FAA Approved Airplane Flight Manual Supplement

190-00716-02 Rev. 2 Hawker Beechcraft King Air 300/300LW

FAA APPROVED Page 37 of 135

ENGINE FAILURE (AUTOPILOT ENGAGED)

1. AP/YD DISC / TRIM INTRPT Button .......................................................... PRESS and RELEASE

2. Engine Failure Procedure in

EMERGENCY PROCEDURES Section of AFM ........................................................ COMPLETE

3. Trim Tabs .............................. MANUALLY ADJUST ELEVATOR, AILERON, AND RUDDER TABS

4. Autopilot ............................................................. PRESS ‘AP’ BUTTON (if desired) to RE-ENGAGE

5. Rudder Tab ............................................................... MANUALLY ADJUST AS REQUIRED AFTER

POWER AND CONFIGURATION CHANGES

ELECTRICAL SYSTEM

DUAL GENERATOR FAILURE [L DC GEN] [R DC GEN]

This procedure should be performed prior to completing the respective section of the AFM checklist.

If Neither Generator Will Reset:

1. Standby Battery Switch ............................................................................... INDICATES ARM or ON

2. The following equipment will be functional while the G1000 is powered from the aircraft’s battery

power, Avionics Master Power Switch is ON, and the [L GEN TIE OPEN], [R GEN TIE OPEN],

[L DC GEN] and [R DC GEN] annunciators are illuminated.

Pilot’s Attitude, Heading, Air Data, and Nav CDI

Copilot’s Attitude, Heading, Air Data, and Nav CDI

MFD, Engine Gauges

Com 1, Pilot’s Audio Panel, GPS 1, GPS 2, VHF Nav 1, VHF Nav 2, Transponder 1

Autopilot, Flight Director, Yaw Damper/Rudder Boost

NOTE

Inoperative G1000 equipment items will be displayed in the ALERTS window on both PFDs.

NOTE

The aircraft’s battery will continue to power the G1000 equipment for at least 30 minutes following

complete loss of normal electrical power generation. Once the aircraft’s battery can no longer

power the G1000, the standby battery will automatically power the standby attitude indicator,

altimeter vibrator, the instrument emergency lights, and the internal lighting of the three standby

instruments and magnetic compass for an additional 30 minutes.

NOTE

The Copilot and Standby Altimeter and Airspeed indicators may be unreliable in visible moisture

because the Right Pitot Heat is not powered by the aircraft battery. The Left Pitot Heat remains