ATP INDEX COPYRIGHT 2007 COPYRIGHT IS NOT CLAIMED AS TO ANY PART OF AN ORIGINAL WORK PREPARED BY A UNITED STATES GOVERNMENT OFFICER OR EMPLOYEE AS PART OF THAT PERSONS OFFICIAL DUTIES OR BY ANY OTHER THIRD PARTY OFFICER OR EMPLOYEE AS PART OF THAT PERSONS DUTIES. "ATP" is a registered trademark of Aircraft Technical Publishers. All original authorship of ATP is protected under U.S. and foreign copyrights and is subject to written license agreements between ATP and its Subscribers. ALL RIGHTS RESERVED. NO PART OF THIS PUBLICATION MAY BE REPRODUCED, STORED IN A RETRIEVAL SYSTEM, OR TRANSMITTED IN ANY FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING, RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF THE PUBLISHER.
Transcript
ATPINDEX
COPYRIGHT 2007
COPYRIGHT IS NOT CLAIMED AS TO ANY PART OF AN ORIGINAL WORKPREPARED BY A UNITED STATES GOVERNMENT OFFICER OR EMPLOYEE ASPART OF THAT PERSONS OFFICIAL DUTIES OR BY ANY OTHER THIRD PARTY
OFFICER OR EMPLOYEE AS PART OF THAT PERSONS DUTIES.
"ATP" is a registered trademark of Aircraft Technical Publishers. All originalauthorship of ATP is protected under U.S. and foreign copyrights and is subject
to written license agreements between ATP and its Subscribers.
ALL RIGHTS RESERVED. NO PART OF THIS PUBLICATION MAY BEREPRODUCED, STORED IN A RETRIEVAL SYSTEM, OR TRANSMITTED IN ANY
FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING, RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF THE
PUBLISHER.
Aircraft Technical Publishers Customer Service
101 South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Raytheon Aircraft Co.
Super King Air 200 Series (8200, B200C, B200CT, 8200T)
Maintenance Manual Supplement-A/C with Pro Line 21 Equipment
Section Topic
General Information
Title PageManufacturer’s Introduction
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)List of Effective Pages
Aircraft General
05.00.00 Time Limits/Maintenance Checks
05.00.00 List of Effective Pages05.00.00 General
08.00.00 Leveling and Weighing08.00.00 List of Effective Pages08.00.00 General
Airframe Systems
22.00.00 Autoflight22.00.00 List of Effective Pages22.00.00 General
22.10.00 Autopilot
23.00.00 Communications
23.00.00 List of Effective Pages23.10.00 Speech Communication
23.10.00 VHF System
03/09/2006 Copyright Aircraft Technical Publishers Page 1 of 3
BC 1260 Mg
Section Topic
23.10.01 HF-9000 High-Frequency Communications System23.12.00 AirCell ST 3100 Satellite Telecommunication System23.30.00 Passenger Address, Entertainment and Comfort
23.30.00 Passenger Address System
23.50.00 Audio Integrating23.50.00 Audio Integrating System
24.00.00 Electrical Power
24.00.00 List of Effective Pages24.20.00 AC Generation
24.20.00 AC Electrical System24.30.00 DC Generation
24.30.00 DC-DC Converter Power Supply System24.60.00 DC Electrical Load Distribution
24.60.00 DC Electrical Load Distribution
31.00.00 Indicating/Recordinn Systems31.00.00 List of Effective Pages31.40.00 Central Computers31.40.00 Central Computers (Integrated Avionics Processor System)31.60.00 Central Display Systems31.60.00 Central Display Systems (Electronic Fit Instrument Sys)
33.00.00 Lights33.00.00 List of Effective Pages33.10.00 Flight Compartment33.10.00 Flight Compartment Lights33.11.00 Light Dimmer Power Supply System
34.00.00 Navigation34.00.00 List of Effective Pages34.00.00 General
34.10.00 Flight Environment Data
34.10.00 Air Data System34.20.00 Attitude and Direction
34.20.00 Attitude and Direction
34.25.00 Electronic Standby Instrument System (ESIS)
34.30.00 Landing and Taxiing Aids
34.30.00 VOR/ILS Navigation System34.40.00 Independent Position Determining34.40.00 Weather Radar System
03/09/2006 Copyright Aircraft Technical Publishers Page 2 of 3
BC 1260 M9
Section Topic
34.42.00 Radio Altimeter System
34.43.00 Skywatch Traffic Collision Avoidance System (TCAS I)
34.43.01 Traffic Alert and Collision Avoidance System (TCAS II)
34.47.00 Enhanced Ground Proximity Warning System
34.50.00 Dependent Position Determining
34.52.00 Global Positioning System34.54.00 Distance Measureing Equipment34.55.00 Air Traffic Control Radar Beacon System
34.56.00 Data Base Unit
34.60.00 Flight Management Computing34.60.00 Flight Management System
39.00.00 Electrical Panels and Multipurpose Parts
39.00.00 List of Effective Pages
39.10.00 Instrument and Control Panels
Power Plant
77.00.00 Engine Indicating77.00.00 List of Effective Pages
77.40.00 Integrated Engine Instrument Systems
End of Index
03/09/2006 Copyright Aircraft Technical Publishers Page 3 of 3
BC 1260 Mg
IVI FG,
INTRO
RBytheOn Aircraft Campany
Super King Air 200 Series
B200 BB-1834, BE-1843 and After
B200C BL-148 and After
B200CT BN-lO and After
B200T BT-47 and After
Maintenance Manual Supplement
for
Airplanes with Pro Line 21 Equipment Installed
This Supplement is Applicable to the Following Manual(s):101 -590010-19 or Subsequent
This supplement is to be used in conjunction with the Super King Air 200 Series Maintenance Manual for airplanesequipped with Pro Line 21 equipment. The information contained herein applies only to the equipment as delivered
by Raytheon Aircraft. Refer to the basic maintenance manual for the servicing and maintenance procedurescommon to the standard version of the Super King Air 200 Series airplanes.
Copyright 0 Raytheon Aircraft Company 2005
P/N 101-590010-431 P/N 101-590010-431Al
Issued: November 14, 2003 Revised: January 31, 2005
Published byRAYTHEON AIRCRAFT COMPANY
P.O. Box 85
Wichita, Kansas 67201
U.S.A.
The export of these commodities, technology or software are subject to the US ExportAdministration Regulations. Diversion contrary to U.S. law is prohibited. For guidance on exportcontrol requirements, contact the Commerce Department’s Bureau of Export Administration at 202-
482-4811 or at www.bxa.doc.gov.
Member of GAMA
Aircraft CompanyGmnl IvlPtlan
GA~HA uanuractursrs Association
RECORD OF REVISIONS
MFG REV
NO DESCRIPTION ISSUEDATE ATPREVDAT INSERTED BY
Original Issue 11114/2003 3/24/2006 ATPIRLL
Al IChapters 23, 31, and 34 1/31/2005 3/24/2006 ATP/RLL
319/2006
RaytheMI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Record of Revisions
Rev. Date Rev. Date Rev. Date
No. Inserted BYNo. Inserted BY No. Inserted By
3/24/2006 ATE~Al 3/24/2006
When a revision is inserted, the revision number, the date the revision is inserted into the manual, and the initials of
the person(s) inserting the revision should be recorded on this page.
RByehdMI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
LIST OF EFFECTIVE REVISIONS
PART NUMBER DATE CHAPTERS AFFECTED
101-59001 0-431 November 14, 2003 Original Issue
101-590010-431Al January 31, 2005 Introduction, 23, 31 and 34
Al
Basic publications are assigned a part number which appears on the title page with the date of the issue. Subsequent revisions are identified by the addition of a
revision code after the part number. Ai after a part number denotes the first revision to the basic publication, A2 the second, etc. Occasionally, it is necessary to
completely reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto. As these replacement reissues are made,the code will also change to the next successive letter of the alphabet at each Issue. For example, B for the first reissue, C for the second, etc.
When ordering a manual, give the basic number, and the reissue code when applicable, if a complete up-to-date publication is desired. Should only revision pagesbe required, give the basic number and revision code for the particular set of revision pages you desire.
RECORD OF TEMPORARY REVISIONS
TEMP ATP REV INSERT DATE REV REMOVE
REV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY
3/9/2006
Raltheon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21 MAINTENANCE MANUAL SUPPLEMENT
PM 101-590010-431, REVISION Al, JAN 31/05
The chapters which have been revised are listed below with the Highlights of each change. Remove the affected
pages and insert the Al revision in accordance with the attached Instruction Page. Enter the revision number and
the date inserted on the Record of Revisions page of this manual. The Highlights Page may be retained with the
manual for future reference.
HIGHLIGHTS
Chapter/Section Description
Introduction Added supplier manual references and revised the Chapter/System Index Guide.
23-10-01 Added information on the HF-9000 High-Frequency Communications System.
23-12-00 Added information on the AirCell ST 3100 Satellite Telecommunication System.
31-60-00 Revised the Central Display Systems (Electronic Flight Instrument System) Descriptionand Operation.
34-43-01 Added information on the Traffic Alert and Collision Avoidance System (TCAS II).
PagelAl Jan 31/05
Rayn#on Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21 MAINTENANCE MANUAL SUPPLEMENT
INSTRUCTIONS
for
REVISION 101-590010-431Al
REMOVE INSERT
PAGE CHAPTER PAGE CHAPTER DATED
Title Page Title Page Jan 31/05
Logo Page Logo Page
"A" Page "A" Page Jan 31/05
"B" Page "B" Page Jan 31/05
All Introduction All Introduction Jan 31/05
All 23-LOEP All 23-LOEP Jan 31/05
All 23-CONTENTS All 23-CONTENTS Jan 31/05
All 23-10-01 Jan 31/05
All 23-12-00 Jan 31/05
All 31-LOEP All 31-LOEP Jan 31/05
1 and 2 31-60-00 1 and 2 31-60-00 Jan 31/05
All 34-LOEP All 34-LOEP Jan 31/05
All 34-CONTENTS All 34-CONTENTS Jan 31/05
All 34-43-01 Jan 31/05
After compliance, this Instruction Sheet may be discarded.
Page 1 of 1
RBy~hgOn Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
LIST OF EFFECTIVE PAGES
SECTION PAGE DATE SECTION PAGE DATE
Title Page Jan 31/05 Introduction 1 thru 4 Jan 31/05
Logo Page
"A"Page Al
"B" Page Al
NOTE The chapter List of Effective Pages is located in the front of each chapter.
Al
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INTRODUCTION- GENERAL
NOTE
Service Publications reissues or revisions are not automatically provided to the holders of this
manual. For information on how to obtain current issues applicable to this manual, refer to the latest
revision of Raytheon Aircraft Company Service Bulletin No. 2001.
IWdRNINOIWARNING
Use only genuine Raytheon Aircraft or Raytheon Aircraft approved parts, obtained from
Raytheon Aircraft approved sources, in connection with the maintenance and repair of
Raytheon airplanes.
Genuine Raytheon Aircraft parts are produced and inspected under rigorous procedures to
insure airworthiness and suitability for use in Raytheon airplane applications. Parts
purchased from sources other than Raytheon Aircraft Company even though outwardlyidentical in appearance, may not have had the required tests and inspections performed,may be different in fabrication techniques and materials, and may be dangerous wheninstalled in an airplane
Salvaged airplane parts, reworked parts obtained from non-Raytheon Aircraft Companyapproved sources, or parts, components, or structural assemblies, the service history of
which is unknown
This Maintenance Manual Supplement is for Raytheon Aircraft 200 Series models with Pro Line 21 equipmentinstalled. This Maintenance Manual is supplemented by the following Publications which must be obtained from the
appropriate supplier:
NOTE
It shall be the responsibility of the owner/operator to ensure that the latest revision of publicationsreferenced in this handbook are utilized during operation, servicing, and maintenance of the
airplane.
Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System
Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation Manual 523-0771862
Rockwell Collins, Inc. APS-85 Autopilot System Installation Manual 523-0772076
Rockwell Collins, Inc. AHS-3000 Attitude Heading Reference System Installation Manual 523-0780184
Rockwell Collins, Inc. TRW-850 Turbulence Weather Radar System Installation Manual 523-0774652
Rockwell Collins, Inc. HF-9000 High-Frequency Communications System Operator’s Manual, P/N 523-
0774344-008217
Rockwell Collins, Inc. RTU-4200/4210/4220 Radio Tuning Unit Pilot’s Guide, 2nd edition, dated May 1, 1996,or later edition
Rockwell Collins, Inc. RTU installation manual, P/N 523-0780424-041116
ni Introduction
ltaYtheen AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Rockwell Collins, Inc. TCAS-4000 Installation Manual P/N 523-0780448 (or later)
Goodrich Avionics Systems, Inc. Installation and Operation Manual GH-3100, 501-1860-()
BFGoodrich Aerospace Service Letter SL-80J or later
Goodrich Avionics SKY899 Installation Manua1009-11900-001 Rev A or later
Honeywell MK VIII Enhanced Ground Proximity Warning System Installation Design Guide 060-4314-125
AirCell ST 3100 Satellite Telecommunication System Users Manual, P/N 810-10680, Rev. F or later revision
Since a variety of avionics systems are used and because avionics suppliers normally supply parts and servicingmanuals, avionics publications are not inclitded in this manual. The manufacturer of the equipment/systems should
be contacted when additional parts or servicing information is required.
If a question should arise concerning the care of your airplane, it is important to include the airplane serial number.
NOTE
Raytheon Aircraft Company expressly reserves the right to supersede, cancel and/or declare
obsolete any parts, part numbers, kits or publications that may be referenced in this manual without
prior notice.
INFORMATION ON THE MANUAL
AIRPLANE CONDITION
Each procedure in this manual is a stand-alone procedure; that is, the procedure the user is performing is the onlyprocedure being performed at that time. This policy is required, as the manual cannot address every maintenanceaction being performed on the airplane at any given instant and how the various actions may interact with each other.
Therefore, it is the responsibility of the user of this manual to determine the interaction between different
maintenance procedures at a given time.
SUBSYSTEM/SECTION INDEX GUIDE
Information contained in the following Subsystem/Section Index Guide supplements the existing basic Maintenance
Manual.
Chapter/System Index Guide
SYSTEM/
CHAPTER SUBSYSTEM/SECTION TITLE
INTRODUCTION
AIRCRAFT GENERAL
5 TIMES LIMITS/MAINTENANCE
CHECKS
Jan 31/052~fS Introduction
Raltheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Chapter/System Index Guide (Continued)
SYSTEM/
CHAPTER SUBSYSTEM/SECTION TITLE
00-00 General
8 LEVELING AND WEIGHING
00-00 General
AIRFRAME SYSTEMS
22 AUTO FLIGHT
00-00 General
10-00 Autopilot
23 COMMUNICATIONS
10-00 Speech Communications VHF System
10-01 HF-9000 High-Frequency Communications
System
12-00 AirCell ST 3100 Satellite Telecommunication
System
30-00 Passenger Address
50-00 Audio Integrating System
24 ELECTRICAL POWER
20-00 AC Generation
30-00 DC Generation
60-00 DC Electrical Load Distribution
31 INDICATING/RECORDING
SYSTEMS
40-00 Central Computers
60-00 Central Display Systems
33 LIGHTS
10-00 Flight Compartment
11-00 Light Dimmer Power Supply System
34 NAVIGATION AND PITOT/STATIC
Al Introduction Jan 31/05Page 3
RBYtheOl Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
43-01 Traffic Alert and Collision Avoidance System(TCAS II)
47-00 Enhanced Ground Proximity Warningsystem
52-00 Global Positioning System
54-00 Distance Measuring Equipment
55-00 Air Traffic Control Radar Beacon System
56-00 Data Base Unit
60-00 Flight Management System
39 ELECTRIC PANELS AND
MULTIPURPOSE PARTS
10-00 Instrument and Control Panels
77 ENGINE INDICATING
40-00 Integrated Engine Instrument Systems
Jan Introduction A1
CHAPTER
TIME LIMITS/
MAINTENANCE
CH ECKS
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 5 TIME LIMITS/MAINTENANCE CHECKS
TABLE OF CONTENTS
SOBJECT PAGE
5-00-00
Time Limits/Maintenance Checks General ...............1
eOO-HourPhase Inspection Program .1
Inspection and Maintenance Timetable .................1
Pro Linee1 Inspection Program ....2
Pro Linee1 Scheduled InspectionGeneral Information .....2
Pro Line21 Special Inspection General Information. .......5
5-CONTENTS Nov 14/03Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 5 TIME LIMITS/MAINTENANCE CHECKS
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
5-LOEP 1 Nov 14/03
5-CONTENTS 1 Nov 14/03
5-00-00 1 thru 5 Nov 1 4/03
5-LOEP Nov 14/03Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TIME LIMITS/MAINTENANCE CHECKS GENERAL
Reference Raytheon Aircraft Company approved inspection in the Airplane Maintenance Manual. This supplementaddresses the addition of inspection tasks for the Pro Line 21 installation.
200-HOUR PHASE INSPECTION PROGRAM
A complete inspection cycle is 800 hours or 24 months. The inspection cycle is divided into four phases and each
inspection cycle is done at 200 hours with each consecutive phase 200 hours after the previous phase. The Phase
1, 2, 3 and 4 inspections provide a thorough inspection of specific components and systems.
A complete inspection cycle is as follows:
PHASE HOURS
1 200
2 400
3 600
4 800
INSPECTION AND MAINTENANCE TIMETABLE
The Inspection and Maintenance Timetable contains a listing of the components and system requiring scheduled
inspection and/or maintenance action. Components are listed in order of chapter reference where applicable. This
form has four columns labeled: Item, Inspection Timetable, Interval and Phase Inspection Area.
Item Column This list the various items to be inspected.
Inspection Timetable Column Items are marked to indicate at which phase (1, 2, 3 or 4) they are to be inspectedor to indicate that an interim (INT), complete (COMP) or special inspection (SPL) is required.
Interval Column This column indicates the recommended hours, calendar time or cycles between inspection or
maintenance actions.
Phase Inspection Area Column The letter(s) in this column represents the location of the inspection line item in the
scheduled inspection forms.
5-00-00 Nov 14/03Pagel
RBy~hCOII nircrart CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Inspection and Maintenance Timetable
INSPECTION
TIMETABLE
1, 2, 3, 4 PHASE
INT, COMP INSPECTION
ITEM orSPL INTERVAL AREA
Autopilot Servo Mount Slip Clutch Test SPL 12,000 hours
The owner or operator is ultimately responsible for maintaining the airplane in an airworthy condition, includingcompliance with all applicable Airworthiness Directives as specified in Part 39 of Title 14 of Code of Federal
Regulations (14 CFR). It is further the responsibility if the owner operator to ensure that the airplane is inspected in
conformity with the requirements of 14 CFR 91.409 (f) (3) of the Federal Aviation Regulation. This CFR part covers
the requirements concerning approved airplane inspection programs. This supplement addresses addition of Pro
Line 21 specific inspection items to the existing 200 Series inspection program.
This Pro Line 21 installation generates additions to the 200 Series Inspection program and is provided to enable the
owner/operator to inspect and maintain the airplane on an ongoing basis. This addition to the inspection program
are not intended to be all-inclusive, for no such program can replace the good judgment of a certified airframe and
powerplant mechanics in the performance of their duties.
The time periods for the inspection noted in this schedule are based on normal usage under average environmental
conditions. Airplane operated for other than normal operations may need more frequent inspections for wear,
corrosion, lubrication, operation, and/or lack of maintenance. Under these adverse conditions, periodic inspectionin compliance with this supplement at more frequent inten/als until the owner or operator can set their own inspectionperiods based on the contingencies of field experience.
PRO LINE 21 SCHEDULED INSPECTION GENERAL INFORMATION
A complete schedule inspection tall phase 1, 2, 3, and 4 inspections) must be accomplished within 24-calender
month period. Any part of the inspection that has not been accomplished will become due immediately. Completionof the Phase 1, 2, 3, and 4 Inspections shall be considered as a complete inspection. The following Pro Line 21
installation items are added to the existing King Air 200 Series maintenance program.
Nov 5-00-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Phase 1 Inspection
ATA
F. CABIN SECTION REFERENCE MECH INSP
Autopilot Servo and Cable Inspect the aileron servo and mount for 22-10-00
security. Inspect mount capstan for cable wear, contamination and
excessive cable spool-off angle. Inspect cables for wear and damage.Verify cable tensions are within limits specified in the basic maintenance
manual.
Phase 1 Inspection
ATA
G. REAR FUSELAGE and EMPENNAGE REFERENCE MECH INSP
Autopilot Servos and Cables Inspect the rudder, elevator and elevator 22-10-00
trim servos and mounts for security. Inspect mount capstans for cable
wear, contamination and excessive cable spool-off angle. Inspectcables for wear and damage. Verify cable tensions are within limits
specified in the basic maintenance manual.
Phase 1 Inspection
ATA
Q. OPERATIONAL INSPECTION REFERENCE MECH INSP
Autopilot DCU Aural Warning Perform the AUTOPILOT DATA 22-10-00
CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
procedure.
Stall Warning Autopilot Disconnect Perform the STALL WARNING 22-10-00
AUTOPILOT DISCONNECT INSPECTION procedure.
Phase 2 Inspection
ATA
Q. OPERATIONAL INSPECTION REFERENCE MECH INSP
Pilot Display Switch Perform the ENGINE INDICATrON REVERSION 77-40-00
INSPECTION procedure.
Autopilot DCU Aural Warning Perform the AUTOPILOT DATA 22-10-00
CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
procedure.
Stall Warning Autopilot Disconnect Perform the STALL WARNING 22-10-00
AUTOPILOT DISCONNECT INSPECTION procedure.
5-00-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Phase 3 Inspection
ATA
Q. OPERATIONAL INSPECTION REFERENCE MECH INSP
Autopilot DCU Aural Warning Perform the AUTOPILOT DATA 22-10-00
CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
procedure.
Stall Warning Autopilot Disconnect Perform the STALL WARNING 22-10-00
AUTOPILOT DISCONNECT INSPECTION procedure.
Phase 4 Inspection
ATA
Q. OPERATIONAL INSPECTION REFERENCE ~ECH INSP
Pilot Display Switch Perform the ENGINE INDICATION REVERSION 77-40-00
INSPECTION procedure.
Autopilot DCU Aural Warning Perform the AUTOPILOT DATA 22-10-00
CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
procedure.
Stall Warning Autopilot Disconnect Perform the STALL WARNING 22-10-00
AUTOPILOT DISCONNECT INSPECTION procedure.
Complete Inspection
ATA
Q. OPERATIONAL INSPECTION REFERENCE MECH INSP
Pilot Display Switch Perform the ENGINE INDICATION REVERSION 77-40-00
INSPECTION procedure.
Autopilot DCU Aural Warning Perform the AUTOPILOT DATA 22-10-00
CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
procedure.
Stall Warning Autopilot Disconnect Perform the STALL WARNING 22-10-00
AUTOPILOT DISCONNECT INSPECTION procedure.
Nov 14/03~bs 5-00-00
RBYtheon nirtraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
PRO LINE 21 SPECIAL INSPECTION GENERAL INFORMATION
Special Inspection
INSPECTION
SPECIAL INSPECTION INTERVAL MECH INSP
Autopilot Servo Mount Slip Clutch Test Perform the AUTOPILOT 12,000 hours
SERVO MOUNT SLIP CLUTCH TEST procedure as described in
Chapter 22-10-00.
Perform the ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) 3 to 6 months
BATTERY (PS835D) PERIODIC CHECK procedure in Chapter 34-25-
00.
Perform the ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) Annual
BATTERY (PS835D) CAPACITY TEST procedure in Chapter 34-25-00.
5-00-00 Nov 14/03Page 5
CHAPTER
LEVELING AND
VVEIGHING
RBytheOn nireraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 8 1 LEVELING AND WEIGHING
TABLE OF CONTENTS
SUBJECT PAGE
8-00-00
Leveling and Weighing Description and Operation ........1
Raytheoa Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 22 1 AUTO FLIGHT
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
22-LOEP 1 Nov 14/03
22-CONTENTS 1 and 2 Nov 14/03
22-00-00 1 Nov 14/03
22-1 0-00 1 Nov 14/03
201 thru 219 Nov 14/03
22-LOEP Nov 14/03Pagel
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUTO FLIGHT DESCRIPTION AND OPERATION
RECOMMENDED MATERIALS
The recommended materials listed in Chart 1 as meeting federal, military or supplier specifications are provided for
reference only and are not specifically recommended by Raytheon Aircraft Company. Any product conforming to the
specification listed may be used. The products included in this chart have been tested and approved for aviation
usage by Raytheon Aircraft Company, by the supplier or by compliance with the applicable specification. Generic
or locally manufactured products which conform to the requirements of the specification listed may be used even
though not included herein. Only the basic number of each product specification is listed. No attempt has been made
to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the
current revision of the applicable specification prior to usage of the product listed. This can be done by contactingthe supplier of the product to be used.
Chart 1
Recommended Materials
MATERIALS SPECIFICATION PRODUCT SUPPLIER
1. Adhesive RTV-732 General Electric Co.,Silicone Products Dept.Waterford, NY 12188
Raylheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUTO FLIGHT AUTOPILOT DESCRIPTION AND OPERATION
The Flight Guidance System (FGS) provides autopilot and flight guidance functions. The FGS has two identical
FGC-3000 Flight Guidance Computers (FGCs), three Primary Servos, one Pitch Trim Servo, and one FGP-3000
Flight Guidance Panel (FGP).
Two FGC-3000 Flight Guidance Computers (FGCs) reside in the Integrated Avionics Processor System (IAPS)Card Cage which is located in the left nose avionics rack. These computers provide independent flight guidancecomputation and operate together to provide 8axis autopilot and pitch trim functions. The FGCs receive Attitude
Heading System (AHS) data directly from the Attitude Heading Computer (AHC); Air Data System (ADS), Radio
Sensor System (RSS), and Flight Management System (FMS) data through the IAPS concentrators. The PrimaryFlight Displays (PFDs) also display FCS mode and autopilot information.
The SVO-3000 Primary Servos (SVOs) precisely move the airplane’s elevator, aileron and rudder, while another
SVO-3000 is for trim. The SVO-3000 servos are mounted on SMT-65 mounts. Each servo mates with their
respective servo mount to provide a precision drive mechanism for controlling the displacement of the primary and
trim control surfaces of the aircraft. The servos consist of a permanent magnet de motor, an electromagnetic engageclutch and a precision multistage gear train. The drive motor and engage clutch are mounted to a housing that
contains the gear train and provides the mounting surface of the servo. The elevator trim servo is enclosed in a cover
for environmental protection. The servo is mounted directly to the back of the mount.
Aileron Servo is mounted beneath the cabin center aisle floorboards forward of the aft spar. Cables from the servo
mount capstan are connected to the aileron quadrant regulator. When the autopilot is engaged, the servo rotates,
causing aileron deflection in a direction dependent on the servo rotation.
Rudder servo is located in the tail section aft of the aft pressure bulkhead. The cable is wrapped around the servo
mount capstan and connected to the main left rudder torque bell crank and the right rudder cable. When the yawaxis is engaged, the servo rotates in response to autopilot signals, causing rudder deflection in a direction
dependent on direction of servo rotation.
Elevator servo is located in the tail section aft of the pressure bulkhead next to the rudder servo. Cables wrappedaround the mount capstan are connected to the primary (up and down) elevator control cables. When the autopilotis engaged, the servo rotates, causing elevator deflection in a direction dependent upon the direction of the servo
rotation.
The FGP-3000 Flight Guidance Panel (FGP) provides autopilot, yaw damper, and pitch trim control and flightguidance and is located above the flight instrument panel. Flight Guidance Modes are selected by the push on/off
buttons on the FGP. Flight Guidance Modes include Lateral, Roll Hold, Heading Select, Navigation (NAV), Approach(Lateral and Vertical), Back Course, Go Around, Vertical, Pitch Hold, Altitude Hold (ALT), Preselect Altitude, Vertical
Speed, Flight Level Change, Vertical Navigation (VNAV) and Overspeed Mode.
22-10-00 ,,V~Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUTO FLIGHT AUTOPILOT MAINTENANCE PRACTICES
FLIGHT GUIDANCE COMPUTER (FGC-3000) REMOVAL
NOTE
The two FGC-3000 Flight Guidance Computers are located in the IAPS card cage in the left nose
avionics rack (Ref. Figure 201).
a. Remove electrical powerfrom airplane.
b. Remove the left avionics compartment door.
c. Remove the appropriate Flight Guidance Computer. Perform the ICC-3000 IAPS CARD CAGE MODULES
REMOVAL procedure. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21
Avionics System.)
FLIGHT GUIDANCE COMPUTER (FGC-3000) INSTALLATION
NOTE
The two FGC-3000 Flight Guidance Computers are located in the IAPS card cage in the left nose
avionics rack (Ref. Figure 201).
a. Install the appropriate Flight Guidance Computer. Perform the ICC-3000 IAPS CARD CAGE MODULES
INSTALLATION procedure. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line
21 Avionics System.)
b. Perform the FLIGHT GUIDANCE COMPUTER (FGC-3000) ADJUSTMENTTTEST procedure.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the FGC-3000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
22-10-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
´•I
AB DETMLA
1.122-3001
2. PWR-3000 NO. 1
3. FGC-3000 NO. 1
4. CSU-S100 NO. 1 DCM-3100 NO. 1
5. FMC-3000 NO. 1
6. 100-3100 NO. 1
7. MDC-3110
8. PWR-3000 NO. 2
9. FGC-3000 NO. 2
10. CSU-3100 NO. 2 DCM-3100 NO.2
11. FMC-3000 NO. 2
12. 100-3001 NO. 2
7
10
12
8
DETAIL B88228
0347´•UAA.AI
Flight Guidance Computer (FGC-3000) Locations
Figure 201
Nov 22-10-00
Raytheon nircrart CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
FLIGHT GUIDANCE PANEL (FGP-3000) REMOVAL
NOTE
The FGP-3000 Flight Guidance Panel is located above the flight instrument panel (Ref. Figure 202).
a. Remove electrical powerfrom the airplane.
b. Remove the guidance panel. Perform the PANEL MOUNTED UNITS (SCREW) REMOVAL procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
FLIGHT GUIDANCE PANEL (FGP-3000) INSTALLA TION
NOTE
The FGP-3000 Flight Guidance Panel is located above the flight instrument panel (Ref. Figure 202).
a. Install the guidance panel. Perform the PANEL MOUNTED UNITS (SCREW) INSTALLATION procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the FLIGHT GUIDANCE PANEL (FGP-3000) ADJUSTMENTTTEST procedure.
FLIGHT GUIDANCE PANEL (FGP-3000) ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING and TROUBLESHOOTING procedure for the FGP-3000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
22-10-00 203
Raytheon nircrart CompanySUPER KING AIR 200 SERIES PRO LINE 21
r7) I´•I II II 1´•1 ~211´•1 11 111’1´•1 11 II I´•I CO
~7 P ~I EiV 5´•
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AUDIOAUDIO I I I I CONTROLCONTROL I I I I PANELPANEL (ACP)(ACP) LEFT RIGHT
INBOARD INBOARD
SUBPANEL SUBPANEL
LEFT RIGHTRADIO OUTBOARDOUTBOARDTUNING UNIT SUBPANELSUBPANEL(RTU-4200)
REVERSIONARY PANEL
DISPLAY CONTROL
DISPLAY CONTROL --1 PANEL(DCP-3000)
PANEL(DCP-3000)
88348033959F1F1
Flight Guidance Panel (FGP´•3000) Location
Figure 202
Nov 22-10-00
RayNheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AILERON SERVO AND MOUNT SERVICING
NOTE
The Autopilot uses the aileron servo to move the airplane control surfaces. The aileron servo is
attached to the aileron servo mount.
AILERON SERVO AND MOUNT REMOVAL
a. Remove electrical power from the airplane.
b. Gain access to the aileron servo and mount by removing the floorboard panels at station 221 (Ref. Figure 203).
c. If the servo mount is being removed, perform the AILERON SERVO CABLE REMOVAL procedure.
d. Remove the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure for data to be used for removal of the item. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and
FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65.)
AILERON SERVO AND MOUNT INSTALLATION
a. Install the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation
Manual 523-0771862 for SVO-3000 and SMT-65.) (Ref. Figure 203).
b. If the servo mount was installed, perform the AILERON SERVO CABLE INSTALLATION procedure.
c. Perform the AILERON SERVO AND MOUNT ADJUSTMENT/TEST procedure.
d. Installthefloorboard panels.
AILERON SERVO AND MOUNT ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING and TROUBLESHOOTING procedure for the SVO-3000 servo and SMT-65 mount. (Ref.Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation Manual 523-0771862 for
SVO-3000 and SMT-65.)
c. Remove electrical power from the airplane.
22-10-00 205
Ray~heon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AILERONSER\IO
/´•1
i
i.
C~3
Aileron Servo Location
Figure 203
22110100
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AILERON SERVO CABLE REMOVAL
a. Remove electrical power from the airplane.
b. Gain access to the aileron servo cable by removing up the floorboard panels at station 221.
c. Perform the AILERON SERVO (APS-65 OR AP-106) CABLE REMOVAL procedure in Chapter 22-10-00 of the
Super King Air 200 Series Maintenance Manual.
AILERON SERVO CABLE INSTALLATION
NOTE
When performing the procedure in Step a., set the final cable tension to 25 2 pounds at 59"F.
a. Perform the AILERON SERVO (APS-65 OR AP-106) CABLE INSTALLATION AND RIGGING (EXCEPTAIRPLANES WITH THE OPTIONAL CAMERA BAY) procedure in Chapter 22-10-00 of the Super King Air 200
Series Maintenance Manual.
b. Perform the AILERON SERVO AND MOUNT ADJUSTMENT/TEST procedure.
c. Install the floorboard panels.
RUDDER SERVO AND MOUNT SERVICING
NOTE
The Autopilot uses the rudder servo to move the airplane control surfaces. The rudder servo is
attached to the rudder servo mount.
RUDDER SERVO AND MOUNT REMOVAL
a. Removeelectrical powerfromtheairplane.
b. Openthetail avionicsbayhatch.
c. If the servo mount is being removed, perform the RUDDER SERVO CABLE REMOVAL procedure.
d. Remove the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure for data to be used for removal of the item. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and
FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65.) (Ref. Figure 204).
RUDDER SERVO AND MOUNT INSTALLATION
a. Install the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure for data to be used for removal of the item. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and
FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65.) (Ref. Figure 204).
b. If the servo mount was installed, perform the RUDDER SERVO CABLE INSTALLATION procedure.
c. Perform the RUDDER SERVO AND MOUNT ADJUSTMENTTTEST procedure.
d. Close the tail avionics bay hatch.
22-10-00 207
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
RUDDER SERVO AND MOUNT ADJUSTMENTTTEST
a. Apply electrical powertotheairplane.
b. Perform the TESTING and TROUBLESHOOTING procedure for the SVO-3000 servo and SMT-65 mount. (Ref.Rockwell Collins, Inc. APS-65 Autopilot and FGS Plight Guidance System Installation Manual 523-0771862 for
SVO-3000 and SMT-65.)
c. Remove electrical power from the airplane.
Page 208Nov14/03 22-1 0-00
RaYlIOeoe AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
YAoOO
RUDDER SERVO
ELRIATORSERVO
63 h\ I RUB BLOCK
r-
r
DETAIL Av ~su
Rudder and Elevator Servo Location
Figure 204
22-10-00
NoVMloMl AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
RUDDER SERVO CABLE REMOVAL
a. Remove electrical power from the airplane.
b. Open the tail avionics bay hatch.
c. Perform the RUDDER SERVO (APS-65 OR AP-106) CABLE REMOVAL procedure in Chapter 22-10-00 of the
Super King Air 200 Series Maintenance Manual.
RUDDER SERVO CABLE INSTALLATION
NOTE
When performing the procedure in Step a., set the final cable tension to 25 2 pounds at 59"F.
a. Perform the RUDDER SERVO (APS-65 OR AP-106) CABLE INSTALLATION AND RIGGING procedure in
Chapter 22-10-00 of the Super King Air 200 Series Maintenance Manual.
b. Perform the RUDDER SERVO AND MOUNT ADJUSTMENT~TEST procedure.
c. Close the tail avionics bay hatch.
ELEVA TOR SERVO AND MOUNT SERVICING
NOTE
The Autopilot uses the elevator servo to move the airplane control surfaces. The elevator servo is
attached to the elevator servo mount.
ELEVATOR SERVO AND MOUNT REMOVAL
a. Remove electrical power from the airplane.
b. Open the tail avionics bay hatch.
c. If the servo mount is being removed, perform the ELEVATOR SERVO CABLE REMOVAL procedure.
d. Remove the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure for data to be used for removal of the item. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and
FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65.) (Ref. Figure 204).
e. If the servo is being replaced, remove the rub block from the servo for use on the replacement servo. Remove
the adhesive from the servo with MPK or Naphtha ~2 or 3, Chart 1, 22-00-00).
ELEVATOR SERVO AND MOUNT INSTALLATION
a. If the servo was replaced, install the rub block on the replacement servo (Ref. Figure 204). Clean the servo and
rub block with MPK or Naphtha (2 or 3, Chart 1, 22-00-00). Use adhesive (1, Chart 1, 22-00-00) to secure the
rub block to the servo. Apply the adhesive to the center and inside edges of cutout. Let the adhesive cure for 24
hours before flying the airplane.
Nov 22-10-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
b. Install the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation
Manual 523-0771862 for SVO-3000 and SMT-65.).
c. If the servo mount was installed, perform the ELEVATOR SERVO CABLE INSTALLATION procedure.
d. Perform the ELEVATOR SERVO AND MOUNT ADJUSTMENTTTEST procedure.
e. Closethetail avionicsbay hatch.
ELEVATOR SERVO AND MOUNT ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the SVO-3000 servo and SMT-65 mount.
(Ref. Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation Manual 523-
0771862 for SVO-3000 and SMT-65.)
c. Remove electrical power from the airplane.
ELEVATOR SERVO CABLE REMOVAL
a. Remove electrical power from the airplane.
b. Openthetail avionicsbay hatch.
c. Perform the ELEVATOR SERVO CABLE REMOVAL procedure in Chapter 22-10-00 of the Super King Air 200
Series Maintenance Manual.
ELEVATOR SERVO CABLE INSTALLATION
NOTE
When performing the procedure in Step a., set the final cable tension to 15 2 pounds at 59"F.
a. Perform the ELEVATOR SERVO CABLE INSTALLATION procedure in Chapter 22-10-00 of the Super King Air
200 Series Maintenance Manual.
b. Perform the ELEVATOR SERVO AND MOUNT ADJUSTMENT/TEST procedure.
c. Close the tail avionics bay hatch.
ELEVATOR TRIM SERVO AND MOUNT SERVICING
NOTE
The Autopilot uses the elevator trim servo to move the airplane control surfaces. The elevator trim
servo is attached to the elevator trim servo mount
22-10-00 211
RBytheMI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELEVATOR TRIM SERVO AND MOUNT REMOVAL
a. Remove electrical power from the airplane.
b. Openthetailavionics bay hatch.
c. Remove the elevator trim servo cover (Ref. Figure 205).
d. Remove the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure for data to be used for removal of the item. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and
FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65.)
ELEVATOR TRIM SERVO AND MOUNT INSTALLATION
a. Install the servo and/or mount, refer to the INSTALLATION OF SERVO and/or INSTALLATION OF SERVO
MOUNT procedure. (Ref. Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation
Manual 523-0771862 for SVO-3000 and SMT-65.) (Ref. Figure 205).
b. Perform ELEVATOR TRIM SERVO AND MOUNT ADJUSTMENT/TEST procedure.
c. Install the elevator trim servo cover.
d. Close the tail avionics bay hatch.
ELEVATOR TRIM SERVO AND MOUNT ADJUSTMENTTTEST
NOTE
Elevator Trim Servo cables must be rigged as specified in Chapter 27.
a. Apply electrical powertotheairplane.
b. Perform the TESTING and TROUBLESHOOTING procedure for the SVO-3000 servo and SMT-65 mount. (Ref.Rockwell Collins, Inc. APS-65 Autopilot and FGS Flight Guidance System Installation Manual 523-0771862 for
SVO-3000 and SMT-65.)
c. Remove electrical power from the airplane.
Nov 22-10-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELEVATOR TRIM SERVO COVER
00"3
B
ELEVATOR TRIM SERVO
DETAIL A0347BgAA.AI
Elevator Trim Servo Location
Figure 205
22-1 0-00 Nov 14/03Page 213
Raythetyn AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUTOPILOT SERVO MOUNT SLIP CLUTCH TEST (SMT-65)
NOTE
Every 12,000 flight hours (or at maintenance interval nearest to 12,000 hours) the operation of the
servo mount should be verified on aircraft servo mount slip clutch test.
a. Remove electrical power from the airplane.
b. Gain access to the servo by opening the respective panels.
NOTE
When performing Step c., refer to the SLIP CLUTCH SETTINGS chart for the value desired for the
applicable servo.
c. Perform the SERVO MOUNT CLUTCH ADJUSTMENT PROCEDURE (Ref. Rockwell Collins, Inc. APS-65
Autopilot and FGS Flight Guidance System Installation Manual 523-0771862 for SVO-3000 and SMT-65).
d. Close all panels that were opened to gain access to the servos.
Slip Clutch Settings
SURFACE SERVO TYPE MOUNT MOUNT SLIP CLUTCH SETTING
Aileron SVO-3000 SMT-65 21.8 2 in.-lbs
Rudder SVO-3000 SMT-65 21.8 ~t 2 in.-lbs
Elevator SVO-3000 SMT-65 7.3 1 in.-lbs
Elevator Trim SVO-3000 SMT-65 6 1 in.-lbs
NOTE Mount Slip Clutch Settings are to be measured at the pinion.
Nov 14/03Page 214 22-1 0-00
RaytheMI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUTOPILOT- DATA CONCENTRATOR UNIT (DCU) AURAL WARNING INSPECTION
a. Apply electrical power to the airplane.
b. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP) (Ref. Figure 206).
c. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
d. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
e. Open the DCU 1 circuit breaker on the left hand circuit breaker panel.
f. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
g. Close the DCU 1 circuit breaker on the left hand circuit breaker panel.
h. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
i. Open the DCU 1 SEC circuit breaker on the left hand circuit breaker panel.
i. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
k. Close the DCU 1 SEC circuit breaker on the left hand circuit breaker panel.
I. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
rn. Open the DCU 2 circuit breaker on the left hand circuit breaker panel.
n. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
o. Close the DCU 2 circuit breaker on the left hand circuit breaker panel.
p. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
q. Open the DCU 2 SEC circuit breaker on the left hand circuit breaker panel.
r. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
s. Close the DCU 2 SEC circuit breaker on the left hand circuit breaker panel.
t. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
u. Open the DCU 1 and DCU 1 SEC circuit breakers on the left hand circuit breaker panel.
v. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
w. Close the DCU 1 and DCU 1 SEC circuit breakers on the left hand circuit breaker panel.
x. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
y. Open the DCU 2 and DCU 2 SEC circuit breakers on the left hand circuit breaker panel.
22-10-00 215
RBy~heMI nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
z. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
aa. Close the DCU 2 and DCU 2 SEC circuit breakers on the left hand circuit breaker panel.
ab. Remove electrical power from the airplane.
Nov 22-10-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
AUDIO I I I I LCONTROLCONTROL I I I PANELPANEL (ACP)(ACP) LEFT RIGHT
INBOARD INBOARD
SUBPANEL SUBPANEL
LEFT RIGHTRADIO OUTBOARDOUTBOARDTUNING UNIT SUBPANELSUBPANELCRTU-4200)
REVERSIONARY PANEL
DISPLAY CONTROL
DISPLAY CONTROL ---I PANEL(DCP-3000)
PANEL(DCP-3000)
BB34B033959RR
Flight Guidance Panel (FGP-3000) Location
Figure 206
22-1 0-00 Nov 14/03Page 217
RBYsheMI AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
STALL WARNING AUTOPILOT DISCONNECT INSPECTION
a. Apply electrical powertotheairplane.
b. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP) (Ref. Figure 206). Verifythe green AP is displayed on the PFD indicating engaged autopilot.
c. Disengage the autopilot by pushing down the YD/AP DISC bar. Verify that aural warning for autopilot disconnect
is sounded.
d. Engage the autopilot by pressing the AP button on the Flight Guidance Panel (FGP).
e. Initiate a stall warn test through the STALL WARN TEST switch in the right inboard subpanel (Ref. Figure 207).Verify that the aural warning for the stall warning is sounded followed by autopilot disconnect. Monitor the PFD
for red flashing AP indicating a disengaged autopilot.
f. To stop the autopilot aural warning, press the red AP Disconnect button on the pilot or copilot control wheel.
g. Removeelectrical powerfromtheairplane.
Nov 22-10-00
NaYthe(Hl Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
iii ~1 a a ale
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B82LB034765RF1
Stall Warning Test Switch Location
Figure 207
22-1 0-00 Nov 14/03Page 219
CHAPTER
COMM U N I:CAT IONS
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 23 1 COMMUNICATIONS
TABLE OF CONTENTS
SUBJECT PAGE
23-10-00
Speech Communications VHFSystem Description and Operation. ............t
Speech Communication VHF System Maintenance Practices .........,,..201
Audio Control Panel (ACP) (Mode1804/805) Removal 201
Audio Control Panel (ACP) (Mode1804/805) Installation. 201
Audio Control Panel (ACP) (Mode1804/805)Test. 201
Db SystemsAudioControl Amplifier(Model 700) Removal. 203
Db SystemsAudio ControlAmplifier (Model 700) Installation 203
Db Systems Audio Control Amplifier(Model 700) Test 203
Db SystemsAuralWarning Generator(Modele30) Removal 205
Db SystemsAuralWarning Generator(ModelB30) Installation 205
Db SystemsAuralWarning Generator(Model 530)Test. 205
Jan 31/05~, PS-CONTENTS
RByH~MI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 23 COMMUNICATIONS
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
23-LOEP 1 Jan 31/05
23-CONTENTS 1 and 2 Jan 31/05
23-1 0-00 1 Nov 14/03
201 thru 204 Nov 14/03
23-10-01 1 thru 6 Jan 31/05
201 thru 206 Jan 31/05
23-12-00 1 thru 9 Jan 31/05
201 thru 203 Jan 31/05
23-30-00 1 Nov 14/03
201 and 202 Nov 14/03
23-50-00 1 Nov 14/03
201 thtu 205 Nov 14/03
Al 23-LOEP Jan 31/05Page 1
RaYnyeOyy Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
SPEECH COMMUNICATIONS VHF SYSTEM DESCRIPTION AND OPERATION
The VHF-4000 is used with the Radio Tuning Unit (RTU) or Control Display Unit (CDU-3000), an antenna, and the
airplane audio system to provide e-way VHF voice communications. The RTU or CDU may be used to tune the
transceiver.
The VHF-4000 transceiver is a remote mounted Very High Frequency (VHF) communications transceiver providingdouble side band (DSB) amplitude modulated (AM) voice/analog data operation. The standard VHF-4000 operatesin the aeronautical VHF communications band from 118.000 through 136.975 MHz with 25 KHz channel spacingfrequency.
23-10-00 N,Y’:Z:
RBYtheOR Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
SPEECH COMMUNICATION VHF SYSTEM MAINTENANCE PRACTICES
VHF TRANSCEIVER (VHF-4000) REMOVAL
NOTE
The VHF transceivers are located in the right nose avionics bay (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the right avionics compartment door.
c. Remove the appropriate VHF Transceiver. Perform the RACK MOUNTED LRU REMOVAL procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
VHF TRANSCEIVER (VHF-4000) INSTALLATION
NOTE
The VHF transceivers are located in the right nose avionics bay (Ref. Figure 201).
a. Install the appropriate VHF Transceiver. Perform the RACK MOUNTED LRU INSTALLATION procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
b. Perform VHF TRANSCEIVER (VHF-4000) ADJUSTMENTTTEST procedure.
c. Install the right avionics compartment door.
VHF TRANSCEIVER (VHF-4000) ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the VHF-4000. (Ref. Rockwelr Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
c. Remove electrical power from the airplane.
23-10-00 N~:
Ray2heon AiKra)t CompanySUPER KING AIR 200 SERIES PRO LINE 21
GLOBAL POSITIONINGGLOBAL POSITIONING SYSTEM (GPS-4000A) NO. 1
SYSTEM (GPS-4000A) NO. 2
(OPTIONAL) B ee238DETAIL 03~766AA.AI
VHF Transceivers (VHF-4000) Location
figure 201
Nov 14/03Page 202 23-1 0-00
RBYtheOl Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
VHF COMM ANTENNA REMOVAL
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in the Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
VHF COMM ANTENNA INSTALLATION
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in the SuperKing Air 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform the VHF TRANSCEIVER (VHF-4000) ADJUSTMENTTTEST procedure.
RADIO TUNING UNIT (RTU-4200) REMOVAL
NOTE
The RTU-4200 Radio Tuning Unit is located in the flight instrument panel (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Remove the Radio Tuning Unit. Perform the PANEL MOUNTED UNITS (SCREW) REMOVAL procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
RADIO TUNING UNIT (RTU-4200) INSTALLATION
NOTE
The RTU-4200 Radio Tuning Unit is located in the flight instrument panel (Ref. Figure 202).
a. Install the Radio Tuning Unit. Perform the PANEL MOUNTED UNITS (SCREW) INSTALLATION procedure.(Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
b. Perform the RADIO TUNING UNIT (RTU-4200) ADJUSTMENTTTEST procedure.
RADIO TUNING UNIT(RTU-4200) ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the RTU-4200. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System).
c. Remove electrical powerfrom the airplane.
23-10-00
Ray~lleon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
RIGHTLEFT RADIO OUTBOARDOUTBOARD TUNING UNIT SUBPANELSUBPANEL CRTU-4200)
REVERSIONARY PANEL
DISPLAY CONTROLPANEL(DCP-3000)
DISPLAY CONTROLPANELCDCP-3000)
88348033959F1F1
Radio Tuning Unit (RTU-4200) Location
Figure 202
Page 204Nov 14/03 23-1 0-00
Ray~beon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
HF-9000 HIGHIFREQUENCY COMMUNICATIONS SYSTEM DESCRIPTION AND
OPERATION
The Collins HF-9000 High-Frequency Communications System provides a worldwide communications capability.The system consists of an HF-9031A Receiver-Transmitter and a HF-9041 Antenna Coupler, both located in the aft
avionics compartment. An HF wire antenna is located on the top of the fuselage and extends back to the vertical
stabilizer. All functions of the HF radio can be controlled through the pilot’s CDU and/or the Radio Tuning Unit (RTU).The HF radio is powered from the Left Generator Avionics Bus. Two circuit breakers are located on the right circuit
breaker panel, one placarded HF COM (25 amps) to protect the receiver-transmitter, and one placarded HF ANT (5amps) to protect the antenna coupler. Power is applied to the HF radio when the Avionics Master switch is turned on.
The HF radio operates in the HF band of 2.0000 to 29.9999 MHz in 100-Hz steps. Operating Emission modes
include upper sideband voice (UV), lower sideband voice (LV) and amplitude modulation equivalent (AM). Both
Simplex and Half-Duplex Tuning Modes are available.
NOTE: The AM Emission Mode has a frequency band width of 15 KHz. Thus, radio stations with frequenciesseparated by 15 KHz or less may be received simultaneously.
Four HF Tuning Modes are available; a Frequency Tuning Mode, an Emergency Tuning Mode, a Maritime (ITU)Tuning Mode, and a Preset Tuning Mode. The Frequency Tuning Mode allows any valid frequency (either Simplexor Half-Duplex) and its emission mode to be manually set in the Active frequency window or the Recall frequencywindow of the RTU, or the Active frequency window of the CDU. The Emergency Tuning Mode consists of 6
emergency channels (stored in non-volatile memory) which may be set into the Active or Recall window of the RTU,or the Active frequency window of the CDU. The Maritime Tuning Mode consists of 249 ITU (InternationalTelecommunications Union) public correspondence channels that are stored in non-volatile memory. These
channels may also be set into the Active or Recall frequency windows of the RTU or the Active frequency window
of the CDU. A listing of the available public correspondence channels may be found in the Collins HF-9000
Operator’s Manual. The Preset Tuning Mode consists of twenty user-defined channels. The 20 available channels
in the RTU are independent from the 20 available channels in the CDU. Thus, a total of 40 different presetfrequencies are available; 20 in the RTU and 20 in the CDU. The 20 channels in the RTU can only be filled with
Simplex or Half-Duplex frequencies and their emission modes. Maritime and Emergency channels cannot be stored
in this unit. The CDU can be filled with Simplex and Half-Duplex frequencies and their emission modes as well as
Emergency channels and Maritime channels.
A TEST mode is available for testing the system on the ground or in the air. The test may be conducted from the
RTU or the CDU. No HF setting can be changed during the test.
Three levels of transmission power are available; LO (approximately 15 Watts average), MED (approximately 30
Watts average), and HI (approximately 50 Watts average.)
Because Mi radio transmissions can interfere with ADF signal reception, the ADF receiver freezes the existingbearing indication whenever the HF transmitter is keyed.
The RTU contains three pages that can be used for control of the HF radio; the NEXT page of the Top Level DisplayPage, the HF Main Display page (HF) and the HF Preset pages (HF).
The CDU also contains three pages that can be used for control of the HF radio; page 2 of the TUNE page, the HF1
Control Page and the HF1 Presets page.
The following table shows which HF features can be set on each page of the RTU and the CDU:
n, 23-1 0-01 L~6:Page 1
Raytheon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Function Top Level HF1 Main HF1 Presets
Display, Next Display Page Page (HF1Page (HF1 Control) Presets)
RTU CDU RTU CDU RTU CDU
Tune Active f X X X X X
Tune Recall f X X
Change X X X X
Squelch
Change X X X X X
Emission
Mode (UV, LV,AM)
Change X X
Transmission
Power (LO,MED, HI)
Access HF1 X X
Preset page
Conduct SELF X X
TEST
Select Simplex X X X X X
or Duplex
Change i X
Tuning Mode
(FREQ,PRESET,EMER, MAR)
Program I (X X
Preset f’s
The following procedures are a basic guide to operating the HF radio using the RTU and the CDU. A short hand is
used to denote key positions. For example, the third Line Select Key on the Right side of the display will appear as
LSK R3.
RTU
a. From the Top Level Display page, select the NEXT PAGE using LSK L4 to access the Top Level HF DisplayPage which shows the Active and Recall HF frequencies.
b. The display of HF Active and Recall frequencies will vary depending on the Tuning Mode of the HF radio (FREQ,PRESET, EMER, or MAR) and whether or not Simplex or Half-Duplex frequencies are being used.
Jan 31/05~:m, 23-1 0-01 Al
Raylheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
1. FREQ Mode. In this mode frequencies from 2.0 to 29.9999 MHz may be set in the Active or Recall display.If the Half-Duplex mode has been selected, both a receive (R) and a transmit (T) frequency may be set in.
either display.
2. PRESET Mode. In this mode a preset channel from 1 to 20 can be selected. A preset channel may contain
a Simplex frequency, or a Half-Duplex frequency. Emergency and Maritime channels can not be
programmed into a preset channel of the RTU.
3. EMER Mode. In the Emergency Mode one of six emergency channels may be selected.
4. MAR Mode. In the Maritime Mode, one of 249 ITU public correspondence channels may be selected. (0401429, 0601 0608, 0801 0837, 1201 1241, 1601 1656, 1801 1815, 2202 2253, and 2501 2510.)
c. The Active and Recall HF frequencies and corresponding Emission modes may be set on the Top Level HF
Display page as well as the Squelch setting. For example, to set the active frequency window:
1. Push LSK L1 to activate the tuning window.
2. Rotate the large knob to position the window at the location where a change needs to be made.
3. Rotate the small knob to change the value.
4. Rotate the large knob to the next position and repeat the process.
5. The Squelch can be adjusted in increments from 0 to 3 using the small knob.
6. The Emission source can be set at UV, LV or AM using the small knob.
d. The Recall frequency and Emission mode is set on the Top Level HF Display page in a similar manner.
e. Press the LSK L1 twice (if tuning window has not been selected) to access the HF Main Display page.
1. Use LSKs L1 and R1 and the control knobs to set Active and Recall HF frequencies in the same manner
used on the Top Level Display.
2. Use LSK L2 to set the transmission power to LO, MED, or HI. Each press of the key will cycle the radio to
the next power level.
3. Use LSK L3 to select the Preset page.
4. Use LSK L4 to return to the Top Level Display page.
5. Use LSK R2 to select the SIMPLEX or DUPLEX Mode. The DUPLEX Mode refers to Half-Duplex operationwhere the transmit frequency is different from the receive frequency. For this key to be active, the tuningwindow must be selected in either the Active freiluency display by pressing key L1 or selected in the Recall
frequency display by pressing key R1. Each press of key R2 cycles the radio between SIMPLEX and
DUPLEX.
6. Press and release LSK R3 to run the HF self-test. The white TEST legend will enlarge and change color to
cyan. The Active frequency will be replaced with the cyan message IN TEST, both on this page, the TopLevel Display page, and the Preset page. The test lasts approximately 40 seconds. If successful, the pagereturns to normal. If unsuccessful, a six digit code will appear on the RTU. This code may be interpretedfrom the RTU installation manual, P/N 523-0786424-041116.
Note: The Active frequency will be inoperative after a self-test has been conducted. To reactivate the frequency,cycle it to the Recall window, then back to the Active window.
*1 23-1 0-01 Jan 31/05Page 3
Raytheon Aireraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
f. Press the LSK L3 to select the Preset page.
’1. Seven Preset pages are available for setting up to 20 preset frequencies. Press LSK R3 to select the tune
window, then rotate either the large or small control knob to change the page number from 1 to 7.
2. Press LSK L1, L2, or R1 to activate the tuning window for the channel to be preset.
3. Press LSK R2 to select either the SIMPLEX or DUPLEX mode for the frequency to be preset.
4. Then use the large and small knobs to set the frequency and Emission mode.
5. The LSK L3 may be used to change the tuning mode of the radio (FREQ, PRESET, EMER, and MAR). Each
press of the key selects the next mode.
6. Press LSK L4 to return to the HF Main Display page.
CDU
a. Press the Tune Function Key to select the Tune page.
b. Select page 2 of the Tune page by pressing the NEXT key.
c. The active HF frequency is shown in the HF sub-display opposite LSK L4 along with the associated Emission
mode.
d. The Squelch setting is shown between LSKs 5 and 6. These LSKs may be used to adjust the squelch from 0 to 3.
e. The HF frequency may be tuned by entering it in the scratch pad and then pressing LSK L4. The followingprocedures are used to enter the desired frequency or channel.
1. Enter the frequency in MHz in the scratch pad using up to 6 digits, followed by the desired Emission mode
(e.g. 10.2345AM). The decimal point is optional if no decimal digits are required; however, if a decimal pointis not used, add the letter F after the digit to distinguish is from an emergency channel.
Example: 5F may be entered for the frequency 5.0000. (lf the FREQ Tuning Mode of the radio has been
selected, the F is not required.)
2. If only the Emission mode of the existing frequency needs to be changed, enter only the desired mode in
the scratch pad (e.g. UV, LV or AM).
3. If a Half-Duplex operating mode is required, enter either the Transmitting or Receiving frequency, precededby the letter T or R. Enter a space using the SP key, then enter the second frequency preceded by T or R.
The Emission mode follows the last frequency with no space.
Example: T10.1234(space)R15. 1234UV.
4. When entering an Emergency or Maritime (ITU) channel, the letter E or M must follow the channel unless
the Tuning Mode of the preset frequency matches the existing Tuning Mode of the radio.
For example, the following channels would be entered as shown: 6E Emergency channel 6 and 403M
Maritime channel 0408.
f. Press LSK L4 to select the HF1 Control page.
1. The active HF frequency and Emission mode is displayed adjacent to LSK L1 and may be changed as
described in step e.
2. The squelch may be adjusted using LSKs L3 and L4 as previously described.
Jan 23-1 0-01
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
3. The Tuning Mode may be changed using LSK L5. Each push of the LSK cycles the Tuning Mode between
FREQ, EMER, and MAR.
4. The HF1 Presets page is selected using LSK L6.
5. The transmission power of the HF radio is set using LSK R1. Each push of the LSK cycles the powerbetween LO, MED, and HI.
6. Press LSK R2 to activate the self-test.
a) The white TEST legend changes to cyan and enlarges.
b) After approximately 14 seconds, the cyan TEST legend is replaced by a green PASS message. This
message will remain unless the frequency, power level, or Tuning Mode is changed. However, it is not
necessary to clear the PASS message in order to run another self-test or use the radio.
Note: The Active frequency will be inoperative after a self-test has been conducted. To reactivate the frequency,cycle it to the Recall window, then back to the Active window using the RTU.
g. Press LSK L6 to select the HF1 Presets page.
1. The active frequency can be changed using LSK L1 as previously described in step e.
2. Twenty preset frequencies and/or channels can be set on five preset pages. Pages are selected using the
NEXT or PREV keys.
3. A preset frequency may be entered as a Simplex frequency, Half-Duplex frequency, Emergency channel,or a Maritime channel using the procedures previously described.
4. An identifier can be associated with a preset frequency or channel. The identifier can be up to 12 characters
long, must begin with a letter, but may contain digits. If sufficient space is available in the scratch pad, the
identifier may be included as the last portion of the frequency entry, with a space separating the two. If
sufficient space is not available, the identifier may be added as a separate entry after the frequency has
been entered.
The general format is: T(freq)spaceR(freq)(emission mode)space(identifier). The identifier will be displayedin cyan to the right of the preset frequency.
5. To load a preset frequency into the active window, use either the left or right LSK associated with the desired
frequency. The frequency will be loaded into the CDU and RTU active frequency window.
More detailed information may be found in the following documents.
Collins HF-9000 High-Frequency Communications System Operator’s Manual, P/N 523-0774344-008217
Collins RTU-4200/4210/4220 Radio Tuning Unit Pilot’s Guide, 2nd edition, dated May 1, 1996, or later edition
AVTECH CSD-714 SELCAL DECODER
The SELCAL (Selective Call) Decoder system consists of a CSD-714 decoder mounted in the aft avionics
compartment and a control panel mounted on the pedestal in the cockpit. The decoder is powered by the No. 3
Avionics Bus through a l-amp circuit breaker, placarded SELCAL, located on the right circuit breaker panel. The
control panel, placarded SELCAL, consists of a PUSH OFF switch/annunciator, and a red test button placardedSELF TEST. Backlighting of the control panel is adjusted using the OVHD FED 3 SUBPANEL rheostat located on
the overhead panel. The white HF SELCAL annunciator on the switch is illuminated when a SELCAL code is
nl 23-1 0-01Pege 5
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
received. The annunciator may be tested using the annunciator PRESS TO TEST button located on the glareshield.The illumination of the annunciator is adjusted using the ANNUN PUSH-BRT rheostat located on the overhead
panel. The decoder is capable of receiving 16 tone codes.
When a SELCAL code is received by the decoder, the HF SELCAL annunciator on the control panel will begin to
blink and a single tone will be heard over the speakers (speaker switch on or off) and the headsets. The annunciator
can be extinguished by pressing the switch/annunciator.
The SELCAL decoder may be manually tested by pressing the SELF TEST button on the control panel. When the
button is pressed, a single tone will be heard over the speakers and headsets and the white HF SELCAL annunciator
will blink for approximately 5 seconds, then extinguish.
The SELCAL decoder can function in normal operation only when the HF radio is set to the AM Emission Mode.
Jan 31/0523-1 0-01 c~,
Raytkcon nireraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
HF-9000 HIGH-FREQUENCY COMMUNICATIONS SYSTEM I MAINTENANCE PRACTICES
RECNVER/TRANSCEIVER (HF-9031A) REMOVAL
NOTE: The HF-9031A transceiver/receiver is located in the aft avionics compartment (Ref. Figure 201).
a. Open, safety and tag the circuit braker labeled HF COM.
b. Open the tail equipment bay hatch.
c. Cut and remove the lockwire from the two fiber optic plugs. Disconnect the fiber optic plugs from the connectors
on the receiver/transmitter. Install protective caps and covers to the plugs and connectors.
d. Disconnect the electrical plugs from the receiver/transmitter connectors. Install protective caps and covers to
the electrical plugs and connectors.
e. Cut and remove the lockwire from the mounting tray knurled knobs. Loosen the knurled knobs and remove the
receiver/transmitter.
RECEIVER/TRANSCEIVER (HF-903 IA) INSTALLA ~ON
NOTE: The HF-9031 A transceiver/receiver is located in the aft avionics compartment (Ref. Figure 201).
a. Install the receiver/transmitter to the mounting tray and tighten the knurled knobs. Lock the knurled knobs with
lockwire.
b. Remove the caps and covers from the fiber optic plugs and connectors.
Warning: When you install the fiber optic plugs, do not tighten them more than hand tight.
c. Install and hand tighten the fiber optic plugs to the receiver/transmitter connectors.
Warning: When you lock the fiber optic plugs do not overtighten the wire,
d. Safety the fiber optic plugs with lockwire. Do not overtighten the lockwire.
e. Remove the caps and covers from the electrical plugs and connectors.
f. Install and tighten the electrical plugs to the receiver/transmitter connectors.
g. Closethetail equipmentbay hatch.
h. Close the circuit breaker labeled HF COM.
ANTENNA COUPLER (HF-9041) REMOVAL
NOTE: The HF-9041 antenna coupler is located in the aft avionics compartment (Ref. Figure 201).
a. Open, safety and tag the circuit braker labeled HF ANT.
b. Open the tail equipment bay hatch.
c. Cut and remove the lockwire from the two fiber optic plugs. Disconnect the fiber optic plugs from the connectors
on the antenna coupler. Install protective caps and covers to the plugs and connectors.
Al 23-1 0-01 Jan 31/05Page 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
d. Disconnect the electrical plugs from the antenna coupler connectors. Install protective caps and covers to the
electrical plugs and connectors.
e. Cut and remove the lockwire from the mounting tray knurled knobs.
f. Loosen the knurled knobs. Carefully pull the antenna coupler forward and disengage the cable from the back
side of the antenna coupler.
g. Remove the antenna coupler from the airplane.
ANTENNA COUPLER (HF-904 1) INSTALLATION
NOTE: The HF-9041 antenna coupler is located in the aft avionics compartment (Ref. Figure 201).
a. Put the antenna coupler onto the mounting tray and install the cable on the back side of the antenna coupler.
b. Tighten the knurled knobs and lock with lockwire.
c. Remove the caps and covers and connect the electrical plugs to the antenna coupler connectors.
d. Remove the caps and covers from the fiber optic plugs and connectors.
Warning: When you install the fiber optic plugs, do not tighten them more than hand tight.
e. Install and hand tighten the fiber optic cable plugs to the antenna coupler connectors.
Warning: When you lock the fiber optic plugs do not overtighten the wire.
f. Lock the fiber optic plugs with lockwire. Do not overtighten the lockwire.
g. Close the tail equipment bay hatch.
h. Close the circuit breaker labeled HF ANT.
RP ANTENNA REMOVAL
a. Remove all electrical power from the airplane.
b. Remove the screw, washers, lockwasher and nut attaching the antenna to the tail mounting straps (Ref. Figure202).
c. Unscrewthe antenna support sleeve.
d. From inside the tail section, remove the cap nut, washer, and antenna lead-in wire.
e. Pull the antenna wire out of the lead-through insulator, the elbow insulator, and the antenna support sleeve.
f. Remove the antenna from the airplane. r
HFANTENNA INSTALLATION
a. Removeallelectrical powerfromtheairplane.
b. Insert the antenna wire through the antenna support sleeve, the elbow insulator, and the lead-through insulator
(Ref. Figure 202).
Jan 31/05Page 202 23-1 0-01 A1
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
c. Screw the antenna support sleeve into the elbow insulator.
d. From inside the tail section, connect the antenna lead-in wire with the washer and cap nut.
e. Loop the center conductor around the tension unit as shown in the illustration. Install the screw, washers,lockwasher and nut attaching the antenna to the tail mounting straps.
nl 23-1 0-01 Jan 31/05Page 203
RayYheon AiKraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
WSHLD HF ADCZ
o aWPIR I r~T
IIPILOTSURF )I PFD MFD
DEICE ---HEATER HV\TEA
13
DETAIL B
COAX ASSY
HF- 90314 RECEIVERFIBER OPTIC TRANSMITTER
(REF DES
2312P83 (XI (REFDES (REFDES (REF DES 231241)
231205) n12PZ)
CI) DES~C FIBER OPTIC
(REF DES (REF DESHF 9041 COUPLER I I TREF DES
2312P4) 2312P1)(REFDES2312A2) n12P11)
(REF DES 2312P83
UPPERHARNESS ASSY
AVIONICS
SHELF
LOWER
(REF DES AVIONICS
2321P1) SHELF
2321P2)s~D,:´• loy \HARNESSASSY j~0 0
CONN
SELCAL UNIT BRACKET I [PI(MODELCSD-714)(REF DES 232141)
ROTATED 180 DEGREES
DETAIL A88138
050MO*A.*I
ReceiverTTrensmitter, Antenna Coupler and SELCAL Unit
Figure 201 (Sheet 1 of 2)
Page 204Jan31/05 23-1 0-01 Al
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
HF ANTENNA
FOLLOW CONTOUR TO ALLOWPROPER CLEARANCE FROM CLEQUIPMENT FIND MAINTAIN ACFT1.5 INCH CLEARANCE FROM REFANTENNA WIRE OR COAX
STRAP
COAXASSY
HF-9041 ANTENNA COUPLER
LOOKING FWD AT HF EQUIPMENT ON AVIONICS SHELF
DETAIL CFL238046187~Fl
ReceiverTTransmitter, Antenna Coupler and SELCAL Unit
Figure 201 (Sheet 2 of 2)
At 23-1 0-01 Jan 31/05Page 205
RaYtReos AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TAIL MOUNTING ST
TENSION UNITCENTER CONDUCTOR
ANTENNA WIRE
ANTENNA SUPPORT SLEEVE
ELBOW INSULATOR
AIRPLANE SKIN
LEAD-THROUGH INSULATOR
CHUCK JAWS
ANTENNA LEAD-IN WIRES
CFIP NUT FL23B046245FIF1
HF Antenna Installation
Figure 202
Jan 31/05Pege 206 23-1 0-01 A1
RIIYChCOII AiKraft companySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIRCELL ST 3100 SATELLITE TELECOMMUNICATION SYSTEM DESCRIPTION AND
OPERATION
The AirCell ST 3100 system provides worldwide voice and data communication using the Iridium satellite network
of 66 low-earth orbit satellites and operates in the frequency range of 1616 to 1625.5 MHz. Communications are
available on the ground, provided line-of-sight is maintained with the satellites, and in the air.
NOTE: This system is not considered a portable system and thus 14 CFR Part 91.21, Portable Electronic Devices,
does not apply. In addition, the FCC has issued a limited waiver which exempts the system from the
requirements of 47 CFR Part 22.925.
The AirCell ST 3100 system includes the following equipment:
An AirCell Satellite Transceiver with RS 232 Modem installed in the aft avionics compartment
An AirCell Cordless Handset mounted on a base station in the cabin
A serial port located next to each table in the cabin to support laptop computers
A Northern Airborne Technology PTA12-100 POTS Telephone Adapter, located in the cockpit pedestal
An Iridium Patch antenna, located on top of the fuselage
Two circuit breakers (TEL and DIALER) located on the right circuit breaker panel
The pilot’s and copilot’s audio panels include a TEL position on the Mic Select switch and a TEL audio ON-OFF
switch and volume control. These controls, along with the Telephone Adapter, allow the pilot and copilot to make
and receive calls in the cockpit using headsets or speakers, and boom mics or hand mics. In addition, the crew can
join a telephone conversation that was initially received in the cabin.
Power to the transceiver and base station for the cordless phone is provided by the Left Generator Avionics Bus
through the 7 1/2-amp TEL circuit breaker. Power to the Telephone Adapter is provided by the same Avionics bus
through the I-amp DIALER circuit breaker. Power to both units is controlled by the Avionics Master switch.
Lighting to the Telephone Adapter is controlled by the Master Panel Lights switch and the OVHD FED SUBPANEL
rheostat. The brightness of the display is controlled by the BRT key on the Telephone Adapter.
m23-1 2-00 JanPB~b:Page 1
RBYYheOn nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
PTR12 II 111121(3\ I~´•I-J ABC
1
~JD: I~3 ~i3 ~3HOLD FLF~SHsPncE
FL23B046246FIA
PTA12´•100 POTS Telephone AdapterFillure 1
Jan 31/05Page 2 23-1 2-00 A1
RBYCheOll Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TELEPHONE ADAPTER IThe following is a basic description of the controls on the Telephone Adapter.
CONTROL DESCRIPTION
HOOK Key This key is pressed to initiate or receive a call. Each time the key is pressed the hook switch
toggles on and off. When the switch is "off-hook" the condition is similar to lifting a telephonehandset off the hook, and is indicated by the illumination of the green LED above the HOOK keyand the message Call Mode shown on the display. The push-to-talk switches on the control
wheels are not required to transmit over the telephone.
HOOK LED When the Telephone Adapter is inactive, or on-hook, the LED will blink to indicate an incoming I(green) call. When the HOOK key is pressed to answer a call, the LED will illuminate steady.
HOLD Key The HOLD key is used to mute the mic and audio when the Telephone Adapter is active. Each
push of the key cycles between the Mute Mode and the un-muted mode.
HOLD LED The LED illuminates steady when the HOLD key is pressed to mute the mic and audio during a
(green) call.
REDIAL Key This key is used to recall and redial the last number dialed. The last number is stored in non-
volatile memory and thus will be retained when the system is powered down.
FLASH Key This key has no function on this installation I I
VOL Key This key increases (up arrow) and decreases (down arrow) the output volume of the phone when
the HOOK switch is active or when the Ringer Detect circuit is active (i.e. the phone is ringing.)Volume increments can be adjusted from 1 (lowest) to 32 (highest). When the HOOK switch is
inactive, the key is used to enter the Recall Mode and cycles through the 16 (01 16) available
addresses which can be programmed with names and telephone numbers.
BRT Key This key is used to control the brightness of the display. Brightness levels from 1 (dimmest) to 8 I(brightest) are available.
ENTR Key Pressing the ENTR key sends a number dialed from the default or Recall Mode. It is also used to Iselect the Edit Mode. This mode is used to program up to 16 names and telephone numbers.
ESC Key In the Default Mode this key will cancel the current key activity. In the Edit Mode pressing the key Ireturns the system to the Default Mode.
BASIC AUDIO PANEL OPERATION
a. Interphone Control This control may be either on or off when using the telephone.
b. Speaker Control If the speakers are selected on, the telephone audio will be heard over the speakers.
c. AUTO COMM Switch This switch interacts with the TEL position of the Transmit switch and the TEL audio
control as follows:
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Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
1. With the AUTO COMM Switch on, selecting the TEL position of the Transmit switch will take the telephoneOff Hook unless the other side of the cockpit has both the TEL mic select switch and AUTO COMM Switch
on.
2. Deselecting the TEL position of the Transmit switch or turning the AUTO COMM Switch off will place the
telephone back ON HOOK (disconnect the phone call) unless the opposite side has selected the TEL
transmit switch and the AUTO COMM Switch.
3. With the pilot and copilot AUTO COMM Switches off, the mic key on the control wheel or the hand mic can
be used to transmit over the telephone. This mode of operation is not recommended.
The TEL audio control must be on.
The mic key must be continuously held down.
If the mic key is released, the phone will hang up.
With either AUTO COMM Switch on, neither the pilot’s nor the copilot’s mic switch will activate the
telephone Hook switch.
4. Transmissions cannot be made on the phone unless the AUTO COMM Switch is selected on either the
pilot’s panel or the copilot’s panel. With at least one switch selected on, both pilot and copilot can transmit
on the phone. Neither mic switch is required to talk, even on the side with the AUTO COMM Switch off.
d. ~When the telephone has been taken Off Hook using the TEL transmit switch or AUTO COMM Switch, the
telephone can be placed ON Hook by pressing the HOOK key on the telephone adapter.
e. If either crew member wishes to leave a phone conversation without disconnecting a call, the other crew
member should ensure that the TEL mic switch and AUTO COMM Switch are selected.
f. The Interphone switch does not have to be on far both crew members to talk on the phone.
g. The TEL Audio Control and the master volume control (located on the mic select switch) may be used to
modulate the output volume set on the telephone adapter. The master volume control cannot increase the
volume above the level set on the Telephone Adapter.
USING THE TELEPHONE ADAPTER
The following abbreviated procedures can be used to operate the Northern Airborne Technology PTA12-100
(POTS) Telephone Adapter. For more detailed information refer to the PTA12-100 POTS Telephone AdapterOperator’s Manual, obtained from Northern Airborne Technology Ltd.
TO MAKE A CALL IN THE CALL MODE
a. Place the Mic Select Switch in the TEL position.
b. Place the AUTO COMM Switch in the ON position.
NOTE: If the opposite side has the TEL mic switch and the AUTO COMM Switch selected on, the above two stepswill not take the phone OFF HOOK.
c. If required, press the Hook Key to take the phone OFF HOOK.
The green HOOK LED will illuminate
Jan 31/05Page 4 23-1 2-00
Ray~heon nircraff CompanySUPER K1NG AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Call Mode will be displayed
A dial tone will be heard
d. Type in Phone Number
1 Area Code Telephone Number
(US and Canada)
00 Country Code Area Code Telephone Number
(Outside US and Canada)
e. Press the ENTR Key and note the following:
1. Phone Numberwillbedialed
2. A series of short tones will be heard
3. The number called will ring
f. Use Boom mic (or hand mic) and headsets (or speakers) to communicate.
g. Press the HOOK Key to end the call.
TO MAKE A CALL IN THE RECALL MODE
a. Place the Mic Select Switch in the TEL position.
b. Place the AUTO COMM Switch in the ON position.
NOTE: If the above steps take the phone OFF HOOK, press the HOOK key on the telephone adapter to place the
phone back ON HOOK.
c. Key in valid address for a stored number (01 10) or press VOL Key on the up or down arrow to scroll throughthe list.
d. Press the HOOK Key. The following will occur:
1. The green HOOK LED will illuminate.
2. The phone number will be displayed.
3. Adialtonewillbe heard.
e. Press the ENTR Key. The following will occur:
1. The phone number will be dialed.
2. A series of short tones will be heard.
3. The number called will ring.
f. Use the Boom mic (or hand mic) and headsets (or speakers) to communicate.
g. Press the HOOK Key to end the call.
nl 23-1 2-00 Jan 31/05Page5
Rsylkeon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TO MAKE A CALL USING THE REDIAL KEY
a. Place the Mic Select Switch in the TEL position.
b. Place the AUTO COMM Switch in the ON position.
NOTE: If the above steps take the phone OFF HOOK, press the HOOK key on the telephone adapter to place the
phone back ON HOOK.
c. Press the REDIAL Key. The last number called will be displayed.
d. Press the HOOK Key. The following will occur:
1. The green HOOK LED will illuminate.
2. The phone number will be displayed.
3. A dial tone will be heard.
e. Press the ENTR Key. The following will occur:
1. Phone Numberwillbedialed.
2. A series of short tones will be heard.
3. The number called will ring.
f. Use the Boom mic (or hand mic) and headsets (or speakers) to communicate.
g. Press the HOOK Key to end the call.
TO RECEIVE A CALL
The green HOOK LED will blink and the ringer will sound in the headset if the TEL audio switch is pulled on. If the
speaker(s) are on, the ringer will sound through the speaker(s).
a. Place the Mic Select Switch in the TEL position.
b. Place the AUTO COMM Switch in the ON position.
c. If required, press the HOOK Key. The following will occur:
1. The green HOOK LED will steadily illuminate.
2. Call Mode will be displayed.
d. Use the Boom mic (or hand mic) and headsets (or speakers) to communicate.
e. Press the HOOK Key to end the call.
EDIT MODE
NOTE: Pressing the ESC key during any portion of the Edit Mode will return the Telephone Adapter to the Default
Mode indicated by the display PTA12-100 X.XX.X.
Jan 31/0523-1 2100 al
RBYBeOl AiKraft companySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
STORING A NEW NAME AND PHONE NUMBER
a. If required, press the ESC Key to return to the Default Mode.
b. Press the ENTR Key. The Edit Mode message appears for 2 3 sec. followed by up down arrows or the
Address message.
c. Select empty address by pressing the VOL Key up arrow or down arrow to select address (01 16) or, keyingin address directly (01 16). Emptyl message indicates empty address.
d. Press the ENTR Key. The Enter Name message will be displayed.
e. Press the appropriate key repeatedly until the desired letter or number appears. For example, pressing the "3
DEF" key once D, twice E, three times F and 4 times the number 3.
f. To correct an entry, use the left arrow or right arrow keys. This will activate a cursor which can be placed over
the character that requires a change.
g. To enter a space, press the "O Space" key.
h. If two successive letters and/or numbers are on the same key, the right arrow key will need to be pressed to
advance to the next space before entering the next letter/number.
i. Press the ENTR Key to store the name. The Enter Number message will be displayed.
j. Press the appropriate keys to enter the phone number using the above procedures. (Alpha characters are not
active in this mode. Press each key only once to enter a number. Press the "0 Space" key twice to enter a
space.)
k. Press the ENTR Key to store the number. The Storedl message will be displayed.
I. Press the ESC Key to return to the Default Mode.
EDITING AN OCCUPIED ADDRESS
a. If required press the ESC Key to return to the Default Mode.
b. Press the ENTR Key. The Edit Mode message appears for 2 3 sec. followed by up down arrows or Address
message.
c. Select desired address by pressing the up or down arrow keys to select address (01 16) or, keying in the
address directly(0l 16).
d. Press the ENTR Key. Del left arrow or Edit right arrow message will be displayed.
e. Press the right arrow key to edit the name in a selected address. The address name will be displayed.
f. Press the left arrow key to place the cursor over the character to be edited, then press the desired key to changethe character.
g. Press the ENTR Key to store the name. The telephone number will be displayed.
h. Press the left arrow key to place the cursor over the number to be edited, then press the desired key to changethe number.
i. Press the ENTR Key to store the number. The Storedl message will be displayed.
nl 23-1 2-00 Jan 31/05Page 7
Rayuheon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
j. Press the ESC Key to return to the Default Mode.
DELETING AN OCCUPIED ADDRESS
a. If required, press the ESC Key to return to the Default Mode.
b. Press the ENTR Key. The Edit Mode message appears for 2 3 sec followed by up and down arrows or
Address message.
c. Select desired address by pressing the up or down arrow keys to select address (01 16) or, keying in address
directly(0l- 16).
d. Press the ENTR Key. The Del left arrow or Edit right arrow message will be displayed.
e. Press the left arrow key to delete the name and number in the selected address. The ENTR to Delete messagewill be displayed.
f. Press the ENTR Key. The Deletedl message will be displayed.
g. Press the ESC Key to return to the Default Mode.
Refer to the AirCell ST 3100 Satellite Telecommunication System Users Manual, P/N 810-10680, Rev. F or later
revision, for information concerning the cordless handset installed in the cabin.
AIRCELL CORDLESS HANDSET
The following are abbreviated procedures for using the AirCell Cordless Handset. For more detailed information,refer to the PTA12-100 POTS Telephone Adapter Operator’s Manual, obtained from Northern Airborne TechnologyLtd.
TO MAKE A CALL
a. Remove handsetfromcradle.
b. Verifylridium appearsinthedisplay.
c. Verify the message No Serv does not appear in the display.
d. Dial Telephone Number
1 Area Code Telephone Number
(US and Canada)
00 Country Code Area Code Telephone Number
(Outside US and Canada)
e. Press the SND key.
f. In Use message appears and Iridium disappears in the display.
g. Volume can be adjusted using the up or down key.
h. Pressthe ENDkeytoendthecall.
Jan 23-1 2-00 p~l
RlytheOl Airc~raft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TO JOIN A CALL MADE FROFA THE COCKPIT
a. Remove handsetfromcradle.
b. Verify Iridium appears in the display.
c. Mute message appears in the display.
d. Press the FCN key followed by the 7 key to unmute the handset.
e. Pressthe SND key.
TO RECEIVE A CALL
a. Remove handsetfromcradle.
b. Press the SND key to answer the phone.
c. In Use message appears in the display.
d. Volume can be adjusted using the up or down arrow key.
e. Pressthe ENDkeytoendthecall.
23-1 2-00Page 9
Rayt~wm Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIRCELL ST 3100 SATELLITE TELECOMIMUNICATION SYSTEM MAINTENANCE
PRACTICES
AIRCELL SA TELLITE TRANSCEIVER WITH MODEM REMOVAL
NOTE: The Aircell Satellite Transceiver With Modem is located at the aft end of the bottom tail equipment shelf (Ref.Figure 201).
a. Remove electrical power from the airplane.
b. Openthetail equipmentbayhatch.
c. Identify, tag and disconnect the electrical connectors from the transceiver. Install protective caps on all
connectors.
d. Loosen the knurled knob and remove the transmitter/receiver from the mount.
AIRCELL SATELLITE TRANSCEIVER WITH MODEM INSTALLATION
NOTE: The Aircell Satellite Transceiver With Modem is located at the aft end of the bottom tail equipment shelf (Ref.Figure 201).
a. Remove aircraft power and slide the transceiver into the mount.
b. Position the knurled knob on the front of the mount to engage the unit-mounting projections and tighten the
knurled knob.
c. Press on the front panel to ensure that the unit is fully seated in the mount. Retighten the knurled knobs until
the unit is secure in the mount.
d. Ensure that a good electrical bond exists between the unit and the mount.
e. Remove the protective caps from the connectors. Connect the electrical connectors to the transceiver. Remove
the tags.
f. Close the tail equipment bay hatch.
IRIDIUM SA TELLITE ANTENNA REMOVAL
NOTE: The Iridium Satellite Antenna is located on the top of the fuselage (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in Super King Air
8300/8300C Maintenance Manual, Chapter 23-00-00.
IRIDIUM SA TELLITE ANTENNA INSTALLA TION
NOTE: The Iridium Satellite Antenna is located on the top of the fuselage (Ref. Figure 202).
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in Super KingAir 8300/8300C Maintenance Manual, Chapter 23-00-00.
nl 23-1 2-00 Jan 31/05Page 201
Raytlbeon AiKraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Kj/~Ao´•o"".
TRANSCEIVER
COAX
B)
HARNESS
00~00
DETAIL A
Satellite Transceiver With Modem Installation
Figure 201
Jan 23-12-00 A1
gaYtheen nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
A
12
IRIDIUM SATELLITEANTENNA INSTALLATION
DETAIL A
BT23B050095AA
Iridium Satellite Antenna Installation
Figure 202
Al 23-1 2-00 Jan 31/05PaIle 203
RayfheoR nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
PASSENGER ADDRESS SYSTEM DESCRIPTION AND OPERATION
The passenger address system provides audio links between the flight crew and the passengers to ensure their
safety and comfort. The passenger address system provides the passengers with various flight information as
provided by the flight crew.
The dB Systems Model 240 Passenger Speaker Amplifier is a rack mounted unit located in the top left nose avionics
shelf. In addition to paging functions, it provides Seat Belt and No Smoking sign chimes tones. It also powers both
left and right speaker amplifier channels.
There is one dB Systems Model 700 audio control amplifier for each pilot station. The audio control amplifiers are
also rack-mounted units located in the left nose avionics bay. The Audio Control Panel (ACP) continuously reads
the status of all audio control switches and settings of potentiometers and compiles this information into the form of
a digital signal. The digital signal is sent to the Model 700 amplifier. The Model 700 amplifier receives the signal,demultiplexes this signal, and converts it into audio control information. Receiver, sidetone, headphone, interphone,and speaker audio and all operating modes are electronically switched and controlled by the signal from the ACP.
The speakers produce amplified Seat Belt and No Smoking sign chime tones and cabin paging. Audio signals to the
speakers are routed from both cockpit Audio Control Panels.
23-30-00 NoVP;~b:Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
PASSENGER ADDRESS SYSTEM MAINTENANCE PRACTICES
PASSENGER SPEAKER AMPLIFIER (MODEL 240) REMOVAL
NOTE
The passenger speaker amplifier is located on the left nose avionics bay.
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Remove the screws and washes securing the passenger speaker amplifier to the left nose avionics rack (Ref.
Figure 201).
d. Identify, tag and disconnect the electrical connectors from the rear of the passenger speaker amplifier.
e. Remove the speaker amplifier from the rack.
f. Install protective covers on the speaker amplifier and airplane wiring connectors.
a. Remove the protective covers from the passenger speaker amplifier and airplane wiring connectors.
b. Connect the electrical connectors to the rear of the passenger speaker amplifier (Ref. Figure 201).
c. Position the passenger speakers on the nose avionics rack and secure amplifier with washers and screws.
d. Apply electrical powerto the airplane.
e. Make a passenger/cabin address at various audio volume levels using the audio system to verify operation of
the Passenger Speaker Amplifier.
f. Remove electrical power from the airplane.
g. Install the left avionics compartment door.
23-30-00
Rayfheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
B
DETAILA
PASSENGER SPEAKER
AMPLIFIER (MODEL 240)
DB SYSTEMS AUDIO CONTROL
AMPLIFIER (MODEL 700) NO. 1
DB SYSTEMS AUDIO CONTROL
AMPLIFIER (MODEL 700) NO. 2
DB SYSTEMS AURAL WARNING
GENERATOR (MODEL 630)
DETAIL B
Passenger Speaker Amplifier (Model 240) Location
Figure 201
Nov 23-30-00
Ray~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUDIO INTEGRATING SYSTEM DESCRIPTION AND OPERATION
The audio integration system manages the communication, navigation, aural warning, and passenger address audio
in the airplane. The audio integrating system controls the output of the communication, navigation, aural warning,and passenger address to the flight crew (headphones, oxygen mask) and the airplane speakers (cockpit and
cabin). The system also controls the output of the flight crew microphones to the communication and navigationtransmitters.
There are two dB Systems Audio Control Panels (ACPs) installed on the sides of the instrument panel. These panelsenable the crew members to individually select and regulate audio control, both transmission and reception for the
communication and navigation equipment. A Model 804 Audio Control Panel is installed on the left side of the
instrument panel and a Model 805 Audio Control Panel is installed on the right side of the instrument panel.
One dB Systems Model 700 audio control amplifier is installed for each pilot station. The audio control amplifiers are
also rack-mounted units located in the left nose avionics bay. The Audio Control Panel (ACP) continuously reads
the status of all audio control switches and settings of potentiometers and compiles this information into the form of
a digital signal. The digital signal is sent to the Model 700 amplifier. The Model 700 amplifier receives the signal,demultiplexes this signal, and converts it into audio control information. Receiver, sidetone, headphone, interphone,and speaker audio and all operating modes are electronically switched and controlled by the signal from the ACP.
The Model 630 Aural Warning Generators provide aural warnings to the cockpit audio control amplifiers. There are
distinctive tones programmed into the aural warning generator which are activated by respective control signalsbeing applied to the associated control input. When the input of the aural warning generator receives the input
signal, the distinctive tone signal is out put in the pilot and copilot’s channels to the audio control amplifiers. Tones
activated simultaneously will result in the tone with the higher priority taking precedent within 3 seconds.
The control wheel press to talk (PTT) switches are located on both the pilot and copilot’s control wheel yokes. These
allow the flight crew to safely communicate as necessary without removing their hand form the yoke.
There are two speakers located in the cockpit headliner. One speaker is located on each side of the airplane. The
speakers output the same audio that is heard through the headphones.
23-50-00 NDVP:Q~:Page 1
Raytheo~ AiKraft companySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AUDIO INTEGRATING SYSTEM MAINTENANCE PRACTICES
AUDIO CONTROL PANEL (ACP) (MODEL 804/805) REMOVAL
NOTE
There are two dB Systems Model 804 and 805 Audio Control Panels (ACPs) installed on the sides
of the instrument panel.
a. Removeelectrical powerfromtheairplane.
b. Loosen the screws securing the audio control panel and carefully pull the panel from the instrument panel (Ref.Figure 201).
c. Identify, tag and disconnect the electrical connector from the panel.
d. Install protective covers on all electrical connectors.
AUDIO CONTROL PANEL (ACP) (MODEL 804/805) INSTALLA TION
a. Remove the protective covers from the electrical connectors.
b. Connect plug to the connectors (Ref. Figure 201).
c. Position the audio control panel into the instrument panel and secure with the screws.
d. Perform the AUDIO CONTROL PANEL (ACP) (MODEL 804/805) TEST procedure.
AUDIO CONTROL PANEL (ACP) (MODEL 804/805) TEST
a. Applyelectrical powertotheairplane.
b. Test speaker and mic audio associated with Passenger Address, VHF Communication, Navigation Radios,ADF, Marker Beacon, Interphone, Cockpit, and Cabin Speakers. Make sure audible audio can be heard throughthe speaker
c. Remove electrical power from the airplane.
23-50-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
~Yb 6 6cL-~ 14--4 QI I II II I I~I I II ii I~II 11 II I loC1 I´•I 11 1~1’1 11 II I´•I C,
crPT’i 43
rE PP
a´• ~st
cy_
t
I~ II~9 Q~’9:
AUDIOAUDIO I I I I I 1 1-CONTROLCONTROL I I I I I I PANELPANEL CACP)(FICP) LEFT RIGHT
INBOARD INBOARD
SUBPANEL SUBPFlNEL
LEFT RIGHTRADIO OUTBOARDOUT BOARDTUNING UNIT SUBPANELSUBPANEL (RTU-4200)
REVERSIONARY PANEL
DISPLAY CONTROL
DISPLAY CONTROL PANELCDCP-3000)
PANEL(DCP-3000)
88348033959F1R
Audio Control Panels (ACP) Location
Figure 201
Nov 14/03Page 202 23-50-00
Ral~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DB SYSTEMS AUDIO CONTROL AMPLIFIER (MODEL 700) REMOVAL
NOTE
The audio control amplifiers are located in the left nose avionics bay.
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Loosen and release the knurled knobs securing the audio control amplifierto the nose avionics rack (Ref. Figure202).
d. Slide the audio control amplifier out of its rack.
e. Disconnect the electrical connectors and remove the audio control amplifier.
f. Install protective covers on all electrical connectors.
DB SYSTEMS AUDIO CONTROL AMPLIFIER (MODEL 700) INSTALLATION
a. Remove the protective covers from the electrical connectors.
b. Slide the audio control amplifier into the nose avionics rack until the electrical connectors can be installed to the
rear of the audio control amplifier (Ref. Figure 202).
c. Connect the electrical connectors to the audio control amplifier.
d. Position the knurled knobs in the front of the nose avionics rack to engage the audio control amplifier and tightenthe knurled knobs until the audio control amplifier is secure to the nose avionics rack.
e. Perform the DB SYSTEMS AUDIO CONTROL AMPLIFIER (MODEL 700) TEST procedure.
f. Install the left avionics compartment door.
DB SYSTEMS AUDIO CONTROL AMPLIFIER (MODEL 700) TEST
a. Apply electrical power to the airplane.
b. Test speaker and mic audio associated with Passenger Address, VHF Communication, Navigation Radios,ADF, Marker Beacon, Interphone, Cockpit, and Cabin Speakers. Make sure audio can be heard and transmitted
through the audio system.
c. Remove electrical power from the airplane.
23-50-00 NP~:
GeYttmee AiKraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
B
DETAILA
PASSENGER SPEAKER
AMPLIFIER (MODEL 240)
DB SYSTEMS AUDIO CONTROL
AMPLIFIER (MODEL 700) NO. 1
DB SYSTEMS AUDIO CONTROL
AMPLIFIER (MODEL 700) NO. 2
DB SYSTEMS AURAL WARNING
GENERATOR(MODEL~SO)
DETAIL B
Audio Control Amplifier (Model 700) and Aural Warning Generator (Model 630) Location
Figure 202
Nov 14/03Page 204 23-50-00
RaytheMI nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DB SYSTEMS AURAL WARNING GENERATOR (MODEL 630) REMOVAL
NOTE
The audio warning generator is located in the left nose avionics bay.
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Remove the screws and washers securing the aural warning generator to the nose avionics rack (Ref. Figure202).
d. Disconnect the electrical connectors and remove the aural warning generator.
e. Install protective covers on all electrical connectors.
DB SYSTEMS AURAL WARNING GENERATOR (MODEL 630) INSTALLATION
a. Remove the protective covers from the electrical connectors.
b. Install and secure the electrical connector to the rear of the aural warning generator (Ref. Figure 202).
c. Position the aural warning generator on the nose avionics rack and secure with the washers and screws.
d. Perform the DB SYSTEMS AURAL WARNING GENERATOR (MODEL 630) TEST procedure.
e. Install the left avionics compartment door.
DB SYSTEMS AURAL WARNING GENERATOR (MODEL 630) TEST
a. Applyelectrical powertotheairplane.
b. Test the Aural Warning Generator by pressing the Press to Test Button located immediately to the right of the
warning annunciator panel. Aural Warning tones should be heard through the cockpit speakers.
c. Test the Aural Warning Generator by selecting the Stall Warning, Overspeed and Landing Gear Test switches
in the right inboard subpanel.
d. Remove electrical power from the airplane.
23-50-00 Nov 14/03Page 205
CHAPTER
ELECTRICAL
POVVER
RayRheon AiKraff CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 24 ELECTRICAL POWER
TABLE OF CONTENTS
SUBJECT PAGE
24-20-00
AC Electrical System Description and Operation .........1
24-30-00
DC-DC Converter(RR-lb) PowerSupply System Descriptionand Operation .....1
DC Electrical Load Distribution Description and Operation .1
DC Electrical Load Distribution Maintenance Practices ..201
Periodic Inspection of Dual-Bus-Feeder Diodes. ........201
24-CONTENTS ,~:L:Pege 1
RllytheOn AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 24 ELECTRICAL POWER
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
24-LOEP 1 Nov 14/03
24-CONTENTS 1 Nov 14/03
24-20-00 1 Nov 14/03
24-30-00 1 Nov 14/03
201 and 202 Nov 14/03
24-60-00 1 thru 3 Nov 14/03
201 thru 203 Nov 14/03
24-LOEP Nov 14/03Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AC ELECTRICAL SYSTEM DESCRIPTION AND OPERATION
NOTE
The 400 Hz AC Electrical system is removed on airplanes equipped with the Pro Line 21 system.The 110 vac (60 Hz) cabin power is retained. The cockpit lighted panels are driven by 5 vde and
110 vac. Refer to Chapter 33-11-00 for information on the Light Dimmer Power Supply System.
24-20-00 Nov 14/03Page 1
RayWleon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DCIDC CONVERTER (RR-18) POWER SUPPLY SYSTEM DESCRIPTION AND
OPERATION
The DC-DC Converter power supply system consists of two KGS Electronics RR-18 power supplies. Each RR-18
power supply converts 10-24 vdc input voltage to a dual regulated 24 vdc output. DC-DC converters are used to
power Pilot Flight Display (PFD), Multi Function Display (MFD), Attitude Heading Computer (AHC) 1 and AHC 2.
DC-DC Converter No. 1 provides power to Pilots PFD and AHC No. 1. DC-DC Converter No. 2 provides power to
the MFD and AHC No. 2.
24-30-00 NovPal~
Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DC-DC CONVERTER POWER SUPPLY SYSTEM MAINTENANCE PRACTICES
CC-CC CONVERTER SUPPL Y (RR-18) REMOVAL
NOTE
The two RR-18 DC-DC Converters are located between FS266.37 and FS287.50 under the
floorboards (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Removethe floorboards.
NOTE
Removal of DC-DC Converter No. 2 requires removal of DC-DC Converter No. 1.
c. Identify, tag and disconnect the electrical connector from the rear of DC-DC Converter. Install protective caps
on all connectors.
d. Remove the DC-DC Converter mounting screws, washers and spacers. Save mounting hardware for
installation.
oC-oC CONVERTER SUPPL Y (RR- 1 8) INSTALLA TION
NOTE
Installation of DC-DC Converter No. 2 requires installation of DC-DC Converter No. 1.
a. Align the DC-DC Converter’s mounting holes with mounting nutplate’s holes (Ref. Figure 201).
b. Secure DC-DC Converters to mounting location nutplates.
c. Remove the protective caps from the connectors. Connect the electrical connector to the rear of DC-DC
Converter. Remove the tags.
d. Perform DC-DC CONVERTER SUPPLY (RR-18) ADJUSTMENTTTEST procedure.
e. Install thefloorboards.
oC-oC CONVERTER SUPPL Y (RR- 18) ADJUSTMENTrrEST
a. Apply electrical powertotheairplane.
b. Perform the respective PFD or MFD check by performing the ADAPTIVE FLIGHT DISPLAY (AFD-3010)ADJUSTMENTTTEST procedure in Chapter 31-60-00.
c. Perform the respective ATTITUDE HEADING COMPUTER (AHC-3000) ADJUSTMENTTTEST procedure in
Chapter 34-20-00.
d. Remove electrical power from the airplane.
24-30-00 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
f;C
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DC-DC Converter Supply (RR-18) Installation
Figure 201
24130100
Raytlleon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DC ELECTRICAL LOAD DISTRIBUTION DESCRIPTION AND OPERATION
The electrical load distribution system provides the means of supplying direct current to the various airplane systems(Ref. Figure 1). Direct current is provided from the battery and generators to each system via the DC Power
Distribution Panel assembly located under the center aisle floor boards immediately forward of the main spar. The
DC Power Distribution Panel assembly supplies power to four dual-bus loops. Each of the four dual-bus loopsreceives power through a limiter on the left bus and a limiter on the right bus of the DC Power Distribution Panel
assembly. Isolation from a ground fault on either bus is provided by a pair of isolation diodes for each dual-bus loop.The DC Power Distribution Panel assembly also provides power to de systems that are not dual fed. A hot batterybus is located in the lower right center section, adjacent to the battery box. Systems powered from this bus may be
operated even though the battery master switch is off.
24-60-00
Ral~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
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Nov 14/03Page 2 24160-00
Ray~bwM nircraft CompanySUPER I(ING AIR 200 SERIES PRO LINE 21 MAINTENANCE MANUAL SUPPLEMENT
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24-60-00 Page 3
Nov 14/03
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DC ELECTRICAL LOAD DISTRIBUTION MAINTENANCE PRACTICES
The dual-bus-feeder diodes and fuel-panel-blocking diodes should be inspected at the proper interval. Refer to
Chapter 5-20-00 of the Super King Air 200 Series Maintenance Manual. Whenever the dual bus has been modified
or extensive repairs have been made that could result in the dual-bus loops being interconnected or open, it is
necessary to perform a DUAL-BUS CONFORMITY INSPECTION as outlined in Chapter 24 of the Super King Air
200 Series Maintenance Manual. This will ensure that the original design of the dual bus is maintained.
PERIODIC INSPECTION OF DUAL-BUS-FEEDER DIODES
An open or shorted dual-bus-feeder diode cannot be detected during the normal operation of the airplane electrical
system. Should a malfunction occur which would cause a bus-isolation limiter to open, such as a ground fault on a
generator bus, an open dual-bus-feeder diode could not supply power to its respective dual-bus loop. A shorted
diode would not isolate its respective dual bus from a ground fault. The inspection procedure outlined here will
ensure the dual-bus capability. The inspection may be performed at a normal periodic inspection of the airplane and
either battery power or an auxiliary ground power unit connected to the external power receptacle may be used. A
suggested inspection procedure follows:
rCAUTION ICAUTION
Voltage is required to energize the avionics master power relays to remove the power from the
avionics equipment; therefore, never apply external power to the airplane without first applyingbattery voltage. If the battery is removed from the airplane or if the battery switch is placed in the
off position, connect an external battery in parallel to the external power unit prior to energizing the
power unit.
a. Remove all electrical power from the airplane.
b. Remove the center aisle floorboards and covers as necessary to gain access to the power distribution panel(Al 45).
c. Remove the left isolation limiter (F131).
d. Turn the battery master switch ON or apply power from an auxiliary ground power unit.
rcp~vnohl ICAUTION
Verify both pitot masts are free of obstructions before operating the pitot heat systems in the
following steps. Pitot heat should only be applied for a short interval of time.
e. Bus voltage should be present on the right generator bus (W109). This may be verified by attempting to
momentarily operate the right pitot heat system. Successful operation of the right pitot heat system will cause
the R PITOT HEAT caution annunciator to extinguish. Operation of the right pitot heat system will verifycontinuity of the right isolation limiter (F1 32).
f. By observing the following annunciators, power to each of the four buses will be ensured: L FUEL PRESS, R
FU~EL PRESS, L BL AIR FAIL and R BL AIR FAIL. If any of the annunciators fail to illuminate, the associated
limiter (F148, F149, F150 or F154), one of the four dual-bus-feeder diodes (CR2) or dual-bus circuit breakers
(RH NO. 1, RH NO. 2, RH NO. 3 or RH NO. 4) is open. If failure of an annunciator is apparent, reset or replacethe faulty component and repeat the test.
24-60-00
Ral~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
g. Attempt to momentarily operate the left pitot heat system. It should not operate. The L PITOT HEAT caution
annunciator should remain illuminated. If the left pitot heat system does operate (L PITOT HEAT caution
annunciator extinguishes) at least one of the dual-bus-feeder diodes is shorted. Detection of the shorted
diode(s) may be accomplished by performing the following steps:
1. Open the following dual-bus-feeder circuit breakers: LH NO.1, LH NO. 2, LH NO. 3 and LH NO. 4.
2. Momentarily operate the left pitot heat system. The L PITOT HEAT caution annunciator should remain
illuminated.
3. Close the LH NO. 1 circuit breaker. Momentarily operate the left pitot heat system. The L PITOT HEAT
caution annunciator should remain illuminated. If the L PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the LH NO. 1 circuit breaker. Replace the diode (A134CR1).
4. Close the LH NO. 2 circuit breaker. Momentarily operate the left pitot heat system. The L PITOT HEAT
caution annunciator should remain illuminated. If the L PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the LH NO. 2 circuit breaker. Replace the diode (A135CR1).
5. Close the LH NO. 3 circuit breaker. Momentarily operate the left pitot heat system. The L PITOT HEAT
caution annunciator should remain illuminated. If the L PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the LH NO. 3 circuit breaker. Replace the diode (A143CR1).
6. Close the LH NO. 4 circuit breaker. Momentarily operate the left pitot heat system. The L PITOT HEAT
caution annunciator should remain illuminated. If the L PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the LH NO. 4 circuit breaker. Replace the diode (A144CR1).
7. Close the following dual-bus-feeder circuit breakers: LH NO.1, LH NO. 2, LH NO. 3 and LH NO. 4.
8. After replacement of the shorted diode(s), repeat this test.
h. Remove all electrical power from the airplane.
i. Replace the left isolation limiter (F131). Remove the right isolation limiter (F132).
j. Turn the battery master switch ON or apply power from an auxiliary ground power unit.
k. Bus voltage should be present on the left generator bus (W103). This may be verified by attempting to
momentarily operate the left pitot heat system. Successful operation of the left pitot heat system will cause the
L PITOT HEAT caution annunciator to extinguish. Operation of the left pitot heat system will verify continuity of
the left isolation limiter (F131).
I. By observing the following annunciators, power to each of the four buses will be ensured: L FUEL PRESS, R
FUEL PRESS, L BL AIR FAIL and R BL AIR FAIL. If any of the annunciators fail to illuminate, the associated
limiter (F145, F146, F147 or F153), one of the four dual-bus-feeder diodes (CR1) or dual-bus circuit breakers
(LH NO. 1, LH NO. 2, LH NO. 3 or LH NO. 4) is open. If failure of an annunciator is apparent, reset or replacethe faulty component and repeat the test.
m. Attempt to momentarily operate the right pitot heat system. It should not operate. The R PITOT HEAT caution
annunciator should remain iliuminated. If the right pitot heat system does operate (R PITOT HEAT caution
annunciator extinguishes) at least one of the dual-bus-feeder diodes is shorted. Detection of the shorted
diode(s) may be accomplished by performing the following steps:
1. Open the following dual-bus-feeder circuit breakers: RH NO.1, RH NO. 2, RH NO. 3 and RH NO. 4.
Nov 24-60-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
2. Momentarily operate the right pitot heat system. The R PITOT HEAT caution annunciator should remain
illuminated.
3. Close the RH NO. 1 circuit breaker. Momentarily operate the right pitot heat system. The R PITOT HEAT
caution annunciator should remain illuminated. If the R PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the RH NO. 1 circuit breaker. Replace the diode (A134CR2).
4. Close the RH NO. 2 circuit breaker. Momentarily operate the right pitot heat system. The R PITOT HEAT
caution annunciator should remain illuminated. If the R PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the RH NO. 2 circuit breaker. Replace the diode (A135CR2).
5. Close the RH NO. 3 circuit breaker. Momentarily operate the right pitot heat system. The R PITOT HEAT
caution annunciator should remain illuminated. If the R PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the RH NO. 3 circuit breaker. Replace the diode (A143CR2).
6. Close the RH NO. 4 circuit breaker. Momentarily operate the right pitot heat system. The R PITOT HEAT
caution annunciator should remain illuminated. If the R PITOT HEAT caution annunciator extinguishes, the
failed diode is on this circuit. Open the RH NO. 4 circuit breaker. Replace the diode (A144CR2).
7. Close the following dual-bus-feeder circuit breakers: RH NO.1, RH NO. 2, RH NO. 3 and RH NO. 4.
8. After replacement of the shorted diode(s), repeat this test.
n. Remove all electrical power from the airplane.
o. Replace the right isolation limiter (F132).
24-60-00 Nov 14/03Page 203
CHAPTER
INDICATING/RECORDINGSYSTEMS
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 31 INDICATING/RECORDING SYSTEMS
TABLE OF CONTENTS
SUBJECT PAGE
31-40-00
Central Computers (Integrated Avionics Processor System)- Description and Operation. ..............1
Central Computers (Integrated Avionics Processor System)- Maintenance Practices ................201
Display Control Panel (DCP-3000) Installation. .........203
Display Control Panel (DCP-3000) Adjustment/Test .....203
31-CONTENTS
RBYHICOn AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 31 INDICATING/RECORDING SYSTEMS
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
31-LOEP 1 Jan 31/05
31-CONTENTS 1 Nov 14/03
31-40-00 1 and 2 Nov 14/03
201 thru 212 Nov 14/03
31-60-00 1 and 2 Jan 31/05
201 thru 203 Nov 14/03
Al 31-LOEP Jan 31/05Page 1
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CENTRAL COMPUTERS (INTEGRATED AVIONICS PROCESSOR SYSTEM)DESCRIPTION AND OPERATION
The Integrated Avionics Processor Systems (IAPS) performs a part of the integration function required to
interconnect and manage the various avionics systems in the airplane. The IAPS may be considered a part of the
airplane wiring that physically houses some avionics units. The ICC-3000 IAPS Card Cage (ICC) provides an
isolated interface between the resident Line Replaceable Modules (LRMs) and external avionics units. The ICC is
a fully wired card cage containing two Configuration Strapping Units (CSUs), two Flight Guidance Computers(FGCs), one IAPS Environmental Controller (IEC), two independent Input/Output data Concentrators (IOCs) and
two independent power supplies (PWRs).
NOTE
The empty ICC-3000 IAPS Card Cage (ICC) is a line replaceable unit. Each CSU, FGC, IEC, IOC
and PWR installed in the ICC is an individual line replaceable module. If any of the modules fail,
they can be replaced individually without replacing the entire IAPS ICC assembly.
The CSU-3000 Configuration Strapping Units provide a matrix of configuration shunts that program the IAPS
specifically for operation on the King Air 200 Series airplane. Each CSU provides configuration strapping for its half
of the IAPS assembly. There is one OCM-3100 Options Configuration Module (OCM! plugged on each of the two
CSU-3100 Configuration Strapping Units (CSU). The OCM-3100 interacts with the Input/Output Concentrators
(IOCs) to enable specific avionics options.
The two FGC-3000 Flight Guidance Computers provide the autopilot and flight director functions, provideindependent flight guidance computation and operate together to provide three axis autopilot, pitch trim and rudder
boost functions. The FGC-3000 receives attitude heading system data directly from the Attitude Heading Computer(AHC) and receives air data system, navigation radio and flight management system data through the IAPS IOC.
The IEC-3001 IAPS Environmental Controller monitors the temperature sensors and controls cooling fans and
heaters to automatically regulate the IAPS environment. The temperature sensors are installed on each half of the
ICC motherboard.
The IOC-3100 I/O Concentrators provide a data management function by acting as a central data collection and
distribution point. These concentrators receive data bus inputs from each major LRU on the airplane, process (sort)the data words and then transmit to the receiving LRU as needed.
A single MDC-3110 Maintenance Diagnostic Computer (MDC) module is on the right side of the IAPS card cage. Its
function is to monitor the airplane avionics and store diagnostic data in memory. The MDC receives data from IOC
and outputs data to IOC, Multifunction Display (MFD) and Data Base Unit (DBU). The MDC memory consists of
programmable read only memory and nonvolatile random access memory. The programmable read only memorycontains executable routines required to perform MDC function. The nonvolatile random access memory stores
software variable maintenance tables, fault equations and maintenance history logs.
There is one FMC-3000 (No. 1) Flight Management Computer (FMC) in the IAPS card cage. There are also
provisions for an optional FMC-3000 (No. 2). The FMC is a lateral and vertical navigator used by the autopilot to flya programmed flight plan. The FMC also provides a navigation data base storage and several control/planningfunctions. The FMC-3000 receives input from the cross-side FMC counterpart (if installed), onside control displayunit and from the IOC. The FMC provides output bus to the cross-side FMC (if installed) onside multifunction display.The data base unit is used to update the data base memories of both FMCs.
31-40-00
Ray~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
The Power Supplies provide two separate power sources. One PWR powers the left side LRMS and the associated
portions of the ICC. The other PWR powers the right side LRMs and associated portions of the ICC. The power
supply protects itself and the LRMs from operation at excessive current levels or excessively high or low voltagesand temperatures through internal monitoring and shutdown circuitry.
Nov 14/03~e,’4/o3 31-40-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CENTRAL COMPUTERS (INTEGRATED AVIONICS PROCESSOR SYSTEM)-MAINTENANCE PRACTICES
INTEGRATED CARD CAGE (ICC-3000) REMOVAL
NOTE
The integrated card cage is located in the left nose avionics rack (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Removethe leftavionics compartmentdoor.
c. Perform the ICC-3000 REMOVAL procedure in the SPECIAL MOUNTS section. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
INTEGRATED CARD CAGE (ICC-3000) INSTALLATION
NOTE
The integrated card cage is located in the left nose avionics rack (Ref. Figure 201).
a. Perform the ICC-3000 INSTALLATION procedure in the SPECIAL MOUNTS section. (Ref. Rockwell Collins,Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the INTEGRATED CARD CAGE (ICC-3000) ADJUSTMENTTTEST procedure.
c. Install the left avionics compartment door.
INTEGRATED CARD CAGE (ICC-3000) ADJUSTMENT/TEST
a. Apply electrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the ICC-3000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
31-40-00 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
O000~)/
A
B DETAIL A
IAPS CARD CAGE (ICC-3000)
DETAIL B
IAPS Card Cage Location
Figure 201
Nov 14/03Page 202 31 -40100
Raytheon AiKraft CampanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
s
s
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AB DETAIL A
i. IEC-3001
2. PWR-3000 NO. 1
3. FGC-3000 NO. 1
4. CSU-3100 NO. 1 DCM-3100 NO. 1
5. FMC-3000 NO. i
6. IOC-3100 NO. 1
7. MDC-3110
3. PWR-3000 NO. 2
9. FGC-3000 NO. 2
10. CSUS100 NO. 2 DCM-3100 N0.2
11. FMC-3000 NO. 2
12. IOC-3001 NO. 2
j
7
10
11
12
8
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03474~AA.AI
IAPS Card Cage Module Location
Figure 202
31-40-00 Nov 14/03Page 203
Ral~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
POWER SUPPL Y (PWR-3000) REMOVAL
NOTE
The PWR-3000 Power Supply is located in the IAPS card cage (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Perform the ICC-3000 IAPS CARD CAGE MODULES REMOVAL procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
POWER SUPPL Y (PWR-3000) INSTALLA TION
NOTE
The PWR-3000 Power Supply is located in the IAPS card cage (Ref. Figure 202).
a. Perform the ICC-3000 IAPS CARD CAGE MODULES INSTALLATION procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the POWER SUPPLY (PWR-3000) ADJUSTMENT~EST procedure.
c. Install the left avionics compartment door.
POWER SUPPL Y (PWR-3000) ADJUSTMENT/TEST
a. Apply electrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the PWR-3000 1/PWR-3000 2. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
INPUT/OUTPUT CONCENTRATOR (IOC-3100) REMOVAL
NOTE
The IOC-3100 Input/Output Concentrator is located in the IAPS card cage (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Perform the ICC-3000 IAPS CARD CAGE MODULES REMOVAL procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
Nov 31-40-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INPUT/OUTPUT CONCENTRA TOR (IOC-3 1 00) INSTALLA TION
NOTE
The IOC-3100 Input/Output Concentrator is located in the IAPS card cage (Ref. Figure 202).
a. Perform the ICC-3000 IAPS CARD CAGE MODULES INSTALLATION procedure. (Ref. Rockwell Collins, inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform INPUT/OUTPUT CONCENTRATOR (IOC-3100) ADJUSTMENTTTEST procedure.
c. Install the left avionics compartment door.
INPUT/OUTPUT CONCENTRA TOR (IOC-3 100) ADJUSTMENT/TEST
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the IOC-3100. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
ENVIRONMENTAL CONTROLLER (IEC-3001) REMOVAL
NOTE
The IEC-3001 Environmental Controller is located in the IAPS card cage (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Perform the ICC-3000 IAPS CARD CAGE MODULES REMOVAL procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
ENVIRONMENTAL CONTROLLER (IEC-300I) INSTALLATION
NOTE
The IEC-3001 Environmental Controller is located in the IAPS card cage (Ref. Figure 202).
a. Perform the ICC-3000 IAPS CARD CAGE MODULES INSTALLATION procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform ENVIRONMENTAL CONTROLLER (IEC-3001) ADJUSTMENTTTEST procedure.
c. Install the left avionics compartment door.
31-40-00 205
Ray4heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
b. Perform the TESTING AND TROUBLESHOOTING procedure for the IEC-3001. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
CONFIGURATION STRAPPING UNIT (CSU-3100) REMOVAL
NOTE
The CSU-3100 Configuration Strapping Unit is located in the IAPS card cage (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Removethe leftavionics compartmentdoor.
c. Remove the CSU by performing the ICC-3000 IAPS CARD CAGE MODULES REMOVAL procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
The CSU-3100 Configuration Strapping Unit is located in the IAPS card cage (Ref. Figure 202).
a. Perform the CONFIGURATION STRAPPING UNIT (CSU-3100) SETTINGS procedure.
b. Install the CSU by performing the ICC-3000 IAPS CARD CAGE MODULES INSTALLATION procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Perform the CONFIGURATION STRAPPING UNIT (CSU-3100) ADJUSTMENTTTEST procedure.
d. Install the left avionics compartment door.
CONFIGURATION STRAPPING UNIT(CSU-3100) SETTINGS
FCAUTION ICAUTION
Configuration Strapping Unit settings are unique to each aircraft configuration based on options,operator preferences, LRUs installed, etc. Verify airplane configuration before modifyingConfiguration Strapping Unit settings.
Nov 14/03Page 206 31-40-00
RayWleon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
a. Open CSU cover by loosening screws and sliding cover in the direction of OPEN arrow.
b. Set CSU Strapping for the aircraft configuration as illustrated in Figure 203.
c. Slide the CSU cover closed and secure by tightening screws.
CONFIGURATION STRAPPING UNIT (CSU-3100) ADJUSTMENTrrEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the CSU-3100. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
31-40-00 Nov 14/03Page 207
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Nov 31-40-00
Ral~heon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21 MAINTENANCE MANUAL SUPPLEMENT
NOTES: CONFIGURATION SHOWN IS STANDARD CONFIGURATION FOR CSU SWITCH POSITIONS. FOR OPTIONAL CONFIGURATIONS CHANGE SWITCH POSITIONS AS SHOWN IN TABLE i.
FOR ACCESS TO CSU BOARD REMOVE FRONT COVER OF ICC-3000 I~PS BOX.
O SET FOR ODD PARITY TABLE 1. COMM VHF CHANNEL SEPARATION 1= 8.33 kHz ACTIVE0= 25 kHz ACTIVE
121 ADF 2 (OPTIONAL) 1=PRESENT I~ COMM VHF EXTENDED RANGE: BIT 13 14
O DME 2 (OPTIONRL) I=PRESENT0 1 118 136. 975
1 1 118 135.975
141 GPS 2 PRESENT (OPTIONAL) I=PRESENT 1 O =118 151.975
O FMS CONFIGUR~TIcN:BIT 9 10 11FMS CONFIGURATION SYNG INDEP: BIT 9 10
O 1 FIXED INDEP
1 O O SINGLE LEFT FMC. SINGLE CDU O 0 FIXED SYNC
1 1 O DUAL FMC, DUAL CDU (OPTIONAL) 1 0 PAGE SELECTABLE SYNC
1 1 PAGE SELECTABLE INDEP ss~ls034748RF~
Configuration Strapping Unit SettingsFigure 203
31-40-00 Nov 14/03Page 209
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Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
b. Perform the TESTING AND TROUBLESHOOTING procedure for the FGC-3000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
Nov 31-40100
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CENTRAL alSPLAY SYSTEMS (ELEcTRoNIc FLIGHT INSTRUMENT SYSTEM)-DESCRIPTION AND OPERATION
The AFD-3010 Adaptive Plight Display (AFD) is the heart of the Electronic Flight Information System (EFIS). The
Electronic Flight Instrument System (EFIS) AFDs receive various sensor data from aircraft avionics systems and
generates graphic displays to present this information to the flight crew. The EPIS displays air data, attitude and
heading, EFIS multifunction and navigation sensor information.
When functioning as a primary flight display (PFD), the AFD provides the functions of airspeed indicator (ASI),altitude indicator (ALI), conventional attitude direction indicator(ADI), horizontal situation indicator (HSI) and vertical
(navigation), decision height, flight director commands, flight control system annunciations, heading (compass),minimum descent height, preselect altitude, radio altitude, TCAS advisory, temperature, and vertical speedinformation.
When functioning as a Multi Function Display (MFD), the AFD shows Enhanced Ground Proximity Warning System(EGPWS), comprehensive navigation (HSI or present position map format), weather radar return, TCAS traffic map,maintenance pages and checklist information.
Each AFD receives data from the IAPS on data buses. One of these buses is from the left side of IAPS and the other
is from the right side of IAPS. Each AFD receives on-side and cross-side air data, navigation, attitude, flightmanagement and TCAS (if dual) system information. Each AFD transmits and receives cross-talk data from the
other AFDs. Each AFD also receives EGPWS and Weather Radar System (WXT) data.
The AFDs are interchangeable. The AFD reads a number of configuration discretes so that they assume the correct
(PFD or MFD) function and show the desired display format when installed in the airplane.
The DCP-3000 Display Control Panel (DCP) provides the user interface required to control the AFD formats such
as bearing and navigation sources, range selection and weather radar control (such as tilt angle). The DCP has
seven input discretes that are controlled by the following external cockpit switches:
Check List Enable switch on the pilot and copilot control wheel enables the checklist display function.
Checklist Line Advance switches on the pilot and copilot control wheel advances the cursor to the next checklist
line.
FeetlMeter Select switch on the overhead switch panel selects feet or meters. I
FL180 Alert Disable switch on the overhead switch panel inhibits the FL180 alerter function.
INHG/HPA Select switch on the overhead switch panel selects or deselects hectopascals.
Maintenance Enable switch on the left-hand circuit breaker panel enables the maintenance display function.
Overspeed Warn switch on the pilot inboard sub panel activates the air data system overspeed warningfunction.
The AFDs have the following switches:
CAT 2 Arm switch on the overhead switch panel allows CAT2 annunciation on PFD. (This option is not active.)
ADC Source Select switch on the reversionary panel selects the on-side or cross-side air data information to be
shown on the display format.
nl 31-60-00Page 1
Ray~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL S.UPPLEMENT
AHRS Source Select switch on the reversionary panel selects the on-side or cross-side attitude headinginformation to be shown on the display format.
Jan 31/05Page 2 31-60-00
Ra~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CENTRAL DISPLAY SYSTEMS (ELECTRONIC FLIGHT INSTRUMENT SYSTEM)-MAINTENANCE PRACTICES
ADAPTIVE FLIGHT DISPLA YS (AFD-3010) REMOVAL
NOTE
Both PFDs and the MFD are adaptive flight displays with similar removal procedures. Further
discussion will refer to the units as adaptive flight displays only. All adaptive flight displays are
located on the flight instrument panel (Ref. Figure 201).
a. Remove electrical power from the airplane.
NOTE
When removing the PFD, position the control wheel to the full aft position and tilt the face of the PFD
up. This will aid in clearing the control column yoke support during the removal procedure.
b. Perform the AFD-3010 ADAPTIVE FLIGHT DISPLAY (PFD AND MFD) REMOVAL procedure. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
ADAPTIVE FLIGHT DISPLA YS (AFD-3010) INSTALLATION
NOTE
Both PFDs and the MFD are adaptive flight displays with similar installation procedures. Further
discussion will refer to the units as adaptive flight displays only. All adaptive flight displays are
located on the flight instrument panel (Ref. Figure 201).
NOTE
When installing the PFD, position the control wheel to the full aft position and tilt the face of the PFD
up. This will aid in clearing the control column yoke support during the installation procedure.
a. Perform the AFD-3010 ADAPTIVE FLIGHT DISPLAY (PFD AND MFD) INSTALLATION procedure. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the ADAPTIVE FLIGHT DISPLAYS (AFD-3010) ADJUSTMENT/TEST procedure.
B oL;71 Jk~co ii I II II I Issl I II II Ic~ll II II I Is L1~
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i -is´• ´•59 ’ii Vf
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AUDIOAUDIO I I I I I LCONTROLCONTROL I I I I I PANEL
LEFI I I I AIGHI (FlCP)
INBOARD INBOARD
SUBPF1NEL SUBP~NEL
LEFT RIGHTRADIO OUTBOARDOUTBOARDTUNING UNIT SUBPANELSUBPANEL(RTU-4200)
REVERSIONARY PANEL
DISPLAY CONTROL
DISPLAY CONTROL --J PANEL(DCP-3000)
PANEL(DCP-3000)
88348OJ3959FK1
Adapti\re Flight Display (PFD and MFD) (AFD-3010) and Display Control Panel (DCP-3000) Locations
Figure 201
Page 202Nov14/03 31-60-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DISPLAY CONTROL PANEL (DCP-3000) REMOVAL
NOTE
The two DCP-3000 Display Control Panels are located on the flight instrument panel (Ref. Figure201).
a. Remove electrical power from the airplane.
b. Perform the PANEL MOUNTED UNITS (SCREWS) REMOVAL procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
DISPLAY CONTROL PANEL (DCP-3000) INSTALLATION
NOTE
The two DCP-3000 Display Control Panels are located on the flight instrument panel (Ref. Figure201).
a. Perform the PANEL MOUNTED UNITS (SCREWS) INSTALLATION procedure. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the DISPLAY CONTROL PANEL (DCP-3000) ADJUSTMENT/TEST procedure.
DISPLA Y CONTROL PANEL (DCP-3000) ADJUSTMENT/TEST
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the DCP 1/DCP 2. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
31-60-00 Nov 14/03Page 203
CHAPTER
LIGHTS
Raydheon Aircraft CompanySUPER RING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 33 LIGHTS
TABLE OF CONTENTS
SUBJECT PAGE
33-10-00
FlightCompartment Lights- Description And Operation ....1
Electroluminescent (EL) Power Supply AdjustmentTTest ..203
33-CONTENTS
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 33 LIGHTS
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
33-LOEP 1 Nov 14/03
33-CONTENTS 1 Nov 14/03
33-1 0-00 1 Nov 14/03
33-11-00 1 Nov 14/03
201 thru 204 Nov 14/03
33-LOEP Nov 14/03Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
FLIGHT COMPARTMENT LIGHTS I DESCRIPTION AND OPERATION
FLIGHTAND GYRO INSTRUMENT LIGHTS
NOTE
The flight and gym instruments function is performed by the Adaptive Flight Displays. Therefore,
flight and gym instrument lights are deactivated on airplanes with the Pro Line 21 system installed.
All aspects associated with the flight and gyro instrument lights are not applicable to airplanes with
the Pro Line 21 system installed.
ENGINE INSTRUMENT LIGHTS
NOTE
The engine instruments function is performed by the Adaptive Flight Displays. Therefore, engineinstrument lights are deactivated on airplanes with the Pro Line 21 system installed. All aspectsassociated with the engine instrument lights are not applicable to airplanes with the Pro Line 21
system installed.
33-10-00 NoVP;9~b:Page 1
Raycheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
LIGHT DIMMER POWER SUPPLY SYSTEM DESCRIPTION AND OPERATION
The light dimmer power supply system consists of three KGS Electronics LT-55(C) 5 vdc power supplies and one
LSI Systems Electroluminescent (EL) power supply. The LT55(C) 5 vdc power supply receives a 28 vdc input and
provide a 5 vdc output for panel lighting for cockpit controls and display units. The power supplies provide 5 vdc
Panel lighting for Audio Control Panels (ACP), Adaptive Flight Displays (AFD), Display Control Panels (DCP), Radio
Tuning Unit (RTU), Flight Guidance Panel (FGP), Reversionary Switch Panel, Control Display Units (CDU) and
Radio Call Light. The EL power supply receives a 28 vdc input and provides 115 vac outputs for all cockpit panels.
The pilot instrument 5 vdc power supply (3310PS1) is controlled by a potentiometer in the overhead panel. The pilotinstrument 5 vdc power supply (3310PS1) provides 5 vdc panel lighting for the FGP, RTU, Reversionary Switch
Panel, Multi Function Display (MFD), pilot DCP, Primary Flight Display (PFD) and ACP.
The pedestal 5 vdc power supply (3310PS2) is controlled by a potentiometer in the overhead panel. The pedestalpower supply (3310PS2) provides 5 vdc panel lighting for the No. 1 and No. 2 (if installed) CDU.
The copilot instrument 5 vdc power supply (3310PS3) is controlled by a potentiometer in the overhead panel. The
copilot instrument 5 vdc power supply provides 5 vdc panel lighting for the Radio Call Panel, Copilot PFD, ACP and
DCP.
The EL Power supply is controlled by potentiometers in the overhead panel. The EL Panel power supply provideslighting for all subpanels, pedestal switch, fuel control, overhead instrument, over head control, right circuit breaker
panel, engine and rudder control EL panels.
33-11-00 N.~;e;
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
LIGHT DIMMER POWER SUPPLY SYSTEM MAINTENANCE PRACTICES
5 VDc POWER SUPPL Y (LT-55(C~ REMOVAL
NOTE
The three LT-55(C) power supplies are located in the right nose avionics bay (Ref. Figure 201).
a. Remove electrical power from the airplane
b. Remove the right avionics compartment door.
c. Perform the GLOBAL POSITIONING SYSTEM RECEIVER (GPS-4000A) REMOVAL procedure in Chapter 34-
52-00.
d. Identify, tag and disconnect the electrical connector from the rear of appropriate power supply. Install protectivecaps on all connectors.
e. Remove the two screws, lock washers and washers securing the power supply to the shelf.
f. Remove the two washers under the power supply from the shelf.
5 VDC POWER SUPPL Y (L T-55(C) INSTALLA TION
NOTE
The three LT-55(C) power supplies are located in the right nose avionics bay (Ref. Figure 201).
a. Place the two washers over the airplane’s shelf holes.
b. Align the power supply’s mounting holes with airplane’s shelf holes.
c. Secure the power supply to airplane shelf with two screws, lock washers and washers.
d. Remove the protective caps from the connectors. Connect the electrical connector to the rear of appropriatepower supply. Remove the tags.
e. Perform the GLOBAL POSITIONING SYSTEM RECEIVER (GPS-4000A) INSTALLATION procedure in
Chapter 34-52-00.
f. Perform the 5 VDC POWER SUPPLY (LT-55) ADJUSTMENTTTEST procedure.
g. Install the right avionics compartment door.
5 Voc POWER SUPPL Y (LT-55(C~ ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Check that the power supply lights the cockpit 5 vdc-panel lights for its respective cockpit display or control.
c. Remove electrical power from the airplane
33-11-00 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ood"".
B
A
DETAIL A
5 VDC POWER SUPPLY
(LT-55) NO. 3
5 VDC POWER SUPPLY
(LT-55) NO. 2
5 VDC POWER SUPPLY :x>(LT-55) NO.1
-~a
DETAIL B
BVDC Power Supply (LT-55 (C)) Installation
Figure 201
33111100
RBytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELECTROLUMINESCENT (EL) POWER SUPPL Y REMOVAL
NOTE
The EL power supply is located under the floor boards between FS 246.75 and 256.25 (Ref. Figure202).
a. Remove electrical power from the airplane
b. Identify, tag and disconnect the electrical connector from the rear of EL panel power supply. Install protectivecaps on all connectors.
c. Loosen the four mounting screws and remove the power supply.
ELECTROLUMINESCENT (EL) POWER SUPPL Y INSTALLA TION
NOTE
The EL power supply is located under the floor boards between FS 246.75 and 256.25 (Ref. Figure202).
a. Align the EL power supply’s mounting holes with nutplate holes.
b. Tighten the four mounting screws and secure the EL power supply to the shelf.
c. Remove the protective caps from the connectors. Connect the electrical connector to the rear of EL power
supply. Remove the tags.
d. Perform the ELECTROLUMINESCENT (EL) POWER SUPPLY ADJUSTMENTTTEST procedure.
ELECTROLUMINESCENT (EL) POWER SUPPL YADJUSTMENT/TEST
a. Apply electrical powertotheairplane.
b. Check that the EL power supply lights the cockpit panel lights.
c. Remove electrical power from the airplane
33-11 -00 Nov 14/03Page 203
RayZheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
,0´•04
ic!
ELECTROLUMINESCENT
(EL) POWER SUPPLY
I
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88338
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Electroluminascent (EL) Power Supply Installation
Figure 202
Page 33111100
CHAPTE R
NAVIGATION
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 34 NAVIGATION AND PITOT/STATIC
TABLE OF CONTENTS
SUBJECT PAGE
34-00-00
Navigation- General
Special Tools and Equipment. .....1
34-10-00
Air DataSystem- Description andOperation. .............1
Air Data System Maintenance Practices. ..............201
Air Data Computer (ADC-3000) Removal. ...........,201
Air Data Computer(ADC-3000) Installation .........,.201
CONNECTOR: MIL MS27467T25F35S CONNECTOR: JMS27656T25B35A
STRAIN RELIEF: MIL M85049/49-2-24N BI7CKSHELL: MIL M85049/49-2-24W
USE 22 GFI. WIRE. USE SHIELDED WIRES AS SHOWN. HARNESS LENGTH IS 10 FEET.
saJ~ze034752F1F1
Attitude Heading Computer Extension Cables
Figure 2
34-00-00 Nov 14/03Page 5
Raytheon AiKraft companySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIR DATA SYSTEM DESCRIPTION AND OPERATION
The Air Data System (ADS) is a dual system that consists of two ADC-3000 Air Data Computers (ADCs). Air data
parameters output by the ADS include Pressure Altitude, BARO Corrected Altitude, Barometric Pressure, Total
Pressure, Impact Pressure, Static Pressure, Vertical Speed, Airspeed, Mach, Maximum Airspeed, True Airspeed,Total Air Temperature, Static Air Temperature and ISA Delta Temperature. Barometric Pressure is set through a
control knob on the Display Control Panel (DCP).
The ADC-3000 Air Data Computer (ADC) is an instrument grade air data sensor/processor. Pitot and static
pneumatic inputs and total air temperature sensors provide raw air data information to the ADC. The ADC also
receives reference inputs from the integrated avionics processor (IAPS). The ADC outputs processed air data to
both Attitude Heading Computers (AHCs), Integrated Avionics Processors (IAPS), left and right Primary FlightDisplays (PFDs) and the Multi Function Display (MFD).
34-10-00
RaYnyeOyl Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIR DATA SYSTEM MAINTENANCE PRACTICES
AIR DATA COMPUTER (ADC-3000) REMOVAL
NOTE
The two ADC-3000 Air Data Computers are located in the right nose avionics bay (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the right avionics compartment door.
c. Perform the applicable RACK MOUNTED LRU REMOVAL procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
AIR DATA COMPUTER (ADC-3000) INSTALLATION
NOTE
The two ADC-3000 Air Data Computers are located in the right nose avionics bay (Ref. Figure 201).
a. Perform the applicable RACK MOUNTED LRU INSTALLATION procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the PITOT SYSTEM PRESSURE TEST and STATIC SYSTEM LEAK TEST procedures in Chapter 34-
00-00 of the Super King Air 200 Series Maintenance Manual.
c. Perform the AIR DATA COMPUTER (ADC-3000) ADJUSTMENT/TEST procedure.
d. Install the right avionics compartment door.
AIR DATA COMPUTER (ADC-3000) ADJUSTMENTrrEST
a. Remove electrical power from the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the ADC-3000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Applyelectrical powertotheairplane.
34-10-00 NPOBy9:4~:
RBYtheO´• Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Air Data Computer (ADC-3000) No. 1 and No. 2 Location
Figure 201
Nov 34110100
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ATTITUDE AND DIRECTION DESCRIPTION AND OPERATION
ATTITUDE HEADING SYSTEM
The Attitude Heading System (AHS) consists of two AHC-3000 Attitude Heading Computers (AHCs), two FDU-3000
Flux Detector Unit (FDUs) and two ECU-3000 External Compensation Units (ECUs).
The Attitude Heading Computer (AHC) is a solid state strap-down reference system that generates angular rates
and linear acceleration about the body axis of the aircraft and digitally processes this data to obtain 3-axis angle,rate and acceleration parameters. The AHC computed parameters such as pitch, roll, heading, body rates and
accelerations are transmitted to the displays and IAPS. Operation of the Attitude Heading System is automatic when
electrical power is applied to the system.
The Flux Detector Units (FDUs) are gimbaled 2-axis magnetic sensors that detect components of the earth’s
magnetic field through a pendulous sensing element. The FDUs provide the magnetic flux measurements to the
AHC for use in computing accurate airplane heading.
The External Compensation Units (ECUs) are mounted close to the AHCs and contain particular aircraft AHRS
alignment and compass correction parameters. They are re-programmed during AHS leveling or compass swingprocedure. The ECUs provide electrical compensation for any flux detector errors caused by the airplane alteringthe earth’s magnetic field.
The controls for the Attitude Heading System are located on the Reversionary Switch Panel. The operating controls
for the Attitude Heading System (AHS) are external switches, which are used to select the directional gym and slew
pushbuttons. The AHS provides two modes of Heading Function Operation: Magnetic Heading (Slaved) Mode and
Directional Gym (DG or Free Gyro) Mode. The DG MODE Switch is used to select either the Slaved Mode or DG
Mode. In the Slaved Mode, the heading computations in the AHC are slaved to the FDU. This is the primary headingmode during normal operation. In the DG (Directional Gym) or Free Gym Mode, the input from the FDU is not used
to slave the heading of the AHC. The AHC performs like a directional gym in this mode.
The slew pushbuttons are momentary action buttons used to periodically correct for drift, right or left. In DG Mode,
pushing either slew button causes the heading computations in the AHC to slew toward the selected direction. In
slaved mode, pushing either slew button also causes the heading computation to slew towards the selected
direction. However, when the button is released, the heading will slowly slave back to the heading sensed by the
FDU.
34-20-00 1
Rayt~on AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ATTITUDE AND DIRECTION MAINTENANCE PRACTICES
A TTITUDE HEADING COMPUTER (AHC-3000) REMOVAL
NOTE
The two AHC-3000 Attitude Heading Computers are located in the left (Ref. Figure 201) and right(Ref. Figure 202) lower nose avionics racks.
a. Remove electrical power from the airplane.
b. Remove the left or right avionics compartment door.
c. Perform the appropriate RACK MOUNTED LRU REMOVAL procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
ATTITUDE HEADING COMPUTER (AHC-3000) INSTALLATION
NOTE
The two AHC-3000 Attitude Heading Computers are located in the left (Ref. Figure 201) and right(Ref. Figure 202) lower nose avionics racks.
a. Perform the appropriate RACK MOUNTED LRU INSTALLATION procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
NOTE
Perform the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST procedure if the Attitude
Heading Computer is being installed after its mounting rack has been removed from the shelf or if
the shelf has been removed from the airplane structure. The computer must be installed in a
position that is level in relation to airplane level to function properly.
b. Perform the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST procedure, if required.
c. Perform the ATTITUDE HEADING COMPUTER (AHC-3000) ADJUSTMENT/TEST procedure.
d. Install the left or right avionics compartment door.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the AHC 1 AHC 2 (ECU 1 AND ECU 2)system. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics
System.)
c. Remove electrical power from the airplane.
34-20-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
o´•o~ /a
R’d~ ~L
DETAIL A
~ii.jli: i
I
DETAIL B88348034761AA
Attitude Heading Computer (AHC-3000) No. 1 and External Compensation Unit (ECU-3000) No. 1 Location
Figure 201 (Sheet 1 of 2)
34120100
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
\j;‘iCOMPENSF1IION
ri (ECU-3000) NO.2
-h´•l.I-..~.., EXTERNAL COMPENSATION
~P_ UNIT (ECU5000) NO. I
I
i;7h0’ ~´•:-L,
MTAIL C
Y P
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VIEW LOOKING UP
DETAIL D
Attitude Heading Computer (AHC-3000) No. 1 and External Compensation Unit (ECU-3000) No. 1 Location
Figure 201 (Sheet 2 of 2)
34120-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
GLOBAL POSITIONINGGLOBAL POSITIONING SYSTEM (GPS-4000A) NO. 1
SYSTEM (GPS-4OOOA) NO. 2
(OPTION*L) B
Attitude Heading Computer (AHC-3000) No. 2 and External Compensation Unit (ECU-3000) No. 2 Location
Figure 202 (Sheet 1 of 2)
Nov 14/03Page 204 34-20-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
EXTERNAL COMPENSATIONUNIT (ECU-3000) NO.2
iL1~/nZ~\Y
EXTERNAL COMPENSATION
~P_ UNIT (ECU-3000) NO. I
ja i;411::3
[IICi
\Yu/´•~
DETAIL C
Y
VIEW LOOKING UPBB34B
DETAIL D o~4759na
Attitude Heading Computer (AHC-3000) No. 2 and External Compensation Unit (ECU-3000) No. 2 Location
Figure 202 (Sheet 2 of 2)
34-20-00
Rarytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ATTITUDE HEADING SYSTEM FUNCTIONAL TEST
NOTE
This procedure may be used to test the entire Attitude Heading System or a portion of the system.
Perform the steps under TEST PREPARATION AND RECOVERY and the MODULAR MOUNTING
TRAY (MMT) LEVELING MODE portion of the functional test, if this test is being performed due to
one of the following situations: (1) removal of the AHC mounting rack; (2) removal of the shelf to
which the AHC mounting rack has been attached; (3) the replacement or installation of the Weather
Radar Receiver/Transmitter/Antenna (RTA-852); (4) the replacement of an External CompensationUnit.
TEST PREPARATION AND RECOVERY
NOTE
Use a stopwatch to record timed events.
a. Remove the left and right avionics compartment doors.
b. Open AHC NO. 1 and AHC NO. 1 SEC circuit breakers.
c. Open AHC NO. 2 and AHC NO. 2 SEC circuit breakers.
d. On the Reversionary Switch Panel ensure the listed switches are positioned as follows:
1. AHRSswitchto NORM.
2. PILOTDISPLAYswitchto NORM.
3. Pilot and Copilot DG FREE/NORM switches to NORM.
4. Pilot and Copilot SLEW switches to center position.
e. Apply external electrical power to the airplane.
f. Perform the required tests.
g. After testing is complete, remove electrical power from the airplane.
h. Ensure that AHC 1 and AHC 2 are secured in the equipment racks.
i. Remove extension cables from AHC 1 and AHC 2, if installed.
j. Ensure the Leveling and Compensation Test Box is removed from the airplane.
k. Ensure all circuit breakers are closed.
I. Install the left and right avionics compartment doors.
Nov 14/03Pege 206 34-20-00
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test
Action Result
A. AHC 1 and AHC 2 Power Up
1. Close AHC NO. 1 and AHC NO. 1 SEC circuit PFD 1: Displays ATT and HDG ALIGNING DO NOT
breakers. TAXI. Displays red ATT and HDG flags.MFD: Displays red HDG flag.
2. Wait approximately 30 to 60 seconds for AHC PFD 1: Displays normal ADI and HSI formats. Displaysinitialization to be completed, a white XAHS boxed in yellow annunciation. Red ATT
and HDG flags are removed.
MFD: Displays normal HSI format. Red HDG flag is
removed.
3. Close AHC NO. 2 and AHC NO. 2 SEC circuit PFD 1: Displays normal ADI and HSI formats. Displaysbreakers. a white XAHS boxed in yellow annunciation. No red ATT
and HDG flags are displayed.PFD 2: Displays ATT and HDG ALIGNING DO NOT
TAXI. Displays red ATT and HDG flags.MFD: Displays normal HSI format. No red HDG flag is
displayed.
4. Wait approximately 30 to 60 seconds for AHC PFD 1: Displays normal ADI and HSI formats. White
initialization to be completed. XAHS boxed in yellow annunciation is removed. No red
ATT and HDG flags are displayed.PFD 2: Displays normal ADI and HSI formats. No red
ATT and HDG flags are displayed.MFD: Displays normal HSI format. No red HDG flag is
displayed.
B. AHRS 1 Flags
1. Open AHC NO. 1 and AHC NO. 1 SEC circuit PFD 1:477 and HDG flags appear.breakers. PFD 2: XAHS flag appears.
MFD: HDG flag appears.
2. Close AHC NO. 1 and AHC NO. 1 SEC circuit PFD 1:477 and HDG flags are removed (afterbreakers, initialization). XAHS flag is displayed.
PFD 2: Has normal display.MFD: Alignment message is displayed, HDG flag and
message is removed (after alignment, approximately 30
seconds)
C. AHRS2Flags
1. OpenAHCNO.2andAHC NO.2SECcircuit PFD 1: XAHS flag appears.breakers. PFD 2: ATT and HDG flags appear.
2. CloseAHCNO. 2andAHC NO.aSECcircuit PFD 1: XAHS Flag is removed.
breakers. PFD 2: A7T and HDG flags are removed (afterinitialization).
34-20-00 Nov 14/03Page 207
Raythgo´• Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
D. Modular Mounting Tray (MMT) Leveling Mode
AHC 1 and AHC 2
1. Open AHC NO. 1 and AHC NO. 1 SEC circuit
breakers. Open AHC NO. 2 and AHC NO. 2
SEC circuit breakers.
2. Perform the AIRPLANE LEVELING procedurein Chapter 8-00-00. After the airplane is level,ensure both the left and right main gear squatswitches are positioned to provide a Weight on
Wheels signal.
3. Close AHC NO. 1 and AHC NO. 1 SEC circuit
breakers.
NOTE The Attitude Heading System must be thermallystable during the leveling procedure. Allow the systemto operate for 60-minutes to warm-up before continuingwith this procedure. Remove and apply power as quicklyas possible to maintain the temperature when
performing Steps D.4. thru D.8..
4. Open AHC NO. 1 and AHC NO. 1 SEC circuit
breakers.
5. Ensure all switches on the Leveling and
Compensation Test Box (3, Chart 1, 34-00-00)are set to the NORMAL position.
6. Attach connector P1 of the Leveling and
Compensation Test Box to connector 3456J2
ton right side of pedestal).
7. On the Leveling and Compensation Test Box,set L AHC AUTO LEVEL/NORMAL switch to
AUTO LEVEL.
8. Close AHC NO. 1 circuit breaker.
9. Use the MFD PREV/NEXT keys to view the MFD: Displays DIAGNOSTIC DATA page. DiagnosticMAINTENANCE MAIN MENU page. Select data cycles from HEX format to BINARY format.
LRU INDEX/OPERATION. Use the UP/DOWN
keys to move to AHC 1 then press SELECT
key. Use tab key to switch to code line. Then
use UP/DOWN key to highlight 351 word then
press SELECT.
10. Monitor AHC 1 labels 351 bits 24 -21 to ensure PFD 1: ATT and HDG flags will alternately flash at a 1
the unit has entered the MMT leveling mode (bit Hz rate. Compass card will begin to turn CW from the
23 set to 1). 360" heading mark. The displayed HDG counts down
from 360" to O" over a 5 minute period (~t 30 sec).MFD: Verify bits 24 21 of label 351 are set to 1.
Page 208Nov14/03 34-20-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
11. After the 5 minute period when displayed HDG PFD 1: Displays a continuous ATT flag. HDG flag will be
reaches 0". removed.
Note: If the above condition cannot be met, re-level the
aircraft and repeat this procedure. Proceed with this
procedure if the above condition is met.
12. Toggle Pilot’s DG FREE/NORM switch from PFD 1: Displays ATT and HDG flags.NORM to DG FREE to NORM to store leveling Displays DG to the right of Course display.
parameters in ECU.
13. On the Leveling and Compensation Test Box, PFD 1: Verify indicated pitch is within 1 line width of
set L AHC AUTO LEVEUNORMAL switch to horizon line. Verify indicated roll is within 1 line width
16. Press MFD NEXT MODE line key to select MFD: Displays INPUT MODE parameters.INPUT MODE.
17. Use MOVE CURSOR to select top inputparameter line.
18. Press SCROLL UP or SCROLL DOWN as MFD: Left and Right PTH is 0.0" 0.2").
required to scroll to PTH parameter.
19. Use MOVE CURSOR to select next inputparameter line.
20. Press SCROLL UP or SCROLL DOWN as MFD: Left and Right ROL is 0.0" 0.2").
required to scroll to ROL parameter.
21. Use MFD FORMAT key to cycle display until a
normal PPOS format is displayed (if required).
22. Open AHC NO. 1 circuit breaker.
23. Ensure all switches on the Leveling and
Compensation Test Box (3, Chart 1,34-00-00)are set to the NORMAL position.
24. Close AHC NO. 2 and AHC NO. 2 SEC circuit
breakers.
NOTE The Attitude Heading System must be thermallystable during the leveling procedure. Allow the systemto operate for 60-minutes to warm-up before continuingwith this procedure.
25. Open AHC NO. 2 SEC circuit breaker.
26. On the Leveling and Compensation Test Box,
set R AHC AUTO LEVEUNORMAL switch to
AUTO LEVEL.
34-20-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
27. Use the MFD PREV/NEXT keys to view the MFD: Displays DIAGNOSTIC DATA page. DiagnosticMAINTENANCE MAIN MENU page. Select data cycles from HEX format to BINARY format.
LRU INDEX/OPERATION. Use the UP/DOWN
keys to move to AHC 2 then press SELECT
key. Use tab key to switch to code line. Then
use UP/DOWN key to highlight 351 word then
press SELECT.
28. Monitor AHC 2 labels 351 bits 24 21 to ensure PFD 2: ATT and HDG flags will alternately flash at a 1
the unit has entered the MMT leveling mode (bit Hz rate. Compass card will begin to turn CW from the
23 set to 1). 360" heading mark. The displayed HDG counts down
from 360" to O" over a 5 minute period 30 sec).MFD: Verify bits 24 21 of label 351 are set to 1.
29. After the 5 minute period when displayed HDG PFD 2: Displays a continuous A‘TT flag. HDG flag will be
reaches 0". removed.
Note: If the above condition cannot be met, re-level the
aircraft and repeat this procedure. Proceed with this
procedure if the above condition is met.
30. Toggle Copilot’s DG FREE/NORM switch from PFD 2: Display ATT and HDG flags.NORM to DG FREE to NORM to store leveling Displays DG to the right of Course display.parameters in ECU.
31. On the Leveling and Compensation Test Box, PFD 2: Verify indicated pitch is within 1 line width of
set R AHC AUTO LEVEVNORMAL switch to horizon line. Verify indicated roll is within 1 line width
34. Press MFD NEXT MODE line key to select MFD: Displays INPUT MODE parameters.INPUT MODE.
35. Use MOVE CURSOR to select top inputparameter line.
36. Press SCROLL UP or SCROLL DOWN as MFD: Left and Right PTH is 0.0" 0.2").required to scroll to PTH parameter.
37. Use MOVE CURSOR to select next inputparameter line.
38. Press SCROLL UP or SCROLL DOWN as MFD: Left and Right ROL is 0.0" 0.2").required to scroll to ROL parameter.
39. Use MFD FORMAT key to cycle display until a
normal PPOS format is displayed (if required).
40. Open AHC NO. 2 circuit breaker.
41. If all testing is completed, remove the Levelingand Compensation Test Box from the aircraft.
Nov 34-20-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
E. AHRS 1 Pitch and Roll NOTE Two people are required to perform this
procedure.
i. Open AHC NO. 2 circuit breaker.
2. Open AHC NO. 1 circuit breaker and remove
AHC 1 from mounting rack so unit may be tilted
freely. Install an Attitude Heading ComputerExtension Cable (4, Chart 1,34-00-00)between the AHC and the airplane wiringharness. Close AHC NO. 1 circuit breaker and
allow AHRS to re-initialize before continuing.
3. Slowly tilt AHC 1 up (aft). PFD i: Displays a pitch up indication.
4. Slowly tilt AHC 1 down (forward). PFD 1: Displays a pitch down indication.
16. Set PILOT DISPLAY switchto the NORM PFD i: Returns to normal display.position. MFD: Returns to normal display.
17. Set AHC 1 in its mounting rack.
18. Open AHC NO. 1 circuit breaker.
F. AHRS 2 Pitch and Roll NOTE Two people are required to pertorm this
procedure.
i. Open AHC NO. 1 circuit breaker.
2. Open AHC NO. 2 circuit breaker and remove
AHC 2 from mounting rack so unit may be tilted
freely. Install an Attitude Heading ComputerExtension Cable (4, Chart 1, 34-00-00)between the AHC and the airplane wiringharness. Close AHC NO. 2 circuit breaker and
allow AHRS to re-initialize before continuing.
34-20-00 Nov 14/03Page 211
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MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
3. Slowly tilt AHC 2 up (aft). PFD 2: Displays a pitch up indication.
4. SlowlytiltAHCedown (forward). PFD 2: Displays a pitch down indication.
1. Open AHC NO. 1 circuit breaker and monitor PFD 1: Normal ADI and HSI formats are removed after
displays for 10 to 12 minutes. 11 1 min. Displays red ATT and HDG flags.MFD: Normal HSI format is removed. Displays red HDG
flag.
Nov 14/03Page 214 34-20-00
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MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System Functional Test (Continued)
Action Result
2. Open AHC NO. 2 circuit breaker and monitor PFD 2: Normal ADI and HSI formats are removed after
displays for 10 to 12 minutes. 11 1 min. Displays red ATT and HDG flags.MFD: Normal HSI format is removed. Displays red HDG
flag.
3. Close AHC NO. 1 and AHC NO. 2 circuit PFD 1: Displays ATT and HDG ALIGNING DO NOT
breakers. TAXI. Displays red ATT and HDG flags.PFD 2: Displays ATT and HDG ALIGNING DO NOT
TAXI.
MFD: Displays red HDG flag.
4. Wait approximately 30 to 60 seconds for PFD 1: Displays normal ADI and HSI formats. Red ATT
initialization to be completed. and HDG flags are removed.
PFD 2: Displays normal ADI and HSI formats. Red ATT
and HDG flags are removed.
MFD: Displays normal HSI format. Red HDG flag is
removed.
ATTITUDE HEADING SYSTEM AND STANDBY COMPASS SWING
GENERAL INFORMATION
During compensation, airplane and personnel movements must be kept to an absolute minimum.
The FDU Compensation and Standby Compass Swing will be performed with ENGINES RUNNING.
During FDU Compensation and Standby Compass Swing all normally operated Avionics and Electrical
equipment MUST BE energized.
The FDU Compensation Mode can only be accessed during AHC power up, with Weight on Wheels.
The FDU compensation mode and Standby Magnetic Compass Swing can only be performed OUTSIDE THE
HANGAR AREA, away from all metal structures and any magnetic interference sources.
Attitude Heading System and Standby Compass Swing
Action Result
A. AHS Preparation
1. Ensure all switches on the Leveling and
Compensation Test Box (3, Chart 1, 34-00-00)are set to the NORMAL position.
2. AttachconnectorP1 oftheLevelingandCompensation Test Box to connector 3456J2
ton right side of pedestal).
34-20-00 Nov 14/03Page 215
Ray~heMI nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
B. ESIS Preparation
1. Open ESIS DISP and ESIS HDG SNSR circuit
breakers to remove input power from the GH-
3100 system
NOTE Perform only the steps provided in the
ELECTRONIC STANDBY FLIGHT DISPLAY (GH-3100) REMOVAL procedure in Chapter 34-25-00 that
are required to provide access for connection of the
Calibration Test Set. The Calibration Test Set cables
should be routed behind the instrument panel.
2. Connect the Calibration Test Set (2, Chart 1,
34-00-00) as follows:
a. Removeairplane connector3425P1 from
GH-3100 connector J1.
b. Remove DCM-3100fromGH-3100
connector J2.
c. AttachTestSetCable (570-8552-10)connector P1 to Adapter Cable (570-8984-01) connector P1.
d. Attach Adapter Cable (570-8984-01) P2 to
GH-3100 connector J1.
e. Attach Test Set Cable connector P2 to GH-
3100 connector J2.
f. Attach Adapter Cable (570-8984-02)connector P4 to airplane connector
3425P1.
g. Attach Test Set Cable connector J2 to
DCM-31 00.
h. Attach Test Set Cable connector J1 to
Adapter Cable (570-8984-02) connector
P3.
3. Position the GH-3100 in the instrument paneland tighten down the mounting screws. NOTE
The GH-3100 MUST be at the correct panelangle during calibration.
4. Performthe MAGNETOMETER (MAG-3000A)REMOVAL procedure (Ref. Chapter 34-25-00).Install the MAT-3000A (part of Calibration Test
Set) in its place.
5. Apply external electrical power to the airplane.
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Raythwm Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
6. Close ESIS DISP and ESIS HDG SNSR circuit "Aligning" message appears for about 3 minutes.
breakers. Wait approximately 3 minutes for the
"Aligning" message to disappear from the GH-
3100 display.
7. Using the ESIS menu, Fast Erect the GH-3100, Attitude compensation data is written to the DCM-3100.
wait approximately 3 seconds, then Test Set will prompt you to remove power.
momentarily depress the Data Entry button,and wait while the attitude compensation data is
being written to the DCM-3100. When
prompted by the message on the Calibration
Test Set display, remove input power from the
GH-3100 system by opening ESIS DISP and
ESIS HDG SNSR circuit breakers.
NOTE The MAT-3000A is calibrating the roll and pitchdifference between the GH-3100 mounting in the
airplane and the MAG-3000A mounting in the airplane.
8. Remove electrical power from the airplane.
9. Remove the MAT-3000A from the airplane.Perform the MAGNETOMETER (MAG-3000A)INSTALLATION procedure (Ref. Chapter 34-
25-00).
C. Test
1. Refer to the Super King Air 8200 and B200C
Pilot’s Operating Handbook and FAA ApprovedAirplane Flight Manual for the engine start and
run procedures. Follow all normal airplanepower up and engine starting and ground run
procedures.During this test procedure the following systemneeds to be on: Beacon lights.The following systems shall be off: Air
Conditioning, Stab Anti-ice and Landing lights.
2. Taxi the airplane to a compass rose and
position it to North heading (O" 5").
3. Open AHC NO. 1,AHC NO. 1 SEC, AHC NO. 2
and AHC NO. 2 SEC circuit breakers.
4. OntheLevelingand CompensationTestBoxset L AHC and R AHC COMP/NORMAL
switches to COMP.
5. Close AHC NO. 1 and AHC NO. 2 circuit PFD 1 and 2: Once AHC initialization is complete,breakers. system will display an ATT flag and heading will become
Valid.
34-20-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
NOTE The ATT will be flagged for the duration of the
calibration procedure.
6. Using MFD line keys, go to the MAINTENANCE
MENU format and enter the MDC
DIAGNOSTIC DATA page.
7. Use the MFD PREV/NEXT keys to view AHRS
1 and 2 data and the BIN/HEX key to displaydata in the binary form.
8. MonitorAHRS1 andAHRS2labels:351 bit MFD: Verify bit 24 of label 351 is set to 1 as shown;24. AHRS 1: 351-xxx1 xxxx Ixxx Ixxx xxxx xxxx (x n/a)
AHRS 2: 351-xxx1 xxxx Ixxx Ixxx xxxx xxxx (x n/a)
9. Toggle Pilot i Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment.
NOTE The following steps may be accomplished OFF
the compass rose.
10. Reposition airplane to 45" 5") as indicated on
PFD 1.
11. Toggle Pilot Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
12. Reposition airplane to 90" 5") as indicated on
PFD 1.
13. Toggle Pilot Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
14. Reposition airplane to 135" 5") as indicated
on PFD 1.
15. Toggle Pilot Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
16. Reposition airplane to 180" 5") as indicated
on PFD 1.
Nov 34-20-00
RBYtheOn AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
17. Toggle Pilot/ Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
18. Reposition airplane to 225" 5") as indicated
on PFD 1.
19. Toggle Pilot Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
20. Reposition airplane to 270" 5") as indicated
on PFD 1.
21. Toggle Pilot Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
22. Reposition airplane to 315" 5") as indicated
on PFD’1.
23. Toggle Pilot/ Copilot DG FREE/NORM PFD 1 and 2: Displays HDG flags (25 to 35 sec.), and
switches as follows: NORM to DG FREE to then HDG flags are removed.
NORM to begin alignment. MonitorAHRS 1 and
2 labels 353 bit 11 during the alignment to
ensure bit is set to O.
24. NOTE If after 1 minute the heading does not
become valid after completing the last
compensation on heading (315"), and label 353
bit 12 is set to 1 then the AHC is in an "Out-of
Limits" condition. Abort the alignment byrestarting the compensation at step 2.
D. IndexAdjustment Procedure
NOTE Maximum Index Compensation allowed is ~L 5".
The slew switches will not drive the Index beyond this
limit.
1. Align airplane on compass rose to O" 2"
(North).
2. Set Pilot Copilot DG FREE/NORM switches to PFD 1 and 2: Displays HDG flag(s), then HDG flags are
DG FREE and momentarily activate the Pilot removed.
Copilot and SLEW switches.
34-20-00
Raltheen Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
6. Use MOVE CURSOR to select any inputparameter line.
7. Press the SCROLL UP or SCROLL DOWN MFD: Displays Left and Right HDG MAG to the tenth of
as required to scroll to HDG MAG parameter. a degree.
8. Set PLT SLEW switch to either plus or Minus MFD: Indicates left HDG MAG to be O" 0.1").to slew the AHRS 1 HDG MAG to O" 0.1").
9. Set COPLT SLEW switch to either plus or MFD: Indicates right HDG MAG to be O" 0.1").Minus to slew the AHRS 2 HDG MAG to O"
(f o.10)~
10. Toggle Pilot/ Copilot DG FREE/NORM
switches as follows: NORM to DG FREE to
NORM.
11. On the Leveling and Compensation Test Box
set L AHC and R AHC COMP/NORMAL
switches to NORMAL.
12. A check of the alignment for the AHRS and the
ESIS will be performed in the CALIBRATION
CHECK portion of this procedure.
E. ESIS HeadingCalibration
NOTE Unless otherwise specified, all references to
"switches" and switch "buttons" used within the
procedures of this section are those of the Calibration
Test Set.
NOTE The GH-3100 heading display will be flaggedduring calibration.
1. Close ESIS DISP and ESIS HDG SNSR circuit "Aligning" message appears for about 3 minutes.
breakers. Wait approximately 3 minutes for the
"Aligning" message to disappear from the GH-
3100 display.
2. Align the airplane to a cardinal heading (i.e., Airplane heading displayed on the test set will match the
north, south, east, or west). Up to 5" of airplane magnetic cardinal heading.misalignment may be compensated for via the
Calibration Test Set. Use the Inc/Dec switch as
required to make the "airplane heading" number
displayed on the Calibration Test Set agreeswith the actual heading.
Page 34-20-00
Raykheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
NOTE Ignore heading tape information at the bottom
of GH-3100 display until this procedure is complete.
3. UsingtheESISmenu, FastErecttheGH-3100, Data is saved.
wait approximately 3 seconds, and then
momentarily depress the Data Entry button.
4. Repeat Steps 2. and 3. above for each of the
remaining cardinal headings. NOTE The
headings may be sequenced in any order. Also,if a mistake is made, data for a heading may be
re-entered (only the last data entered for each
heading will be saved).
5. After data has been entered for each of the four Expected Result screen is displayed on test set.
cardinal headings, depress the Display Select
button twice to go to the Calibration Test Set
Expected Result (write) screen. NOTE -Access
to the expected result screen will only be
available if data has been entered for each of
the four cardinal headings.
6. Momentarily depress the Data Entry button and Heading calibration data is written to the DCM-3100.
wait while the heading calibration data is being Test Set will prompt you to remove power.written to the DCM-3100. When prompted bythe message on the Calibration Test Set
display, remove power from the GH-3100
system by opening ESlS DISP and ESIS HDG
SNSR circuit breakers.
7. Remove the Calibration Test Set from the
airplane and return the GH-3100 and DCM-
3100 to a normal installation configuration.Perform only the steps provided in the
ELECTRONIC STANDBY FLIGHT DISPLAY
(GH-3100) INSTALLATION procedure in
Chapter 34-25-00 needed to accomplish the
return to normal configuration.
F. Calibration Check
1. Close ESIS DISP and ESIS HDG SNSR circuit "Aligning" message appears for about 3 minutes.
breakers. Wait approximately 3 minutes for the
"Aligning" message to disappear from the GH-
3100 display.
2. Verify that the AHC NO. 1, AHC NO. 1 SEC, PFD 1 and 2: Once AHC initialization is complete will
AHC NO. 2 and AHC NO. 2 SEC circuit display a valid attitude and heading.breakers are closed.
34-20-00 Nov 14/03Page 221
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MAINTENANCE MANUAL SUPPLEMENT
Attitude Heading System and Standby Compass Swing (Continued)
Action Result
NOTE When checking the ESIS compass, after
positioning the aircraft to a heading you must Fast Erect
the GH-3100 and then wait approximately 3 seconds
before recording the heading displayed on the GH-
3100.
3. Position the airplane at each heading listed on
Chart 201 and record the AHRS 1, AHRS 2 and
ESIS compass readings.
4. Verify AHRS 1 compass system is within ~1" of
actual airplane heading.
5. Verify AHRS 2 compass system is within ~1" of
actual airplane heading.
6. Verify ESIS compass system is within 3" of
actual airplane heading.
7. Shut the airplane engines down. Refer to the
Super King Air 8200 and 8200C Pilot’s
Operating Handbook and FAA ApprovedAirplane Flight Manual for the engine shutdown
procedures. Remove electrical power from the
airplane.
8. Remove the Leveling and Compensation Test
Box from the airplane.
EXTERNAL COMPENSATION UNIT (ECU-3000) REMOVAL
NOTE
The two ECU-3000 External Compensation Units are located in the left (Ref. Figure 201) and right(Ref. Figure 202) lower nose avionics racks.
a. Remove electrical power from the airplane.
b. Remove the left or right avionics compartment door.
c. Perform the appropriate SPECIAL MOUNTS REMOVAL procedure. (Ref. Rockwell Collins, Inc. System Manual
(523-0790063) for the King Air Pro Line 21 Avionics System.)
EXTERNAL COMPENSATION UNIT (ECU-3000) INSTALLATION
NOTE
The two ECU-3000 External Compensation Units are located in the left (Ref. Figure 201) and right(Ref. Figure 202) lower nose avionics racks.
Nov 34-20-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
a. Perform the appropriate SPECIAL MOUNTS INSTALLATION procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
NOTE
If the ECU is replaced, the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST and ATTITUDE
HEADING SYSTEM AND STANDBY COMPASS SWING procedures must be performed to providethe ECU with system data for storage.
b. If required, perform the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST and ATTITUDE HEADING
SYSTEM AND STANDBY COMPASS SWING procedures.
c. Perform the EXTERNAL COMPENSATION UNIT (ECU-3000) ADJUSTMENT/TEST procedure.
d. Install the left or right avionics compartment door.
EXTERNAL COMPENSATION UNIT (ECU-3000) ADJUSTMENT/TEST
a. Applyelectrical powertothe airplane.
rCAUTION 1CAUTION
Whenever an ECU is replaced, the FDU COMPENSA 7/ON MODE procedure shall be performedto ensure proper operation of the Attitude Heading System.
NOTE
Perform Step b. if the ECU was replaced. Perform Step c. if the original ECU was re-installed in the
airplane.
b. Perform the FDU COMPENSATION MODE procedure. (Ref. Rockwell Collins, Inc. AHS-3000 Attitude HeadingReference System Installation Manual 523-0780184.)
c. Perform the TESTING AND TROUBLESHOOTING procedure for the AHC 1 AHC2 (ECU 1 AND ECU 2)system. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics
System.)
d. Remove electrical powerfrom the airplane.
FLUX DETECTOR UNIT (FDU-3000) REMOVAL
NOTE
The two FDU-3000 Flux Detector Units are located in the horizontal stabilizer of the airplane (Ref.Figure 203).
a. Remove electrical power from the airplane.
b. Remove the panel covering the flux detector.
c. Identify, tag and disconnect the electrical connector from the FDU. Install protective caps on all connectors.
34-20-00 ~:Page 223
RayCheon AiKlaft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
d. Note the position of the three screws against the scale on the FDU elongated screw holes.
e. Remove the three screws and washers
f. Remove the FDU from the airplane.
FLUX DETECTOR UNIT (FDU-3000) INSTALLATION
NOTE
The two FDU-3000 Flux Detector Units are located in the horizontal stabilizer of the airplane (Ref.Figure 203).
I CAUTION 1CAUTION
If any Flux Detector Unit mounting hardware is replaced, ensure that the new hardware is made of
nonmagnetic material.
a. Position the FDU on the mounting bracket. Make sure the elongated screw hole with scales is placed as
illustrated in the FDU location figure.
b. Secure the FDU to the mounting bracket using the screws and washers. Make sure the position of the screws
in the elongated holes is the same as noted in the FLUX DETECTOR UNIT (FDU-3000) REMOVAL procedure.
c. Remove the protective caps from the connectors. Connect the electrical connector to the FDU. Remove the
tags.
NOTE
If the FDU is replaced, the ATTITUDE HEADING SYSTEM AND STANDBY COMPASS SWING
procedure must be performed to provide the External Compensation Unit with system data for
storage.
d. If required, perform the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST procedure.
e. Perform the FLUX DETECTOR UNIT (FDU-3000) ADJUSTMENTTTEST procedure.
f. Install the panel covering the flux detector.
FLUX DETECTOR UNIT (FDU-3000) ADJUSTMENT/TEST
a. Apply electrical powertotheairplane.
I CAUTION ICAUTION
Whenever a FDU is replaced, the FDU COMPENSA TION MODE procedure shall be performed to
ensure proper operation of the Attitude Heading System.
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MAINTENANCE MANUAL SUPPLEMENT
NOTE
Perform Step b. if the FDU was replaced. Perform Step c. if the original FDU was re-installed in the
airplane.
b. Perform the FDU COMPENSATION MODE procedure. (Ref. Rockwell Collins, Inc. AHS-3000 Attitude HeadingReference System Installation Manual 523-0780184.)
c. Perform the TESTING AND TROUBLESHOOTING procedure for the AHC 1 AHCP (ECU 1 AND ECU 2)system. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics
System.)
d. Remove electrical power from the airplane.
34-20-00 225
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ooBO
iO
3
II FLUX DETECTORUNIT (FDU-~000)
J/DETAIL A
034758AR
Flux Detector Unit (FDU-3000) Location
Figure 203
Nov 14/03Page 226 34-20-00
RBytheOl Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) I DESCRIPTION AND OPERATION
The GH-3100 Electronic Standby Instrument System (ESIS) provides a visual display of attitude (pitch and roll) and
slip/skid information computed from an internal three-axis inertial sensor cluster. Air Data information for bare
corrected altitude, air speed and vertical speed is provided by the pitot and static inputs. The Electronic StandbyInstrument System (ESIS) comprises of a GH-3100 Electronic Standby Display, a DCM-3000 Detachable
Configuration Module and a MAG-3000A Magnetometer.
The GH-3100 Electronic Standby Display is installed in the instrument panel. It is a self-contained solid state
instrument requiring pitot and static pressure and the supply of input power to provide attitude, slip/skid and air datainformation. Information is displayed on a color Active Matrix Liquid Crystal Display (AMLCD). A bezel mounted lightsensor provides automatic display dimming capability, with manual offset control achieved through the menu mode.
The DCM-3100 Detachable Configuration Module is a solid state device intended for installation on the GH-3100Electronic Standby Display’s J2 connector.
NOTE
If the GH-3100 Electronic Standby Display is removed for maintenance, the DCM-3100 remainswith the aircraft via a chain that is attached to the GH-3100 airplane wiring harness.
The MAG-3000A Magnetometer is installed in the tail cone at STA 471.234. The Magnetometer uses a three axis
magnetic sensor that senses magnetic fields and converts these signals into a digital format that is then transmittedto the Electronic Standby Display attitude indicator. The signal is then used with the pitch and roll attitude of theElectronic Standby Display to compute the magnetic heading of the aircraft.
The standby instrument battery bus powers the standby instrument system. During normal operation, the No. 3 dualfed bus supplies power to the standby instrument battery bus through the BFGoodrich PS-835D Standby Instrument
Battery. In the event that aircraft power fails, the PS-835D takes over the duties of supplying DC power to the
standby instrument battery bus.
34-25-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS)- MAINTENANCE PRACTICES
ELECTRONIC STANDBY FLIGHT DISPLA Y (GH-3100) REMOVAL
NOTE
The standby flight display is installed on the flight instrument panel (Ref. Figure 201).
NOTE
If the GH-3100 Electronic Standby Display is removed for maintenance, the DCM-3100 remains
with the aircraft via a chain that is attached to the GH-3100 airplane wiring harness.
a. Remove electrical power from the airplane.
b. Remove the Electronic Standby Display by loosening the two larger screws. Loosen until the Electronic StandbyDisplay can be pulled out from the mounting clamp.
c. Identify, tag and disconnect the electrical connector from the display and DCM-3100 configuration module.
Install protective caps on all connectors.
d. Identify, tag and disconnect the pitot and static connectors from the display. Install protective caps on all
connectors.
e. Remove the Electronic Standby Display.
ELECTRONIC STANDBY FLIGHT DISPLA Y (GH-3 1 00) INSTALLA TION
NOTE
The standby flight display is installed on the flight instrument panel (Ref. Figure 201).
a. Remove the protective caps from the connectors.
b. Remove the protective caps from the electrical connectors. Connect the electrical connectors to the display and
DCM-3100 configuration module. Remove the tags.
c. Remove the protective caps from the pitot and static connectors. Connect the pitot and static connectors to the
display. Remove the tags.
d. Position the Electronic Standby Display on the mounting clamp.
e. Tighten the two larger screws until the Electronic Standby Display is secure.
f. Perform the PITOT SYSTEM PRESSURE TEST and STATIC SYSTEM LEAK TEST procedures in Chapter 34-
00-00 of the Super King Air 200 Series Maintenance Manual.
g. Perform the ELECTRONIC STANDBY INSTRUMENT FLIGHT DISPLAY (GH-3100) ADJUSTMENTTTEST
procedure.
34-25-00 Nov 14/03Page 201
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
MAGNETOMETER (MAG-3000A) REMOVAL
NOTE
The magnetometer is located in the tail cone section under the rudder torque tube (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Open the panels on the sides of the tail cone.
c. Remove the screws and washers securing the magnetometer to the mounting bracket.
d. Identify, tag and disconnect the electrical connectors from the magnetometer. Install protective caps on all
connectors.
e. Removethe magnetometer.
f. Install protective covers on all connectors.
MAGNETOMETER (MAG-3000A) INSTALLATION
NOTE
The magnetometer is located in the tail cone section under the rudder torque tube (Ref. Figure 202).
a. Remove the protective covers from all connectors.
b. Remove the protective caps from the connectors. Connect the electrical connectors to the magnetometer.Remove the tags.
c. Position the magnetometer on the mounting bracket and secure with the washers and screws.
d. If the magnetometer was replaced, perform the AHRS AND STANDBY COMPASS SWING procedure in
Chapter 34-20-00.
e. Perform MAGNETOMETER (MAG-3000A) ADJUSTMENTTTEST procedure.
f. Close the panels on the sides of the tail cone.
MAGNETOMETER ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the POST INSTALLATION CHECKS (REMOVE AND REPLACE) CHECKOUT procedure for the
Magnetometer. (Ref Goodrich Avionics Systems, Inc. Installation and Operation Manual GH-3100, 501-1860-
0´•)
c. Remove electrical power from the airplane.
Nov 34-25-00
igal(HfeoN Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ooOaO
MFlGNETOMETER (MAG-3000A)
MOUNTINGBRACKET
DETAIL A ee34Bo34757nn
Magnetometer (MAG´•3000A) Location
Figure 202
34-25-00 Nov 14/03Page 205
Ral~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) BATTERY(PS835D) PREFLIGHT
CHECK
NOTE
Preflight check is optional for this aircraft because it has remote test capability. The PS835D
standby instrument system battety is located in the right nose avionics bay (Ref. Figure 203).
a. Remove the right avionics compartment door.
b. Perform the PRE-FLIGHT CHECK procedure for the PS835 battery. (Ref. BFGoodrich Aerospace Service
Letter SL80J or subsequent.)
c. Install the right avionics compartment door.
ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) BA TTERY (PS835D) PERIODIC
CHECK
NOTE
The Electronic Standby Instrument System (ESIS) Battery periodic 3 to 6 month check is required.The PS835D standby instrument system battery is located in the right nose avionics bay (Ref.Figure 203).
a. Remove the right avionics compartment door.
b. Perform the PERIODIC 3 TO 6 MONTH CHECK procedure for the PSS35D battery. (Ref. BFGoodrich
Aerospace Service Letter SL-80J or subsequent.)
c. Install the right avionics compartment door.
ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS) BA TTERY (PS835D) CAPACITY
TEST
NOTE
The Electronic Standby Instrument System (ESIS) Battery Annual Capacity Testing check is
required. The PS835D standby instrument system battery is located in the right nose avionics bay(Ref. Figure 203).
a. Remove the right avionics compartment door.
b. Perform the CAPACITY TESTING procedure for the PS835 battery. (Ref. BFGoodrich Aerospace Service Letter
SL-80J or subsequent.)
c. Install the right avionics compartment door.
Nov 14/03Page 206 34-25-00
Ray~heMI nirtraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Electronic Standby Instrument System (ESIS) Battery (PS835D) Location
Figure 203
34-25-00 Nov 14/03Page 207
RayBeon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
VOR/ILS NAVIGATION SYSTEM DESCRIPTION AND OPERATION
The NAV-4000 hosts the VOR/ILS (VIR-4000) and the ADF (ADF-4000) function. The VIR-4000 NavigationReceiver is a fully integrated VOR/LOC, Glideslope, Marker Beacon and ADF Receiver. The unit operates with
Radio Tuning Unit (RTU), antennas and Adaptive Flight Displays to depict the navigation situation. Standard VOR/
LOC and Marker Beacon audio outputs are provided to the Audio Integrating System.
34-30-00 N,V’~Pagel
Raytheon AiKraft companySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
VORnLS NAVIGATION SYSTEM MAINTENANCE PRACTICES
NAVIGATION TRANSCNVER (NAV-4000/NAV-4500) REMOVAL
NOTE
The two NAV-4000/NAV-4500 Series Navigation Transceivers are located in the right middle nose
avionics racks (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the right avionics compartment door.
c. Perform the RACK MOUNTED LRU REMOVAL procedure. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
NA VIGA TION TRANSCEIVER (NA V-4000/NA V-4500) INSTALLA TION
NOTE
The two NAV-4000/NAV-4500 Series Navigation Transceivers are located in the right middle nose
avionics racks (Ref. Figure 201).
a. Perform the RACK MOUNTED LRU INSTALLATION procedure. (Ref. Rockwell Collins, Inc. System Manual
(523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the NAVIGATION TRANSCEIVER (NAV-4000/NAV-4500) ADJUSTMENTTTEST procedure.
c. Install the right avionics compartment door.
NA VIGA TION TRANSCEIVER (NA V-4000/NA V-4500) ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the NAV1/NAV2 system. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
34-30-00 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
RBl~hMYII nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
NA VANTENNA REMOVAL
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in the Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
NA V ANTENNA INSTALLA TION
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in the Super
King Air 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform the NAVIGATION TRANSCEIVER (NAV-4000) ADJUSTMENTTTEST procedure.
34-30-00 203
RaY(YheOn Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
WEATHER RADAR SYSTEM DESCRIPTION AND OPERATION
The RTA-852 Weather Radar receiver/transmitter aids the pilot in the detection and avoidance of areas of
precipitation and precipitation related turbulence in and around thunderstorms. The RTA-852 Weather Radar
receiver/transmitter is a solid state X-Band radar system that shows in color, precipitation related targets in up to a
250 nautical mile range. The RTA-852 assembly features one-piece construction combining the receiver,
transmitter, and antenna into a single unit. The receiver/transmitter/antenna assembly is located in the nose radome
of the airplane.
The Weather Radar System includes the Test Mode, Standby (STBY) Mode, Weather (WX) Mode, Map (MAP)Mode, Sector (SEC) Scan Mode, antenna stabilization (STAB), receiver gain, auto tilt, weather plus turbulence
(WX+T) and turbulence (TURB) only functions. Weather Radar targets and mode information are available for
display on the Primary Flight Display (PFD) and the Multi Function Display (MFD). Detectable weather appears in
one of four colors: green, yellow, red, or magenta indicating different intensities of precipitation.
Control of the radar is via a combination of switches in the Display Control Panel (DCP) and the Adaptive FlightDisplay (AFD) mounted line select keys. The DCP provides the radar button used to activate the radar menu on the
display. The menu allows the pilots to select modes, gain, and stabilization.
A detailed description and operation of the RTA-852 Weather Radar/ReceiverTTransmitter is located in the Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.
34-40-00 NovPalekb:
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
The area within the scan are of an operating Weather Radar System can be a hazardous area.
The Collins RTA-852 has a hazardous scan are of about two feet; however, a fifteen foot are
should be flagged off before operating. DO NOT operate in any mode except STBY or TEST
when the antenna might scan over personnel within that range. Refer to FAA AdvisoryCircular 20-688 on the radiation hazards associated with ground operation of airborne radar.
For added safety in modes other than STBY or TEST, operate outside the building with the
The area within the scan are of an operating Weather Radar System can be a hazardous area.
The Collins RTA-852 has a hazardous scan are of about two feet; however, a fifteen foot are
should be flagged off before operating. DO NOT operate in any mode except STBY or TEST
when the antenna might scan over personnel within that range. Refer to FAA AdvisoryCircular 20-688 on the radiation hazards associated with ground operation of airborne radar.
For added safety in modes other than STBY or TEST, operate outside the building with the
antenna tilted up and with SEC SCAN on.
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for weather radar/receiver/antenna. (Ref.Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
The area within the scan are of an operating Weather Radar System can be a hazardous area.
The Collins RTA-852 has a hazardous scan are of about two feet; however, a fifteen toot are
should be flagged off before operating. DO NOT operate in any mode except STBY or TEST
when the antenna might scan over personnel within that range. Refer to FAA AdvisoryCircular 20-688 on the radiation hazards associated with ground operation of airborne radar.
For added safety in modes other than STBY or TEST, operate outside the building with the
antenna tilted up and with SEC SCAN on.
a. Remove electrical power from the airplane.
b. Remove the attaching screws from the radome.
c. Remove the radome.
d. Perform the AIRPLANE LEVELING procedure in Chapter 8-00-00.
e. Place a digital inclinometer (1, Chart 1, 34-00-00) on flat side of hinge mounting face of WXR Antenna Base to
measure Antenna Base Roll (Ref. Figure 202, Position A). Ensure the Antenna Base is 0.1" of aircraft roll axis
measured in Step d..
f. Place the inclinometer on left 8 right side of Antenna Base and below hinge to measure Antenna Base Pitch
(Ref. Figure 202, Positions B and C). Ensure The Left and Right Antenna Base should be 0. i" of aircraft Pitch
axis measured in Step d..
g. Place inclinometer on Antenna Faceplate to measure Pitch (Ref. Figure 202, Position D). Ensure Antenna
Faceplate Pitch is ~t 0.25" of Antenna Base Pitch.
Nov 14/03Page 204 34-40-00
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MAINTENANCE MANUAL SUPPLEMENT
h. Applyelectrical powertotheairplane.
i. Cycle power to the RTA by opening and closing the RADAR circuit breaker.
j. On PFD, ensure operating mode is STBY.
k. Place the inclinometer on the Radar Antenna Faceplate and ensure that the antenna should "Boresight" (O"Pitch 4 O" Roll relative), and PFD 1, PFD 2 and MFD show STBY annunciation at RDR status at R-LSK2 of PFD
1, PFD 2 and MFD.
I. If the Radar Antenna Faceplate is not within limits, repeat the WEATHER RADAR RECEIVERTTRANSMITTER/
ANTENNA (RTA-852) INSTALLATION procedure while adjusting the shimming between the RTA assemblybaseplate and the radome bulkhead, then repeat this procedure in its entirety.
m. Remove electrical power from the radar system.
n. Remove electrical power from the airplane.
o. Installthe radome.
p. Securethe radomewiththescrews.
NOTE
The Attitude Heading System (AHS) must be calibrated if this procedure is being performed due to
the installation or replacement of the radar antenna.
q. If required, perform the ATTITUDE HEADING SYSTEM FUNCTIONAL TEST procedure in Chapter 34-20-00.
34-40-00 Nov 14/03Page 205
Ray~heMI Aircraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
RADIO ALTIMETER SYSTEM DESCRIPTION AND OPERATION
The ALT-4000 Radio Altimeter System provides height above terrain from 2,500 feet to touchdown for use by the
Flight Guidance System and the Electronic Flight Instrument System. The ALT-4000 Transmitter/Receiver (T/R)
applies a signal to the transmit antenna. The transmit antenna beams the signal to the terrain, and the terrain
reflected signal is received by the receive antenna. The return signal is applied to the receiver section of the ALT-
4000 Transmitter/Receiver (T/R). The altitude of the airplane, above the terrain, is proportional to the time requiredfor a transmitted signal to make the round trip to the terrain and back to the radio altimeter system.
Radio Altitude, Radio Altitude based Decision Height (DH, also referred to as RADIO), and Decision Height (DH)alert is displayed on the PFDs. The RADIO or DH value is set via the REFS (Reference) menu on the PFD. The
REFS menu is selected with the REFS button on the DCP. No other pilot control operation is required.
A detailed description and operation of the ALT-4000A Transmitter/Receiver (T/R) is located in the Rockwell Collins,
Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.
34-42-00 N,~Jb:
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
RADIO ALTIMETER SYSTEM MAINTENANCE PRACTICES
RADIO ALTIMETER TRANSMITTER/RECEIVER (ALT-4000) REMOVAL
NOTE
The ALT-4000 Radio Altimeter Transmitter/Receiver is located between FS 299 and FS 312 under
the floorboards (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the floorboards to gain access to the radio altimeter.
c. Perform the RACK MOUNTED LRUs REMOVAL procedure for the ALT-4000 system. (Ref. Rockwell Collins,
Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
RADIO ALTIMETER TRANSMITTER/RECEIVER (ALT-4000) INSTALLATION
NOTE
The ALT-4000 Radio Altimeter Transmitter/Receiver is located between FS 299 and FS 312 under
the floorboards (Ref. Figure 201).
a. Perform the RACK MOUNTED LRUs INSTALLATION procedure for the ALT-4000 system. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform RADIO ALTIMETER TRANSMITTER/RECEIVER (ALT-4000) ADJUSTMENTTTEST procedure.
RADIO ALTIMETER TRANSMITTER/RECEIVER (AL T-4000) ADJUSTMENT/TEST
a. Apply electrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the ALT-4000. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
34-42-00 201
RaYthooo AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
o´•"o RFIDIO F1ITIMETER
A TR~NSMITTER/RECEIVER(ALT-4000)
"i
II-:
1~
DETAIL A BB34B034762FIA
Radio Altimeter TransmitterrReccever (ALT-4000) Location
Figure 201
34142100
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
RADIO ALTIMETER TRANSMITAND RECEIVE ANTENNA REMOVAL
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in the Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
RADIO AL TIMETER TRANSMIT AND RECEIVE ANTENNA INSTALLA TION
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in the SuperKing Air 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform RADIO ALTIMETER TRANSMITTER/RECEIVER (ALT-4000) ADJUSTMENT/TEST procedure.
34-42-00 Nov 14/03Page 203
RayPheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
SKYWATCH TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS I)- DESCRIPTION AND
OPERATION
The Goodrich Sk~watch Traffic Collision Avoidance System (TCAS I) interrogates ATC Transponders in nearbyaircraft and use the computer processing to identify and display potential and predicted collision threats on the Multi
Function Display (MFD). Reference Goodrich Avionics SKY899 Installation Manua1009-11900-001 Rev A (or later)more information.
34-43-00 1
Raytheon AiKraff CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
SKYWATCH TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS I)- MAINTENANCE
PRACTICES
TRANSMITTER/RECEIVER COMPUTER (TRC899) REMOVAL
NOTE
The Skywatch Transmitter/Receiver Computer (TRC899) is located on the bottom side of the toptail equipment shelf (Ref. Figure 201).
a. Remove electrical powerfrom the airplane.
b. Openthetail equipmentbay hatch.
c. Identify, tag and disconnect the electrical connectors from the computer. Install protective caps on all
connectors.
d. Loosen the knurled knobs and remove the computer from the mount.
The Slcslwatch Transmitter/Receiver Computer (TRC899) is located on the bottom side of the toptail equipment shelf (Ref. Figure 201).
a. Position the computer in the mount and secure by tightening the knurled knobs.
b. Remove the protective caps from the connectors. Connect the electrical connectors to the computer. Remove
the tags.
NOTE
When the TCAS Antenna or Computer is installed or reseated, a calibration of the TCAS I systemmust be performed. Reference Goodrich Avionics SKY899 Installation Manual 009-11900-001 Rev
A (or subsequent) for more information.
c. Perform the USING THE TERMINAL DEVICE procedure land select the Calibration Function) in the Goodrich
If the TCAS Computer was replaced, the TRANSMITTER/RECEIVER COMPUTER SETTINGS
procedure must be performed after installation of the computer in the airplane.
d. If required, perform the TRANSMITTER/RECEIVER COMPUTER SETTINGS procedure.
e. Perform the SKYWATCH TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS I) TEST procedure.
f. Close the tail equipment bay hatch.
34-43-00 201
ga14heea Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TRANSMI~ER/RECEIVER COMPUTER SETTINGS
Perform the USING THE TERMINAL DEVICE procedure land select the Calibration Function). Refer to the
Goodrich Avionics SKY899 Installation Manual 009-11900-001 Rev. A or subsequent. The Avionics equipmentsettings that are applicable to the Skywatch TCAS I with Pro Line 21 are shown in the following table.
SKYWATCH TRAFFIC COLLISION A VOIDANCE SYSTEM (TCAS I) TEST
a. Applyelectrical powertotheairplane.
b. While the aircraft is on ground, make sure the TCAS ON/STBY switch on the reversionary switch panel is off.
c. Press the TCAS TEST/ALT on reversionary switch panel to initiate TCAS Test. The TCAS system will performa self-test. The MFD will indicate TCAS TEST. The audio system will annunciate "SKYWATCH SYSTEM TEST
PASS". The TCAS ON/STBY annunciator turns ON during the test.
d. Remove electrical power from the airplane.
Nov 14/03Page 202 34-43-00
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS II)- DESCRIPTION AND
OPERATION
The Collins TCAS-4000 is a TCAS II system designed to protect a volume of airspace around the TCAS Ii-equippedairplane by warning the pilot of the threat of other transponder equipped airplanes penetrating that airspace. The
system interrogates Mode C and Mode S transponders in nearby airplanes and analyzes their replies to identifypotential and predicted collision threats. The system advises the pilot when to climb, descend, or maintain altitude
to avoid passing too close to, or colliding with, the threat airplane. When an intruder airplane is equipped with TCAS
II, the system coordinates avoidance maneuvers with this airplane using the data link capability of the Mode S
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
OVZiO O O
REMOVE SCREWS
V (4 PLACES)
TNC CONNECTOR(4 PLACES)
DETAIL AFL34BD46L89RA
TRE-920 TCAS Antenna Installation
Figure 202
A1 34-43-01 205
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
Q
DMEI~RANSPONDER
ANTENNA
Oa
a
~"P
GASKET
8
j_8
~38
o
8o
COXIAL
CABLE
DETAIL A
DNIEITransponder Antenna Installation
Figure 203
Jan 31/0534-43-01 A1
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ENHANCED GROUND PROXIMITY WARNING SYSTEM DESCRIPTION AND OPERATION
The Enhanced Ground Proximity Warning System (EGPWS) computer is located in the nose right middle shelf.
The EGPWS Configuration Module is installed in the aircraft wiring to store aircraft/EGPWS interface configuration.The Configuration Module is read by the EGPWS during power up. The configuration is programmable via an RS-
232 interface with the EGPWS. The contents of the Configuration Module can be read back via the RS-232 interface.
Refer to the Honeywell MKVIII Enhanced Ground Proximity Warning System rnstallation Design Guide 060-4314-
125.
34-47-00 Nov 14/03Pagel
Raynheon AiKraff CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ENHANCED GROUND PROXIMITY WARNING SYSTEM MAINTENANCE PRACTICES
ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) COMPUTER REMOVAL
NOTE
The Enhanced Ground Proximity Warning System (EGPWS) computer is located in the nose rightmiddle shelf (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the right avionics compartment door.
c. Identify, tag and disconnect the electrical connectors from the computer. Install protective caps on all
connectors.
d. Loosen the knurled knob and remove the computer from the mount.
ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) COMPUTER
INSTALLATION
NOTE
The Enhanced Ground Proximity Warning System (EGPWS) computer is located in the nose rightmiddle shelf (Ref. Figure 201).
a. Position the computer in the mount and secure by tightening the knurled knob.
b. Remove the protective caps from the connectors. Connect the electrical connectors to the computer. Remove
the tags.
c. Perform the ENHANCED GROUND PROXIMITY WARNING SYSTEM CONFIGURATION MODULE
PROGRAMMING procedure.
d. Install the right avionics compartment door.
34-47-00 N’o"V":~:Page 201
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Enhanced Ground Proximity Warning System (EGPWS) Computer Installation
Figure 201
34147-00
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ENHANCED GROUND PROXIMITY WARNING SYSTEM CONNGURA TION MODULE
PROGRAMMING
Perform the CONFIGURATION MODULE PROGRAMMING procedure and the REGIONAL TERRAIN DATABASE
LOADING procedure. (Ref. Honeywell MKVIII EGPWS Installation Design Guide 060-4314-125.) The following
Category IDs are applicable to the EGPWS MKVIII with software Version -010:
NOTE
Apply and remove EGPWS power as directed by the above procedure.
Category Type ID
1 Aircraft/Mode Type 0
2 Air Data Type 255
3 Position Type 0
4 Altitude Callout Menu 0
5 Audio Menu 0
6 Display Type 254
7 Options Select Group #1: 31
8 Radio Altitude Type 254
9 Navigation 254
10 Attitude 255
11 Heading Type 255
12 Windshear select type 0
13 Discrete I/O Type 7
14 Audio Output Level Type 0
15 Undefined Type 0
34-47-00 Nov 14/03Page 203
Raytheon Airrraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
GLOBAL POSITIONING SYSTEM DESCRIPTION AND OPERATION
The GPS-4000A Global Positioning System (GPS) provides accurate worldwide navigation capabilities. The GPS-
4000A Global Positioning System processes GPS satellite signals to provide navigational data outputs. The
baseline GPS System contains one GPS-4000A receiver and one GPS antenna. An optional system containing two
receivers and antennas may be available. The GPS antenna provides the GPS-4000A receiver with the radio
frequency signals from the GPS satellites. The antenna is an active receive only device operating with the L-band
frequency of 1575.42 MHz. The antenna uses right hand circular polarization and is a microscopy patch type design.The Rockwell Collins, Inc. CDU-3000 Control Display Unit (CDU) provides backup display pages for the GPS
navigation data. The GPS receivers process the GPS signals received from the antenna together with inputs from
other airplane sensors to provide position, velocity, and time outputs through the integrated avionics processor’sinput/output data concentrators to the flight management system.
In the baseline equipped airplane configuration equipped with one CDU only, the CDU can display GPS data. With
the optional dual CDU and dual GPS, both CDUs can display GPS data. The CDU INDEX page is used to select
the FMSI GPS Control display page. The FMS1 GPS CONTROL display page is used to select a GPS receiver for
position data and to deselect all usage of GPS data. The FMS1 GPS CONTROL display shows the positiondifference between each GPS receiver position and flight management computers computed position.
The CDU-3000 INDEX page is used to select the GPS1 display page. The GPS1 page displays the followinginformation from the on-side GPS receiver: GPS Date, Latitude, Longitude, Track Angle, Ground Speed, Receiver
Autonomous Integrity Monitoring (RAIM) Limit, Probable Error, GPS Mode and Number of GPS Satellites used.
All GPS position data, date, and time are displayed in green. If GPS data is flagged or missing, the GPS positionData is replaced with yellow dashes.
A detailed description and operation of the GPS-4000A Global Positioning Receiver and CDU-3000 Control DisplayUnit (CDU) is located in the Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21
Avionics System.
34-52-00
RBYtheon nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
GLOBAL POSITIONING SVSTEM MAINTENANCE PRACTICES
GLOBAL POSITIONING SYSTEM RECEIVER (GPS-4000A) REMOVAL
NOTE
The GPS-4000A Global Positioning System Receiver(s) is located in the right middle nose avionics
rack (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the right avionics compartment door.
c. Perform the RACK MOUNTED LRUs REMOVAL procedures for the GPS-4000A system. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
GLOBAL POSITIONING SYSTEM RECNVER (GPS-4000A) INSTALLATION
NOTE
The GPS-4000A Global Positioning System Receiver(s) is located in the right middle nose avionics
rack (Ref. Figure 201).
a. Perform the RACK MOUNTED LRUs INSTALLATION procedures for the GPS-4000A system. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform GLOBAL POSITIONING SYSTEM ADJUSTMENT/TEST procedure.
c. Install the right avionics compartment door.
GLOBAL POSITIONING SYSTEM ADJUSTMENT/TEST
a. Apply electrical powerto the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the GPS-4000A. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
34-52-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Global Positioning System Receiver (GPS-4000A) Location
Figure 201
Nov 14/03Page 202 34-52-00
Ray~eon Aircraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
GLOBAL POSITIONING SYSTEM ANTENNA (GPS-ANT) REMOVAL
NOTE
The GPS-ANT Global Positioning System Antenna No. 1 is located at FS 148.90 to 158.00 and the
optional GPS ANT No. 2 is located at FS 168.75 to 179.53.
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in Super King Air
200 Series Maintenance Manual, Chapter 23-00-00.
GLOBAL POSITIONING SYSTEM ANTENNA (GPS-ANT) INSTALLATION
NOTE
The GPS-ANT Global Positioning System Antenna No. 1 is located at FS 148.90 to 158.00 and the
optional GPS ANT No. 2 is located at FS 168.75 to 179.53.
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform GLOBAL POSITIONING SYSTEM ADJUSTMENTTTEST procedure.
34-52-00 NP~y9:42m033Page 203
Raythi?on AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DISTANCE MEASURING EQUIPMENT DESCRIPTION AND OPERATION
The DME-4000 is a three-channel unit designed to provide position navigation information. It measures line of sightdistance between the airplane on which it is mounted and the selected DME ground station, additionally decodingthe station identifier and calculating the rate of closure and time to reach the selected station. The DME operateson 252 channel assignments, each 1 MHz wide, in a range of 962 to 1213 MHz; each channel having an air to groundfrequency assignment in the range from 1025 to 1 150 MHz and a ground to air frequency which is either in the rangeof 962 to 1024 MHz or 1151 to 1213 MHz. Most DME channel assignments are paired with VOR and ILS facilities
and are selected by inputting the associated VOR and ILS frequency to the DME.
34-54-00 NDV~:Page 1
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
The DME-4000 Distance Measuring Equipment Transceiver is located in the right lower nose
avionics rack (Ref. Figure 201).
a. Perform the RACK MOUNTED LRUs INSTALLATION procedures for the DME-4000. (Ref. Rockwell Collins,Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform DISTANCE MEASURING EQUIPMENT TRANSCEIVER (DME-4000) ADJUSTMENTTTEST
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform DISTANCE MEASURING EQUIPMENT TRANSCEIVER (DME-4000) ADJUSTMENT/TEST
procedure.
34-54-00 Nov 14/03Page 203
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIR TRAFFIC CONTROL RADAR BEACON SYSTEM DESCRIPTION AND OPERATION
The TDR 94/94D ATC Radar Transponder System is a solid state radar beacon system consisting of transponders(TDR-94/94D), Control Display Units (CDU) and L-band antenna(s). The system allows ATC controllers to locate
and quickly identify individual airplanes on the ATC ground controller’s plan position indicator within the control area.
The system is capable of interrogating and receiving replies up to a line of sight range of approximately 200 nautical
miles.
The ATC system is activated as soon as power is applied and flight management system is operational. However,
on the ground the transponder can only receive, irrespective of the position of the ATC switch on the reversionarypanel. The transponders on this airplane operate in mode-A, mode-C, and mode-S. Mode-A gives airplaneidentification data in response to beacon radar interrogations. Mode-C responds with airplane altitude data. Mode-
S provides identification that adds a datalink to provide better communications between air and ground, and with
airborne airplanes within range. In addition, the TDR-94/94D can receive and send datalink messages that are
required for ATC automation. The added datalink capability allows the transponder to perform additional air traffic
control and airplane separation assurance functions.
With mode-S, each airplane is assigned a unique identification code. This code allows automatic and uniqueinterrogation and display of specific airplanes. The airplane identification is assigned at installation and is based on
the tail number. The altitude information for mode-C is provided by the air data computer. Altitude data is suppliedto the transponders through the IAPS.
A detailed description and operation of the TDR-94/94D ATC Radar Transponder is located in the Rockwell Collins,Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.
34-55-00
RayNheon Airuaft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
AIR TRAFFIC CONTROL RADAR BEACON SYSTEM MAINTENANCE PRACTICES
ATC RADAR TRANSPONDER (TDR-94/94D) REMOVAL
I WARNING)WARNING
During removallinstallation of ATC Radar Transponder, support unit with hand to avoid
injury or damage to the connectors.
NOTE
The TDR-94/94D ATC Radar Transponder(s) is located on the bottom side of the top tail equipmentshelf (Ref. Figure 201).
a. Remove electrical powerfrom the airplane.
b. Openthetail equipmentbay hatch.
c. Perform the RACK MOUNTED LRUs REMOVAL procedures for the TDR-94/94D. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
ATC RADAR TRANSPONDER (TDR-94/94D) INSTALLATION
I WARNING
During removallinstallation of ATC Radar Transponder, support unit with hand to avoid
injury or damage to the connectors.
NOTE
The TDR-94/94D ATC Radar Transponder(s) is located on the bottom side of the top tail equipmentshelf (Ref. Figure 201).
a. Perform the RACK MOUNTED LRUs INSTALLATION procedures for the TDR-94/94D. (Ref. Rockwell Collins,Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform ATC RADAR TRANSPONDER (TDR-94/94D) ADJUSTMENTTTEST procedure.
c. Closethetail equipmentbay hatch.
34-55-00 201
Raythellll nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
o´•´•o"
FlTC RADAR TRANSPONDER(TDR-94/94D) NO. 1
COCKPITVOICERECORDER
i\i i
I I >I
FlTC RADAR TRANSPONDER(TDR-94/94D) NO. 2
SKYWATCH TRANSMITTER/RECEIVERCOMPUTER (TRC899)
DETAIL A
88348034753AA
ATC Radar Transponder (TDR-94/94D) Installation
Figure 201
Nov 34-55-00
RaytheMI nircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
b. Perform the TESTING AND TROUBLESHOOTING procedure for the TDR-94/94D. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
ATC RADAR TRANSPONDER ANTENNA REMOVAL
a. Remove electrical power from the airplane.
b. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL procedure in Super King Air
200 Series Maintenance Manual, Chapter 23-00-00.
ATC RADAR TRANSPONDER ANTENNA INSTALLATION
a. Perform the COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION procedure in Super KingAir 200 Series Maintenance Manual, Chapter 23-00-00.
b. Perform ATC RADAR TRANSPONDER (TDR-94/94D) ADJUSTMENT/TEST procedure.
34-55-00
Ray4heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DATA BASE UNIT DESCRIPTION AND OPERATION
The DBU-4100 is a data loader with a 3.5-inch high-density disk drive used primarily to load monthly database
updates to the FMC. It is also used to download maintenance data from the maintenance diagnostic computer. The
DBU is located in the pedestal.
34-56-00 Nov 14/03Page 1
RBytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
DATA BASE UNIT MAINTENANCE PRACTICES
DA TA BASE UNIT (DBU-4 1 00) REMOVAL
NOTE
The DBU-4100 Data Base Unit is located in the pedestal (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Perform the PANEL MOUNTED UNITS (DZUS) REMOVAL procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
DA TA BASE UNIT (DBU-$ 1 00) INSTALLA TION
NOTE
The DBU-4100 Data Base Unit is located in the pedestal (Ref. Figure 201).
a. Perform the PANEL MOUNTED UNITS (DZUS) INSTALLATION procedure. (Ref. Rockwell Collins, (nc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the DATA BASE UNIT (DBU-4100) ADJUSTMENTTTEST procedure.
DA TA BASE UNIT (DBU-$ 1 00) ADJUSTMENT/TEST
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the DBU-4100. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
UPDATING SYSTEM INFORMATION USING THE DATA BASE UNIT (DBU-4 100)
NOTE
The Data Base Unit is used to update information on VHF navaid and airport information, etc.
NOTE
The Personal Computer Data Loading System (5, Chart 1,34-00-00) may be used in place of the
Data Base Unit.
a. Apply electrical power to the airplane.
b. Perform the DATA BASE UPDATE PROCEDURE. (Ref. Rockwell Collins, Inc. System Manual (523-0790063)for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
34-56-00
Rayl~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
e~ ~-e
a-I ~eCONTROL a-I ~-e
DISPLAY UNIT a a OPTIONAL CN0.2)(CDU-3000) CONTROL DISPLAY
a aUNIT LOCATION
a-i ~a
CONNECTORFOR TEST
EQUIPMENTl7ND LF)PTOP
COMPUTER
O@Oo~ooooo (ON SIDEOF PEDESTAL)
s@RUDDERBOOST
’S jmnosETCABI 1000
rrs. FBli
RATE INaevrr wrc~ ~scarm
or c
WARNINGa-PRESSIRI~ CI~IH I I DATA BASE UNITBEFORE LIY(OIM (DBU-41 00)
88348034749F1FI
Data Base Unit (DBU-41 00) Installation
Figure 201
Nov 14/03Page 202 34-56-00
Rayt~on AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
FLIGHT MANAGEMENT SYSTEM DESCRIPTION AND OPERATION
The Rockwell Collins, Inc. FMS-3000 Flight Management System (FMS) provides cockpit management functions.
Cockpit management functions include NAV sensor control, radio tuning, and MFD control menus. FlightManagement functions include lateral flight plan point to point navigation (using multiple NAV sensors), vertical
navigation (VNAV), flight parameter computations and lateral/vertical steering outputs to the flight guidancecomputer. The FMS consists of FMC-3000 No. 1 Flight Management Computer, optional FMC-3000 No. 2 FlightManagement Computer (FMC), CDU-3000 No. 1 Control Display Unit and optional CDU No. 2 Control Display Unit
(CDU).
The FMC-3000 is located in the IAPS assembly. The CDU-3000 has an LED display with twelve line select keys,six on each side of the display. There is an alphanumeric keypad and function keys below the CDU display. In
addition to the control display, the CDU functions include stand-alone control for the radios and back-up display of
GPS data. Data entry on the CDU is made via the scratchpad. Alphanumeric data is entered into the scratchpadand then transferred to the appropriate location via the line select keys.
A detailed description and operation of the FMS-3000 Flight Management System and CDU is located in the
Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.
34-60-00
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
FLIGHT MANAGEMENT SYSTEM MAINTENANCE PRACTICES
FLIGHT MANAGEMENT COMPUTER (FMC-3000) REMOVAL
NOTE
The No. 1 and optional No. 2 FMC are located in the IAPS Card Cage (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Perform the ICC-3000 IAPS CARD CAGE MODULES REMOVAL procedures. (Ref. Rockwell Collins, Inc.
System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
If the Flight Management Computer was replaced, perform Step b., otherwise proceed to Step c..
b. Perform the DATA BASE UPDATE PROCEDURE. (Ref. Rockwell Collins, Inc. System Manual (523-0790063)for the King Air Pro Line 21 Avionics System.)
c. Perform the TESTING AND TROUBLESHOOTING procedure for the FMC-3000 1/FMC-3000 2. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
d. Remove electrical powerfrom the airplane.
34-60-00
Ray2heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
5
5
a000~ O
AB DETAIL A
i. 120-3001
2. PWR-3000 NO. 1
3. FGC-3000 NO. 1
4. CSU-9100 NO. 1 DCM9100 NO. 1
5. FMC-3000 NO. 1
6. 100-3100 NO. 1
7. MDC-3110
3. PWR-3000 NO. 2
9. FGC-3000 NO. 2
10. CSUB100 NO. 2 DOM-3100 NO.2
11. FMC-3000 NO. 2
12. 100-3001 NO. 2
7
10
12
Q
DETAIL B88228
034744AP~.AI
Flight Management Computer (FMC-3000) Location
Figure 201
Nov 14/03Page 202 34-60-00
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CONTROL DISPLA Y UNIT (CDU-3000) REMOVAL
NOTE
The No. 1 and optional No. 2 CDUs are located in the cockpit pedestal (Ref. Figure 202).
a. Remove electrical power from the airplane.
b. Perform the PANEL MOUNTED UNITS (DZUS) REMOVAL procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
CONTROL DISPLA Y UNIT (CDU-3000) INSTALLATION
NOTE
The No. 1 and optional No. 2 CDUs are located in the cockpit pedestal (Ref. Figure 202).
a. Perform the PANEL MOUNTED UNITS (DZUS) INSTALLATION procedure. (Ref. Rockwell Collins, Inc. SystemManual (523-0790063) for the King Air Pro Line 21 Avionics System.)
b. Perform the CONTROL DISPLAY UNIT (CDU-3000) ADJUSTMENTTTEST procedure.
CONTROL DISPLA Y UNIT (CDU-3000) ADJUSTMENT/TEST
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the CDU-3000 1/CDU-3000 2. (Ref. Rockwell
Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics System.)
c. Remove electrical power from the airplane.
34-60-00 203
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
a-i t-a
a
CONTROL a-i ~-aDISPLAY UNIT a OPTIONAL (N0.2)
CCDU-3000)a_I I-a CONTROL DISPLAY
UNIT LOCATIONa
CONNECTORDO O DI~ ~3 Iii FOR TEST
O O ~3 00O B EQUIPMENTAND LAPTOP
COMPUTER(ON SIDE
OF PEDESTAL)
s@RUDOER
´•s s
sHEsnseTCABIN 1000
~R; rm a~asE
RATEarrr~r WIIE RCOIW
too as
oc ~8CPBIH I I ~DFITA BASE UNIT
aFaR Lr*mlHi (DBU-41 00)
88348034749FIF1
Control Display Unit (CDU-3000) Location
Figure 202
Page 204Nov14/03 34-60-00
CHAPTER
ELECTRICAL PANELS
AND MULTIPURPOSE
PARTS
RBYthWWI Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 39 ELECTRICAL PANELS AND MULTIPURPOSE PARTS
TABLE OF CONTENTS
SUBJECT PAGE
39-10-00
Instrumentand Control Panels- Description and Operation .1
Instrumentand Control Panels-Maintenance Practices ..201
Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 39 ELECTRIC PANELS, PARTS AND INSTRUMENTS
LIST OF EFFECTIVE PAGES
CH-3E-SU PAGE DATE
39-LOEP 1 Nov 14/03
39-CONTENTS 1 Nov 14/03
39-1 0-00 1 Nov 14/03
201 thru 203 Nov 14/03
39-LOEP Nov 14/03Pagel
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INSTRUMENT AND CONTROL PANELS DESCRIPTION AND OPERATION
Airplane system performance and total airplane system control is achieved though the use of the Audio Control
Panels (ACP), Adaptive Flight Displays (AFD), Display Control Panel (DCP), Electronic Standby Instrument System(ESIS) Display, Radio Tuning Unit (RTU) and Reversionary Panel. These instrument and control panels are located
in the flight compartment.
39-10-00 NovP:g~b:
RayHleon nireraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INSTRUMENT AND CONTROL PANELS MAINTENANCE PRACTICES
NOTE
This chapter contains information unique to the Pro Line 21 system. Referto the Super King Air 200
Series Maintenance Manual for universal information for the airplane.
FLIGHT INSTRUMENT PANEL
The Pro Line 21 System has components on the flight instrument panel. The flight instrument panel componentsconsist of the Audio Control Panels (ACP), Adaptive Flight Displays (AFD), Display Control Panel (DCP), Electronic
Standby Instrument System (ESIS) Display, Radio Tuning Unit (RTU) and Reversionary Panel.
REMOVAL AND INSTALLATION OF FLIGHT INSTRUMENT PANEL COMPONENTS
Refer to Chapter 23-10-00 for procedures for removal and installation of the Radio Tuning Unit (RTU).
Refer to Chapter 23-50-00 for procedures for removal and installation of the Audio Control Panels (ACP).
Refer to Chapter 31-60-00 for procedures for removal and installation of the Adaptive Flight Displays (AFD).
Refer to Chapter 31-60-00 for procedures for removal and installation of the Display Control Panel (DCP).
Refer to Chapter 34-25-00 for procedures for removal and installation of the Electronic Standby Instrument System(ESIS) Display.
Refer to Chapter 39-10-00 for procedures for removal and installation of the Reversionary Panel.
REVERSIONARY PANEL COMPONENT REMOVAL
a. Remove electrical power from the airplane.
I cnu~loFI 1CAUTION
When performing maintenance around panel, take precautions not to scratch or damage the panelsas they cannot always be repaired.
b. Remove the screws securing the panel overlay to the flight instrument panel section and carefully remove it from
the flight instrument panel (Ref. Figure 201).
c. Identify, tag and disconnect all plumbing and/or electrical connectors from the panel components.
d. Perform the ADAPTIVE FLIGHT DISPLAYS (ADF-3010) REMOVAL procedure in Chapter 31-60-00 and
remove the Multi Function Display to gain access to the rear fastener of the component.
e. Remove the jam nut or fasteners securing the components to the front of the panel and remove the componentsfrom the backside of the panel.
39-10-00
Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
REVERSIONARY PANEL COMPONENT INSTALLATION
rCAUTION ICAUTION
When performing maintenance around panel, take precautions not to scratch or damage the panelsas they cannot always be repaired.
a. Position the components in the flight instrument panel and secure with its jam nut or fasteners (Ref. Figure 201).
b. Connect all plumbing and/or electrical connections.
c. Perform the ADAPTIVE FLIGHT DISPLAYS (ADF-3010) INSTALLATION procedure in Chapter 31-60-00.
d. Align the panel overlay with the flight instrument panel structure and secure with attaching screws.
A VIONICS INSTRUMENT PANEL
NOTE
The avionics instrument panel was removed by installation of the Pro Line 21 System.
ENGINE INSTRUMENTS
NOTE
The engine instruments on the flight instrument panel were removed by installation of the Pro Line
21 System.
Nov 14/03Page 202 39-1 0-00
gelllheee AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
CHAPTER 77 ENGINE INDICATING
LIST OF EFFECTIVE PAGES
CH-SE-SU PAGE DATE
77-LOEP 1 Nov 14/03
77-CONTENTS 1 Nov 14/03
77-40-00 1 Nov 14/03
201 thru 206 Nov 14/03
77-LOEP Nov 14/03Pagel
AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INTEGRATED ENGINE INSTRUMENT SYSTEMS DESCRIPTION AND OPERATION
The Engine Indication System (EIS) allows the pilot to monitor the condition of the engine. Some of the information
is primarily displayed in the cockpit on the Multi Function Display (MFD) or Primary Flight Display (PFD) for back up.
The Adaptive Flight Displays (AFDs) engine display format consists of a normal EIS window that displaysInterturbine temperature (ITT) and torque on a shared analog gauge, N1 and Prop speed on another shared analog
gauge and an analog synchroscope scale. Digital displays for the fuel flow, oil pressure and oil temperature are also
displayed within the EIS window. The engine display format can also be displayed in a reduced EIS window, N1speed on individual smaller analog scales, an analog synchroscope and display of other engine parameters on the
same digital only display as the normal EIS window.
Two sources for all engine parameters exist for each engine. One is the Data Concentrator Unit (DCU) and the other
is the Engine Data Concentrator (EDC). The DCU is normally the source of all displayed engine data, and the EDC
is the secondary source of all displayed engine data. The DCU and EDC have identical part numbers. The function
of the unit as a DCU or ECU is determined by external strapping.
77-40-00
Ral~heon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
INTEGRATED ENGINE INSTRUMENT SYSTEMS MAINTENANCE PRACTICES
DATA CONCENTRATOR UNIT(DCU-3001) REMOVAL
NOTE
The two DCU-3001 Data Concentrator Units are located in the left middle nose avionics racks. Each
DCU shares a bracket with an Engine Data Concentrator (EDC) (Ref. Figure 201).
a. Remove electrical power from the airplane.
b. Remove the left avionics compartment door.
c. Identify, tag and disconnect the plugs from the connectors on the DCU.
d. Remove the screws and washers securing the DCU and ECU to the bracket and remove the DCU.
DATA CONCENTRATOR UNIT(DCU-3001) INSTALLATION
NOTE
The two DCU-3001 Data Concentrator Units are located in the left middle nose avionics racks. Each
DCU shares a bracket with an Engine Data Concentrator (EDC) (Ref. Figure 201).
a. Install the DCU and EDC on the bracket on the left middle nose avionics shelf and secure with washers and
screws.
b. Connect the plugs to the connectors on the DCU.
c. Perform the DATA CONCENTRATOR UNIT (DCU-3001) ADJUSTMENTTTEST procedure.
d. Install the left avionics compartment door.
DATA CONCENTRATOR UNIT (DCU-3001) ADJUSTMENT/TEST
a. Applyelectrical powertotheairplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the DCU 1 land EDC 1)/DCU 2 (AND EDC 2)
system. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics
System.)
c. Remove electrical power from the airplane.
ENGINE DATA CONCENTRATOR (EDC-3001) REMOVAL
NOTE
The two EDC-3001 Engine Data Concentrators are located in the left middle nose avionics racks.
Each EDC shares a bracket with a Data Concentrator Unit (Ref. Figure 201).
a. Remove electrical power from the airplane.
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Raytheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
b. Remove the left avionics compartment door.
c. Identify, tag and disconnect the plugs from the connectors on the EDC.
d. Remove the screws and washers securing the EDC and DCU to the bracket and remove the EDC.
ENGINE DATA CONCENTRATOR (EDC-3001) INSTALLATION
NOTE
The two EDC-3001 Engine Data Concentrators are located in the left middle nose avionics racks.
Each EDC shares a bracket with a Data Concentrator Unit (Ref. Figure 201).
a. Install the EDC and DCU on the bracket on the left middle nose avionics shelf and secure with washers and
screws.
b. Connect the plugs to the connectors on the EDC.
c. Perform the ENGINE DATA CONCENTRATOR (EDC-3001) ADJUSTMENTTTEST procedure.
d. Install the left avionics compartment door.
ENGINE DA TA CONCENTRA TOR (EDC-3001) ADJUSTMENT/TEST
a. Apply electrical power to the airplane.
b. Perform the TESTING AND TROUBLESHOOTING procedure for the DCU 1 land EDC 1)/DCU 2 (AND EDC 2)
system. (Ref. Rockwell Collins, Inc. System Manual (523-0790063) for the King Air Pro Line 21 Avionics
System.)
c. Remove electrical power from the airplane.
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Ray~heon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
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DETAIL A
ENGINE DATACONCENTRATOR
ENGINE DATA (EDC-3001) NO. 1CONCENTRATOR(EDC-3001) NO. 2
UNIT (DCU-3001) NO. 1
18
a
DETAIL B88778034764FIR
Data Concentrator Unit (DCU-3001) and Engine Data Concentrator (EDC-3001) Location
Figure 201 (Sheet 1 of 2)
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RayCheon Aircraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
7
I;´•´•-ula~ilENGINE DATACONCENTRATOR(EDC-3001)
DATA CONCENTRATORUNIT (DCU-3001)
DETAIL C
BB77B
Data Concentrator Unit (DCU-3001) and Engine Data Concentrator (EDC-3001) Location
Figure 201 (Sheet 2 of 2)
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Raytheon AiKraft CompanySUPER KING AIR 200 SERIES PRO LINE 21
MAINTENANCE MANUAL SUPPLEMENT
ENGINE INDICATION REVERSION INSPECTION
a. Apply electrical powertotheairplane.
b. Wait for the Primary Flight Display (PFD) and Multi Function Display (MFD) to power up (Ref. Figure 202).
c. Verify the Pilot Display switch is set to NORM.
d. Ensure the left and right engine data is displayed on the MFD EIS Window.
e. Set the Pilot Display switch to PFD.
f. The MFD display blanks and the pilot and copilot PFD displays now show the left and right engine data that was
shown on the MFD EIS Window.
g. Set Pilot Display switch to NORM.
h. The MFD displays the engine data in the EIS window. The PFD displays do not show the left and right enginedata
i. Remove electrical power from the airplane.
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Raytheon AiKraft tompanySUPER KING AIR 200 SERIES PRO LINE 21
