Garmin G1000 Airplane Flight Manual Supplement

4 (1)
Garmin G1000 Airplane Flight Manual Supplement

© Copyright 2007 - 2010 Garmin Ltd. or its subsidiaries All Rights Reserved

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151st Street

Olathe, KS 66062 USA

Telephone: 913-397-8200

www.garmin.com

Hawker Beechcraft C90A and C90GT King Air

190-00682-02 Rev. D

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Garmin International, Inc

Log of Revisions

Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for

G1000 Integrated Avionics System and GFC 700 AFCS In Hawker Beechcraft

C90A and C90GT King Air Aircraft

REV

PAGE

DESCRIPTION

DATE OF

FAA APPROVED

NO.

NO(S)

APPROVAL

 

 

 

 

 

 

 

 

A

ALL

Original Issue

11/08/2007

Robert G. Murray,

DAS Administrator

 

 

 

 

 

 

 

 

Garmin International, Inc.

 

 

 

 

DAS-240087-CE

B

ALL

Repaginated

11/21/2007

Robert G. Murray,

DAS Administrator

 

 

 

 

Garmin International, Inc.

 

 

 

 

DAS-240087-CE

C

17, 24

Added Non-essential equipment

See Cover

See Cover

 

 

list to DUAL GENERATOR

 

 

 

 

FAILURE procedure, added GDU

 

 

 

 

cooling fans to minimum

 

 

 

 

equipment list, editorial updates.

 

 

 

 

 

 

 

D

All

Updated System Software

See Cover

See Cover

 

 

Version from 0636.01 to 0636.02

 

 

 

 

 

 

 

190-00682-02 Rev. D

Hawker Beechcraft C90A and C90GT King Air

 

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Table of Contents

Section 1 – General.......................................................................................................

7

Section 2 – Limitations ...............................................................................................

15

Section 3 - Emergency Procedures ...........................................................................

27

Section 3A - Abnormal Procedures ...........................................................................

37

Section 4 - Normal Procedures ..................................................................................

59

Section 5

– Performance ............................................................................................

80

Section 6

- Weight and Balance .................................................................................

80

Section 7

- Systems Description................................................................................

83

Section 8

– Handling, Service, and Maintenance ...................................................

117

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Section 1 - General

The information in this supplement is FAA-approved material and must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM) when the airplane has been modified by installation of the Garmin G1000 Integrated Avionics System and GFC 700 Digital Automatic Flight Guidance System in accordance with Garmin International, Inc. approved data.

The information in this supplement supersedes or adds to the basic POH/AFM only as set forth below. Users of the manual are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane.

The Garmin G1000 system installed in the Hawker Beechcraft C90A and C90GT King Air Aircraft provides a fully integrated Display, Communications, Navigation and Flight Control system. Functions provided by the G1000 system include Primary Flight Information, Powerplant Monitoring, Navigation, Communication, Traffic Surveillance, TAWS Class B, Weather Avoidance, and a three-axis automatic flight control / flight director system.

USE OF THE HANDBOOK

The following definitions apply to WARNINGS, CAUTIONS and NOTES found throughout the handbook:

WARNING

Operating procedures, techniques, etc., which could result in personal injury or loss of life if not carefully followed.

CAUTION

Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed.

NOTE

Operating procedures, techniques, etc., which is considered essential to emphasize.

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G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS

The Garmin G1000 Integrated Avionics GNSS navigation system installed in this aircraft is a GPS system with a Satellite Based Augmentation System (SBAS) comprised of two TSO-C145a Class 3 approved Garmin GIA 63Ws, TSO-C146a Class 3 approved Garmin GDU 104X Display Units, Comant CI 428-410 and CI 428-200 antennas, and GPS software version 3.0 or later approved version. The G1000 GNSS navigation system in this aircraft is installed in accordance with AC 20-138A.

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the requirements of AC 20-138A and is approved for navigation using GPS and SBAS (within the coverage of a Satellite Based Augmentation System complying with ICAO Annex 10) for IFR en route, terminal area, and non-precision approach operations (including those approaches titled “GPS”, “or GPS”, and “RNAV (GPS)” approaches). The G1000 Integrated Avionics GNSS navigation system installed in this aircraft is approved for approach procedures with vertical guidance including “LPV” and “LNAV/VNAV”, within the U.S. National Airspace System.

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements of AC 90-105 and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF (radius to fix) legs. Part 91 subpart K, 121, 125, 129, and 135 operators require a Letter of Authorization for operational approval from the FAA

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements of AC 90-100A for RNAV 2 and RNAV 1 operations. In accordance with AC 90-100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 and RNAV 1 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require a Letter of Authorization for operational approval from the FAA.

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft has been found to comply with the requirements for primary means of Class II navigation in oceanic and remote navigation (RNP-10) without time limitations in accordance with AC 20-138A and FAA Order 8400.12A. The G1000 can be used without reliance on other long-range navigation systems. This does not constitute an operational approval.

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft has been found to comply with the navigation requirements for primary means of Class II navigation in oceanic and remote navigation (RNP-4) in accordance with AC 20-138A and FAA Order 8400.33. The G1000 can be used without reliance on other long-range navigation systems. Additional equipment may be required to obtain operational approval to utilize RNP-4 performance. This does not constitute an operational approval.

The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the accuracy, integrity, and continuity of function, and contains the minimum system functions required for PRNAV operations in accordance with JAA Administrative & Guidance Material Section One: General Part 3: Temporary Guidance Leaflets, Leaflet No 10 (JAA TGL-10 Rev 1). The GNSS navigation system has two ETSO-145 / TSO-C145a Class 3 approved Garmin GIA 63Ws, and ETSO-146 / TSO-C146a Class 3 approved Garmin GDU 104X Display Units. The G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements for PRNAV and BRNAV operations in accordance with AC 90-96A and JAA TGL-10 Rev 1. This does not constitute an operational approval.

Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database Integrity, quality, and database management practices for the Navigation database. Pilots and operators can view the LOA status at www.Garmin.com > Aviation Databases > Type 2 LOA Status.

Navigation information is referenced to WGS-84 reference system.

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ELECTRONIC FLIGHT BAG

The G1000 Integrated Avionics System as installed in this aircraft supports approval of AC 120-76A Hardware Class 3, Software Type C Electronic Flight Bag (EFB) electronic aeronautical chart applications when using current FliteChart or ChartView data. Additional operational approvals may be required.

For operations under part 91, it is suggested that a secondary or back up source of aeronautical information necessary for the flight be available to the pilot in the aircraft. The secondary or backup information may be either traditional paper-based material or displayed electronically. If the source of aeronautical information is in electronic format, operators must determine non-interference with the G1000 system and existing aircraft systems for all flight phases.

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ABBREVIATIONS AND TERMINOLOGY

The following glossary is applicable within the airplane flight manual supplement

AC

Advisory Circular

 

ADC

Air Data Computer

 

ADF

Automatic Direction Finder

 

AFCS

Automatic Flight Control System

 

AFM

Airplane Flight Manual

 

AFMS

Airplane Flight Manual Supplement

 

AGL

Above Ground Level

 

Ah

Amp hour

 

AHRS

Attitude and Heading Reference System

 

ALT

Altitude, or AFCS altitude hold mode, or ALT button on the GMC 710 AFCS

 

Mode Controller

 

ALTS

AFCS altitude capture using the altitude in the altitude preselect window

ALTV

AFCS altitude capture using the altitude from the VNAV profile vertical

 

constraint

 

AMMD

Airport Moving Map Display

 

AP

Autopilot

 

APR

AFCS Approach mode, or APR button of GMC 710 AFCS mode controller

APTSIGNS

Airport Signs (SVS softkey on the PFD)

 

APV

Approach with Vertical Guidance

 

AS

Airspeed

 

ATC

Air Traffic Control

 

AUX

Auxiliary

 

BANK

Low-bank mode of the AFCS

 

BARO

Barometric Setting

 

BAT

Battery

 

BC

Back Course

 

BRNAV

Basic Area Navigation

 

BRT

Bright

 

C

Celsius

 

CDI

Course Deviation Indicator

 

CLR

Clear

 

COM

Communication radio

 

CRG

Cockpit Reference Guide

 

CRS

Course

 

CWS

Control Wheel Steering

 

 

 

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DA

Decision Altitude

DC

Direct Current

DME

Distance Measuring Equipment

DN

Down

DR

Dead Reckoning

EFB

Electronic Flight Bag

EIS

Engine Indication System

ELEC

Electrical

EMERG

Emergency

ENG

Engine

ENT

Enter

F

Fahrenheit

FAF

Final Approach Fix

FD

Flight Director

FLC

AFCS Flight Level Change mode, or FLC button on the GMC 710 AFCS

 

mode controller

FLTA

Forward Looking Terrain Awareness

FMS

Flight Management System

FPM

Flight Path Marker or Feet Per Minute

FSB

Fasten Seat Belts

ft

Feet

ft-lbs

Foot-Pounds

ft/min

Feet/Minute

GA

Go-around

GCU

Garmin Control Unit

GDC

Garmin Air Data Computer

GDU

Garmin Display Unit

GEA

Garmin Engine/Airframe Unit

GEN

Generator

GEO

Geographic

GFC

Garmin Flight Control

GIA

Garmin Integrated Avionics Unit

GMA

Garmin Audio Panel

GMC

Garmin Mode Control Unit

GP

GPS Glide Path

GPS

Global Positioning System

GRS

Garmin Reference System (AHRS)

 

 

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GS

Glide Slope

 

GSA

Garmin Servo Actuator

 

HDG

AFCS heading mode or the HDG button on the GMC 710 AFCS Mode

 

Controller

 

HITS

Highway in the Sky

 

HPa

Hectopascal

 

HSI

Horizontal Situation Indicator

 

IAF

Initial Approach Fix

 

IAS

Indicated Airspeed

 

ICAO

International Civil Aviation Organization

 

IFR

Instrument Flight Rules

 

ILS

Instrument Landing System

 

IMC

Instrument Meteorological Conditions

 

in-Hg

inches of mercury

 

INOP

Inoperative

 

INST

Instrument

 

ITT

Interstage Turbine Temperature

 

KIAS

Knots Indicated Air Speed

 

Kt(s)

Knot(s)

 

L

Left

 

LCD

Liquid Crystal Display

 

LDA

Localizer Type Directional Aid

 

LNAV

Lateral Navigation

 

LNAV + V

Lateral Navigation with Advisory Vertical Guidance

LNAV/VNAV

Lateral Navigation / Vertical Navigation

 

LOC

Localizer

 

LOI

Loss of Integrity (GPS)

 

LPV

Localizer Performance with Vertical Guidance

 

LRN

Long Range Navigation

 

LRU

Line Replaceable Unit

 

LTNG

Lightning (XM Weather Product)

 

M

Mach

 

MAP

Missed Approach Point

 

MAXSPD

Maximum Speed, AFCS Overspeed Protection mode

MDA

barometric minimum descent altitude

 

MEL

Minimum Equipment List

 

MFD

Multi Function Display

 

 

 

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MLS

Microwave Landing System

MMO

Maximum operation limit speed in mach

MNPS

Minimum Navigational Performance Specifications

NAT

North Atlantic Track

NAV

Navigation, or AFCS navigation mode, or NAV button on the GMC710 AFCS

 

Mode Controller

NEXRAD

Next Generation Radar (XM Weather Product)

NM

Nautical Mile

NPA

Non-precision Approaches

OAT

Outside Air Temperature

OBS

Omni Bearing Selector

OPT

Optional

OVHD

Overhead

P/N

Part Number

PDA

Premature Descent Alert

PED

Pedestal

PFD

Primary Flight Display

PFT

Pre-Flight Test

PIT

AFCS pitch mode

POH

Pilot’s Operating Handbook

PRNAV

Precision Area Navigation

PROC

Procedure button on the GDU or GCU 477

PROP

Propeller

PSI

Pounds per Square Inch

PTCH

Pitch

PWR

Power

R

Right

REF

Reference

RNAV

Area Navigation

RNP

Required Navigation Performance

ROL

AFCS roll mode

RPM

Revolutions per Minute

SBAS

Satellite Based Augmentation System

SDF

Simplified Directional Facility

SID

Standard Instrument Departure

SPD

Speed button on the GMC 710 AFCS Mode Controller. Toggles the FLC

 

speed between Mach and IAS references.

 

 

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STAR

Standard Terminal Arrival Route

 

STBY

Standby

 

STC

Supplemental Type Certificate

 

SUSP

Suspend

 

SVS

Synthetic Vision System

 

SW

Software

 

SYN TERR

Synthetic Terrain softkey

 

SYN VIS

Synthetic Vision softkey

 

TAWS

Terrain Awareness and Warning System

 

TEMP

Temperature

 

TIS

Traffic Information System

 

TMR

Timer

 

TO

Take off

 

TOD

Top of Descent

 

TSO

Technical Standard Order

 

VAPP

AFCS VOR Approach Mode

 

Vdc

Volts DC

 

VDP

Visual Descent Point

 

VFR

Visual Flight Rules

 

VHF

Very High Frequency

 

VMC

Visual Meteorological Conditions

 

VMI

Vibro-meter Inc.

 

VMO

Maximum operation limit speed in knots

 

VNAV

Vertical Navigation

 

VNV

Vertical Navigation button on the GMC 710 AFCS Mode Controller

VOR

VHF Omni-directional Range

 

VPTH

Vertical path

 

VS

Vertical Speed

 

WAAS

Wide Area Augmentation System

 

WFDE

WAAS Fault Detection/Exclusion

 

WGS-84

World Geodetic System – 1984

 

WSHLD

Windshield

 

XFR

Transfer button on the GMC 710 AFCS Mode Controller

XM

XM satellite system

 

XPDR

Transponder

 

XSIDE

Cross Side

 

YD

Yaw Damper

 

 

 

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Section 2 - Limitations

INTRODUCTION

The G1000 Cockpit Reference Guide for Hawker Beechcraft C90A/GT (CRG) must be immediately available to the flight crew. Use the G1000 Cockpit Reference Guide for Hawker Beechcraft C90A/GT, Garmin part number 190-00664-01, revision A or later approved revision when System Software Version 0636.02 is installed. The System Software Version number is displayed at the top right side of the MFD Power-up page.

AIRSPEED LIMITATIONS AND INDICATOR MARKINGS

No change to the airplane’s airspeed limitations. The airspeed indicators on the Primary Flight Displays (PFDs) and the standby airspeed indicator are marked in accordance with the airplane’s POH/AFM.

A low speed awareness band is marked on the PFDs in red from 20 – 78 KIAS. While the airplane is on the ground, the low speed awareness band is suppressed. It displays in flight two seconds after main gear liftoff.

The standby airspeed indicator is marked in accordance with the airspeed markings called out in the airplane’s AFM/POH. The standby airspeed indicator is not marked with a low speed awareness band.

POWER PLANT LIMITATIONS AND INDICATOR MARKINGS

No change to the airplane’s powerplant operating limitations. The engine gauges are marked in accordance with the airplane’s POH/AFM or, if an engine modification has been installed, in accordance with the AFMS for the engine modification.

NOTE

The gauge indicator pointer and digital display will flash inverse red/white video for 5 seconds and then remain steady red if the indicated engine parameter exceeds its established limit.

G1000 INTEGRATED AVIONICS SYSTEM

These limitations apply to Garmin G1000 system software version 0636.02

The Garmin G1000 Cockpit Reference Guide P/N 190-00664-01, Rev A, or later FAA approved revision, must be immediately available to the flight crew.

Required flight crewmembers must wear and use headsets when the overhead cockpit speaker audio is selected OFF.

Do not take off unless all display units are installed and operational.

Do not take off with any display in reversionary mode.

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Do not take off with any of the following messages displayed in the ALERTS window:

GPS1 FAIL and GPS2 FAIL simultaneously

PFD1 SERVICE

GPS NAV LOST

PFD2 SERVICE

GIA1 SERVICE

GMA1 SERVICE

GIA2 SERVICE

GMA2 SERVICE

MFD SERVICE

GEO LIMITS

Do not take off if MFD FAN FAIL is displayed in the ALERTS window AND the Outside Air Temperature is greater than 33OC (91OF).

Do not takeoff if PFD1 FAN FAIL or PFD2 FAN FAIL is displayed in the ALERTS window AND the Outside Air Temperature is greater than 47OC (116OF).

Ground operation of the G1000 system is limited to 20 minutes when the Outside Air Temperature is greater than 49OC (120OF) AND air conditioning is inoperative.

The G1000 system must be turned on and operated for at least 30 minutes before takeoff if ground outside air temperature is -40OC (-40OF) or below.

Use of VNAV is prohibited during the intermediate segment of an approach that includes a teardrop course reversal. VNAV will become ‘Unavailable’ at the beginning of the teardrop segment of the course reversal.

The fuel quantity, fuel required, fuel remaining, and gross weight estimate functions of the G1000 are supplemental information only and must be verified by the flight crew.

Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering. SafeTaxi and Chartview functions do not comply with the requirements of AC 20-159 and are not qualified to be used as an airport moving map display (AMMD). SafeTaxi and Chartview are to be used by the flight crew to orient themselves on the airport surface to improve pilot situational awareness during ground operations.

The use of the colors red and amber within the checklist function has not been evaluated or approved by this STC. Use of the colors red and/or amber within user created checklists may require separate evaluation and approval by the FAA..

G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM LIMITATIONS

The pilot must confirm at system initialization that the Navigation database is current.

Navigation database is expected to be current for the duration of the flight. If the AIRAC cycle will change during flight, the pilot must ensure the accuracy of navigation data, including suitability of navigation facilities used to define the routes and procedures for flight. If an amended chart affecting navigation data is published for the procedure, the database must not be used to conduct the procedure.

GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless the pilot verifies and uses a valid, compatible, and current Navigation database or verifies each waypoint for accuracy by reference to current approved data.

Discrepancies that invalidate a procedure must be reported to Garmin International. The affected procedure is prohibited from being flown using data from the Navigation database until a new Navigation database is installed in the aircraft and verified that the discrepancy has been corrected. Contact

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information to report Navigation database discrepancies can be found at www.Garmin.com>Support>Contact Garmin Support>Aviation. Pilots and operators can view navigation data base alerts at www.Garmin.com > In the Air> NavData Alerts.

For flight planning purposes, in areas where SBAS coverage is not available, the pilot must check RAIM availability. Within the United States, RAIM availability can be determined using the G1000 WFDE Prediction program, part number 006-A0154-01 (010-G1000-00) or later approved version with Comant CI 428-410 and CI 428-200 antennas selected, or the FAA’s en route and terminal RAIM prediction website: www.raimprediction.net, or by contacting a Flight Service Station. Within Europe, RAIM availability can be determined using the G1000 WFDE Prediction program or Europe’s AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home. For other areas, use the G1000 WFDE Prediction program. This requirement is not necessary if SBAS coverage is confirmed to be available along the entire route of flight. The route planning and WFDE prediction program may be downloaded from the GARMIN G1000 website on the internet. For information on using the WFDE Prediction Program, refer to GARMIN WAAS FDE Prediction Program, part number 190-00643-01, ‘WFDE Prediction Program Instructions’.

For flight planning purposes, operations within the U.S. National Airspace System on RNP and RNAV procedures when SBAS signals are not available, the availability of GPS integrity RAIM shall be confirmed for the intended route of flight. In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended route of flight, the flight should be delayed, canceled, or re-routed on a track where RAIM requirements can be met.

For flight planning purposes for operations within European B-RNAV and P-RNAV airspace, if more than one satellite is scheduled to be out of service, then the availability of GPS integrity RAIM shall be confirmed for the intended flight (route and time). In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended flight, the flight should be delayed, canceled, or re-routed on a track where RAIM requirements can be met.

For flight planning purposes, operations where the route requires Class II navigation the aircraft’s operator or pilot-in-command must use the G1000 WFDE Prediction program to demonstrate that there are no outages on the specified route that would prevent the G1000 to provide primary means of Class II navigation in oceanic and remote areas of operation that requires (RNP-10 or RNP-4) capability. If the G1000 WFDE Prediction program indicates fault exclusion (FDE) availability will exceed 34 minutes in accordance with FAA Order 8400.12A for RNP-10 requirements, or 25 minutes in accordance with FAA Order 8400.33 for RNP-4 requirements, then the operation must be rescheduled when FDE is available.

Both GIA 63Ws GPS navigation receivers must be operating and providing GPS navigation guidance to their respective PFD for operations requiring RNP-4 performance.

North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace operations per AC 91-49 and AC 120-33 require both GPS/SBAS receivers to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor. Each display computes an independent navigation solution based on the on-side GPS sensor. However, either display will automatically revert to the cross-side sensor if the on-side sensor fails or if the cross-side sensor is determined to be more accurate. A “BOTH ON GPS1” or “BOTH ON GPS2” message does not necessarily mean that one GPS has failed. Refer to the MFD AUX-GPS STATUS page to determine the state of the unused GPS.

Whenever possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and enroute RNAV “Q” and RNAV “T” routes should be loaded into the flight plan from the database in their entirety, rather than loading route waypoints from the database into the flight plan individually. Selecting and inserting individual named fixes from the database is permitted, provided all fixes along the published route to be flown are inserted. Manual entry of waypoints using latitude/longitude or place/bearing is prohibited.

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“GPS”, “or GPS”, and “RNAV (GPS)” instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Navigation database. GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Navigation database.

Not all published Instrument Approach Procedures (IAP) are in the Navigation database. Pilots planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name.

IFR non-precision approach approval using the GPS/SBAS sensor is limited to published approaches within the U.S. National Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority.

The navigation equipment required to join and fly an instrument approach procedure is indicated by the title of the procedure and notes on the IAP chart. Use of the GARMIN G1000 GPS/SBAS receivers to provide navigation guidance during the final approach segment of an ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for “or GPS” navigation is prohibited. When using the G1000 VOR/LOC/GS receivers to fly the final approach segment, VOR/LOC/GS navigation data is must be selected and presented on the CDI of the pilot flying.

Navigation information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent.

AHRS AREAS OF OPERATION

Flight operations with the G1000 Integrated Avionics installed are prohibited in the following regions due to unsuitability of the magnetic fields near the Earth’s poles:

1.North of 72° North latitude at all longitudes

2.South of 70° South latitude at all longitudes

3.North of 65° North latitude between longitude 75° W and 120° W (Northern Canada)

4.North of 70° North latitude between longitude 70° W and 128° W (Northern Canada)

5.North of 70° North latitude between longitude 85° E and 114° E (Northern Russia)

6.South of 55° South latitude between longitude 120° E and 165° E (Region south of Australia and New Zealand)

NOTE

The Garmin G1000 system is not designed for use as a polar navigator and operation outside the approved operating area is prohibited. The GRS-77 AHRS internally monitors the magnetic field and will display a GEO LIMITS system message when the magnetic field becomes unsuitable for AHRS operation. When the AHRS can no longer reliably compute heading, heading information will be removed from the HSI.

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AUTOPILOT OPERATION LIMITS

One pilot must remain seated at the controls, with seatbelt fastened, during all autopilot operations.

Do not use autopilot or yaw damper during takeoff and landing.

The GFC 700 AFCS preflight test must be successfully completed prior to use of the autopilot, flight director or manual electric trim. Use of the autopilot or manual electric trim system is prohibited if the preflight test is not satisfactorily completed.

When conducting missed approach procedures, autopilot coupled operation is prohibited until the pilot has established a rate-of-climb that ensures all altitude requirements of the procedure will be met.

Minimum speed for autopilot operation is 100 KIAS.

Maximum speed limit for autopilot operation is unchanged from the airplane’s maximum airspeed limit (VMO/MMO).

Do not use autopilot below the following altitudes:

(1)

On takeoff, do not engage the autopilot below

............................ 400 feet Above Ground Level

(2)

Enroute ....................................................................................................................

800 feet AGL

(3)

Approach (GP or GS Mode) ....................................................................................

200 feet AGL

(4)

Approach (FLC, VS, PIT or ALT Mode).....................

Higher of 400 feet AGL or Approach MDA

SYNTHETIC VISION

Use of the Synthetic Vision system display elements alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited.

Use of the Synthetic Vision system alone for navigation, or obstacle or terrain avoidance is prohibited.

Use of the SVS traffic display alone to avoid other aircraft is prohibited.

TAWS AND TERRAIN SYSTEM LIMITS

Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with TAWS warnings.

The TAWS databases have an area of coverage as detailed below:

a)The terrain database has an area of coverage from North 75° Latitude to South 60° Latitude in all longitudes.

b)The Airport Terrain Database has an area of coverage that includes airports from North 75° Latitude to South 60° Latitude in all longitudes.

c)The Obstacle Database has an area of coverage that includes the United States and Europe.

Use of the TAWS for navigation or terrain and/or obstacle avoidance is prohibited.

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Page 19 of 117

NOTE

The MAP - TAWS page and terrain display is intended to serve as a situational awareness tool only. It may not provide either the accuracy or fidelity, or both, on which to solely base decisions and plan maneuvers to avoid terrain or obstacles.

To avoid unwanted alerts, TAWS should be inhibited when landing at an airport that is not included in the airport database.

TRAFFIC AVOIDANCE SYSTEM LIMITS

Use of the MAP - TRAFFIC MAP to maneuver the airplane to avoid traffic without outside visual reference is prohibited. The Traffic Information System (TIS) or optional Skywatch HP Traffic Alert/Advisory System is intended as an aid for the pilot to visually locate traffic. It is the responsibility of the pilot to see and manually maneuver the airplane to avoid other traffic.

DATA LINK WEATHER (XM WEATHER)

Datalink weather information displayed by the G1000 system is limited to supplemental use only. XM weather data is not a source of official weather information. Use of the NEXRAD and LTNG (XM Lightning) data on the MAP – NAVIGATION MAP and/or MAP - WEATHER DATA LINK page (XM Weather) for hazardous weather, e.g., thunderstorm penetration is prohibited. NEXRAD, and LTNG information on the MAP - NAVIGATION or MAP – WEATHER DATA LINK page is intended only as an aid to enhance situational awareness of hazardous weather, not penetration. It is the pilot’s responsibility to avoid hazardous weather using official weather data sources and the airplane’s in-flight weather radar.

Display of XM NEXRAD data is prohibited if XM ICING or XM TURBULENCE are displayed on the MFD MAPWEATHER DATA LINK page. XM ICING and XM TURBULENCE data must be turned off in order to display XM NEXRAD data

OPTIONAL L3 COMMUNICATIONS AVIONICS SYSTEM WX-500 STORMSCOPE

Stormscope lightning information displayed by the G1000 system is limited to supplemental use only. The use of the Stormscope lightning data on the MAP – NAVIGATION MAP and/or MAP – STORMSCOPE page for hazardous weather (thunderstorm) penetration is prohibited. Stormscope lightning data on the MAP - NAVIGATION or MAP – STORMSCOPE page is intended only as an aid to enhance situational awareness of hazardous weather, not penetration. It is the pilot’s responsibility to avoid hazardous weather using official weather data sources and the airplane’s weather radar.

Hawker Beechcraft C90A and C90GT King Air

190-00682-02 Rev. D

Page 20 of 117

 

PLACARDS

On some aircraft, placards “On Instrument Panel Adjacent to Each Gyroscopic Instrument (Except for Flight Director)” were installed to identify the power source for the instrument (ref. AFM limitations section). With the installation of the G1000, these placards are removed and not required.

On Instrument Panel above the Standby Attitude Indicator:

STANDBY ALT/AS

ALTITUDE – FEET

VMO-KIAS

S.L TO 16,000

226

16,000 TO 20,000

209

20,000 TO 25,000

189

25,000 TO 30,000

169

KINDS OF OPERATION LIMITS

The Hawker Beechcraft models C90A and C90GT are approved for the following types of operations when the required equipment, as shown in the airplane AFM/POH Kinds of Operations Equipment List, supplemented by the Kinds of Operations Equipment List from other applicable Airplane Flight Manual Supplements, and the Kinds of Operations Equipment List contained in this Airplane Flight Manual Supplement, is installed and operable.

1.VFR Day

2.VFR Night

3.IFR Day

4.IFR Night

5.Icing Conditions

KINDS OF OPERATIONS EQUIPMENT LIST

This airplane may be operated in day or night VFR, day or night IFR, and icing conditions when the required systems and equipment are installed and operable.

The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The system and equipment listed must be installed and operable for the particular kind of operation indicated unless:

The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA.

Or:

An alternate procedure is provided in the Pilots Operating Handbook and FAA Approved Flight Manual for the inoperative state of the listed system or equipment and all limitations are complied with.

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Numbers in the Kinds of Operations Equipment List refer to quantities required to be operative for the specified condition. The list does not include all equipment that may be required by specific operating rules. It also does not include components obviously required for the airplane to be airworthy such as wings, empennage, engines, etc.

 

VFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

VFR

 

 

 

 

 

 

 

Night

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Night

 

 

 

 

 

 

 

 

 

Icing

 

System and/or Equipment

 

 

 

 

 

Conditions

 

 

 

 

 

 

 

Remarks and/or Exceptions

 

 

 

 

 

 

 

ELECTRICAL POWER

 

 

 

 

 

 

 

Inverter

0

0

0

0

0

Removed by G1000 modification

INVERTER Annunciator

0

0

0

0

0

Removed by G1000 modification

Standby Battery

0

1

1

1

1

 

ENGINE INDICATIONS

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

ENGINE OIL

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

ENVIRONMENTAL

 

 

 

 

 

 

Temperature limits reduced to 49OC

 

 

 

 

 

 

 

Air Conditioning System

0

0

0

0

0

(120OF) with inoperative air

conditioner or air conditioner not

 

 

 

 

 

 

 

 

 

 

 

 

 

 

used.

FLIGHT CONTROLS

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

FUEL

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

ICE AND RAIN PROTECTION

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

LANDING GEAR

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

LIGHTS

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

NAVIGATION INSTRUMENTS

1

1

1

1

1

 

Magnetic Compass

 

Outside Air Temperature

1

1

1

1

1

 

G1000 Integrated Avionics

 

 

 

 

 

 

 

Garmin G1000 Cockpit Reference

1

1

1

1

1

 

Guide

 

0

0

0

0

0

 

Autopilot

 

Yaw Damper

0

0

0

0

0

 

Control Wheel Autopilot

1

1

1

1

1

Left side is required. Both side

Disconnect/Trim Interrupt Switches

required for two-crew operation.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Hawker Beechcraft C90A and C90GT King Air

190-00682-02 Rev. D

Page 22 of 117

 

 

VFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

VFR

 

 

 

 

 

 

 

Night

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Night

 

 

 

System and/or Equipment

 

 

 

 

 

Icing

 

 

 

 

 

 

Conditions

 

 

 

 

 

 

 

Remarks and/or Exceptions

 

 

 

 

 

 

 

VHF Communications System

0

0

1

1

1

Or as required by operating

regulation.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Pilot's audio panel required for single

 

 

 

 

 

 

 

Audio Control Panel

1

1

1

1

1

pilot operation. Both sides required

 

 

 

 

 

 

 

for two-crew operation.

Primary Flight Display

2

2

2

2

2

 

Multi Function Display

1

1

1

1

1

 

Air Data Computer

2

2

2

2

2

 

Attitude/Heading Reference System

2

2

2

2

2

 

(AHRS)

 

 

 

 

 

 

 

 

Standby Attitude Indicator

0

0

1

1

1

 

Standby Altimeter

1

1

1

1

1

 

Standby Airspeed Indicator

1

1

1

1

1

 

ATC Transponder

0

0

1

1

1

Or as required by operating

regulation.

 

 

 

 

 

 

 

VHF Navigation Receiver

0

0

0

0

0

Or as required by operating

regulation.

 

 

 

 

 

 

 

Automatic Direction Finder (ADF)

0

0

0

0

0

Or as required by operating

regulation.

 

 

 

 

 

 

 

Distance Measuring Equipment

0

0

0

0

0

Or as required by operating

(DME)

regulation.

 

 

 

 

 

 

Marker Beacon Receiver

0

0

0

0

0

Or as required by operating

regulation.

 

 

 

 

 

 

 

Terrain Awareness and Warning

0

0

0

0

0

Or as required by operating

System (TAWS)

regulation.

 

 

 

 

 

 

Weather Radar

0

0

0

0

0

Or as required by operating

regulation.

 

 

 

 

 

 

 

XM Datalink Weather

0

0

0

0

0

MFD fan is required if OAT is above

 

 

 

 

 

 

 

GDU Cooling Fans (3 total)

2

2

2

2

2

33°C (91°F).

All fans are required if OAT is above

 

 

 

 

 

 

 

 

 

 

 

 

 

 

47°C (116°F).

RNAV Operations, Equipment and

 

 

 

 

 

 

Components

1

1

2

2

2

GPS/SBAS receiver with GPS

Software 3.2 or later approved

 

 

 

 

 

 

version **Note 1, 2

 

 

 

 

 

 

GDU 104X Display

2

2

2

2

2

GDU 1500 Display

1

1

1

1

1

Comant CI 428-410 antenna

1

1

1

1

1

Comant CI 428-200 antenna

1

1

1

1

1

 

 

 

 

 

 

 

Equipment and components required for RNAV 2, RNAV 1, B-RNAV, P-RNAV, Class II navigation, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and enroute RNAV “Q” and RNAV “T” routes, and “GPS”, “or GPS”, and “RNAV (GPS)” instrument approach operations.

NOTE 1: Some operations require two functioning GPS/SBAS receivers.

NOTE 2: If only one is required, and only one is operative, it must be #1.

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VFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

VFR

 

 

 

 

 

 

 

Night

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Day

 

 

 

 

 

 

 

 

IFR

 

 

 

 

 

 

 

Night

 

 

 

System and/or Equipment

 

 

 

 

 

Icing

 

 

 

 

 

Conditions

 

 

 

 

 

 

 

Remarks and/or Exceptions

 

 

 

 

 

 

 

OXYGEN

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

PROPELLER

 

 

 

 

 

 

 

No Changes - Refer to Aircraft Flight

 

 

 

 

 

 

 

Manual

 

 

 

 

 

 

 

VACUUM SYSTEM

0

0

0

0

1

 

Gyro Suction Gage

 

Instrument Air System

0

0

0

0

1

 

Hawker Beechcraft C90A and C90GT King Air

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Section 3 - Emergency Procedures

 

Table of Contents

 

AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................

29

AUTOPILOT MALFUNCTION / ELEVATOR TRIM RUNAWAY............................................................

29

MANUAL AUTOPILOT DISCONNECT ..................................................................................................

30

AUTOPILOT ABNORMAL DISCONNECT.............................................................................................

30

AUTOPILOT FAILURE ...........................................................................................................................

30

PITCH AXIS FAILURE............................................................................................................................

30

ROLL AXIS FAILURE.............................................................................................................................

31

YAW AXIS FAILURE ..............................................................................................................................

31

PITCH TRIM FAILURE ...........................................................................................................................

31

AUTOPILOT PRE-FLIGHT TEST FAIL..................................................................................................

32

AUTOPILOT OVERSPEED RECOVERY...............................................................................................

32

ENGINE FAILURE (AUTOPILOT ENGAGED) ......................................................................................

32

ELECTRICAL SYSTEM................................................................................................

32

DUAL GENERATOR FAILURE [L GEN OFF] [R GEN OFF] ................................................................

32

TAWS............................................................................................................................

34

TAWS WARNING ...................................................................................................................................

34

TAWS FAIL .............................................................................................................................................

34

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Bolded checklist steps in the EMERGENCY PROCEDURES section indicate pilot memory action items. The pilot shall perform these items without reference to the checklist in this section.

AUTOMATIC FLIGHT CONTROL SYSTEM

AUTOPILOT MALFUNCTION / ELEVATOR TRIM RUNAWAY

If the airplane deviates unexpectedly from the planned flight path:

1.

Control Wheel............................................................................................................

GRIP FIRMLY

2.

AP/YD DISC / TRIM INTRPT Button ................................................................

PRESS AND HOLD

 

 

(Be prepared for possible high elevator control forces)

3.

Aircraft Attitude.............................................................

MAINTAIN/REGAIN AIRCRAFT CONTROL

 

 

use standby attitude indicator if necessary

 

 

NOTE

 

Do not release the AP/YD DISC / TRIM INTRPT Button until after pulling the AFCS SERVOS

 

Circuit Breaker.

 

4.

Elevator Trim.........................................................

RETRIM if necessary using Elevator Tab Wheel

5.

AFCS SERVOS Circuit Breaker................................................................................................

PULL

 

 

(Right circuit breaker panel)

6.

AP/YD DISC / TRIM INTRPT Button ................................................................................

RELEASE

WARNING

IN FLIGHT, DO NOT OVERPOWER THE AUTOPILOT. DIRECTION OPPOSING THE OVERPOWER FORCE, OUT-OF-TRIM FORCES.

THE TRIM WILL OPERATE IN THE WHICH WILL RESULT IN LARGE

DO NOT ATTEMPT TO RE-ENGAGE THE AUTOPILOT OR USE MANUAL ELECTRIC PITCH TRIM UNTIL THE CAUSE OF THE MALFUNCTION HAS BEEN CORRECTED.

NOTE

The maximum altitude lost during malfunction tests was:

Climb – 0 Feet

Cruise – 50 Feet

Descent – 320 Feet

Maneuvering – 0 Feet

Approach – 54 Feet

One-engine inoperative approach – 45 Feet

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Page 29 of 117

MANUAL AUTOPILOT DISCONNECT

If necessary, the autopilot can be manually disconnected using any one of the following methods.

1.

AP/YD DISC / TRIM INTRPT Button ............................................................

PRESS and RELEASE

 

 

(Pilot’s or Copilot’s control wheel)

2.

AP Button (Autopilot mode control panel)..............................................................................

PRESS

 

 

(Yaw damper remains engaged)

3.

Pitch Trim Switch (Pilot’s or, if installed, Copilot’s control wheel)....................................

ACTIVATE

 

 

(Yaw damper remains engaged)

4.

Go-Around (GA) switch..........................................................................................................

PRESS

 

(Left power lever) (Yaw damper remains engaged)

5.

AFCS SERVOS Circuit Breaker................................................................................................

PULL

 

 

(Right circuit breaker panel)

AUTOPILOT ABNORMAL DISCONNECT

(Red ‘AP’ flashing on PFD, Continuous high-low aural tone)

1.

A/P DISC/TRIM INTRPT Button

..................................................................PRESS AND RELEASE

 

 

(to cancel disconnect tone)

2.

Aircraft Attitude.............................................................

MAINTAIN/REGAIN AIRCRAFT CONTROL

NOTE

The autopilot disconnect may be accompanied by a red boxed PTCH (pitch), ROLL, or AFCS on the PFD, indicating the axis which has failed, or that the automatic flight control system has failed. The autopilot cannot be re-engaged with any of these annunciations present.

AUTOPILOT FAILURE

(Red annunciator on PFD, Red ‘AP’ flashing on PFD, Continuous high-low aural tone)

1. AP/YD DISC / TRIM INTRPT Button

.....................................................................................PRESS

 

(to cancel disconnect tone)

If red ‘AFCS’ is displayed, the autopilot, yaw damper, and manual electric pitch trim will be inoperative.

PITCH AXIS FAILURE

(Red annunciator on PFD)

Indicates a failure of the pitch axis of the autopilot. The autopilot will be inoperative.

NOTE

If the red annunciator illuminates without the autopilot engaged, it may indicate a faulted AHRS. Monitor both PFDs and the standby attitude indicator for abnormal attitude indications

Hawker Beechcraft C90A and C90GT King Air

190-00682-02 Rev. D

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