Cessna 208B Grand Caravan EX. Airplane Flight Manual (2012)

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 10

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 10

CARGO DOORS REMOVED KIT

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

20 June 2013

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S10-1 thru S10-6

Original

FAA APPROVED

S10-2

U.S.

208BPHCUS-S10-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 10

GARMIN G1000

SERVICE BULLETIN CONFIGURATION LIST

The following is a list of Service Bulletins that are applicable to the

operation of the airplane, and have been incorporated into this

supplement. This list contains only those Service Bulletins that are

currently active.

Airplane Serial

Revision

Incorporated

Number Title

Effectivity

Incorporated

in Airplane

FAA APPROVED

208BPHCUS-S10-00

U.S.

S10-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 10

MODEL 208B 867 SHP

GARMIN G1000

CARGO DOORS REMOVED KIT

GENERAL

The Cargo Doors Removed Kit is designed to improve passenger

comfort and facilitate passenger-to-pilot communications during special

purpose operations such as skydiving, aerial photography, emergency

air drops, etc. The kit consists of a vented spoiler installed on the

forward cargo door hinges to minimize airflow buffeting within the cabin

with the cargo doors removed.

OPERATING LIMITATIONS

1. Intentional stalls with cargo doors removed are prohibited.

2. Removal of the cargo doors requires that the spoiler be

installed.

3. With the cargo door removed, maximum airspeed must not

exceed 155 KIAS.

FAA APPROVED

S10-4

U.S.

208BPHCUS-S10-00

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 10

MODEL 208B 867 SHP

GARMIN G1000

EMERGENCY PROCEDURES

EMERGENCY DESCENT

SMOOTH AIR

WING FLAPS

Airspeed

155 KIAS

(maximum)

NORMAL PROCEDURES

Both cargo doors (upper and lower) must be removed in order to install

the spoiler. Installation of the spoiler substantially reduces airflow

buffeting in the cabin; however, all loose equipment should be removed

or secured. Face protection is also recommended for passengers near

the door opening.

With the Cargo Doors Removed Kit installed, flight characteristics are

essentially unchanged.

PERFORMANCE

Airplane performance information provided in the POH/AFM does not

apply when the airplane is flown with the Cargo Doors Removed Kit

installed since significant performance decrements result.

TAKEOFF

Takeoff distance is increased by as much as 200 feet.

CLIMB

Maximum rate of climb is reduced by approximately 150 FPM.

CRUISE

Cruise speed is reduced by approximately 15 KIAS.

FAA APPROVED

S10-6

U.S.

208BPHCUS-S10-00

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 12

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 12

DUAL GARMIN GMA 1347 AUDIO PANELS

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

19 December 2012

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S12-1 thru S12-8

Original

FAA APPROVED

S12-2

U.S.

208BPHCUS-S12-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 12

GARMIN G1000

SERVICE BULLETIN CONFIGURATION LIST

The following is a list of Service Bulletins that are applicable to the

operation of the airplane, and have been incorporated into this

supplement. This list contains only those Service Bulletins that are

currently active.

Number

Title

Airplane Serial

Revision

Incorporated

Effectivity

Incorporated

in Airplane

FAA APPROVED

208BPHCUS-S12-00

U.S.

S12-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 12

MODEL 208B 867 SHP

GARMIN G1000

DUAL GARMIN GMA 1347 AUDIO PANELS

GENERAL

With the Dual Garmin GMA 1347 audio panel installation a second

audio panel has been added between the MFD and copilot's PFD.

Refer to the Garmin G1000 CRG for specific operating information on

all Garmin equipment.

A pushbutton switch labeled DISPLAY BACKUP on each audio panel

allows manual selection of reversionary mode for the respective PFD

and MFD. The MFD can operate in reversionary mode by pressing

either DISPLAY BACKUP switch on either audio panel.

Each cockpit speaker is tied to the respective audio panel and the

audio is controlled by the individual audio selector switches and

adjusted for volume level by using the selected receiver volume

controls. The system is designed so that microphones are voice

activated, with transmission over the COM radios controlled by the

push-to-talk switches.

The headsets plug into microphone and headset jacks located on the

left side of the instrument panel for the pilot and the right side of the

instrument panel for the copilot. Push-to-talk switches for the headsets

are mounted on the both control wheels.

Four additional passenger intercom headset jacks are available as an

option to the Dual Garmin GMA 1347 audio panel installation. Volume

control for these four headsets is controlled by using the audio panel 2

volume control knob, while the standard intercom headset volume is

controlled by audio panel 1.

(Continued Next Page)

FAA APPROVED

S12-4

U.S.

208BPHCUS-S12-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 12

GARMIN G1000

GENERAL (Continued)

ENHANCED DUAL AUDIO PANEL FUNCTIONALITY

The installation of the Dual Garmin GMA 1347 audio panel includes

certain protection and system prioritization not available in the standard

single audio panel configuration. Protection against simultaneous

transmission over a single VHF COM radio and simultaneous

transmission over two different VHF COM radios are standard with the

Dual Garmin GMA 1347 audio panel installation.

Each pilot has priority when transmitting using their respective VHF

COM radio

(e.g. pilot transmitting using COM1 or the copilot

transmitting using COM2) over the cross-side pilot. If the cross-side

pilot attempts to transmit on the opposite VHF radio (copilot attempting

to transmit over COM1 using audio panel number 2) the onside pilot's

push-to-talk switch will override the transmission when selected.

If both pilots have COM1 selected on their respective audio panels, the

pilot's transmission will override the copilot's transmissions. The same

priority logic applies to COM2 when the copilot transmits, it will override

the pilot's transmissions.

Additionally, the system protects against simultaneous transmission by

both pilots over COM1 and COM2. If the pilot's push-to-talk switch is

keyed while on either COM, the copilot cannot transmit on the other

COM radio. If the copilot's push-to-talk switch is keyed while on COM1,

the pilot's push-to-talk switch will have no effect on COM2.

The COM3 radio does not have simultaneous transmission protection.

If one pilot transmits on COM3, it will not interfere with the other pilot's

transmissions on COM1, COM2 or COM3. COM3 is normally reserved

for use by the HF radio option.

FAA APPROVED

208BPHCUS-S12-00

U.S.

S12-5

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 12

MODEL 208B 867 SHP

GARMIN G1000

OPERATING LIMITATIONS

The following Operating Limitations supersede and/or are in addition to

the Operating Limitations set forth in the basic Pilot's Operating

Handbook and FAA Approved Airplane Flight Manual:

GARMIN GFC

700 AUTOMATED FLIGHT CONTROL

SYSTEM (AFCS)

Use of the autopilot is prohibited when both audio panels are

inoperative, since the aural alert will not be provided when autopilot is

disengaged.

EMERGENCY PROCEDURES

There is no change to the airplane emergency procedures for airplanes

equipped with Dual Garmin GMA 1347 Audio Panels.

FAA APPROVED

S12-6

U.S.

208BPHCUS-S12-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 12

GARMIN G1000

ABNORMAL PROCEDURES

DISPLAY UNIT FAILURE

This is indicated by a complete loss of image on a display. If only

individual elements of the display are failed, refer to appropriate

procedures for the individual failures.

IF PFD FAILS

1. DISPLAY BACKUP Button (affected side)

PRESS

(Flight and EICAS information is displayed on MFD)

NOTE

The PFD CDI SYNC and BARO SYNC settings must be ON

to allow the copilot’s PFD controls to affect settings on the

MFD. These settings are accessible using the PFD MENU

button.

2. Flight Director

TRANSFER

(Press XFR button to operating PFD)

3. FD Modes/AUTOPILOT

RESELECT and REENGAGE

(as required)

4. Transponder

SWITCH

(to operating transponder)

5. COM and NAV Radios

SWITCH

(to operating COM and NAV radios)

6. PFD Controls

USE OPERATING PFD

(for required data entry (COM, NAV, Baro setting, etc.))

IF MFD FAILS

1. Either DISPLAY BACKUP Button

PRESS

(EICAS information will be displayed on the respective PFD)

FAA APPROVED

208BPHCUS-S12-00

U.S.

S12-7

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 12

MODEL 208B 867 SHP

GARMIN G1000

ABNORMAL PROCEDURES (Continued)

AUDIO PANEL FAILURE

Audio panel failure may be indicated by a GMA 1 or (2) FAIL Garmin

System Message or the inability to communicate using the affected

audio panel. This failure may also be accompanied by the loss of some

aural warnings such as Altitude Alert, Autopilot Disconnect, TAWS, and

Traffic alerts.

1. AUDIO 1 or AUDIO 2 Circuit Breaker (affected side) . . . OPEN

(pull out)

2. SPKR Button (operating audio panel)

3. COM Radio

USE ON-SIDE RADIO

FOR COMMUNICATION

NOTE

• In the event of an AUDIO 1 failure, a fail-safe circuit

connects the pilot’s headset directly to the COM 1 radio.

The speakers on the affected side will be inoperative.

• The operating audio panel will not be able to listen to

COM or NAV audio from the side with the inoperative

audio panel.

CAUTION

A fail-safe circuit is not provided for an AUDIO 2 failure,

which will result in the copilots' headset and right

cockpit speaker becoming inoperative.

NORMAL PROCEDURES

There is no change to the airplane normal procedures for airplanes

equipped with Dual Garmin GMA 1347 Audio Panels.

PERFORMANCE

There is no change to the airplane performance for airplanes equipped

with Dual Garmin GMA 1347 Audio Panels.

FAA APPROVED

S12-8

U.S.

208BPHCUS-S12-00

CESSNA MODEL 208B

867 SHP - GARMIN G1000

Serials 208B2197 and 208B5000 and On

SUPPLEMENT 13

HONEYWELL KHF 1050 HF TRANSCEIVER

WITH PS440 CONTROL DISPLAY UNIT

SERIAL NO.

REGISTRATION NO.

This supplement must be inserted into Section 9 of the Pilot's Operating Handbook

and FAA Approved Airplane Flight Manual when Honeywell KHF

1050 HF

Transceiver with PS440 Control Display Unit is installed.

19 DECEMBER 2012

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA

208BPHCUS-S13-00

U.S.

S13-1

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 13

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 13

HONEYWELL KHF 1050 HF TRANSCEIVER WITH

PS440 CONTROL DISPLAY UNIT

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

19 December 2012

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S13-1 thru S13-6

Original

FAA APPROVED

S13-2

U.S.

208BPHCUS-S13-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 13

GARMIN G1000

SERVICE BULLETIN CONFIGURATION LIST

The following is a list of Service Bulletins that are applicable to the

operation of the airplane, and have been incorporated into this

supplement. This list contains only those Service Bulletins that are

currently active.

Number

Title

Airplane Serial

Revision

Incorporated

Effectivity

Incorporated

in Airplane

FAA APPROVED

208BPHCUS-S13-00

U.S.

S13-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 13

MODEL 208B 867 SHP

GARMIN G1000

HONEYWELL KHF 1050 HF TRANSCEIVER WITH

PS440 CONTROL DISPLAY UNIT

GENERAL

The KHF-1050 HF System is a solid-state high frequency single

sideband transceiver system providing voice communications to the

pilot and co-pilot in the 2 to 29.9999 MHz band with 100 Hz resolutions.

A basic KHF-1050 HF System consists of five individual units; PS440

HF Control Head, KAC-1052 Antenna Coupler, KPA-1052 Power

Amplifier, KRX-1053 Receiver/Exciter, and a HF antenna. The PS440

Control Display Unit provides the pilot's display and control interface.

Frequency, channel, mode, audio gain, and squelch level selections

are entered via its controls. Fault monitoring and fault annunciation are

also provided by the PS440. The PS440 provides the pilot access to

100 manual channels and 246 ITU channels to interface with maritime

radiotelephone networks. The PS440 uses a liquid crystal display to

show frequency, channel, and mode of operation. The manual

channels can be programmed on the ground or in the air, and

nonvolatile memory stores this information even when the system is

turned off.

OPERATING LIMITATIONS

The KHF

1050/PS440 Pilot's Guide, Publication Number

006-18289-0000, Revision 1, dated May 2003, or later appropriate

revision, must be readily available to the flight crew when operating the

KHF 1050 transceiver.

FAA APPROVED

S13-4

U.S.

208BPHCUS-S13-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 13

GARMIN G1000

EMERGENCY PROCEDURES

There is no change to the airplane emergency procedures for airplanes

equipped with Honeywell KHF

1050 HF Transceiver with PS440

Control Display Unit.

ABNORMAL PROCEDURES

There is no change to the airplane abnormal procedures for airplanes

equipped with Honeywell KHF

1050 HF Transceiver with PS440

Control Display Unit.

NORMAL PROCEDURES

There is no change to the airplane normal procedures for airplanes

equipped with Honeywell KHF

1050 HF Transceiver with PS440

Control Display Unit.

PERFORMANCE

There is no change to the airplane performance for airplanes equipped

with Honeywell KHF 1050 HF Transceiver with PS440 Control Display

Unit.

FAA APPROVED

208BPHCUS-S13-00

U.S.

S13-5

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 14

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 14

115 VOLT ALTERNATING CURRENT (115 VAC)

POWER OUTLETS

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

19 December 2012

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S14-1 thru S14-8

Original

FAA APPROVED

S14-2

U.S.

208BPHCUS-S14-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 14

GARMIN G1000

115 VOLT ALTERNATING CURRENT (115 VAC)

POWER OUTLETS

GENERAL

The 115 Volt Alternating Current power outlet installation is primarily

designed to provide power to low power Portable Electronic Devices

(PED), such as cassette, compact disc, and MP3 players, laptop

computers and accessory chargers.

This installation includes a 115 VAC POWER OUTLET Switch, installed

in the pilot-side switch panel, a 115 Volt AC power inverter installed in

the tailcone, power controller located under the cabin floor and four 115

VAC, 60 Hz, electrical power outlets. Two outlets are installed in the

sidewall of the cabin just aft of the Pilot and Copilots seats. The 208B

Passenger Version has two additional outlets installed in the aft cabin

sidewall.

The system has a maximum load capacity of 4.3 amps (500 watts) and

is protected by two circuit breaker(s) on the left sidewall circuit breaker

panel. The two breakers are labeled 115 VAC OUTLET CTRLR and

115 VAC PWR INVTR, located on the bottom row, fifth and sixth circuit

breaker from the forward end.

The system is designed to automatically shutdown all power outlets

anytime the maximum load capacity of

4.3 amps (500 watts) is

exceeded by opening the 115 VAC PWR INVTR circuit breaker.

The system is also designed to automatically disconnect an individual

power outlet anytime the outlet maximum load capacity of 2.0 amps

(230 watts) is exceeded. An overload at the outlet level will not open

either circuit breaker or effect the operation of the remaining power

outlets.

Either overload condition can be corrected by disconnecting all

electrical devices and having the pilot reset the 115 VAC system by

following the procedures listed in abnormal checklist.

CAUTION

If the circuit breakers opens (trips) again. Do not close

(reset) circuit breaker a second time and have system

inspected and repaired prior to next flight.

FAA APPROVED

208BPHCUS-S14-00

U.S.

S14-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 14

MODEL 208B 867 SHP

GARMIN G1000

OPERATING LIMITATIONS

1. Each 115 VAC power outlet is limited to a maximum electrical

load of 2 amps (230 watt).

2. The electrical current from all devices connected to the 115 VAC

power outlets may not exceed 4.3 amps (500 watts).

3. The 230 watts is not available to each outlet simultaneously as

the inverter limits power output to 500 watts continuous.

4. The 115 VAC POWER OUTLETS Switch must be switched to

OFF when not in use.

5. The 115 VAC power outlets may not be used to power flight-

critical communication, navigation, or attitude reference devices.

6. Use of the 115 VAC power system is prohibited during takeoff

and landing.

7. Use of the 115 VAC power system is prohibited in Instrument

Meteorological Conditions (IMC) unless the pilot has determined

that each device powered by the 115 VAC power outlets will not

cause interference with the navigation or communication

systems of the airplane.

8. As OAT temperatures increase, inverter power output may be

reduced up to 100 watts. Reduce total electrical load to prevent

circuit breaker tripping.

FAA APPROVED

S14-4

U.S.

208BPHCUS-S14-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 14

GARMIN G1000

EMERGENCY PROCEDURES

ENGINE FAILURE DURING FLIGHT

X. Electrical Load

REDUCE

115 VAC POWER OUTLETS Switch

OFF

AIRSTART

X. Electrical Load

REDUCE

115 VAC POWER OUTLETS Switch

OFF

GENERATOR FAILURE

X. Electrical Load

REDUCE

115 VAC POWER OUTLETS Switch

OFF

ABNORMAL PROCEDURES

LOSS OF 115 VAC ELECTRICAL POWER AT ALL POWER

OUTLETS AND 115 VAC PWR INVTR CIRCUIT BREAKER

OPENS

1. Electrical Devices

DISCONNECT

(from all power outlets)

115 VAC POWER OUTLETS Switch

OFF

115 VAC PWR INVTR Circuit Breaker

CLOSE (push in)

(bottom row, fifth circuit breaker from the forward end)

115 VAC POWER OUTLETS Switch

Electrical Devices

RECONNECT AS NECESSARY

(maximum load 4.3 amps (500 watts))

FAA APPROVED

208BPHCUS-S14-00

U.S.

S14-5

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 14

MODEL 208B 867 SHP

GARMIN G1000

ABNORMAL PROCEDURES (Continued)

LOSS OF A SINGLE 115 VAC POWER OUTLET

1. Electrical Device

DISCONNECT

(from affected power outlet)

NOTE

Flight maybe continued using remaining working 115 VAC

power outlets.

IF OFFLINE POWER OUTLET IS REQUIRED

2. Electrical Devices

DISCONNECT

(from faulted power outlet)

NOTE

Advise remaining power outlet users that 115 VAC power

will be momentarily off as the 115 VAC system is reset.

115 VAC POWER OUTLETS Switch

OFF; THEN ON

Electrical Devices

RECONNECT AS NECESSARY

CAUTION

Maximum electrical load for all power outlets is 4.3

amps (500 watts), maximum individual outlet load is

limited to 2.0 amps (230 watts).

NORMAL PROCEDURES

BEFORE STARTING ENGINE

X. Passenger Briefing

COMPLETE

Refer to 14 CFR 91.21 and Advisory Circular 91.21-1 “Use of

Portable Electronic Devices Aboard Aircraft” for passenger

briefing information and requirements regarding the use of

portable electronic devices in aircraft.

BEFORE TAKEOFF

115 VAC POWER OUTLETS Switch

OFF

FAA APPROVED

S14-6

U.S.

208BPHCUS-S14-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 14

GARMIN G1000

NORMAL PROCEDURES (Continued)

115 VAC POWER OUTLET OPERATION

TO SUPPLY POWER TO THE 115 VAC POWER OUTLETS

115 VAC POWER OUTLETS Switch

CAUTION

Maximum electrical load for all power outlets is 4.3

amps (500 watts), maximum individual outlet load is

limited to 2.0 amps (230 watts).

BEFORE LANDING

115 VAC POWER OUTLETS Switch

OFF

PERFORMANCE

There is no change to the airplane performance when the 115 VAC

power outlets are installed.

FAA APPROVED

208BPHCUS-S14-00

U.S.

S14-7

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 15

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 15

NICKEL CADMIUM (NiCAD) BATTERY

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

19 December 2012

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S15-1 thru S15-10

Original

FAA APPROVED

S15-2

U.S.

208BPHCUS-S15-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 15

GARMIN G1000

SERVICE BULLETIN CONFIGURATION LIST

The following is a list of Service Bulletins that are applicable to the

operation of the airplane, and have been incorporated into this

supplement. This list contains only those Service Bulletins that are

currently active.

Airplane Serial

Revision

Incorporated

Number Title

Effectivity

Incorporated

in Airplane

FAA APPROVED

208BPHCUS-S15-00

U.S.

S15-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 15

MODEL 208B 867 SHP

GARMIN G1000

NICKEL CADMIUM (NiCAD) BATTERY

GENERAL

When the NiCAD battery is installed, a battery temperature monitoring

system is provided to detect an overheat condition of the battery

electrolyte. An amber BATTERY HOT annunciation indicates the

temperature within the battery is 140 - 160°F (60 - 71°C) and will

remain illuminated until the temperature drops below 115°F (46°C).

Once the temperature of the electrolyte exceeds 160°F (71°C), the

amber BATTERY HOT annunciation will go out and be replaced by a

red BATTERY OVHT annunciation. The red BATTERY OVHT

annunciation will remain on until the temperature drops below 46°C

(145°F) at which time the amber BATTERY HOT annunciation will

come back on. In either case, it is necessary to immediately stop

providing charging current to the battery from the airplane power

system. This is accomplished by turning the BATTERY Switch to OFF

and using the appropriate checklist procedures contained in this

supplement. During these procedures, BAT AMPS indication should be

used to verify that charging current has been reduced to zero (0).

A red BATTERY OVHT annunciation with temperatures above 160°F

(71°C) is considered critical and the flight should be terminated as soon

as practical.

An amber BATTERY HOT annunciation with temperatures of 140°F

(60°C) may become critical if the temperature and charging current

continue to rise.

Under high ambient temperature conditions, OAT above 100°F (38°C),

a battery temperature of 140°F (60°C) is not considered critical if a

decreasing charging current trend is verified and maintained by

monitoring the BAT AMPS indication.

OPERATING LIMITATIONS

There are no additional airplane operating limitations when the Nickel

Cadmium (NiCAD) battery is installed.

FAA APPROVED

S15-4

U.S.

208BPHCUS-S15-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 15

GARMIN G1000

EMERGENCY PROCEDURES

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS

RED BATTERY OVHT ANNUNCIATOR COMES ON

1. BATTERY Switch

OFF

2. GENERATOR Switch

TRIP

3. STBY ALT PWR Switch

OFF

WARNING

• Without electrical power all electrically operated

flight and engine indications, fuel boost pump,

EIS annunciators, WING FLAPS Handle and all

navigation and communications will be

inoperative.

• All standby instruments, including torque

indicator and vacuum-driven standby attitude

indicator, will be operative.

4. AVIONICS No. 1 and No. 2 Power Switches

OFF

WARNING

With AVIONICS No. 1 and No. 2 OFF, use standby

flight instruments.

5. BUS 1 PWR and

BUS 2 PWR Circuit Breakers

OPEN (pull out)

(all six rows, first breaker from aft end)

(Continued Next Page)

FAA APPROVED

208BPHCUS-S15-00

U.S.

S15-5

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 15

MODEL 208B 867 SHP

GARMIN G1000

EMERGENCY PROCEDURES (Continued)

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS (Continued)

RED BATTERY OVHT ANNUNCIATOR COMES ON

(Continued)

6. Electrical Load

REDUCE

a. CABIN Lights Switch

OFF

b. POWER OUTLET Switch(es)

OFF

c. BCN Lights Switch

OFF

d. LDG and TAXI/ RECOG Light Switches

OFF

NOTE

Keep LDG and TAXI/RECOG lights OFF until required for

approach and landing. Prior to landing, turn both LEFT and

RIGHT LDG light switches to ON.

e. VENT AIR FANS

OFF

AIR CONDITIONING (if installed)

OFF

GEN CONT and

GEN FIELD Circuit Breakers

OPEN (pull out)

(first row, last two breakers on forward end)

h. RDNG LIGHT Circuit Breaker

OPEN (pull out)

(third row, second breaker from aft end)

RADAR R/T Circuit Breaker

OPEN (pull out)

(AVN BUS 1, second row, sixth breaker from left side)

HF RCVR and

HF AMP Circuit Breakers

OPEN (pull out)

(AVN BUS 2, second row, fifth and sixth breakers from left

side)

STBY ALT PWR Switch

AVIONICS STBY PWR Switch

AVIONICS BUS TIE Switch

10. ALT AMPS

VERIFY BELOW 75 AMPS

(continue shedding if not below 75 amps)

11.

Flight

LAND AS SOON AS PRACTICAL

NOTE

With standby alternator powering the electrical system, the

flight can continue to destination airport with the amber

GENERATOR OFF annunciator shown. Monitor ALT AMPS

load using ENGINE SYSTEM page.

FAA APPROVED

S15-6

U.S.

208BPHCUS-S15-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 15

GARMIN G1000

ABNORMAL PROCEDURES

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS

AMBER BATTERY HOT ANNUNCIATOR COMES ON

1. BATTERY Switch

OFF

2. BAT AMPS

CHECK

IF BAT AMPS INDICATOR NOT SHOWING A CHARGE

CONDITION (0 ZERO)

a. Amber BATTERY HOT annunciator

MONITOR

(annunciator will go out once battery cools)

IF BAT AMPS INDICATOR STILL SHOWING A CHARGE

CONDITION (+ POSITIVE)

a. GENERATOR Switch

TRIP

b. STBY ALT PWR Switch

OFF

WARNING

• Without electrical power all electrically operated

flight and engine indications, fuel boost pump,

EIS annunciators, WING FLAPS Handle and all

navigation and communications will be

inoperative.

• All standby instruments, including torque

indicator and vacuum-driven standby attitude

indicator, will be operative.

3. AVIONICS No. 1 and No. 2 Switches

OFF

WARNING

With AVIONICS No. 1 and No. 2 OFF, use standby

flight instruments.

4. BUS 1 PWR and

BUS 2 PWR Circuit Breakers

OPEN (pull out)

(all six rows, first breaker from aft end)

(Continued Next Page)

FAA APPROVED

208BPHCUS-S15-00

U.S.

S15-7

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 15

MODEL 208B 867 SHP

GARMIN G1000

ABNORMAL PROCEDURES (Continued)

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS (Continued)

AMBER BATTERY HOT ANNUNCIATOR COMES ON

(Continued)

5. Electrical Load

REDUCE

a. CABIN Lights Switch

OFF

b. POWER OUTLET Switch(es)

OFF

c. BCN Lights Switch

OFF

d. LDG and TAXI/ RECOG Light Switches

OFF

NOTE

Keep LDG and TAXI/RECOG lights OFF until required for

approach and landing. Prior to landing, turn both LEFT and

RIGHT LDG light switches to ON.

e. VENT AIR FANS

OFF

AIR CONDITIONING (if installed)

OFF

GEN CONT and

GEN FIELD Circuit Breakers

OPEN (pull out)

(first row, last two breakers on forward end)

h. RDNG LIGHT Circuit Breaker

OPEN (pull out)

(third row, second breaker from aft end)

RADAR R/T Circuit Breaker

OPEN (pull out)

(AVN BUS 1, second row, sixth breaker from left side)

HF RCVR and

HF AMP Circuit Breakers

OPEN (pull out)

(AVN BUS 2, second row, fifth and sixth breakers from left

side)

STBY ALT PWR Switch

AVIONICS STBY PWR Switch

AVIONICS BUS TIE Switch

ALT AMPS

VERIFY BELOW 75 AMPS

(continue shedding if not below 75 amps)

10. Flight

LAND AS SOON AS PRACTICAL

NOTE

With standby alternator powering the electrical system, the

flight can continue to destination airport with the amber

GENERATOR OFF annunciator shown. Monitor ALT AMPS

load using ENGINE SYSTEM page.

FAA APPROVED

S15-8

U.S.

208BPHCUS-S15-00

CESSNA MODEL 208B

867 SHP - GARMIN G1000

Serials 208B2197 and 208B5000 and On

SUPPLEMENT 20

L-3 COMMUNICATIONS FA2100 COCKPIT VOICE AND

FLIGHT DATA RECORDER

SERIAL NO.

REGISTRATION NO.

This supplement must be inserted into Section 9 of the Pilot's Operating Handbook

and FAA Approved Airplane Flight Manual when the L-3 Communications FA2100

Cockpit Voice and Flight Data Recorder is installed.

20 JUNE 2013

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA

208BPHCUS-S20-00

U.S.

S20-1

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 20

MODEL 208B 867 SHP

GARMIN G1000

SUPPLEMENT 20

L-3 COMMUNICATIONS FA2100 COCKPIT VOICE

AND FLIGHT DATA RECORDER

Use the Log of Effective Pages to determine the current status of this

supplement.

Pages affected by the current revision are indicated by an asterisk (*)

preceding the page number.

Supplement Status

Date

Original Issue

20 June 2013

LOG OF EFFECTIVE PAGES

Page

Revision

Number

Status

Number

S20-1 thru S20-6

Original

FAA APPROVED

S20-2

U.S.

208BPHCUS-S20-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 20

GARMIN G1000

SERVICE BULLETIN CONFIGURATION LIST

The following is a list of Service Bulletins that are applicable to the

operation of the airplane, and have been incorporated into this

supplement. This list contains only those Service Bulletins that are

currently active.

Number

Title

Airplane Serial

Revision

Incorporated

Effectivity

Incorporated

in Airplane

FAA APPROVED

208BPHCUS-S20-00

U.S.

S20-3

SECTION 9 - SUPPLEMENTS

CESSNA

SUPPLEMENT 20

MODEL 208B 867 SHP

GARMIN G1000

L-3 COMMUNICATIONS FA2100 COCKPIT VOICE

AND FLIGHT DATA RECORDER

GENERAL

The FA2100 Cockpit Voice and Flight Data Recorder

(CVDR) is

mounted on a shelf in the tailcone of the Model 208B, and is designed

to record multiple flight parameters and audio that can be recovered to

aid in an investigation in the event of an accident. The system is

transparent to the flight crew and posts an advisory message only if the

Cockpit Voice or Flight Data Recorder has failed.

If a white CVR FAIL or FDR FAIL message is posted, the Cockpit Voice

or Flight Data Recorder functions, respectively, of the FA2100 CVDR

are inoperative. There is no effect on the safety of continued flight with

either or both messages posted. The unit should be serviced for proper

operation.

Data is recorded digitally based on inputs from a Garmin Data

Concentrator Unit GSD 41 located on the bottom shelf in the tailcone,

and an accelerometer and a flap potentiometer located in the cabin

overhead. The Voice Recorder uses two audio summing amplifiers

located in the forward pedestal structure, recording audio from the

cockpit area microphone located directly over the audio panel, both

crew members' headset audio and microphones, aural tones, and

speaker audio activity.

The CVDR is powered by the main electrical bus and protected by a

pull-off type circuit breaker labeled CVDR, located on the electrical

equipment circuit breaker panel in the cockpit. Power to the CVDR is

interrupted by an impact switch located near the CVDR to prevent

recording over existing data after an impact. The Data Concentrator

Unit GSD 41 is powered by Avionics Bus 1 and protected by a pull-off

type circuit breaker labeled DCU, located on the avionics circuit

breaker panel in the cockpit.

The FA2100 CVDR system meets TSO C123a and C124a

requirements, and it includes an underwater locator beacon approved

under TSO C121. Neither Cockpit Voice Recorder (CVR) or Flight Data

Recorder (FDR) is required for Part 91 or Part 135 operations on the

Model 208B in the U.S. This CVDR installation does not record all the

data parameters specified by 14 CFR Part 135, Appendix F.

FAA APPROVED

S20-4

U.S.

208BPHCUS-S20-00

CESSNA

SECTION 9 - SUPPLEMENTS

MODEL 208B 867 SHP

SUPPLEMENT 20

GARMIN G1000

OPERATING LIMITATIONS

There are no additional airplane operating limitations when L-3

Communications FA2100 Cockpit Voice and Flight Data recorder is

installed.

EMERGENCY PROCEDURES

There is no change to the airplane emergency procedures when the L-

3 Communications FA2100 Cockpit Voice and Flight Data recorder is

installed.

NORMAL PROCEDURES

There is no change to the airplane normal procedures when the L-3

Communications FA2100 Cockpit Voice and Flight Data recorder is

installed.

PERFORMANCE

There is no change to the airplane performance when the L-3

Communications FA2100 Cockpit Voice and Flight Data recorder is

installed.

FAA APPROVED

208BPHCUS-S20-00

U.S.

S20-5

Cessna 208B Grand Caravan EX. Airplane Flight Manual (2012) - page 9