE WING STRUT
For Training Purposes Only
5HYLVHG$SULO
1-7
AS-01 Aircraft Overview
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
29(5+($'3$1(/
LEFT SIDE CONTROL PANEL
s FLAP MOTOR
STBY
NORM
DOWN
ON
BUS
UP
STBY
STARTER
OFF
OFF
ON
RESET
ON
NORM
TRIP
OFF
FAN/OPE
N
N
OPEN/FA
OFF
FUEL
BOOST
GENERATOR
1000
1500
500
2000
0
USE NO
OIL
CLOSE
ON
ON
START
OFF
NORM
MOTOR
PSI
uy
CLOSE
OXYGEN
SUPPLY PRESSURE
MADE IN USA
OFF
ON
STBY PWR
OFF
IGNITION
1
ON
OFF
RIG
HT
FT
LE
STARTER
FUEL TANK
SELECTORS
ON
165
GAL
ON
165
GAL
2
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT : 200 LBS
OFF
30
AVIONICS
STBY
PWR
AVIONICS
BUS TIE
30
AVIONICS
OUTSIDE AIR TEMPERATURE (OAT) GAUGE
CIRCUIT BREAKER PANEL
40
60
20
0
0
80
20
-20
-20
40
100
-40
-40
BUS
1
PWR
STBY
PWR
FLAP
MOTOR
STBY
FLAP
MOTOR
IGN
10
5
30
40
10
BUS
2
PWR
STBY
PWR
LEFT
VENT
BLWR
RIGHT AUX FUEL RIGHT ANNUN STALL AIR
VENT FUEL CONT TURN/ PANEL WARN COND
BLWR PUMP HEATER BANK
CONT
10
10
5
FUEL
TOTAL
LEFT
FUEL
QTY
OIL
TEMP
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Cessna
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10
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For Training Purposes Only
Revised: February 15, 2017
5
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R-T GRAPHICS SCP
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5
1-8
AS-01 Aircraft Overview
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PREFLIGHT INSPECTION
Unrestrained propellers are apt to windmill. To prevent
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located on the lower right hand cowl.
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1. &DELQ
PILOT OPERATING HANDBOOK
2. Left Side
3. Left Wing Leading Edge
Every Cessna Model 208B is
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operations a Pilot Operating
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revision status.
Left Wing Trailing Edge
5. Empennage
6. Right Wing Trailing Edge
7. Right Wing Leading Edge
8. Nose
TIEDOWNS
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and tie the airplane down at all three points. If extreme
For Training Purposes Only
Revised: February 15, 2017
• Normal Procedures
• Performance
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• Systems Description
AS-01 Aircraft Overview
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Weight and Balance chapter will have information for
the exact aircraft and the Supplements section will
have information for additional equipment installed of
individual aircraft.
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OIL
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7RWDO&DSDFLW\(DFK7DQN . . . . . . . . . . .167.5 U.S. gallons.
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are complied with.
For Training Purposes Only
Revised: February 15, 2017
1-10
AS-01 Aircraft Overview
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ELECTRICAL SYSTEM
T
he airplane is equipped with a 28-volt, direct-current
electrical system. The system uses a 24-volt leadacid battery; or a 24-volt sealed lead acid battery; or a
24-volt Ni-Cad battery, located on the front right side of
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engine-driven starter-generator is used to maintain the
battery’s state of charge. Power is supplied to most
general electrical and all avionic circuits through two
general buses, two avionic buses and a battery bus.
The battery bus is energized continuously for memory
keep-alive, clock and cabin/courtesy light functions.
The two general buses are on anytime the battery
switch is turned on. All DC buses are on anytime the
battery switch and the two avionic switches are turned
on.
An optional standby electrical system, which consists
of an engine driven alternator and separate busing
system, may be installed in the airplane. For details
of this system, refer to Section 9, Supplements in the
AFM/POH.
the event of a high-voltage or reverse current condition,
the generator is automatically disconnected from the
buses. The generator contactor (controlled by the GCU)
connects the generator output to the airplane bus. If
any GCU function causes the generator contactor to
de-energize, the red GENERATOR OFF light on the
annunciator panel will come on.
GROUND POWER MONITOR
The ground power monitor is located inside the electrical
power control assembly mounted on the left hand side
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senses the voltage level applied to the external power
receptacle and will close the external power contactor
when the applied voltage is within the proper limits. In
addition, the ground power monitor senses airplane
bus voltage and will illuminate the VOLTAGE LOW light
on the annunciator panel when bus voltage drops to
battery voltage.
BATTERY SWITCH
GENERATOR CONTROL UNIT
ON
BUS
STARTER
OFF
OFF
ON
RESET
ON
ON
NORM
TRIP
OFF
FUEL
BOOST
GENERATOR
ON
ON
START
OFF
NORM
MOTOR
OFF
STBY PWR
IGNITION
1
30
AVIONICS
STBY
PWR
The generator control unit (GCU) is mounted inside
the cabin on the left forward fuselage sidewall. The
unit provides the electrical control functions necessary
for the operation of the starter-generator. The GCU
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is above 46. Below 46, the starter-generator functions
as a starter, and above 46, the starter-generator
functions as a generator when the starter switch is
OFF. The GCU provides voltage regulation plus high
voltage protection and reverse current protection. In
For Training Purposes Only
Revised: February 15, 2017
AVIONICS
BUS TIE
OFF
STARTER
ON
OFF
2
30
AVIONICS
The battery switch is a two-position toggle-type switch,
labeled BATTERY, and is located on the left sidewall
switch and circuit breaker panel. The battery switch is
ON in the forward position and OFF in the aft position.
When the battery switch is in the ON position, battery
power is supplied to the two general buses. The OFF
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bus.
2-1
AS-02 Electrical Power Systems
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GENERATOR SWITCH
STARTER SWITCH
ON
BUS
ON
BUS
STARTER
STARTER
OFF
OFF
ON
RESET
ON
ON
ON
NORM
TRIP
ON
OFF
FUEL
BOOST
GENERATOR
OFF
START
ON
ON
OFF
NORM
STBY PWR
NORM
MOTOR
AVIONICS
BUS TIE
MOTOR
OFF
STARTER
ON
30
AVIONICS
STBY
PWR
The starter switch is a three-position toggle-type
switch, labeled STARTER, on the left sidewall switch
and circuit breaker panel. The switch has OFF, START,
and MOTOR positions. For additional details of the
starter switch, refer to the Starting System paragraph
in the AFM/POH.
IGNITION SWITCH
ON
STARTER
OFF
OFF
ON
RESET
ON
ON
S
OFF
NORM
M
OFF
FUEL
BOOST
GENERATOR
ON
ON
START
OFF
NORM
MOTOR
OFF
STBY PWR
IGNITION
30
AVIONICS
BUS TIE
AVIONICS
BUS TIE
ON
OFF
2
GENERATOR
30
AVIONICS
The generator switch is a three-position toggle-type
switch, labeled GENERATOR, on the left sidewall switch
and circuit breaker panel. The switch has ON, RESET,
and TRIP positions. With the switch in the ON position,
the GCU will automatically control the generator line
contactor for normal generator operation. The RESET
and TRIP positions are momentary positions and are
spring-loaded back to the ON position. If a momentary
fault should occur in the generating system (as
evidenced by the GENERATOR OFF and/or VOLTAGE
LOW lights illuminating), the generator switch can be
momentarily placed in the RESET position to restore
generator power. If erratic operation of the generating
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momentarily placing the generator switch to the TRIP
position. After a suitable waiting period, generator
operation may be recycled by placing the generator
switch momentarily to RESET.
STARTER
1
AVIONICS
STBY
PWR
ON
NORM
TRIP
STARTER
1
30
TRIP
MOTOR
IGNITION
STARTER
AVIONICS
BUS
NORM
STBY PWR
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2
OFF
30
AVIONICS
STBY
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OFF
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ON
START
OFF
OFF
RESET
NORM
TRIP
FUEL
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ON
ON
RESET
START
OFF
GENERATOR
ON
OFF
OFF
ON
OFF
2
Y PWR
AVIONICS POWER SWITCHES
IGNITION
30
AVIONICS
The ignition switch is a two-position toggle-type switch,
labeled IGNITION, on the left sidewall switch and
circuit breaker panel. The switch has ON and NORMAL
positions. For additional details of the ignition switch,
refer to the Ignition System paragraph in the AFM/POH.
For Training Purposes Only
Revised: February 15, 2017
Electrical power from the airplane power distribution
bus to the avionics buses is controlled by two toggletype switch breakers located on the left sidewall
switch and circuit breaker panel. One switch controls
power to the number 1 avionics bus while the other
switch controls power to the number 2 avionics bus.
The switches are labeled AVIONICS and are ON in
2-2
AS-02 Electrical Power Systems
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INVERTER SELECTOR SWITCH
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ON
BUS
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OFF
ON
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ON
1
NORM
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2
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ON
START
OFF
NORM
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BUS TIE
30
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30
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AVIONICS
STBY
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ON
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VIONICS
2
AVIONICS
30
AVIONICS
the forward position and OFF in the aft position. The
avionics power switches should be placed in the OFF
position prior to turning the battery switch ON or OFF,
starting the engine, or applying an external power
source. The avionics power switches may be used in
place of the individual avionics equipment switches.
Two inverters, a main (inverter 1) and a spare (inverter
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inverters operate from D C power supplied through two
circuit breakers on the main bus. Each inverter supplies
26-volt AC and 115-volt AC to the 26-volt AC bus bar
and 115-volt AC bus, respectively. The inverters are
controlled by an inverter selector switch located on the
instrument panel below the avionics stack. The selector
switch had INVERTER 1, INVERTER 2 positions with
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when the battery switch is on and the inverter selector
switch is placed in either INVERTER 1 or INVERTER
2 position.
EXTERNAL POWER SWITCH
AVIONICS BUS TIE SWITCH
ON
BUS
STARTER
OFF
OFF
ON
RESET
ON
ON
BUS
NORM
TRIP
OFF
STARTER
FUEL
BOOST
GENERATOR
OFF
OFF
ON
ON
START
OFF
NORM
MOTOR
ON
RESET
ON
OFF
NORM
TRIP
OFF
STBY PWR
FUEL
BOOST
GENERATOR
ON
ON
START
OFF
NORM
MOTOR
IGNITION
STARTER
1
ON
2
EXTERNAL
SCINOIVA
POWER
EIT SUB
SCINOIV
Y
OFF
STBY PWR
IGNITION
30
AVIONICS
STBY
PWR
STARTER
1
30
ON
OFF
2
VIONICS
Y
AVIONICS
BUS TIE
OFF
30
AVIONICS
AVIONICS
BUS TIE
30
The external power switch is a three-position guarded
toggle-type switch located on the left sidewall switch and
circuit breaker panel. The switch has OFF, STARTER,
The avionics bus tie switch is a two-position guarded and BUS positions and is guarded in the OFF position.
toggle-type switch located on the left sidewall switch When the switch is in the OFF position, battery power
and circuit breaker panel. The switch connects the is supplied to the main bus and to the starter-generator
number 1 and number 2 avionics buses together in the circuit, external power cannot be applied to the main
event of failure of either bus feeder circuit. Because bus, and, with the generator switch in the ON position,
power for each avionics bus is supplied from a separate power is applied to the generator control circuit. When
current limiter on the power distribution bus, failure of the external power switch is in the STARTER position,
DFXUUHQWOLPLWHUFDQFDXVHIDLOXUHRIWKHDႇHFWHGEXV external power is applied to the starter circuit only and
Placing the bus tie switch to the ON position will restore battery power is supplied to the main bus. No generator
power to the failed bus. Operation without both bus power is available in this position. When the external
feeder circuits may require an avionics load reduction, power switch is in the BUS position, external power is
applied to the main bus and no power is available to
depending on equipment installed.
the starter. The battery, if desired, can be connected to
AVIONICS
STBY
PWR
AVIONICS
BUS TIE
For Training Purposes Only
Revised: February 15, 2017
AVIONICS
2-3
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
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the main bus and external power by the battery switch;
however, battery charge should be monitored to avoid
overcharge.
STANDBY ELECTRICAL SYSTEM
Field excitation to the alternator control unit is supplied
through diode logic from a circuit breaker in the standby
alternator relay assembly or the KEEP ALIVE No. 2
circuit breaker in the main power relay box. System
monitoring is provided by two amber annunciators,
labeled STBY ELECT PWR ON and STBY ELECT
PWR INOP, in the annunciator panel. Total amperage
supplied from the standby electrical system can be
monitored on the airplane volt/ammeter with the
selector switch in the ALT position.
The optional standby
electrical
system
serves as a standby
power source after Any time the standby electrical system is turned on,
starting in the event standby power will automatically be supplied to the
the main generator main buses if system voltage drops.
system malfunctions
WARNING
LQ ÀLJKW 7KH V\VWHP
includes an alternator operated at a 75-amp capacity
IN THE EVENT OF A GENERATOR SYSTEM
FAILURE, THE ALTERNATOR-DRIVEN STANDBY
rating. The alternator is belt-driven from an accessory
ELECTRICAL SYSTEM, WHICH HAS 75-AMP
pad on the rear of the engine.
CAPACITY RATING, CAN SUPPLY ESSENTIAL
EQUIPMENT WHEN NONESSENTIAL LOADS
ARE ELIMINATED. DURING A NIGHT FLIGHT IN
ICING CONDITIONS, IT IS POSSIBLE TO HAVE
AN ELECTRICAL LOAD OF APPROXIMATELY
110 AMPS. THIS ELECTRICAL LOAD CAN BE
REDUCED TO THE STANDBY ELECTRICAL
SYSTEM CAPACITY (75-AMPS) BY TURNING OFF
THE FOLLOWING EQUIPMENT:
The system also includes an alternator control unit
located forward of the circuit breaker panel, a standby
alternator contactor assembly on the left front side of
WKH¿UHZDOODQGWZRVZLWFKHVRQWKHOHIWVLGHZDOOVZLWFK
panel.
The standby system switches are a two-position toggletype switch, labeled STBY POWER, and a guarded
two-position switch/breaker, labeled AVIONICS STBY
PWR. The guard covering the standby avionics power
switch must be lifted in order to select the ON position.
Circuit protection and isolation is provided by two circuit
breakers, labeled STBY PWR, on the left sidewall
circuit breaker panel.
• ALL EXTERNAL LIGHTS.
• THE FAILED GENERATOR (TRIP).
• AUTOPILOT AND WEATHER RADAR AND/OR
ENOUGH OTHER NONESSENTIAL AVIONICS AND
LIGHTS TO PREVENT BATTERY DISCHARGE, AS
INDICATED BY THE AMMETER WITH THE BATT
POSITION SELECTED OR ILLUMINATION OF THE
RED VOLTAGE LOW ANNUNCIATOR.
ON
BUS
STARTER
OFF
OFF
ON
ON
RESET
ON
TRIP
S
CIRCUIT BREAKERS
OFF
FUEL
BOOST
GENERATOR
ON
ON
START
OFF
NORM
MOTOR
OFF
STBY PWR
IGNITION
30
AVIONICS
BUS TIE
For Training Purposes Only
Revised: February 15, 2017
OFF
STARTER
1
AVIONICS
STBY
PWR
ON
NORM
ON
OFF
AVIONICS
2
30
STBY PWR
NORM
Most of the electrical circuits in the airplane are
SURWHFWHGE\³SXOORႇ´W\SHFLUFXLWEUHDNHUVPRXQWHGRQ
M left sidewall switch and circuit breaker panel. Should
the
an overload occur in any circuit, the controlling circuit
breaker will trip, opening the circuit. After allowing the
circuit breaker to cool for approximately three minutes,
it may be reset (pushed in).
2-4
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
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BUS
1
PWR
STBY
PWR
FLAP
MOTOR
30
40
10
BUS
2
PWR
STBY
PWR
LEFT
VENT
BLWR
30
40
BUS
1
PWR
FIRE
DET
10
5
START LEFT ANNUN GEN GEN
CONT TURN/ PANEL CONT FIELD
BANK
5
5
5
5
15
RIGHT AUX FUEL RIGHT ANNUN STALL AIR
VENT FUEL CONT TURN/ PANEL WARN COND
BLWR PUMP HEATER BANK
CONT
10
10
5
AFT
VENT
BLWR
OIL
TEMP
BLEED
AIR
HEAT
5
5
5
RIGHT AIR PROP DE-ICE RIGHT PROP PROP
FUEL SPEED 0-SPEED BOOT PITOT ANTI-ICE ANTI-ICE
QTY WARN TEST
HEAT
CONT
5
ITT
GAGE
FUEL
FLOW
5
5
5
5
5
LEFT
W/S
W/S
PITOT ANTI-ICE ANTI-ICE
HEAT
CONT
15
5
15
20
30
LEFT STROBE BEACON MAP INST WING SEAT
LGD LIGHT LIGHT LIGHT LIGHT ICE DET BELT
LIGHT
LIGHT
30
10
5
BUS
2
PWR
RIGHT
LDG
LIGHT
TAXI
LIGHT
NAV
LIGHT
10
30
10
15
10
2
5
5
5
5
ENC
ALT
5
COM/NAV
1
XPDR
1
ADF
1
DG
RMI
AUD/
MKR
A/P
FD
ELEV
TRIM
10
5
5
5
5
5
10
5
COM/NAV
2
XPDR
2
ADF
2
DME
RNAV
RADIO
ALT
AVN
FAN
AUDIO
AMP
10
5
5
5
5
FUEL
SEL
WARN
HSI
2
5
GPS/
LORAN
30
HF
XMT
HF
XMT
10
HF
RCVR
Six lights on the annunciator panel indicate the
condition of the standard electrical system to the
pilot. These lights are GENERATOR OFF, VOLTAGE
LOW, BATTERY OVERHEAT (if installed), STARTER
ENERGIZED, BATTERY HOT (if installed), IGNITION
ON and INVERTER INOP (if installed). These lights
should be observed at all times during airplane
operation and if any light illuminates unexpectedly, a
malfunction may have occurred and appropriate action
should be undertaken to correct the problem. For
details of other lights on the annunciator panel, refer to
WKH$60DVWHU:DUQLQJFKDSWHULQWKLV370
5
TORQ
IND
5
RADIO RH
FLOOD ATT
LIGHT GYRO
5
ANNUNCIATOR LIGHTS
10
LEFT
FUEL
QTY
30
30
IGN
FUEL
TOTAL
BUS
2
PWR
BUS
1
PWR
STBY
FLAP
MOTOR
switch is used for the standby alternator system which
may not be installed on some airplanes. In that case, the
position will be inoperative. Refer to Standby Electrical
System in Section 9 of the AFM/POH for further details.
RADAR RADAR RADAR STM
CONT
R-T GRAPHICS SCP
5
GROUND SERVICE PLUG
RECEPTACLE
5
WARNING
A ground service plug receptacle permits the use of
an external power source for cold weather starting and
during lengthy maintenance work on the electrical and
avionics equipment. External power control circuitry is
provided to prevent the external power and the battery
from being connected together during starting. The
external power receptacle is installed on the left side of
WKHHQJLQHFRPSDUWPHQWQHDUWKH¿UHZDOO
MAKE SURE ALL CIRCUIT BREAKERS ARE
ENGAGED BEFORE ALL FLIGHTS. NEVER
OPERATE
WITH
DISENGAGED
CIRCUIT
BREAKERS
WITHOUT
A
THOROUGH
KNOWLEDGE OF THE CONSEQUENCES.
VOLT/AMMETER AND SELECTOR
SWITCH
50
5
AMPS
10
100
15
VOLTS
0
20
150
25
30
200
-50
GEN
ALT
BATT
VOLT
A volt/ammeter and four-position rotary-type selector
switch are mounted on the left side of the instrument
panel so that electrical system operation can be
monitored. The selector switch has GEN, ALT, BATT,
and VOLT positions and selects either generator
current, standby alternator current, battery charge or
discharge current, or system voltage, respectively,
on the volt/ammeter. The ALT position of the selector
For Training Purposes Only
Revised: February 15, 2017
The ground service circuit incorporates polarity reversal
and overvoltage protection. Power from the external
SRZHUVRXUFHZLOOÀRZRQO\LIWKHJURXQGVHUYLFHSOXJ
is correctly connected to the airplane. If the plug
is
accidentally
c o n n e c t e d
backwards or the
ground
service
voltage
is
too
high, no power
ZLOO ÀRZ WR WKH
electrical system,
thereby preventing
any
damage
to
electrical
equipment.
2-5
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
LEFT SIDE CONTROL PANEL
6
ON
BUS
7
STARTER
OFF
OFF
5
ON
RESET
ON
NORM
TRIP
OFF
FUEL
BOOST
GENERATOR
4
ON
ON
START
3
8
OFF
OFF
NORM
STBY PWR
MOTOR
IGNITION
STARTER
2
1
ON
2
1
30
AVIONICS
STBY
PWR
OFF
30
AVI
VION
ONICS
ON
AVIONICS
AVIONICS
BUS TIE
9
1. 1 or 2 AVIONICS STBY PWR Switch
ON (Forward Position) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Connects standby power for avionics buses 1 or 2.
OFF (Aft Position) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disconnects standby power for avionics buses 1 or 2
For Training Purposes Only
Revised: February 15, 2017
2-6
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
CONTINUED
LEFT SIDE CONTROL PANEL
2. AVIONICS BUS TIE Switch
ON (Forward Position) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Connects the number 1 and number 2 avionics buses
together in the event of failure of either bus feeder circuit and will
restore power to the failed avionics bus; 1 or 2 respectively
OFF (Aft Position) . . . . . . . . . . . . . . . . . . . . . . . . . . . .Keeps number 1 and number 2 avionics buses separately powered
3. STBY PWR Switch
ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Standby power will automatically be supplied to the main
power buses if system voltage drops below 27.5 volts
OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Standby power is disconnected
4. IGNITION Switch
ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Provides continuous ignition regardless of the position of the starter switch
NORM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Arms the ignition system so that ignition will be obtained when
the starter switch is placed in the START position
5. GENERATOR Switch
RESET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Restore generator power, if a momentary fault
should occur in the generating system
ON . . . . . . . . . . . . . . . . . . . . . GCU will automatically control the generator line contactor for normal generator operation.
Switch is spring-loaded to the ON position.
TRIP . . . . . . . . . . . . . . . . . . . . 6KXWVRႇWKHV\VWHPPRPHQWDULO\DQGDIWHUDVXLWDEOHZDLWLQJSHULRGJHQHUDWRURSHUDWLRQ
may be recycled by placing the generator switch momentarily to RESET
6. EXTERNAL POWER Switch
BUS . . . . . . . . . . . . . . . . . . . . . . . . . . . .External power is applied to the main bus and no power is available to the starter
STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .External power is applied to the starter circuit only and battery power is
supplied to the main bus. No generator power is available in this position.
OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery power is supplied to the main bus and to the starter-generator circuit,
external power cannot be applied to the main bus, and, with the generator switch
in the ON position, power is applied to the generator control circuit,
7. BATTERY Switch
ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery power is supplied to the two general buses
OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . &XWVRႇSRZHUWRDOOEXVHVH[FHSWWKHEDWWHU\EXV
8. STARTER Switch
START . . . . . . . . . . . . . . . . . Energizes the engine ignition system provided the ignition switch is in the NORMAL position
OFF . . . . . . . . . . . . . . . . . . . . . . 6KXWVRႇWKHLJQLWLRQV\VWHPDQGLVWKHQRUPDOSRVLWLRQDWDOOWLPHVH[FHSWGXULQJHQJLQH
start or engine clearing Switch is spring-loaded to the OFF position.
MOTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Motors the engine without having the ignition circuit energized and is
used for motoring the engine when an engine start is not desired.
9. AVIONICS 1 AND 2 Switches
ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Powers avionics bus, 1 or 2. May be used in place of
the individual avionics equipment switches
OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removes power to the avionics bus, 1 or 2. Should be placed in the
OFF position prior to turning the battery switch ON or OFF,
starting the engine, or applying an external power source
For Training Purposes Only
Revised: February 15, 2017
2-7
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
INDICATORS AND ANNUNCIATORS
ANNUNCIATOR PANEL
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
GENERATOR
OFF
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
Indicates the generator is not connected to the airplane bus.
VACUUM
LOW
,QGLFDWHVWKHYDFXXPV\VWHPVXFWLRQLVOHVVWKHQDSSUR[LPDWHO\LQ+J
BATTERY
OVERHEAT
Indicates the electrolyte temperature in the optional Ni Cad battery is critically high.
STARTER
ENERGIZED
Indicates the starter generator is operating in the starter mode.
BATTERY
HOT
Indicates the electrolyte temperature in the optional Ni Cad battery is excessively high.
IGNITION
ON
Indicates electrical power is being supplied to the engine ignition system.
For Training Purposes Only
Revised: February 15, 2017
2-8
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
INDICATORS AND ANNUNCIATORS
CONTINUED
LEFT STATIONARY PANEL
1
50
VENT
PULL ON
AMPS
10
5
100
15
VOLTS
0
20
150
25
30
200
-50
GEN
ALT
BATT
VOLT
1. VOLT/AMMETER
GEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Monitors generator current
ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Monitors standby alternator current
BATT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Monitors battery current
VOLT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Monitors system voltage
For Training Purposes Only
Revised: February 15, 2017
2-9
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
TYPICAL ELECTRICAL SYSTEM DIAGRAM
For Training Purposes Only
Revised: February 15, 2017
AS-02 Electrical Power Systems
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
STANDBY ELECTRICAL SYSTEM
For Training Purposes Only
5HYLVHG$SULO
2-11
$6(OHFWULFDO3RZHU6\VWHPV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
TYPICAL ELECTRICAL SYSTEM
For Training Purposes Only
5HYLVHG$SULO
2-12
CONTINUED
$6(OHFWULFDO3RZHU6\VWHPV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
TYPICAL ELECTRICAL SYSTEM
For Training Purposes Only
5HYLVHG$SULO
2-13
CONTINUED
$6(OHFWULFDO3RZHU6\VWHPV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
Page left Intentionally blank
For Training Purposes Only
5HYLVHG$SULO
2-14
$6(OHFWULFDO3RZHU6\VWHPV
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
LANDING LIGHTS
LIGHTING
LEFT
LDG
LIGHTS
LIGH
RE
T
he Caravan 208 aircraft lighting system consists
of exterior aircraft lighting, and interior cockpit &
cabin lighting. Exterior aircraft lights are controlled by
switches located on the on the lighting control panel
on the left side of the instrument panel. This panel also
incorporates switches for no smoking signs (labeled
NO SMOKE - passenger version only), the fasten seat
belts (Labeled SEAT BELT - passenger version only),
and the cabin lights (labeled CABIN). Four concentrictype dual lighting control knobs are grouped together
on the lower part of the instrument panel to the left
of the control pedestal and include more controls for
various cockpit lights.
LEFT
LDG
TAXI/
RE
RECOG
ON
RIGHT
LDG
STROBE
STR
ST
ROBE
NAV
BCN
XI/
OG
RIGHT
LDG
ON
SMOKE
NO
SMOKE ON
BELT
SEAT
BELT
CABIN
CABIN
Two landing lights are installed on the airplane, one in
each wing leading edge mounted outboard. The lights
provide illumination forward and downward during
WDNHRႇ DQG ODQGLQJ 7KH OLJKWV DUH SURWHFWHG E\ WZR
³SXOORႇ¶ W\SH FLUFXLW EUHDNHUV ODEHOHG /()7 /'* /7
and RIGHT LDG LT, on the left sidewall switch and
circuit breaker panel.
EXTERIOR LIGHTING
Exterior lighting consists of three navigation lights, two
landing lights, two taxi/recognition lights, two strobe
OLJKWVDÀDVKLQJEHDFRQDQGWZRXQGHUZLQJFRXUWHV\
lights. All exterior lights are controlled by toggle
switches located on the lighting control panel on the
left side of the instrument panel. The toggle switches
are ON in the up position and OFF in the down position. TAXI/RECOGNITION LIGHTS
NAVIGATION LIGHTS
LIGHTS
LEFT
LDG
STROBE
TAXI/
RECOG
ON
NAV
A
RIGHT
LDG
LIGHTS
LIGHTTS
LIGH
LEFT
LDG
TTAXI/
AXI/
RECOG
REC
RE
COG
ON
RIGHT
LDG
STROBE
NAV
NAV
BCN
LEFT
LDG
TAXI/
RECOG
ON
RIGHT
LDG
ON
NAV
ON
SMOKE
NO
SMOKE ON
BELT
SEAT
BELT
CABIN
CABIN
BCN
ON
SMOKE
NO
SMOKE ON
BELT
SEAT
SEAT
BE
BELT
LT
CABIN
CABIN
SMOKE
NO
For Training Purposes Only
Revised: February 15, 2017
Two taxi/recognition lights are mounted inboard of each
landing light in each wing leading edge. The lights are
Conventional navigation focused to provide illumination of the area forward of
lights are installed on the the airplane during ground operation and taxiing. The
wing tips and tailcone lights are also used to enhance the conspicuity of
stinger. The lights are WKH DLUSODQH LQ WKH WUDႈF SDWWHUQ RU HQURXWH7KH WD[L
protected by a “pull- UHFRJQLWLRQ OLJKWV DUH SURWHFWHG E\ D ³SXOORႇ¶ W\SH
Rႇ´ W\SH FLUFXLW EUHDNHU circuit breaker, labeled TAXI LIGHT, on the left sidewall
labeled NAV LIGHT, on switch and circuit breaker panel.
the left sidewall switch
and circuit breaker panel.
BELT
SEAT
3-1
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
lower part of the instrument panel to the left of the control
pedestal. These four controls vary the intensity of the
instrument panel lighting, the left sidewall switch and
circuit breaker panel lighting, the pedestal lighting, and
the overhead panel lighting. The following paragraphs
describe the function of these controls. Other
miscellaneous lighting provided or available includes a
control wheel maplight, cabin lights, passenger reading
lights, and a no smoking/seat belt sign. Discussion of
these lights and their controls is also included in the
following paragraphs.
STROBE LIGHTS
STROBE
LIGHTS
LEFT
LDG
TAXI/
RECOG
ON
RIGHT
LDG
STROBE
STR
ST
ROBE
NAV
BCN
ON
SMOKE
NO
SMOKE ON
BELT
SEAT
BELT
CABIN
CABIN
SMOKE
NO
BE
SEA
A high intensity strobe light system is installed on the
airplane. The system includes two strobe lights (with
remote power supplies) located one on each wing tip.
The lights are used to enhance anti-collision protection
for the airplane and are required anti-collision lights for COCKPIT LIGHTING
night operations. The strobe lights are protected by a
³SXOORႇ¶W\SHFLUFXLWEUHDNHUODEHOHG6752%(/,*+7
LEFT FLIGHT PANEL/LEFT FLOOD
on the left sidewall switch and circuit breaker panel.
LIGHTING CONTROL KNOBS
LIGH
FLASHING BEACON LIGHT
LIGHTS BRT
LIGHT
LIGH
L FL
FFLT
LT PANEL
PANEL
L FL
FFLOOD
LOOD
STROBE
TAXI/
RECOG
ON
NAV
RIGHT
LDG
LLWR
WR PANEL/
P
PED/OVHD
CW/C
CW/CKT BKR
BELT
SEATT
BELTT
RF
RF
ENG INST
RADIO
BCN
ON
SMOKE
NO
SMOKE ON
L FLT PANEL
L FLOOD
BCN
LIGHTS
LEFT
LDG
INERTIAL SEPE
BYPASS - PULL
NORMAL -PUSH
R FLT PANEL
R FLOOD
PARKING
BRAKE
PULL
CABIN
CABIN
ABIN
T
CABIN
$ UHG ÀDVKLQJ EHDFRQ OLJKW
is installed on the top of the
YHUWLFDO ¿Q DV DGGLWLRQDO DQWL
FROOLVLRQSURWHFWLRQLQÀLJKWDQG
for recognition during ground
operation. The light is visible
WKURXJK ƒ 7KH ÀDVKLQJ
beacon light circuit is protected
E\ D ³SXOORႇ¶ W\SH FLUFXLW EUHDNHU ODEHOHG %($&21
LIGHT, on the left sidewall switch and circuit breaker
panel.
COURTESY LIGHTS
Two courtesy lights are installed, one under each wing.
The lights illuminate the area outside of the airplane
adjacent to the crew entry doors. The lights operate
in conjunction with the cabin lights and are controlled
by the cabin light switches as described in the Cabin
Lights paragraph in this section.
The large (outer) knob of this control, labeled L FLT
PANEL, varies the intensity of the postlights illuminating
the left portion of the instrument panel directly in front
of the pilot. The control also varies the intensity of the
integral lighting of the digital clock, HSI, FCI, and radio
instruments. The small (inner) knob of the control,
labeled L FLOOD, varies the brightness of the left side
ÀRRGOLJKWORFDWHGRQWKHULJKWDIWVLGHRIWKHRYHUKHDG
SDQHO 7KLV ÀRRGOLJKW PD\ DOVR EH XVHG WR LOOXPLQDWH
the left sidewall switch and circuit breaker panel.
Clockwise rotation of either of the concentric control
knobs increases lamp brightness and counterclockwise
rotation decreases brightness.
RIGHT FLIGHT PANEL/RIGHT FLOOD
LIGHTING CONTROL KNOBS
S BRT
ANEL
OOD
LIGHTS
LIGHT
LIGH
TS BRT
BRT
BR
L FLT PANEL
L FLOOD
INERTIAL SEPE
BYPASS - PULL
NORMAL -PUSH
R FLT
FFLLT PANEL
PANEL
R FLOOD
FLOOD
FL
LWR
WR P
PANEL/
ANEL/
PED/OVHD
CW/CKT
W/CKT BKR
R FLT PANEL
R FLOOD
ENG INST
RADIO
PARKING
BRAKE
PULL
ANEL/
INTERIOR LIGHTING
ENG INST
The large (outer) knob of this control, labeled R
Instrument and control panel lighting is provided by FLT PANEL, varies the intensity of the postlights
LQWHJUDO ÀRRG DQG SRVW OLJKWV )RXU FRQFHQWULFW\SH LOOXPLQDWLQJ WKH ULJKW ÀLJKW SDQHO GLUHFWO\ LQ IURQW RI
dual lighting control knobs are grouped together on the the right passenger. The small (inner) knob of this
For Training Purposes Only
Revised: February 15, 2017
3-2
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
control, labeled R FLOOD, varies the brightness of counterclockwise rotation of the RADIO knob turns the
WKH ULJKW VLGH ÀRRGOLJKW ORFDWHG RQ WKH OHIW DIW VLGH RI digital readouts on bright for daylight viewing.
the overhead panel. Clockwise rotation of either of the
concentric control knobs increases lamp brightness CONTROL WHEEL MAPLIGHT
and counterclockwise rotation decreases brightness.
LOWER PANEL, PEDESTAL, OVERHEAD,
SWITCH/CIRCUIT BREAKER LIGHTING
CONTROL KNOBS
LIGHTS BRT
L FLT PANEL
L FLOOD
INERTIAL SEPE
BYPASS - PULL
NORMAL -PUSH
R FLT PANEL
R FLOOD
LLWR
WR PANEL/
PANEL/
PED/OVHD
CW/C
W/CKT BKR
W/C
CW/CKT
LWR PANEL/
PED/OVHD
CW/CKT BKR
ENG INST
RADIO
PARKING
BRAKE
PULL
The large (outer) knob of this control, labeled LWR
PANEUPED/O V HD, varies the intensity of postlights
DQG D ÀRRGOLJKW LOOXPLQDWLQJ WKH ORZHU SRUWLRQ RI WKH
LQVWUXPHQWSDQHODÀRRGOLJKWLOOXPLQDWLQJWKHSHGHVWDO
and lights illuminating the overhead panel and OAT
gauge. The small (inner) knob of the control, labeled
6:&.7 %.5 YDULHV WKH LQWHQVLW\ RI WZR ÀRRGOLJKWV
illuminating the left sidewall switch and circuit breaker
panel. Clockwise rotation of either of the concentric
control knobs increases lamp brightness and
counterclockwise rotation decreases brightness.
A control wheel maplight is mounted on the bottom
RI WKH SLORW¶V FRQWURO ZKHHO 7KLV OLJKW LOOXPLQDWHV WKH
lower portion of the cabin in front of the pilot, and is
XVHG IRU FKHFNLQJ PDSV DQG RWKHU ÀLJKW GDWD GXULQJ
night operation. Brightness of the light is adjusted with
a rheostat control knob on the bottom of the control
wheel.
CABIN LIGHTS
LIGHTS
LEFT
LDG
TAXI/
RECOG
ON
RIGHT
LDG
T
T
STROBE
NAV
CABIN
CABIN
BCN
ON
ENGINE INSTRUMENTS/RADIO LIGHTING
CONTROL KNOBS
LIGHTS BRT
L FLT PANEL
L FLOOD
INERTIAL SEPE
BYPASS - PULL
NORMAL -PUSH
R FLT PANEL
R FLOOD
SMOKE
NO
SMOKE ON
ENG INST
RADIO
LWR PANEL/
PED/OVHD
CW/CKT BKR
ENG INST
RADIO
RADIO
PARKING
BRAKE
PULL
The large (outer) knob of this control, labeled ENG
INST, varies the intensity of the post lights which
illuminate the engine instruments on the top center of
the instrument panel and the intensity of the dimmable
lamps on the annunciator panel. The small (inner) knob
of this control, labeled RADIO, controls the integral
lights and digital readouts of the avionics equipment
Clockwise rotation of either of the concentric control
knobs increases lamp brightness and counterclockwise
rotation decreases brightness. However, extreme
For Training Purposes Only
Revised: February 15, 2017
BELT
SEAT
BELT
CABIN
CABIN
ABIN
Four cabin lights are installed in the interior of the airplane
to facilitate boarding or deplaning the airplane or loading
and unloading cargo during night operations. The lights
are located one above the center of the forward cabin
area, one above the left side of the center cabin area,
one above the aft cargo door, and one above the aft right
side of the aft cargo area (Cargo Versions} or above
the passenger entry door (Passenger Version). These
lights (and the courtesy
light located under each
wing) are controlled by a
two-position toggle switch,
labeled CABIN, on the
lighting control panel, a
rocker-type switch located
just forward of the cargo
door on the inside left
sidewall and, on the Passenger Version, a rocker
switch located just forward of the passenger entry
3-3
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
door on the inside right sidewall. Actuating either of
these switches turns on the cabin lights regardless of
the corresponding position of the other switches. This
light circuit does not require power to be applied to
the main electrical system buses (battery switch on)
for operation. The courtesy lights circuit incorporates
a solidstate timer which allows the courtesy lights to
remain illuminated for a period of 30 minutes after the
lights have been turned on.
NO SMOKING/SEAT BELT SIGN
(PASSENGER VERSION ONLY)
LIGHTS
LEFT
LDG
TAXI/
RECOG
ON
RIGHT
LDG
STROBE
NAV
BCN
SMOKE
NO
SMOKE ON
BELT
SEAT
BELT
ON
SMOKE
NO
SMOKE ON
BELT
SEAT
SEA
BELT
BELT
CABIN
C
CABIN
A lighted warning sign may be installed in the airplane
WR IDFLOLWDWH ZDUQLQJ SDVVHQJHUV RI LPSHQGLQJ ÀLJKW
operation s necessitating the fastening of seat belts
Passenger reading lights may be installed near each and/or the extinguishing of all smoking materials. This
RIWKHDIWSDVVHQJHU¶VSRVLWLRQV7KHOLJKWVDUHORFDWHG installation consists of a small lighted panel mounted
in 11 small convenience panels above each seat. A in the cabin headliner immediately aft of the overhead
pushbutton-type ON, OFF switch, mounted in each console and two toggle-type switches, labeled SEAT
panel controls the lights. The lights can be pivoted in BELT and NO SMOKE, on the lighting control panel.
their mounting sockets to provide the most comfortable When these switches are placed in the ON position, the
warning signs illuminate, displaying the international
angle of illumination for the passenger.
JUDSKLF V\PEROLVP IRU ³IDVWHQ VHDW EHOWV´ DQG ³QR
VPRNLQJ´WRWKHUHDUFDELQSDVVHQJHUV7KHFLUFXLWIRU
WKHZDUQLQJVLJQOLJKWVLVSURWHFWHGE\D³SXOORႇ´W\SH
circuit breaker, labeled SEAT BELT SIGN, on the left
sidewall switch and circuit breaker panel.
PASSENGER READING LIGHTS
(PASSENGER VERSION ONLY)
For Training Purposes Only
Revised: February 15, 2017
3-4
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
LIGHTING CONTROL PANEL
LIGHTS
LEFT
LDG
TAXI/
RECOG
ON
RIGHT
LDG
6
7
5
STROBE
NAV
BCN
ON
8
4
3
SMOKE
NO
SMOKE ON
BELT
SEAT
SE
BELT
CABIN
CABIN
9
2
1
1. SEAT BELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on seat belt sign
2. NO SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Switch up turns on no smoking sign
3. NAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on all navigation lights
4. STROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on all stobe lights
5. TAXI/RECOG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on all taxi and recognition lights
6. LEFT LDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on left landing lights
7. RIGHT LDG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on right landing lights
8. BCN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Switch up turns on beacon lights
9. CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Switch up powers cabin lights controls
For Training Purposes Only
Revised: February 15, 2017
3-5
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
CONTINUED
LOWER LEFT OF THE CONTROL PEDESTAL CONTROL PANEL
LIGHTS BRT
L FLT PANEL
L FLOOD
INERTIAL SEPE
BYPASS - PULL
NORMAL -PUSH
R FLT PANEL
R FLOOD
4
5
3
LWR PANEL/
PED/OVHD
CW/CKT BKR
6
RADIO
7
2
1
ENG INST
PARKING
PAR
ARKI
KING
KI
NG
BRAKE
BR
B
RAK
AKE
E
8
1. LWR PANEL/PED/OVHD
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
2. CW/CKT BKR
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
3. L FLT PANEL
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
4. L FLOOD
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
5. R FLOOD
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
6. R FLT PANEL
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
7. RADIO
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
8. ENG INST
TURN CW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illuminates brighter
TURN CCW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 'LPVOLJKWVDQGZKHQGHWHQWLVUHDFKHGOLJKWVZLOOWXUQRႇ
For Training Purposes Only
Revised: February 15, 2017
3-6
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
NORMAL OPERATION
EMERGENCY PROCEDURES
The lighting control panel, located on the left side of
the instrument panel, contains switches for exterior
lights and also incorporates switches for no smoking
signs (labeled NO SMOKE - passenger version only),
the fasten seat belts (Labeled SEAT BELT - passenger
version only), and the cabin lights (labeled CABIN).
Four concentric-type dual lighting control knobs are
grouped together on the lower part of the instrument
panel to the left of the control pedestal and include
more controls for various cockpit lights.
Emergency procedures include but are not limited to
the following items. These may or may not include
immediate action memory items. Further information
is available in the AFM/POH section 3 and the QRH
checklist.
None
LIMITATIONS
None
For Training Purposes Only
Revised: February 15, 2017
3-7
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
Page left Intentionally blank
For Training Purposes Only
Revised: February 15, 2017
3-8
AS-03 Lighting
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
MASTER WARNING
SYSTEM
In normal conditions, the Annunciator Panel is
protected by ANNUN PANEL circuit breakers located
on the left sidewall circuit breaker panel. If the aircraft
has a Standby Alternator installed, power is also routed
through the KEEP ALIVE #2 circuit breaker, located
on the Electrical Power Box, and routed through the
Standby Power Switch. When the Standby Power
switch is placed in the ON position, power is provided
through the KEEP ALIVE #2 circuit breaker only.
OVERVIEW
The annunciator panel is located at the top edge of the
instrument panel directly in front of the pilot. The panel
contains separate indicator lamps which illuminate 28 VDC Annunciator panel power is supplied by the
JUHHQDPEHURUUHGZKHQDVSHFL¿FFRQGLWLRQRFFXUVLQ Keep Alive #2 circuit breaker. When the Standby
the associated airplane system.
Power switch is placed in the ON position, 28 VDC
power supplied to the Annunciator Panel. 28 VDC for
dim/bright power is provided by the circuit breaker
labeled ANNUN PANEL, mounted on the left sidewall
ANNUNCIATOR SYSTEM
circuit breaker panel. When in the Night position, the
switch provides 28 VDC to the Annunciator Panel night
circuitry.
RED LENS ANNUNCIATORS
FIRE
DETECT
A red colored lamp illuminates when a hazardous
condition exists that requires immediate corrective
action.
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
GENERATOR
OFF
EMERGENCY
EMERGENCY
POWER
POWER LEVER
LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
STARTER
ENERGIZED
TEST
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL
FUEL PRESS
PRESS
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY
STBY ELECT
ELECT
PWR INOP
DOOR
WARNING
DE-ICE
PRESSURE
LAMP TEST SWITCH
STARTER
ENERGIZED
WINDSHIELD
ANTI-ICE
DAY/NIGHT SWITCH
DE-ICE
PRESSURE
A green colored lamp illuminates to indicate a normal or
safe condition in the system.
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
For Training Purposes Only
Revised: February 15, 2017
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
WINDSHIELD
WINDSHIELD
ANTI-ICE
The Lamp Test Switch is a press-to-test pushbutton
located to the left of the annunciator panel. When
activated, the LAMP TEST switch illuminates all
lamps on the annunciator panel and activates both
IXHOVHOHFWRURႇZDUQLQJKRUQVSURYLGLQJLQGLFDWLRQRI
normal lamp operation.
IGNITION
ON
FUEL SELECT
OFF
GREEN LENS ANNUNCIATORS
ENGINE
FIRE
DOOR
WARNING
TEST
FUEL
FUEL SELECT
SELECT
OFF
WINDSHIELD
ANTI-ICE
An amber colored lamp illuminates to indicate a
cautionary condition in the system that may or may not
require immediate corrective action.
ENGINE
FIRE
ENGINE
FIRE
VOLTAGE
LOW
IGNITION
ON
AMBER LENS ANNUNCIATORS
VOLTAGE
LOW
-ANNUN PANELLAMP
NIGHT
DE-ICE
PRESSURE
The Day/Night toggle switch is located to the left
of the annunciator panel. The DAY/NIGHT switch
controls annunciator brightness by providing variable
annunciator intensity down to a preset minimum dim
level. Only the green lamps and some amber lamps
dim when the Day/Night toggle switch is in the NIGHT
position. This variable intensity is controlled by the
ENG INST lighting rheostat. Some amber annunciators
and no red annunciators dim, even if the Day/Night
toggle switch is in the NIGHT position. If a red or
4-1
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
non-dimmable amber annunciator illuminates at night
and becomes an unacceptable distraction to the pilot
because of its brightness level, it may be extinguished
IRUWKHUHPDLQGHURIWKHÀLJKWE\SXVKLQJLQRQWKHIDFH
of the light assembly and allowing it to pop out. To
reactivate the annunciator, pull the light assembly out
slightly and push back in.
For Training Purposes Only
Revised: February 15, 2017
4-2
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
INDICATORS
RED LENS ANNUNCIATORS
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
,QGLFDWHVDQH[FHVVLYHWHPSHUDWXUHFRQGLWLRQDQGRUSRVVLEOH¿UHKDVRFFXUUHGLQWKHHQJLQH
compartment.
Indicates engine oil pressure is less than 38 psi.
Indicates the generator is not connected to the airplane bus.
Indicates the emergency power lever is advanced out of the NORMAL position.
VOLTAGE
LOW
Indicates electrical system bus voltage is low and power is being supplied from the battery.
VACUUM
LOW
Indicates the vacuum system suction is less than approximately 3.0 in. Hg.
RESERVOIR
FUEL LOW
FUEL SELECT
OFF
Indicates the fuel level in the reservoir tank is approximately one-half full or less.
,QGLFDWHVRQHRUERWKIXHOWDQNVHOHFWRUVDUHRႇ
DOOR
WARNING
Indicates the upper cargo door and/or upper aft passenger doors (Passenger Version only) are
not latched.
BATTERY
OVERHEAT
Indicates the electrolyte temperature in the optional Ni Cad battery is critically high.
For Training Purposes Only
Revised: February 15, 2017
4-3
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
INDICATORS
AMBER LENS ANNUNCIATORS
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
AUX FUEL
PUMP ON
STARTER
ENERGIZED
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
Indicates the auxiliary fuel pump is operating.
FUEL PRESS
LOW
Indicates fuel pressure in the fuel manifold assembly is below 4.75 psi.
STARTER
ENERGIZED
Indicates the starter generator is operating in the starter mode.
LEFT
FUEL LOW
Indicates fuel quantity in the left fuel tank is 25 gallons or less.
RIGHT
FUEL LOW
Indicates fuel quantity in the right fuel tank is 25 gallons or less.
STBY ELECT
PWR ON
IGNITION
ON
Indicates the standby alternator is supplying electrical power to the bus.
BATTERY
HOT
Indicates the electrolyte temperature in the optional Ni Cad battery is excessively high.
CHIP
DETECTOR
Indicates that metal chips have been detected in either the reduction gearbox case, or accessory
gearbox case.
STBY ELECT
PWR INOP
Indicates electrical power is not available from the standby alternator.
For Training Purposes Only
Revised: February 15, 2017
4-4
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
INDICATORS
GREEN LENS ANNUNCIATORS
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELECT
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELECT
PWR INOP
DOOR
WARNING
IGNITION
ON
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
For Training Purposes Only
Revised: February 15, 2017
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
Indicates electrical power is being supplied to the engine ignition system.
Indicates electrical power is being supplied to the windshield anti-ice power relay.
Indicates pressure in the de-ice boot system has reached approximately 15 psi.
4-5
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
Page Left Intentionally Blank
For Training Purposes Only
Revised: February 15, 2017
4-6
AS-04 Master Warning System
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
SYSTEM DESCRIPTION
FUEL SYSTEM
FUEL TANKS
OVERVIEW
The Cessna Caravan 208B Fuel systems and
associated components provide a means for refueling,
storing, distributing, and measuring fuel quantity. The
system includes Fuel Reservoirs, Ventilating systems,
Distribution controls and all associated Fuel lines,
Valves and Filter components.
The Cessna Caravan 208B is equipped with two vented,
integral (wet cell) fuel tanks that store fuel input through
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has a usable capacity of 167.8 U.S. gallons (1124.25
pounds). Total usable fuel is 332.8
U.S. Gallons
(2224.4 pounds). Each tank is equipped with four fuel
quantity transmitters, one inboard, one center inboard,
one center outboard, and one outboard. These fuel
quantity transmitters detect the quantity of fuel in each
tank and produce signals proportional to the quantity.
AURAL WARNING HORNS
ENGINE
FIREWALL
SHUTOFF VALVE
VENT
FROM FUEL SELECTOR
OFF SWITCHES
FIREWALL FUEL
SHUTOFF CONTROL
FUEL LINE
CONNECTION
COVERS AND
DRAINS
FROM LEFT
FUEL LOW
SWITCH
RESERVOIR MANIFOLD
ASSEMBLY
FUEL SELECTOR
OFF WARNING
RELAY ASSEMBLY
LEFT
FUEL LOW
FROM RIGHT
FUEL LOW
SWITCH
FUEL SELECT
OFF
FUEL PRESS
LOW
RESERVOIR
FUEL LOW
RIGHT
FUEL LOW
ANNUNCIATOR PANEL
LEGEND
FUEL SUPPLY
PRESSURE-FED FUEL
MOTIVE-FLOW FUEL
DRAIN FUEL
VENT
MECHANICAL CONNECTION
ELECTRICAL CONNECTION
VENT
RESERVOIR LOW
FUEL SENSOR
RESERVOIR
LEFT FUEL TANK
FILLER CAP
FUEL LOW
SWITCH
RIGHT FUEL TANK
DRAIN
CONTROL
KNOB
SCREEN
AUX FUEL
PUMP ON
DRAIN
VALVE
DRAIN
VALVE
DRAIN
VALVE
RIG
FUEL TANK
SELECTORS
HT
ON
165
GAL
ON
165
GAL
SCREEN
FUEL LOW
SWITCH
FILLER CAP
AUX FUEL
PUMP SWITCH
FT
LE
SCREEN
DRAIN
VALVE
SCREEN
322 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCED IN FLIGHT : 200 LBS
VENT WITH FLOAT
VALVE AND PRESSURE
RELIEF VALVE
5
4
6
6
4
2
E
8
10
FUEL 12
14
16
G A QTY 0
LL O NS X 1
8
9
FUEL TANK SELECTORS
10
11
LBSX 100
B A SED
5
4
7
3
2
1
E
6
7
3
2
1
E
6
4
2
E
8
10
FUEL 12
14
16
G A QTY 0
LL O NS X 1
8
9
10
11
VENT WITH FLOAT
VALVE AND PRESSURE
RELIEF VALVE
LBSX 100
B A SED
O N 6 .7L BS/G AL
LEFT FUEL QUANTITY
O N 6 . 7L B S / G A L
RIGHT FUEL QUANTITY
C208BDIAGRAM
FUEL SYSTEM
For Training Purposes Only
Revised: February 15, 2017
Fuel5-1System
AS-05 Fuel
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
The signals are sent to the electrically operated Fuel
Quantity Indicators on the instrument panel.
FUEL MANIFOLD
Located just forward of the fuel reservoir, the fuel
manifold inputs fuel from the ejector and auxiliary fuel
pumps and sends it to the engine. Mounted on the fuel
manifold, a fuel pressure switch is used to illuminate
the amber FUEL PRESS LOW annunciator and cause
the auxiliary electric boost pump to energize when fuel
pressure drops below 4.75 PSI. Fuel in the reservoir
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A Fuel Low switch in each tank detects a low fuel
condition when the level of either fuel tank reaches 25
gallons ±5 gallons. These switches send signals to the
Warning Relay Assembly which in turn sends a signal
to the Annunciator Panel to illuminate the amber LEFT/
RIGHT FUEL LOW annunciator for its respective tank.
FIREWALL FUEL SHUTOFF VALVE
FUEL RESERVOIR
The reservoir is located at the low point in the fuel
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valve at each of the four entry points for the fuel lines
entering the fuel reservoir from the fuel tanks. These
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fuel tank fuel lines. The reservoir maintains a head of
fuel around the ejector boost pump and auxiliary boost
pump, which are contained within the reservoir to
prevent pump cavitation in low-fuel quantity situations,
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level of fuel in the reservoir drops below approximately
half-full (2.05 ± .10 gallons), the Low Fuel Level switch
located in the fuel reservoir provides a signal causing
the red RESERVOIR FUEL LOW annunciator to
illuminate.
EJECTOR PUMP
Located in the fuel reservoir, the ejector boost pump,
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operating. There is an Ejector Pump Check Valve
located upstream of the fuel ejector pump, preventing
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AUXILIARY PUMP
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labeled FUEL SHUTOFF-PULL OFF and located on
the right side of the pedestal. The push-pull knob has
a press-to-release button in the center which locks the
knob in position when the button is released
FUEL FILTER
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WKH¿OWHULVE\SDVVLQJIXHO
OIL-TO-FUEL HEAT EXCHANGER
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fuel heater to the engine-driven fuel pump where fuel
is delivered under pressure to the fuel control unit.
The oil-to-fuel heat exchanger continuously heats fuel,
preventing ice from collecting in the fuel control unit.
FUEL CONTROL UNIT
Also located in the fuel reservoir is the auxiliary
electric boost pump. The auxiliary electric boost pump
The fuel control unit meters the fuel and directs it to the
automatically turns on in the event of an ejector boost
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and 14 fuel nozzles located in the combustion chamber.
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Fuel in the reservoir is then pumped to the reservoir
manifold assembly through either the ejector or auxiliary
electric boost pump.
For Training Purposes Only
Revised: February 15, 2017
5-2
AS-05 Fuel
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
external sump drain
valves allow for the
Phillips screwdriver
When the engine is
on the fuel sampler
shut down, residual
to depress the valve
fuel in the engine
and then twist to lock
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the drain valve in the
fuel
drain
can
open position. The
mounted on the front
drain valve for the
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reservoir is controlled
This can should be
by a double-button
drained once a day,
push-pull
drain
or at an interval not
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to exceed six engine
consists of a drain pipe which can be depressed upward
shutdowns. A drain
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valve on the bottom
for fuel spillage when checking the drains as they have
side of the cowling enables the pilot to drain the
a tendency to become lodged with contaminants and
contents of the fuel drain can into a suitable container.
remain open.
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FUEL DRAIN CAN
FUEL PUMP DRAIN RESERVOIR
FUEL VENTING
To control expended lubricating oil from the engine
fuel pump drive coupling area and provide a way to
determine if fuel is leaking past the fuel pump seal,
airplanes are equipped with a drainable reservoir
to collect this allowable discharge of oil and any fuel
seepage. The reservoir is mounted on the front left side
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interval not to exceed six engine shutdowns. A drain
Fuel system venting is essential to system operation.
valve on the bottom side of the cowling enables the
Complete blockage of the vent system will result in
pilot to drain the contents of the reservoir into a suitable
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container. A quantity of up to 3 cc of oil and 20 cc of fuel
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discharge per hour of engine operation is allowable. If
the fuel level inside the tank rises above the valve, the
the quantity of oil or fuel drained from the reservoir is
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One section of the fuel vent system is routed from the
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lines running outboard to each tank. These vent lines
allow the fuel reservoir to be vented to both fuel tanks.
Venting occurs through vent lines, one from each fuel
tank, which protrude from the trailing edge of the wing
at the wing tips.
FUEL DRAINS
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drains should be drained to check for fuel contamination
and grade. Drain valves are located on the inboard end
of each fuel tank, in fuel tank external sumps, on the
left side of the cargo pod for the reservoir tank, and
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For Training Purposes Only
Revised: February 15, 2017
5-3
AS-05 Fuel
3එඔ඗ග7කඉඑඖඑඖඏ0ඉඖඝඉඔ
&ඉකඉඞඉඖ6ඍකඑඍඛ඗ඎ$එකඋකඉඎග
CONTROLS
same time. Normal operation is with both tanks on. A
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the pilot if one or both of the fuel tank selectors are left
in the OFF position inadvertently. The system includes
redundant warning horns, a red FUEL SELECT OFF
annunciator, actuation switches, and miscellaneous
electrical hardware. The dual aural warning system
is powered through the START CONT circuit breaker
with a non-pullable FUEL SEL WARN circuit breaker
installed in series to protect the integrity of the start
system. The annunciator is powered from the ANN
PANEL circuit breaker.
AUXILIARY BOOST PUMP SWITCH
ON
BUS
STARTER
OFF
OFF
ON
ON
RESET
ON
NORM
TRIP
OFF
ON
NORM
FUEL
BOOST
GENERATOR
ON
ON
START
OFF
OFF
NORM
STBY PWR
STARTER
1
30
AVIONICS
STBY
PWR
AVIONICS
BUS TIE
OFF
MOTOR
IGNITION
ON
OFF
FUEL
BOOST
2
30
AVIONICS
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gravity to the fuel reservoir.
An auxiliary boost pump switch, located on the left
sidewall switch and circuit breaker panel, is labeled
FUEL BOOST and has OFF, NORM, and ON positions.
When the switch is in the OFF position, the auxiliary
boost pump is inoperative. When the switch is in the
NORM position, the auxiliary boost pump is armed and
will operate when fuel pressure in the fuel manifold
assembly drops below 4.75 psi. This switch position is
used for all normal engine operation where main fuel
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auxiliary boost pump is used as a standby. When the
auxiliary boost pump switch is placed in the ON position,
the auxiliary boost pump will operate continuously. This
position is used for engine start and any other time
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the switch in the NORM position, and for all operations
utilizing aviation gasoline.
FUEL TANK SELECTORS
The Auxiliary Fuel Pump On
AUX FUEL
annunciator illuminates amber when
PUMP ON
Auxiliary Electric Fuel Pump is
operating such as when the auxiliary boost pump switch
is placed in the ON position or when the auxiliary boost
pump switch is in the NORM position and fuel pressure
in the fuel manifold assembly drops below 4.75 psi.
FUEL PRESS LOW
The Fuel Pressure Low Annunciator
illuminates amber when the Manifold
Fuel Pressure Switch detects less
than 4.75 PSI fuel pressure.
NORM
UP
AUX FUEL PUMP ON
FUEL PRESS
LOW
s FLAP MOTOR
STBY
DOWN
INDICATORS/ANNUNCIATORS
STBY
FAN/OPEN
OPEN/FAN
OFF
1000
1500
500
2000
0
USE NO
OIL
CLOSE
uy
PSI
CLOSE
OXYGEN
SUPPLY PRESSURE
MADE IN USA
ON
OFF
FT
LE
LEFT/RIGHT FUEL LOW
OFF
RIG
HT
FUEL TANK
SELECTORS
ON
165
GAL
ON
165
GAL
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT : 200 LBS
OFF
OFF
Two
amber
fuel
RIGHT
low
warning
FUEL LOW
annunciators, one for
each wing tank, are located on the annunciator panel.
The annunciators are labeled LEFT FUEL LOW and
RIGHT FUEL LOW. Each annunciator will illuminate
when the fuel in the respective tank is 25 gallons or
7KHUH DUH WZR IXHO WDQN VKXWRႇ YDOYHV ODEHOHG /()7 less. Separate circuit breakers provide 28 VDC power
ON and OFF, and RIGHT, ON and OFF, located on the to each of the Left and Right Fuel Quantity Indicators.
overhead panel. The pilot can manually select fuel to
be used from either left or right fuel tanks or both at the
FT
LE
RIG
HT
LEFT
FUEL LOW
FUEL TANK
SELECTORS
ON
165
GAL
ON
165
GAL
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT : 200 LBS
For Training Purposes Only
Revised: February 15, 2017
5-4
AS-05 Fuel