© Copyright 2007 - 2008 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. C |
Page 2 of 95 |
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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 |
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DESCRIPTION |
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APPROVAL |
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Original Issue |
11/08/2007 |
Robert G. Murray, |
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DAS Administrator |
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Garmin International, Inc. |
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DAS-240087-CE |
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Repaginated |
11/21/2007 |
Robert G. Murray, |
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DAS Administrator |
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Garmin International, Inc. |
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DAS-240087-CE |
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C |
17, 24 |
Added Non-essential equipment |
See Cover |
See Cover |
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list to DUAL GENERATOR |
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FAILURE procedure, added GDU |
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cooling fans to minimum |
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equipment list, editorial updates. |
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190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
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Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
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Table of Contents
Section 1 – General (Not FAA Approved).................................................................... |
7 |
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Section 2 – Limitations (FAA Approved)..................................................................... |
9 |
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Section 3 - Emergency Procedures (Not FAA Approved)........................................ |
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Section 3A - Abnormal Procedures (Not FAA Approved)........................................ |
27 |
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Section 4 - Normal Procedures (Not FAA Approved)............................................... |
47 |
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Section 5 |
– Performance (Not FAA Approved) ......................................................... |
67 |
Section 6 |
- Weight and Balance (Not FAA Approved).............................................. |
67 |
Section 7 |
- Systems Description (Not FAA Approved) ............................................ |
69 |
Section 8 |
– Handling, Service, and Maintenance (Not FAA Approved) .................. |
95 |
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
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Page 5 of 95 |
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Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 6 of 95 |
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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, Weather Avoidance, and a three-axis automatic flight control / flight director system.
OPERATIONAL APPROVALS
G1000 GPS/SBAS NAVIGATION SYSTEM
The Garmin G1000 GPS/SBAS receivers incorporating SW version 3.0 or later approved version and Comant CI 428-410 and CI 428-200 antennas are approved under TSO-C145a Class 3 and installed in accordance with AC 20-138A. The Garmin G1000 system has been demonstrated capable of, and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data:
The G1000 Integrated Avionics system as installed in this aircraft complies with AC 20-138A for navigation using GPS and WAAS (within the coverage of a Space-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 system installed in this aircraft is approved for approach procedures with vertical guidance including “LPV”, “LNAV/VNAV”, and “LNAV + V” within the U.S. National Airspace System.
The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of Navigation for oceanic and remote navigation – RNP-10, (per FAA AC 20-138A, FAA Order 8400-12A, and FAA Order 8700-1), when used in conjunction with Garmin WAAS Fault Detection/Exclusion (WFDE) Prediction Program, part number 006-A0154-01 or later approved version with Comant CI 428-200 or Comant CI 428-410 antennas selected. This does not constitute an operational approval. Both GPS/SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation (LRN) sensor.
The G1000 WFDE predication program works in combination with the Garmin AT, Inc. Route Planning Software, version 1.2, or later approved version. The route planning and WFDE prediction program can be downloaded from 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’.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
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Page 7 of 95 |
North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace per AC 91-49 and AC 120-33. Both GPS/SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor.
NOTE
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.
Enroute and Terminal including RNP5/BRNAV and PRNAV (RNP-1) - In accordance with JAA TGL-10 Rev 1, ACJ 20X4, AC 90-96A, and AC 90-100A provided the FMS is receiving usable navigation information from one or more GPS/SBAS receivers.
The G1000 Integrated Avionics system as installed in this is aircraft is eligible for B-RNAV in accordance with AMJ20X2.
The G1000 Integrated Avionics system as installed in this aircraft is eligible for PRNAV in accordance with PRNAV requirements: JAA Administrative & Guidance Material Section One: General Part 3: Temporary Guidance Leaflets, Leaflet No 10: Airworthiness and Operational Approval for Precession RNAV Operations in Designated European Airspace 7.1 Required Functions.
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.
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.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 8 of 95 |
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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 190-00664-00, revision C or later approved revision when System Software Version 0636.01 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 0636.00
The Garmin G1000 Cockpit Reference Guide P/N 190-00664-00, 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.
Do not take off with any of the following messages displayed in the ALERTS window:
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GPS1 FAIL and GPS2 FAIL simultaneously |
PFD1 SERVICE |
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GPS NAV LOST |
PFD2 SERVICE |
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190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
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FAA APPROVED |
Page 9 of 95 |
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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 25 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.
SafeTaxi and Chartview airport moving map display with own-ship position symbol is designed to assist flight crews in orienting themselves on the airport surface to improve pilot positional awareness during taxi operations. The airport moving map display function is not to be used as the basis for ground maneuvering.
G1000 GPS/SBAS NAVIGATION SYSTEM
SBAS AUGMENTED GPS SYSTEM LIMITATIONS
GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless the pilot verifies and uses a valid, compatible, and current Aviation database or verifies each waypoint for accuracy by reference to current approved data.
“GPS”, “or GPS”, and “RNAV (GPS)” instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Aviation database. GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Aviation database.
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.
Use of the Garmin G1000 GPS/SBAS receivers to accomplish ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for “or GPS” is not authorized. Use of the G1000 VOR/LOC/GS receivers to fly approaches not approved for “or GPS” requires that VOR/LOC/GS navigation data is selected and presented on the CDI of the pilot flying (i.e. proper CDI source selection).
NOTE
Not all published approaches are in the AVIATION database. The flight
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 10 of 95 |
FAA APPROVED |
crew must ensure that the planned approach is in the database.
RNP operations are not authorized except as noted in the Operational Approvals section.
When an approach being flown requires a course reversal and is being flown referenced to GPS/SBAS navigation, the initial approach fix must be crossed at a ground speed of 200 KT or less.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
FAA APPROVED |
Page 11 of 95 |
AHRS AREAS OF OPERATION
Flight operations with the G1000 Integrated Avionics installed are prohibited north of 70° North latitude or south of 70° South Latitude due to unsuitability of the magnetic fields near the Earth’s poles. In addition, operations are prohibited in the following two regions:
North of 65° North latitude between longitude 75° W and 120° W (Northern Canada).
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.
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 |
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.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 12 of 95 |
FAA APPROVED |
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.
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.
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.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
FAA APPROVED |
Page 13 of 95 |
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 |
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 14 of 95 |
FAA APPROVED |
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.
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.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
FAA APPROVED |
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IFR |
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Conditions |
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Remarks and/or Exceptions |
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ELECTRICAL POWER |
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Inverter |
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Removed by G1000 modification |
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INVERTER Annunciator |
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Standby Battery |
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ENGINE INDICATIONS |
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No Changes - Refer to Aircraft Flight |
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Manual |
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ENGINE OIL |
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Manual |
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ENVIRONMENTAL |
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Temperature limits reduced to 49OC |
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Air Conditioning System |
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FLIGHT CONTROLS |
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Manual |
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FUEL |
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No Changes - Refer to Aircraft Flight |
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Manual |
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ICE AND RAIN PROTECTION |
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No Changes - Refer to Aircraft Flight |
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LANDING GEAR |
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LIGHTS |
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Manual |
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NAVIGATION INSTRUMENTS |
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Outside Air Temperature |
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G1000 Integrated Avionics |
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Garmin G1000 Cockpit Reference |
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Yaw Damper |
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Control Wheel Autopilot |
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Disconnect/Trim Interrupt Switches |
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VHF Communications System |
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Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 16 of 95 |
FAA APPROVED |
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IFR |
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IFR |
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System and/or Equipment |
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Icing |
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Conditions |
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Remarks and/or Exceptions |
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Pilot's audio panel required for single |
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Audio Control Panel |
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pilot operation. Both sides required |
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for two-crew operation. |
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Primary Flight Display |
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Multi Function Display |
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Air Data Computer |
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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. |
||||||||
|
|
|
|
|
|
|
||
GPS/SBAS Receiver |
1 |
1 |
2 |
2 |
2 |
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). |
|
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 |
|
||
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
FAA APPROVED |
Page 17 of 95 |
This page intentionally left blank.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 18 of 95 |
FAA APPROVED |
Section 3 - Emergency Procedures |
|
Table of Contents |
|
AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................ |
20 |
AUTOPILOT MALFUNCTION / ELEVATOR TRIM RUNAWAY............................................................ |
20 |
MANUAL AUTOPILOT DISCONNECT .................................................................................................. |
21 |
AUTOPILOT ABNORMAL DISCONNECT............................................................................................. |
21 |
AUTOPILOT FAILURE ........................................................................................................................... |
21 |
PITCH AXIS FAILURE............................................................................................................................ |
21 |
ROLL AXIS FAILURE............................................................................................................................. |
22 |
YAW AXIS FAILURE .............................................................................................................................. |
22 |
PITCH TRIM FAILURE ........................................................................................................................... |
22 |
AUTOPILOT PRE-FLIGHT TEST FAIL.................................................................................................. |
22 |
AUTOPILOT OVERSPEED RECOVERY............................................................................................... |
23 |
ENGINE FAILURE (AUTOPILOT ENGAGED) ...................................................................................... |
23 |
ELECTRICAL SYSTEM................................................................................................ |
23 |
DUAL GENERATOR FAILURE [L GEN OFF] [R GEN OFF] ................................................................ |
23 |
TAWS............................................................................................................................ |
25 |
TAWS WARNING ................................................................................................................................... |
25 |
TAWS FAIL ............................................................................................................................................. |
25 |
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
Page 19 of 95 |
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. THE TRIM WILL OPERATE IN THE DIRECTION OPPOSING THE OVERPOWER FORCE, WHICH WILL RESULT IN LARGE OUT-OF-TRIM FORCES.
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
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 20 of 95 |
|
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.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
Page 21 of 95 |
ROLL AXIS FAILURE
(Red 
annunciator on PFD)
•Indicates a failure of the roll axis of the autopilot. The autopilot will be inoperative.
YAW AXIS FAILURE
(Red |
annunciator on PFD) |
•Indicates a failure of the yaw axis of the autopilot. The pitch and roll axes of the autopilot will remain operative. DO NOT pull and reset the AFCS SERVOS circuit breaker. Resetting the AFCS SERVOS circuit breaker could cause the entire autopilot to become inoperative when no fault exists in the pitch and roll axes.
PITCH TRIM FAILURE
(Red |
annunciator on PFD) |
|
|
1. |
CONTROL WHEEL..................................................................................................... |
GRIP FIRMLY |
|
2. |
AP/YD DISC / TRIM INTRPT Button ............................................................ |
PRESS and RELEASE |
|
|
|
|
(Be prepared for possible high elevator control forces) |
3. |
Elevator Trim...................................................... |
AS REQUIRED USING ELEVATOR TAB WHEEL |
|
If Red |
|
Message Clears |
|
• |
Autopilot |
....................................................................................................................... |
RE-ENGAGE |
If Red |
|
Message Remains |
|
4. |
Autopilot |
........................................................................................................ |
DO NOT RE-ENGAGE |
5. |
Elevator Trim.......................................................... |
CONTINUE TO USE ELEVATOR TAB WHEEL |
|
AUTOPILOT PRE-FLIGHT TEST FAIL
(Red 
annunciator on PFD)
•Indicates the AFCS system failed the automatic Pre-Flight test. The autopilot, yaw damper and electric elevator trim is inoperative. Flight Director should still function.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 22 of 95 |
|
AUTOPILOT OVERSPEED RECOVERY
(Yellow MAXSPD |
on PFD) |
|
1. |
Throttle............................................................................................................................... |
REDUCE |
When overspeed condition is corrected: |
||
2. |
Autopilot ..................................................................... |
RESELECT VERTICAL MODE (if necessary) |
NOTE
Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilot operating speed (226 KIAS / 0.46 M). Overspeed recovery is not active in altitude hold (ALT), glideslope (GS), or glidepath (GP) modes.
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 GEN OFF] [R GEN OFF]
1. |
Gen1 and Gen2 Generator Switches |
..........................................................................................OFF |
2. |
Gen1 Switch................................................................................................ |
GEN RESET, THEN ON |
3. |
Operating Generator ....................................................................... |
DO NOT EXCEED 100% LOAD |
If Left Generator Will Not Reset: |
|
|
4. |
Gen1 Switch................................................................................................................................ |
OFF |
5. |
Gen2 Switch................................................................................................ |
GEN RESET, THEN ON |
6. |
Operating Generator ....................................................................... |
DO NOT EXCEED 100% LOAD |
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
Page 23 of 95 |
If Neither Generator Will Reset:
7.Avoid IFR conditions if possible and LAND AT THE NEAREST SUITABLE AIRPORT.
8.Standby Battery Switch............................................................................... INDICATES ARM or ON
9.Non-essential equipment:
a.Left and Right BOOST PUMP……………………………………………………………….OFF
b.Left and Right TRANS. PUMP OVERRIDE………………………………………………..OFF
c.ENG AUTO IGNITION………………………………………………………………………..OFF
d.PROP ICE PROTECTION…………………………………………………………………...OFF
e.All Exterior Lights……………………………………………………………………………..OFF
f.Cabin Lights……………………………………………………………………………………OFF
g.VENT BLOWER…………………………………………………………………………….AUTO
h.CABIN TEMP MODE selector……………………………………………………………….OFF
i.INSTRUMENT EMERG LIGHTS……………………………………………….ON (if required)
j.INSTRUMENT INDIRECT lights……………………………………………….ON (if required)
10.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] and [R GEN TIE OPEN] annunciators are illuminated.
Pilot’s Attitude, Heading, Air Data, and Nav CDI
Copilot’s Attitude, Heading, Air Data, and Nav CDI
Engine Gauges
Com1, Pilot’s Audio Panel
GPS 1, GPS 2, VHF Nav1, VHF Nav2 (Nav2 Audio Inop)
MFD, Flight Director, Transponder 1
NOTE
Inoperative G1000 equipment items will be displayed in the ALERTS window on both PFDs.
The aircraft’s battery will continue to power the G1000 equipment for 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, and the internal lighting of the three standby instruments for an additional 30 minutes.
11.Consider a Flaps UP Landing and Landing Gear Manual Extension to conserve battery power for an instrument approach if needed.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 24 of 95 |
|
TAWS
TAWS WARNING
(Red 
on PFD and aural “PULL UP”)
1. |
AP/YD DISC / TRIM INTRPT Button |
............................................. PRESS and RELEASE |
|
|
(To disconnect the autopilot) |
2. |
Aircraft Attitude....................................................... |
PULL BACK ON CONTROL WHEEL |
3. |
Power.......................................................................................... |
MAXIMUM ALLOWABLE |
4. |
Airspeed........................................................................ |
BEST ANGLE OF CLIMB SPEED |
After Warning Ceases
5. |
Power ......................................................................................... |
MAXIMUM CONTINUOUS |
6. |
Altitude ............................................................... |
CLIMB AND MAINTAIN SAFE ALTITUDE |
7. |
Advise ATC of Altitude Deviation, if appropriate |
|
NOTE
Only vertical maneuvers are recommended, unless either operating in visual meteorological conditions (VMC), or the pilot determines, based on all available information, that turning in addition to the escape maneuver is the safest course of action, or both.
TAWS FAIL
(Red 
on PFD and MFD)
Indicates the G1000 will no longer provide TAWS alerting or display relative terrain elevation. The crew must maintain compliance with procedures that ensure minimum terrain and obstacle separation.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
Page 25 of 95 |
This page intentionally left blank.
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 26 of 95 |
|
|
Section 3A - Abnormal Procedures |
|
|
Table of Contents |
|
AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................ |
29 |
|
AILERON MISTRIM ................................................................................................................................ |
29 |
|
ELECTRIC PITCH TRIM INOPERATIVE ............................................................................................... |
29 |
|
ELEVATOR MISTRIM............................................................................................................................. |
30 |
|
RUDDER MISTRIM |
................................................................................................................................. |
31 |
FLASHING AMBER MODE ANNUNCIATION ....................................................................................... |
32 |
|
YAW DAMPER AUTOMATIC DISCONNECT (Amber Flashing ‘YD’) ................................................. |
32 |
|
G1000 INTEGRATED AVIONICS SYSTEM ................................................................. |
33 |
|
ALTITUDE MISCOMPARE..................................................................................................................... |
33 |
|
AIRSPEED MISCOMPARE .................................................................................................................... |
35 |
|
HEADING MISCOMPARE ...................................................................................................................... |
35 |
|
ROLL MISCOMPARE............................................................................................................................. |
36 |
|
HEADING MISCOMPARE ...................................................................................................................... |
36 |
|
Display Unit Failure..................................................................................................... |
36 |
|
PFD FAILURE......................................................................................................................................... |
|
36 |
MFD FAILURE ........................................................................................................................................ |
|
37 |
DUAL GPS/SBAS FAILURE (AMBER “DR” OR “LOI” ON HSI) ......................................................... |
38 |
|
GPS APPROACH ALARM LIMITS EXCEEDED ................................................................................... |
39 |
|
LOSS OF RADIO TUNING FUNCTIONS ............................................................................................... |
39 |
|
FAILED AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED............................................................ |
40 |
|
FAILED ATTITUDE AND/OR HEADING................................................................................................ |
40 |
|
ENGINE INDICATION SYSTEM (EIS) FAILURE................................................................................... |
42 |
|
LOSS OF NAVIGATION DATA .............................................................................................................. |
42 |
|
INACCURATE FLIGHT DIRECTOR DISPLAY ...................................................................................... |
42 |
|
BOTH ON ADC1, |
BOTH ON ADC2 ..................................................................................................... |
43 |
BOTH ON AHRS 1, BOTH ON AHRS 2................................................................................................. |
43 |
|
BOTH ON GPS 1, BOTH ON GPS 2 ...................................................................................................... |
43 |
|
XSIDE ADC ............................................................................................................................................. |
|
44 |
XSIDE AHRS........................................................................................................................................... |
|
44 |
TAWS ABNORMAL PROCEDURES............................................................................ |
45 |
|
TAWS CAUTION..................................................................................................................................... |
|
45 |
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
|
|
Page 27 of 95 |
TAWS INHIBIT ........................................................................................................................................ |
45 |
TAWS N/A............................................................................................................................................... |
45 |
Hawker Beechcraft C90A and C90GT King Air |
190-00682-02 Rev. C |
Page 28 of 95 |
|
AUTOMATIC FLIGHT CONTROL SYSTEM
AILERON MISTRIM (amber 
or 
annunciation on PFD)
Indicates a mistrim of the ailerons while the autopilot is engaged. The autopilot cannot trim the airplane in roll. During large changes in airspeed, engine failure, or single engine operation, illumination of this message may occur. If the autopilot is disconnected while this message is displayed, high roll forces are possible. The following procedure should be followed:
1. |
Control Wheel ............................................................................................................. |
GRIP FIRMLY |
2. |
Aileron Tab Knob ............................................ |
ROTATE SLOWLY IN DIRECTION OF INDICATED |
|
|
MISTRIM UNTIL THE ANNUNCIATION EXTINGUISHES |
IF THE ANNUNCIATOR STAYS EXTINGUISHED AND NO OTHER ANNUNCIATIONS ILLUMINATE
•Continue to operate the autopilot in a normal manner after the annunciation extinguishes.
IF THE ANNUNCIATOR REMAINS ILLUMINATED OR REAPPEARS WITH NO CHANGE IN AIRSPEED OR CONFIGURATION FROM THE PREVIOUS TRIMMED CONDITION:
3. |
Control Wheel ............................................................................................................. |
|
GRIP FIRMLY |
4. |
Aileron Tab Knob .................................... |
|
ROTATE SLOWLY IN THE DIRECTION OF INDICATED |
|
|
|
MISTRIM UNTIL ANNUNCIATION EXTINGUISHES |
5. |
AP/YD DISC / TRIM INTRPT Button |
............................................................ PRESS and RELEASE |
|
|
|
|
(Pilot’s or Copilot’s control wheel) |
6. |
Roll Trim......................... |
USING AILERON TAB KNOB, MANUALLY RETRIM AIRPLANE |
|
Autopilot should be considered inoperative until the cause of the mistrim has been investigated and corrected. Yaw damper may be re-engaged and used normally
ELECTRIC PITCH TRIM INOPERATIVE
NOTE
This condition may be accompanied by a red 
or 
annunciation on the PFDs.
1. Move both halves of pilot and copilot pitch trim switches to check for stuck switch
2. AFCS SERVOS Circuit Breaker |
............................................................................PULL and RESET |
|
(Right circuit breaker panel) |
The autopilot will enter Pre-Flight Test (PFT) mode when the AFCS SERVOS circuit breaker is reset. If the autopilot successfully completes the Pre-Flight Test, re-engage the autopilot, reselect the desired autopilot modes, and continue to use normally. If the Pre-Flight Test fails, indicated by a red
on the PFDs, the autopilot, yaw damper, and electric pitch trim will be inoperative for the remainder of the flight.
190-00682-02 Rev. C |
Hawker Beechcraft C90A and C90GT King Air |
|
Page 29 of 95 |
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