MAINTENANCE MANUAL

and
INSTRUCTIONS FOR CONTINUED
AIRWORTHINESS
for
Raisbeck Systems
as installed on

TEXTRON’S BEECHCRAFT
KING AIR & SUPER KING AIR
MODEL AIRCRAFT

Models Raisbeck Systems

 B300/B300C  Quiet Turbofan Propellers
 300/300LW  Ram Air Recovery System
 200/B200/B200GT Series  Enhanced Performance Leading Edges
 100/A100/B100  Composite Exhaust Stack Fairings
 G90XT  Dual Aft Body Strakes
 F90  Fully-Enclosed MLG
 E90  Wing Lockers
 C90/C90A/C90GT/C90GTi  Swept Turbofan Propellers
 65-90/65-A90/B90

Document No. 85-120

Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Log of Revisions
Rev Section Description Date Approved By
AK Various Added inspection, maintenance, and ICA 9/18/19 MJS
requirements for 200 Series Five-Blade Swept
Turbofan Propeller System.
05 Updated inspections to align with Beech.
See DCN AK for details.
AL Title Clarified make and model. 3/3/22 Tim Morgan
Introduction Updated referenced OEM maintenance
documents.
Introduction, Replaced all references to obsolete Hartzell
05, 12, 30, 61 Manuals 181, 182, & 183 with Manual No. 180.
05, 61 Typographical corrections. (ER 20-614)
05 Added Alternate Phase Inspection and Biennial
Inspection requirements, Sections 05-20-00-07,
-08, & -09. (ER 18-508, 21-663)
05 Removed Fully Enclosed MLG Doors RH
lubrication requirement from “Phase 3 or
Detailed 3 Inspections”, Section 05-20-00-03.
(ER 21-632)
12 Added figures that identify locker and latch
types, Sections 12-50-10-20 & 12-50-11-20.
(ER 20-606)
05, 12, 30 Added missing references to Hartzell Manual
No. 486, Sections 05-61-00-00, 05-61-00-21,
12-30-61-20, 30-61-00-05, & 30-61-00-20.
30 Corrected circuit breaker amperage notation,
Section 30-61-40-97, Figure 2. (ER 20-607)
12, 61 Corrected Hartzell Owner’s Manual No. for 200
Series composite propellers, Sections
12-61-42-20, 61-00-42-10, & 61-00-42-20.
(ER 21-630)
61 Added Five-Blade Swept, Section 60-00-40-05.
61 Removed references to nonexistent Figure 1
from Section 61-31-42-20.
61 Corrected Section number from 61-72-20-20 to
61-76-20-20.
61 Corrected propeller restricted range tolerance
from ±50 to +50/-0 RPM, Sections 61-76-20-20
& 61-76-30-20. (ER 20-621)
61 Corrected Power Symmetry and Low Pitch
Torque Check instructions, Section
61-76-42-20. (ER 21-665)
61 Updated Section 61-76-42-20 Figures 3 and 4
to correspond with installation clarifications.
AM 61-76-42-20 Corrected propeller restricted range caution
notes and added caution notes specific to
Collins Pro Line 21 or Pro Line Fusion
equipped aircraft.

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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Introduction
The purpose of this manual is to give the necessary data for the normal maintenance of any Raisbeck
System installed on Beechcraft King Air or Super King Air. Chapter 51 gives data for acceptable
repairs and repair limits for selected Raisbeck Systems components. All data given in Chapter 51 are
approved by the Federal Aviation Administration (FAA), Northwest Mountain Region on December
22, 1992. Service Publication reissues or revisions are not automatically provided to the holder of
this manual.
Information in this document is given as supplemental to the applicable Original Equipment
Manufacturers (OEM) model and/or component specific documents listed below at the revision listed,
or later revision:
King Air Series and Super King Air Series Aircraft Manuals:
Maintenance Manuals (MM)
King Air 90 Series Maintenance Manual, P/N 90-590012-13, Revision D0, Dated December
1, 2019
King Air F90 Series Maintenance Manual, P/N 109-590010-19, Revision B7, Dated May 1,
2014
King Air 100 Series Maintenance Manual, P/N 100-590038-17, Revision A33, Dated February
1, 2017
Super King Air 200 Series Maintenance Manual, P/N 101-590010-19, Revision E1, Dated
November 1, 2019
Super King Air Model 300 and 300LW Maintenance Manual, P/N 101-590097-9, Revision
A38, Dated November 11, 2016
Super King Air B300/B300C Maintenance Manual, P/N 130-590031-11, Revision C3, Dated
October 15, 2020
Component Maintenance Manuals (CMM)
King Air Series Component Maintenance Manual, P/N 101-590097-13, Revision B9, Dated
April 1, 2018
Structural Repair Manuals (SRM)
Structural Inspection and Repair Manual, P/N 98-39006, Revision D2, Dated January 1, 2020

Nextant Aerospace for Model G90XT:

NOTE: G90XT aircraft are C90A aircraft modified per Nextant Aerospace STC
SA01902CH.
Nextant Airplane Flight Manual Supplement, NX0250-AFMS-0101, Revision C, October 22, 2015
Aircraft Maintenance Manual Supplement, NX0250-MMS0-0101, Revision A, December 19, 2015
Instructions for Continued Airworthiness, NX0250-ICA0-0101, Revision A, December 19, 2015
GE Turboprop Engines H80-100/H80-200 H75-100/H75-200 H85-100/H85-200 Maintenance
Manual, Document No. 0983402, Rev 13, Dated Feb. 15, 2017

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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Hartzell Propeller Inc. Turboprop Aluminum Propeller Systems:

Propeller Owner’s Manual and Logbook, Manual No. 149, 61-00-49, Revision 28, June 2021
Propeller Ice Protection System Manual, Manual No. 180, 30-61-80, Revision 36, June 2021

Hartzell Propeller Inc. Turboprop Composite Propeller Systems:

Propeller Owner’s Manual and Logbook, Manual No. 147, Revision 17, September 2020
Propeller Owner’s Manual and Logbook, Manual No. 486, Revision 4, June 2021
Composite Propeller Blade Field Maintenance and Minor Repair Manual, Manual No. 170,
Revision 17, July 2021
Propeller Ice Protection System Manual, Manual No. 180, 30-61-80, Revision 36, June 2021
Goodrich/UTC Aerospace Systems De-Icing and Specialty Systems:
Black Standard Pneumatic De-Icer Installation, Maintenance and Repair Manual, ATA 30-10-31,
Revision Original Issue, 15 Nov/96
Component Maintenance Manual, Brush Assemblies, Electrothermal De-Icing Systems, ATA 30-
60-01, Revised March 24, 2015
Installation and Maintenance Manual for Prop De-Icing Systems, ATA 30-60-02, Revised March
20, 2002
Removal and Installation Manual, Electrothermal Propeller De-Icers, ATA 30-60-07, July 14, 2007
SMR Technologies:
Pneumatic De-Icer Installation, Maintenance Manual, and Instructions for continued Airworthiness
SMR Report No. 97-33-047, February 20, 2019 (Rev. 16)

NOTE: Always use the most current revision of the manuals listed above.

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Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Commercial Parts
Maintenance on Raisbeck Systems involving the replacement of Commercial Parts (as defined in
FAA Advisory Circular No. 21-45) should reference the latest revision of either the Illustrated Parts
Catalog, document 85-119, or the following Supplemental Type Certificate (STC) specific Commercial
Parts Lists (CPL) for accepted parts.
Commercial Parts Lists
Dual Aft Body Strakes:
200/A200/B200 Series, STC SA3591NM, reference CPL document 16BC-3591-090
300 Series, STC SA4733NM, reference CPL document 16BC-4733-090
B300 Series, STC SA5151NM, reference CPL document 16BC-5151-090
Exhaust Stack Fairings:
90 Series, 100 Series, F90, 200/A200/B200 Series, and 300/B300 Series, STC SA3683NM,
reference CPL document 17BC-3683-090
Enhanced Performance Leading Edge:
200/A200/B200 Series, STC SA3831NM, reference CPL document 16BC-3831-090
Nacelle Wing Locker System:
90 Series, STC SA2939NM, reference CPL document 16BC-2939-090
100 Series, STC SA3819NM, reference CPL document 17BC-3819-090
F90, STC SA4132NM, reference CPL document 17BC-4132-090
200/A200/B200 Series, STC SA3857NM, reference CPL document 16BC-3857-090
300 Series, STC SA4734NM, reference CPL document 16BC-4734-090
B300 Series, STC SA5152NM, reference CPL document 16BC-5152-090
Ram Air Recovery System:
200/A200/B200 Series, STC SA3366NM, reference CPL document 16BC-3366-090

NOTICE
Raisbeck Engineering specifically reserves the right to supersede, cancel, and/or declare inactive any
part number, kit, or publication that may be referenced in this manual without prior notice.

WARNING
Use only genuine Raisbeck or Beechcraft approved parts in connection with the maintenance and
repair of Raisbeck Systems.
Do not use the data in this Maintenance Manual for the installation of any Raisbeck System. Specific
FAA-Approved Installation Manuals for Raisbeck Systems are supplied with each kit purchased.

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Instructions for Continued Airworthiness for
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Correspondence
Raisbeck Engineering, Inc.
4411 South Ryan Way
Seattle, WA 98178
Telephone:
Domestic (206) 723-2000
International (800) 537-7277
Facsimile (206) 723-2884

Company website: www.raisbeck.com

Technical Support:
e-mail techsupport@raisbeck.com
AOG (206) 390-8690

Spare Parts:
e-mail spares@raisbeck.com
AOG (206) 390-8690

Organization
This Manual is arranged according to ATA Code by Chapter, Section, System, and Subject.
Example:
12-30-57-20
Chapter 12 Servicing
Section 30 Ice and Rain Protection
System 57 Wings (Enhanced Performance Leading Edges)
Subject 20 Standard Practices (Maintenance Procedures)

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Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Eligibility
KING AIR 90 SERIES AIRCRAFT
The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA4010NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA2623NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA2939NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM.
The Raisbeck/Hartzell Quiet Turbofan Propeller system is approved by the FAA under STC
SA3593NM.
The Raisbeck/Hartzell Swept Turbofan Propeller system is approved by the FAA under STC
SA3593NM.

KING AIR F90 AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA4130NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4944NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA4132NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The Raisbeck/Hartzell Quiet Turbofan Propeller system is approved by the FAA under STC
SA4131NM.

KING AIR 100 SERIES AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA3828NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4952NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA3819NM.`
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The Raisbeck/Hartzell Quiet Turbofan Propeller system is approved by the FAA under STC
SA5661NM.

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SUPER KING AIR 200 SERIES AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA3591NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4175NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA3857NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The Raisbeck/Hartzell Quiet Turbofan Propeller system is approved by the FAA under STC
SA2698NM-S.
The Raisbeck/Hartzell Swept Turbofan Propeller system is approved by the FAA under STC
SA2698NM-S.
The Raisbeck/Hartzell Five-Blade Swept Turbofan Propeller System is approved by the FAA under
STC SA2698NM-S.
The Raisbeck Enhanced Performance Leading Edge system is approved by the FAA under STC
SA3831NM.
The Raisbeck Ram Air Recovery System is approved by the FAA under STC SA3366NM.

SUPER KING AIR B200 SERIES AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA3591NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4175NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA3857NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The Raisbeck/Hartzell Quiet Turbofan Propeller system is approved by the FAA under STC
SA2698NM-S.
The Raisbeck/Hartzell Swept Turbofan Propeller system is approved by the FAA under STC
SA2698NM-S.
The Raisbeck/Hartzell Five-Blade Swept Turbofan Propeller System is approved by the FAA under
STC SA2698NM-S.
The Raisbeck Enhanced Performance Leading Edge system is approved by the FAA under STC
SA3831NM.
The installation of the Raisbeck Enhanced Performance Leading Edge (SA3831NM), Dual Aft Body
Strakes (SA3591NM), Ram Air Recovery Systems (SA3366NM), High Flotation Gear Doors
(SA4175NM), and Hartzell/Beechcraft Turbofan Propeller System in accordance with Raisbeck
Engineering Master Drawing List 99-1500 requires the incorporation of Supplemental Type
Certificates SA4175NM (when equipped with high flotation gear), SA3366NM, SA3831NM, and
SA3591NM is approved by the FAA under STC SA00752SE.

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SUPER KING AIR 300/300LW AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA4733NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4175NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA4734NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The Raisbeck/Hartzell Four-Blade Swept Turbofan Propeller System is approved by the FAA under
STC SA02473SE.
The Raisbeck/Hartzell Five-Blade Swept Turbofan Propeller System is approved by the FAA under
STC SA02559SE.

SUPER KING AIR B300/B300C AIRCRAFT

The Raisbeck Dual Aft Body Strake system is approved by the FAA under STC SA5151NM.
The Raisbeck Fully Enclosed Main Landing Gear Door system is approved by the FAA under STC
SA4175NM.
The Raisbeck Nacelle Wing Locker system is approved by the FAA under STC SA5152NM.
The Raisbeck Exhaust Stack Fairing system is approved by the FAA under STC SA3683NM
The installation of the Raisbeck Dual Aft Body Strake system per (STC) SA5151NM and
Raisbeck/Hartzell Four-Blade Swept Turbofan Propeller system is approved by the FAA under STC
SA02473SE.
The installation of the Raisbeck Dual Aft Body Strake system per (STC) SA5151NM and
Raisbeck/Hartzell Five-blade Swept Turbofan Propeller system is approved by the FAA under STC
SA02559SE.

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Table of Contents
00  Chapter Descriptions ............................................................................................................ 1 
04  Airworthiness Limitations .............................................................................................................. 1 
05  Time Limits/Maintenance Checks .................................................................................................. 1 
11  Placards .......................................................................................................................................... 1 
12  Servicing ......................................................................................................................................... 1 
20  Standard Practices Airframe .......................................................................................................... 1 
30  Ice and Rain Protection .................................................................................................................. 1 
32  Landing Gear .................................................................................................................................. 1 
50  Cargo and Accessory Compartments ............................................................................................. 1 
51  Standard Practices Structures ........................................................................................................ 2 
53  Fuselage ......................................................................................................................................... 2 
54  Nacelles/Pylons .............................................................................................................................. 2 
57  Wings ............................................................................................................................................. 2 
61  Propellers ....................................................................................................................................... 2 
04  Airworthiness Limitations .................................................................................................... 3 
04‐00‐00‐01  Mandatory Modification, Replacement, and Structural Inspection for Airframe Systems ............ 3 
04‐61‐00‐01  Mandatory Modification, Replacement, and Structural Inspection for Propellers ........................ 3 
04‐00‐00‐02  Mandatory Replacement Time, Inspection Intervals, and Procedures for Fuel Tanks ................... 3 
04‐00‐00‐03  Mandatory Replacement Time for EWIS Components ................................................................... 3 
04‐00‐00‐04  Limits of Validity of Engineering Data for Structural Maintenance ............................................... 3 
04‐00‐00‐05  Instructions for Continued Airworthiness ....................................................................................... 3 
05  Time Limit/Maintenance Checks .......................................................................................... 4 
05‐00‐00‐00  Description ..................................................................................................................................... 4 
05‐20‐00‐00  Scheduled Inspection...................................................................................................................... 4 
Daily Checks ........................................................................................................................................................... 5 
Phase Inspections .................................................................................................................................................. 6 
Fusion Inspections ................................................................................................................................................. 7 
HUIP Inspections .................................................................................................................................................... 8 
Alternate Phase Inspections .................................................................................................................................. 9 
Biennial Inspections ............................................................................................................................................... 9 
Daily Checklist ...................................................................................................................................................... 10 
05‐20‐00‐01  Scheduled Inspection Program Phase 1 or Detailed 1 Inspection ................................................ 13 
05‐20‐00‐01  Phase 1 or Detailed 1 Inspection Discrepancy Sheet .................................................................... 20 
05‐20‐00‐02  Scheduled Inspection Program Phase 2 or Detailed 2 Inspection ................................................ 21 
05‐20‐00‐02  Phase 2 or Detailed 2 Inspection Discrepancy Sheet .................................................................... 27 
05‐20‐00‐03  Scheduled Inspection Program Phase 3 or Detailed 3 Inspection ................................................ 28 
05‐20‐00‐03  Phase 3 or Detailed 3 Inspection Discrepancy Sheet .................................................................... 35 
05‐20‐00‐04  Scheduled Inspection Program Phase 4 or Detailed 4 Inspection ................................................ 36 
05‐20‐00‐04  Phase 4 or Detailed 4 Inspection Discrepancy Sheet .................................................................... 42 
05‐20‐00‐05  HUIP Routine Inspection .............................................................................................................. 43 
05‐20‐00‐05  HUIP Routine Inspection Discrepancy Sheet ................................................................................ 47 
05‐20‐00‐06  HUIP Inspection:  Detailed 1, 2, 3, & 4 ......................................................................................... 48 

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05‐20‐00‐06  HUIP Inspection:  Detailed 1, 2, 3, & 4 Discrepancy Sheet ........................................................... 54 
05‐20‐00‐07  Alternate Phase Inspection .......................................................................................................... 55 
05‐20‐00‐08  Biennial:  Interim Inspection ........................................................................................................ 55 
05‐20‐00‐08  Biennial:  Interim Inspection Discrepancy Sheet .......................................................................... 59 
05‐20‐00‐09  Biennial:  Complete Inspection ..................................................................................................... 60 
05‐20‐00‐09  Biennial:  Complete Inspection Discrepancy Sheet ....................................................................... 68 
05‐21‐00‐00  Special Inspection Maintenance Practices ................................................................................... 69 
05‐32‐00‐21  Fully Enclosed MLG Doors Special Inspections ............................................................................. 70 
05‐50‐00‐21  Wing Lockers Special Inspections ................................................................................................. 72 
05‐51‐00‐00  Time Limits/Maintenance Checks Airframe Systems ................................................................... 73 
05‐61‐00‐00  Time Limits/Maintenance Checks ‐ Propellers ............................................................................. 73 
05‐53‐00‐21  Dual Aft Body Strakes Special Inspections ................................................................................... 74 
05‐54‐00‐21  Exhaust Stack Fairings Special Inspections .................................................................................. 75 
05‐57‐00‐21  Enhanced Performance Leading Edges Special Inspections ......................................................... 76 
05‐61‐00‐21  Swept Turbofan Propellers, Five‐Blade Swept Turbofan Propellers, and Quiet Turbofan 
Propellers Special Inspections ...................................................................................................... 77 
05‐72‐00‐21  Ram Air Recovery System Special Inspections .............................................................................. 80 
11  Placards and Markings ........................................................................................................ 82 
11‐00‐00‐00  Description and Operation ........................................................................................................... 82 
11‐00‐00‐10  Interior Placards and Limitation Markings .................................................................................. 86 
11‐00‐00‐11  Exterior Placards and Markings Maintenance Practices ............................................................ 102 
12  Servicing ........................................................................................................................... 106 
12‐00‐00‐00  Description ................................................................................................................................. 106 
12‐00‐00‐20  Maintenance Practices ............................................................................................................... 106 
12‐30‐57‐20  Surface De‐Ice Boot Servicing .................................................................................................... 109 
12‐30‐61‐20  Propeller De‐Ice System Servicing .............................................................................................. 109 
12‐30‐72‐20  Ram Air Recovery System Servicing ........................................................................................... 109 
12‐32‐00‐20  Fully Enclosed High Flotation MLG Door Servicing ..................................................................... 109 
12‐50‐10‐20  Short Skirt Wing Locker Servicing ............................................................................................... 110 
Door Hinges ....................................................................................................................................................... 110 
Bayonet Latches................................................................................................................................................. 110 
Cleaning ............................................................................................................................................................. 110 
12‐50‐11‐20  Long Skirt Wing Locker Servicing ............................................................................................... 112 
Door Hinges ....................................................................................................................................................... 112 
Pin Latches ......................................................................................................................................................... 112 
Cleaning ............................................................................................................................................................. 112 
12‐53‐00‐20  Dual Aft Body Strake Servicing ................................................................................................... 114 
12‐54‐10‐20  Stainless Steel Exhaust Stack Fairing Servicing .......................................................................... 114 
12‐54‐11‐20  Composite Exhaust Stack Fairing Servicing ................................................................................ 114 
12‐57‐00‐20  Enhanced Performance Leading Edge Servicing ........................................................................ 114 
12‐61‐10‐20  Raisbeck/Hartzell Quiet Turbofan Propeller Servicing ............................................................... 114 
12‐61‐11‐20  Raisbeck/Hartzell Swept Turbofan Propeller Servicing .............................................................. 114 
12‐61‐20‐20  Raisbeck/Hartzell Quiet Turbofan Propeller Servicing ............................................................... 114 

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12‐61‐30‐20  Raisbeck/Hartzell Quiet Turbofan Propeller Servicing ............................................................... 114 
12‐61‐40‐20  Raisbeck/Hartzell Quiet Turbofan Propeller Servicing ............................................................... 114 
12‐61‐41‐20  Raisbeck/Hartzell Swept Turbofan Propeller Servicing .............................................................. 114 
12‐61‐42‐20  Raisbeck/Hartzell Five‐Blade Swept Turbofan Propeller Servicing ............................................. 115 
12‐61‐51‐20  Raisbeck/Hartzell Swept Turbofan Propeller Servicing .............................................................. 115 
12‐61‐52‐20  Raisbeck/Hartzell Five‐Blade Swept Turbofan Propeller Servicing ............................................. 115 
20  Standard Practices – Airframe ........................................................................................... 116 
20‐00‐00‐00  Description ................................................................................................................................. 116 
20‐01‐00‐00  Torque Application Information ................................................................................................. 116 
20‐02‐00‐00  Electrostatic Discharge Sensitivity Information ......................................................................... 116 
20‐03‐00‐00  Electrical Bonding Information .................................................................................................. 116 
20‐04‐00‐00  Anti‐static Coating ..................................................................................................................... 116 
20‐05‐00‐00  Fastener Locking Device Information ......................................................................................... 116 
20‐06‐00‐00  Airplane Finish Information ....................................................................................................... 116 
20‐07‐00‐00  Corrosion Control ....................................................................................................................... 116 
30  Ice and Rain Protection ..................................................................................................... 117 
Enhanced Performance Leading Edges .................................................................................................................. 117 
30‐57‐00‐00  Description and Operation ......................................................................................................... 117 
30‐57‐00‐05  Inspection ................................................................................................................................... 117 
30‐57‐00‐10  Troubleshooting ......................................................................................................................... 117 
30‐57‐00‐20  Maintenance Practices ............................................................................................................... 117 
Quiet, Swept, and Five‐Blade Swept Turbofan Propellers...................................................................................... 118 
30‐61‐00‐00  Description and Operation ......................................................................................................... 118 
30‐61‐00‐05  Inspection ................................................................................................................................... 118 
Periodic Inspection ............................................................................................................................................ 118 
Daily Checks ....................................................................................................................................................... 119 
30‐61‐00‐10  Troubleshooting ......................................................................................................................... 119 
30‐61‐00‐20  Maintenance Practices ............................................................................................................... 119 
30‐61‐10‐97  90 Series Quiet Turbofan Propellers De‐Ice Wiring .................................................................... 120 
30‐61‐11‐97  90 Series Swept Turboprop Propellers De‐Ice Wiring ................................................................. 120 
30‐61‐20‐97  F90 Series Quiet Turbofan Propellers De‐Ice Wiring Diagrams .................................................. 133 
30‐61‐30‐97  100 Series Quiet Turbofan Propellers De‐Ice Wiring Diagrams .................................................. 137 
30‐61‐40‐97  200 Series Quiet Turbofan Propellers De‐Ice Wiring Diagrams .................................................. 145 
30‐61‐41‐97  200 Series Swept Turbofan Propellers De‐Ice Wiring Diagrams ................................................ 145 
30‐61‐42‐97  200 Series Five‐Blade Swept Turbofan Propellers De‐Ice Wiring Diagrams ............................... 145 
30‐61‐50‐97  B300/B300C Quiet Turbofan Propellers De‐Ice Wiring Diagrams .............................................. 149 
30‐61‐51‐97  300/300LW, B300/B300C Four‐Blade Swept Turbofan Propellers De‐Ice Wiring Diagrams ...... 149 
30‐61‐52‐97  300/300LW, B300/B300C Five‐Blade Swept Turbofan Propellers De‐Ice Wiring Diagrams ....... 149 
Ram Air Recovery System ...................................................................................................................................... 152 
30‐72‐00‐00  Description and Operation ......................................................................................................... 152 
30‐72‐00‐05  Inspection ................................................................................................................................... 153 
Periodic Inspections ........................................................................................................................................... 153 
Daily Checks ....................................................................................................................................................... 153 
Revision AM xi
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

30‐72‐00‐10  Troubleshooting ......................................................................................................................... 156 
30‐72‐00‐20  Maintenance Practices ............................................................................................................... 157 
Repair/Replacement .......................................................................................................................................... 157 
Functional Test/adjustment .............................................................................................................................. 157 
Bypass Door Adjustment ................................................................................................................................... 157 
Particle Separator Adjustment .......................................................................................................................... 157 
32  Landing Gear ..................................................................................................................... 158 
Fully Enclosed Main Landing Gear Doors ............................................................................................................... 158 
32‐00‐00‐00  Description and Operation ......................................................................................................... 158 
32‐00‐00‐05  Inspection ................................................................................................................................... 158 
Periodic Inspections ........................................................................................................................................... 158 
Daily Checks ....................................................................................................................................................... 158 
32‐00‐00‐10  Troubleshooting ......................................................................................................................... 158 
32‐00‐00‐20  Maintenance Practices ............................................................................................................... 159 
Repair/Replacement .......................................................................................................................................... 159 
Rigging Adjustment 65‐90, 65‐A90, B90, C90, C90A, C90GT, E90 ..................................................................... 159 
Rigging Adjustment 100, A100, B100, F90, 200 Series, B300/B300C ................................................................ 159 
Functional Test 65‐90, 65‐A90, B90, C90, C90A, C90GT, E90 ............................................................................ 160 
Functional Test 100, A100, B100, F90, 200 Series, B300/B300C ....................................................................... 160 
50  Cargo and Accessory Compartments ................................................................................. 161 
Nacelle Wing Lockers ............................................................................................................................................. 161 
50‐00‐00‐00  Description and Operation ......................................................................................................... 161 
50‐00‐00‐05  Inspection ................................................................................................................................... 161 
Periodic Inspections ........................................................................................................................................... 161 
Daily Checks ....................................................................................................................................................... 161 
50‐00‐00‐20  Maintenance Practices ............................................................................................................... 162 
Short‐Skirt Wing Locker Removal ...................................................................................................................... 162 
Short‐Skirt Wing Locker Installation .................................................................................................................. 162 
Long‐Skirt Wing Locker Removal ....................................................................................................................... 162 
Long‐Skirt Wing Locker Installation ................................................................................................................... 163 
Long‐Skirt Wing Locker Removal Factory Installed on B300 ............................................................................. 163 
Long‐Skirt Wing Locker Installation Factory installed on B300 ......................................................................... 163 
Door Seal Replacement ..................................................................................................................................... 165 
Wing to Locker Seal Replacement ..................................................................................................................... 166 
Pin Latch Replacement ...................................................................................................................................... 167 
Bayonet Latch Replacement .............................................................................................................................. 168 
Bayonet and Pin Latch Receiver Adjustment ..................................................................................................... 169 
Gas Spring (85‐3520‐077) Replacement ............................................................................................................ 170 
Gas Spring (85‐3520‐098) Replacement ............................................................................................................ 170 
Wing Locker Door Hinge Replacement .............................................................................................................. 171 
51  Standard Practices and Structures ..................................................................................... 172 
51‐00‐00‐00  Description ................................................................................................................................. 172 
51‐00‐11‐00  Composite Description ............................................................................................................... 172 
51‐11‐11‐20  Wet Layup Repair Maintenance Practices ................................................................................. 172 
Materials ............................................................................................................................................................ 173 
General – Repair And Refinishing Instructions .................................................................................................. 174 
Repair Instructions for Damaged Laminated Plies ............................................................................................. 175 
Repair Instructions for Damaged Laminated Plies and Core ............................................................................. 176 
51‐12‐11‐20  Prepreg Layup Fiberglass Repair ................................................................................................ 177 

Revision AM xii
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Materials ............................................................................................................................................................ 177 
General – Repair and Refinishing Instructions .................................................................................................. 178 
Repair Instructions for Damage of Laminated Plies .......................................................................................... 179 
Repair Instructions for Damage Laminated Ply and Core .................................................................................. 179 
51‐20‐11‐20  Repainting Fiberglass Components ............................................................................................ 182 
51‐20‐11‐23  Repainting Fiberglass Components With Anti‐Static Treatment ............................................... 183 
Surface Preparation ........................................................................................................................................... 183 
Application of Anti‐Static Coating ...................................................................................................................... 183 
Resistance Measure of Anti‐Static Coating ........................................................................................................ 184 
Top Coating ........................................................................................................................................................ 184 
53  Fuselage ........................................................................................................................... 185 
Dual Aft Body Strakes ............................................................................................................................................ 185 
53‐00‐00  Description and Operation ......................................................................................................... 185 
53‐00‐00‐05  Inspection ................................................................................................................................... 185 
Periodic Inspections ........................................................................................................................................... 185 
Daily Checks ....................................................................................................................................................... 185 
53‐00‐00‐20  Maintenance Practices ............................................................................................................... 185 
Repair/Replacement .......................................................................................................................................... 185 
54  Nacelles/Pylons ................................................................................................................ 186 
Composite and Stainless Steel Exhaust Stack Fairings ........................................................................................... 186 
54‐00‐00‐00  Description and Operation ......................................................................................................... 186 
54‐00‐00‐05  Inspection ................................................................................................................................... 186 
Periodic Inspections ........................................................................................................................................... 186 
Daily Checks ....................................................................................................................................................... 186 
54‐00‐00‐20  Maintenance Practices ............................................................................................................... 187 
Repair/Replacement .......................................................................................................................................... 187 
Composite Fairing Repair ................................................................................................................................... 187 
Stainless Steel Fairing Repair ............................................................................................................................. 187 
57  Wings ............................................................................................................................... 188 
Enhanced Performance Leading Edges .................................................................................................................. 188 
57‐00‐00‐00  Description and Operation ......................................................................................................... 188 
57‐00‐00‐05  Inspection ................................................................................................................................... 188 
Periodic Inspection ............................................................................................................................................ 188 
Daily Checks ....................................................................................................................................................... 188 
57‐00‐00‐20  Maintenance Practices ............................................................................................................... 188 
Repair/Replacement .......................................................................................................................................... 188 
Intercooler Inlet Abrasion Boot Replacement ................................................................................................... 189 
90 Series Gross Weight Increase ............................................................................................................................ 190 
57‐57‐00‐00  Description and Operation ......................................................................................................... 190 
57‐57‐00‐05  Inspections ................................................................................................................................. 190 
Periodic Inspection ............................................................................................................................................ 190 
100/A100 Series Gross Weight Increase with Quiet Turbofan Propellers .............................................................. 191 
57‐61‐30‐00  Description and Operation ......................................................................................................... 191 
57‐61‐30‐05  Inspections ................................................................................................................................. 191 
Periodic Inspection ............................................................................................................................................ 191 
Daily Checks ....................................................................................................................................................... 191 
61  Propellers ......................................................................................................................... 192 

Revision AM xiii
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

C90, E90 Series Propellers ...................................................................................................................................... 192 
61‐00‐10‐00  Quiet Turbofan Propellers Description and Operation ............................................................... 192 
61‐00‐11‐00  Swept Turbofan Propellers Description and Operation .............................................................. 193 
61‐00‐10‐05  Quiet Turbofan Propellers Inspection......................................................................................... 194 
Periodic Inspections ........................................................................................................................................... 194 
Daily Checks ....................................................................................................................................................... 194 
61‐00‐11‐05  Swept Turbofan Propellers Inspection ....................................................................................... 194 
61‐00‐00‐10  Quiet and Swept Turbofan Propellers Troubleshooting ............................................................. 195 
61‐00‐00‐20  Quiet Turbofan Propellers Maintenance Practices .................................................................... 195 
61‐00‐11‐20  Swept Turbofan Propellers Maintenance Practices ................................................................... 195 
Engine and Propeller Indicating ............................................................................................................................. 196 
61‐31‐10‐00  Description and Operation Quiet Turbofan Propellers ............................................................... 196 
61‐31‐10‐05  Inspections Quiet Turbofan Propellers ....................................................................................... 196 
61‐31‐10‐20  Maintenance Practices Quiet Turbofan Propellers .................................................................... 196 
Airspeed Indicator Range Markings ................................................................................................................... 197 
Propeller Tachometers Range Markings ............................................................................................................ 199 
Torque Meters Range Markings ........................................................................................................................ 200 
Propeller De‐Ice Ammeters Range Markings Quiet Turbofan Propellers and Swept Turbofan Propellers ....... 200 
61‐31‐11‐00  Description and Operation Swept Turbofan Propellers .............................................................. 201 
61‐31‐11‐05  Inspections Swept Turbofan Propellers ...................................................................................... 201 
61‐31‐11‐20  Maintenance Practices Swept Turbofan Propellers ................................................................... 201 
Airspeed Indicator Range Markings ................................................................................................................... 201 
Engine and Propeller Controls ............................................................................................................................... 202 
61‐76‐00‐20  Quiet Turbofan Propellers and Swept Turbofan Propellers Maintenance Practices .................. 202 
Ground Run/Low Pitch Torque Check C90, C90A, & E90 Aircraft Quiet Turbofan Propellers ........................... 203 
Ground Run/Low Pitch Torque: Blackhawk or 1,750 RPM Installations. ........................................................... 205 
Ground Run/Low Pitch Torque Check Aircraft Equipped with Raisbeck Magicam............................................ 206 
Ground Run/Low Pitch Torque Check Aircraft Equipped with Swept Turbofan Propellers .............................. 208 
Ground Run/Low Pitch Torque Check G90XT Aircraft Equipped with HC‐E4W‐3/D9290K Quiet Turbofan 
Propellers ........................................................................................................................................................... 210 
Engine Performance and Data Plate Speed Test ............................................................................................... 212 
Functional Test Magicam Adjustment Quiet Turbofan Propellers .................................................................... 214 
Low Idle Adjustment Aircraft with Magicam Quiet Turbofan Propellers .......................................................... 215 
Low Idle Adjustment Aircraft without Magicam Quiet and Swept Turbofan Propellers ................................... 215 
Takeoff RPM Quiet Turbofan Propellers and Swept Turbofan Propellers ......................................................... 215 
1,600 RPM Cruise Functional Test and Adjustment C90, C90A, C90B, and E90 Quiet Turbofan Propellers 
and Swept Turbofan Propellers ......................................................................................................................... 217 
1,600 RPM Cruise Feathering Adjustment C90, C90A, C90B, and E90 Quiet Turbofan Propellers and Swept 
Turbofan Propellers ........................................................................................................................................... 217 
Constant Speed Governor Adjustment Quiet Turbofan Propellers and Swept Turbofan Propellers ................ 217 
Constant Speed Governors adjusted from 2,200 to 1,900 MAX Takeoff RPM and 1,600 to 1,900 RPM 
Normal Operating Range ................................................................................................................................... 218 
Constant Speed Governors adjusted from 2,200 to 2,000 MAX Takeoff RPM and 1,600 to 2,000 RPM 
Normal Operating Range ................................................................................................................................... 218 
Constant Speed Governors 2,200 MAX Takeoff RPM and 1,600 to 2,200 RPM Normal Operating Range ....... 218 
Overspeed Governor Operational Test for Quiet Turbofan Propellers and Swept Turbofan Propellers .......... 220 
Reverse Not Ready Light Adjustment ................................................................................................................ 221 
Synchrophaser Target‐Screw Installation Configuration 1 ................................................................................ 222 
Synchrophaser Multiple Target Bracket Rework and Installation Configuration 2 ........................................... 222 
Synchrophaser Single Target Bracket Rework and Installation Configuration 3 ............................................... 222 

Revision AM xiv
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Synchrophaser Target Rework and Installation Configuration 4 ....................................................................... 222 
Synchrophaser Target‐Screw Installation Configuration 5 ................................................................................ 223 
Brush Block Mounting Bracket Rework and Installation C90 Series & E90 ....................................................... 223 
Synchrophaser Magnetic Target Pickup Bracket Rework and Installation ........................................................ 223 
F90 Quiet Turbofan Propellers ............................................................................................................................... 228 
61‐00‐20‐00  Description and Operation ......................................................................................................... 228 
61‐00‐20‐05  Inspection ................................................................................................................................... 228 
Periodic Inspections ........................................................................................................................................... 228 
Daily Checks ....................................................................................................................................................... 229 
61‐00‐20‐10  Troubleshooting ......................................................................................................................... 229 
61‐00‐20‐20  Maintenance Practices ............................................................................................................... 229 
Engine and Propeller Indicating ............................................................................................................................. 230 
61‐31‐20‐00  Description and Operation ......................................................................................................... 230 
61‐31‐20‐20  Maintenance Practices ............................................................................................................... 230 
Airspeed Indicators ............................................................................................................................................ 230 
Propeller Tachometers ...................................................................................................................................... 230 
Torquemeter ...................................................................................................................................................... 230 
Ammeters .......................................................................................................................................................... 230 
Engine and Propeller Controls ............................................................................................................................... 231 
61‐76‐20‐20  Maintenance Practices ............................................................................................................... 231 
Ground Run/Low Pitch Torque Check ............................................................................................................... 231 
Low Idle Adjustment .......................................................................................................................................... 233 
High Idle Adjustment ......................................................................................................................................... 233 
Constant Speed Governors ................................................................................................................................ 233 
Overspeed Governors ........................................................................................................................................ 233 
Reversing System ............................................................................................................................................... 233 
Fuel Lever Cutoff Adjustment ............................................................................................................................ 233 
Synchrophaser Target Installation LA‐2 thru LA‐99, LA‐101 .............................................................................. 233 
Synchrophaser Target Installation LA‐100, LA‐102 thru LA‐201 ........................................................................ 233 
Brush Block Mounting Bracket Rework and Installation ................................................................................... 234 
Synchrophaser Magnetic Target Pick‐Up Bracket Rework and Installation ...................................................... 234 
100/A100 Quiet Turbofan Propellers ..................................................................................................................... 237 
61‐00‐30‐00  Description and Operation ......................................................................................................... 237 
61‐00‐30‐05  Inspection ................................................................................................................................... 238 
Inspections ......................................................................................................................................................... 238 
Daily Checks ....................................................................................................................................................... 238 
61‐00‐30‐10  Troubleshooting ......................................................................................................................... 238 
61‐00‐30‐20  Maintenance Practices ............................................................................................................... 239 
Engine and Propeller Indicating ............................................................................................................................. 239 
61‐31‐30‐00  Description and Operation ......................................................................................................... 239 
61‐31‐30‐05  Inspections ................................................................................................................................. 239 
61‐31‐30‐20  Maintenance Practices ............................................................................................................... 239 
Airspeed Indicators ............................................................................................................................................ 240 
Propeller Tachometers ...................................................................................................................................... 240 
Torque Meters ................................................................................................................................................... 240 
Propeller De‐Ice Ammeters Model 100 Only ..................................................................................................... 240 
Engine and Propeller Controls ............................................................................................................................... 241 
61‐76‐30‐20  Maintenance Practices ............................................................................................................... 241 
Ground Run Power Symmetry and Low Pitch Torque Check ............................................................................ 241 

Revision AM xv
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Low Idle Adjustment .......................................................................................................................................... 243 
Propeller Autofeathering System (if installed) .................................................................................................. 243 
Constant Speed Governor Adjustment .............................................................................................................. 243 
Feathering Test and Adjustment ....................................................................................................................... 244 
Overspeed Governor Adjustment ...................................................................................................................... 245 
Overspeed Governor Operational Check ........................................................................................................... 245 
Reverse Not Ready Light Switch Adjustment .................................................................................................... 245 
Synchrophaser Target Installation ..................................................................................................................... 245 
Brush Block Mounting Bracket Rework and Installation ................................................................................... 246 
Synchrophaser Magnetic Target Pick‐up Bracket Rework and Installation ....................................................... 246 
61‐76‐30‐97  Engine and Propeller Controls Wiring ........................................................................................ 248 
Low Pitch Solenoid A100 Only ........................................................................................................................... 248 
Low Pitch Indicator Switch A100 Only ............................................................................................................... 248 
Low Pitch Proximity Switch A100 Only .............................................................................................................. 248 
Super King Air 200 Series Propellers ...................................................................................................................... 252 
61‐00‐40‐00  Quiet Turbofan Propellers Description and Operation ............................................................... 252 
61‐00‐41‐00  Swept Turbofan Propellers Description and Operation .............................................................. 252 
61‐00‐42‐00  Five‐Blade Swept Turbofan Propellers Description and Operation ............................................ 253 
61‐00‐40‐05  Quiet Turbofan Propellers Inspection......................................................................................... 253 
Periodic Inspections ........................................................................................................................................... 253 
Daily Checks ....................................................................................................................................................... 253 
61‐00‐41‐05  Swept Turbofan Propellers Inspection ....................................................................................... 254 
61‐00‐42‐05  Five‐Blade Swept Turbofan Propellers Inspection ...................................................................... 254 
61‐00‐40‐10  Quiet Turbofan Propellers Troubleshooting ............................................................................... 254 
61‐00‐41‐10  Swept Turbofan Propellers Troubleshooting .............................................................................. 254 
61‐00‐42‐10  Five‐Blade Swept Turbofan Propellers Troubleshooting ............................................................ 254 
61‐00‐40‐20  Quiet Turbofan Propellers Maintenance Practices .................................................................... 254 
61‐00‐41‐20  Swept Turbofan Propellers Maintenance Practices ................................................................... 255 
61‐00‐42‐20  Five‐Blade Swept Turbofan Propellers Maintenance Practices .................................................. 255 
Flight Controls Swept Turbofan Propellers ............................................................................................................ 256 
61‐27‐40‐05  Flight Controls Inspection Quiet Turbofan Propellers ................................................................ 256 
61‐27‐41‐05  Flight Controls Inspections Swept Turbofan Propellers .............................................................. 256 
61‐27‐42‐05  Flight Controls Inspections Five‐Blade Swept Turbofan Propellers ............................................ 256 
61‐27‐40‐20  Flight Controls Maintenance Practices Quiet Turbofan Propellers ............................................ 256 
61‐27‐41‐20  Flight Controls Maintenance Practices Swept Turbofan Propellers ........................................... 256 
61‐27‐42‐20  Flight Controls Maintenance Practices Five‐Blade Swept Turbofan Propellers .......................... 257 
Engine and Propeller Indicating ............................................................................................................................. 258 
61‐31‐40‐00  Description and Operation Quiet Turbofan Propellers ............................................................... 258 
61‐31‐41‐00  Description and Operation Swept Turbofan Propellers .............................................................. 258 
61‐31‐42‐00  Description and Operation Five‐Blade Swept Turbofan Propellers ............................................ 258 
61‐31‐40‐05  Inspections Quiet Turbofan Propellers ....................................................................................... 258 
61‐31‐41‐05  Inspections Swept Turbofan Propellers ...................................................................................... 258 
61‐31‐42‐05  Inspections Five‐Blade Swept Turbofan Propellers .................................................................... 258 
61‐31‐40‐20  Maintenance Practices Quiet Turbofan Propellers .................................................................... 258 
Airspeed Indicators Aircraft equipped with Rockwell Collins Pro Line 21 ......................................................... 259 
Airspeed Indicators ............................................................................................................................................ 260 

Revision AM xvi
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Propeller Tachometers ...................................................................................................................................... 260 
Torque meters ................................................................................................................................................... 260 
Ammeters .......................................................................................................................................................... 260 
61‐31‐41‐20  Maintenance Practices Swept Turbofan Propellers ................................................................... 260 
61‐31‐42‐20  Maintenance Practices Five‐Blade Swept Turbofan Propellers .................................................. 261 
Aircraft Equipped with Rockwell Collins Pro Line 21 – OEM ............................................................................. 261 
Aircraft Equipped with Rockwell Collins Pro Line 21 – Aftermarket.................................................................. 262 
Aircraft Equipped with Rockwell Collins Pro Line Fusion – OEM ....................................................................... 263 
Aircraft Equipped with Rockwell Collins Pro Line Fusion – Aftermarket ........................................................... 263 
Aircraft Equipped with Garmin International G1000 ........................................................................................ 263 
Model 200 and A200 Series Airspeed Indicator Rework ................................................................................... 263 
Model B200 Series Airspeed Indicator Rework ................................................................................................. 264 
Propeller Ammeter Rework/Replacement ........................................................................................................ 264 
Engine and Propeller Controls ............................................................................................................................... 265 
61‐76‐40‐20  Maintenance Practices Quiet Turbofan Propellers .................................................................... 265 
Ground Run Power Symmetry and Low Pitch Torque Check ............................................................................ 265 
Low Idle Adjustment .......................................................................................................................................... 268 
Constant Speed Governor Adjustment .............................................................................................................. 268 
Overspeed Governor Operational Test.............................................................................................................. 268 
Feathering Adjustment ...................................................................................................................................... 268 
Synchrophaser Target Screw Installation .......................................................................................................... 269 
Synchrophaser Single Target Installation .......................................................................................................... 269 
Synchrophaser Multiple Target Installation ...................................................................................................... 270 
De‐Ice Brush Block Bracket Rework and Installation ......................................................................................... 271 
Synchrophaser and Dynamic Balancing Pick‐up Bracket Rework and Installation ............................................ 271 
61‐76‐41‐20  Maintenance Practices Swept Turbofan Propellers ................................................................... 276 
61‐76‐42‐20  Maintenance Practices Five‐Blade Swept Turbofan Propellers .................................................. 276 
Power Symmetry and Low Pitch Torque Check ................................................................................................. 276 
Low Idle Check ................................................................................................................................................... 279 
High Idle Check .................................................................................................................................................. 279 
Fuel Cutoff Lever Adjustment ............................................................................................................................ 279 
Propeller Autofeathering System Check ............................................................................................................ 279 
Governor Operational Check ............................................................................................................................. 279 
Propeller Synchrophaser Functional Check ....................................................................................................... 280 
synchrophaser Target and Pick‐Up Installation ................................................................................................. 280 
Type I Synchrophaser Targets ............................................................................................................................ 280 
Type II Synchrophaser Target and Balance Weight ........................................................................................... 280 
Propeller De‐Ice Brush Block Bracket Installation ............................................................................................. 280 
Synchrophaser Pick‐Up Installation ................................................................................................................... 281 
Propeller Brush Block Installation ...................................................................................................................... 281 
Metal Oxide Varistor (MOV) Module Installation .............................................................................................. 281 
Super King Air 300/300LW, B300/B300C Propellers .............................................................................................. 286 
61‐00‐51‐00  Four‐Blade Swept Turbofan Propellers Description and Operation ........................................... 286 
61‐00‐51‐05  Four‐Blade Swept Turbofan Propellers Inspection ..................................................................... 287 
Periodic Inspections ........................................................................................................................................... 287 
Daily Checks ....................................................................................................................................................... 287 
61‐00‐51‐10  Four‐Blade Swept Turbofan Propellers Checks and Fault Isolation ............................................ 288 
Power Symmetry and Low Pitch Torque Check ................................................................................................. 288 
Low Idle Check ................................................................................................................................................... 292 
Dead Band Check ............................................................................................................................................... 292 
High Idle Check .................................................................................................................................................. 292 
Maximum Reverse Check .................................................................................................................................. 293 

Revision AM xvii
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Power Lever Mismatch Check ........................................................................................................................... 293 
Governing RPM Check ....................................................................................................................................... 293 
Solenoid Release Check ..................................................................................................................................... 293 
Ground Solenoid Check ..................................................................................................................................... 293 
Beta Valve Adjustment Check ............................................................................................................................ 293 
Low Pitch Warning Check .................................................................................................................................. 293 
Maximum Power Check ..................................................................................................................................... 293 
Propeller Synchrophaser Functional Check ....................................................................................................... 294 
Continuity Check ................................................................................................................................................ 294 
Governor Operational Check ............................................................................................................................. 295 
Pick‐Up Output Check ........................................................................................................................................ 296 
61‐00‐51‐20  Four‐Blade Swept Turbofan Propellers Maintenance Practices ................................................. 300 
Propeller Removal and Installation ................................................................................................................... 300 
Propeller De‐Ice and Synchrophaser System Bracketry Installation ................................................................. 300 
Synchrophaser Target Installation ..................................................................................................................... 300 
Synchrophaser Pick‐Up Installation ................................................................................................................... 301 
Propeller Balancing ............................................................................................................................................ 301 
Propeller Controls Nominal Setting ....................................................................................................................... 302 
Beta Arm Clevis Nominal Setting ....................................................................................................................... 302 
Beta Valve Nominal Setting ............................................................................................................................... 302 
Nf Link Nominal Setting ..................................................................................................................................... 302 
Ground Fine Solenoid Nominal Setting ............................................................................................................. 302 
61‐30‐51‐20  Four‐Blade Swept Turbofan Propellers De‐Icing System Maintenance Practices ...................... 307 
61‐00‐52‐00  Five‐Blade Swept Turbofan Propellers Description and Operation ............................................ 307 
61‐00‐52‐05  Five‐Blade Swept Turbofan Propellers Inspection ...................................................................... 307 
Periodic Inspections ........................................................................................................................................... 307 
Daily Checks ....................................................................................................................................................... 307 
61‐00‐52‐10  Five‐Blade Swept Turbofan Propellers Checks and Fault Isolation ............................................. 308 
Power Symmetry and Low Pitch Torque Check ................................................................................................. 308 
Low Idle Check ................................................................................................................................................... 312 
Dead Band Check ............................................................................................................................................... 312 
High Idle Check .................................................................................................................................................. 312 
Maximum Reverse Check .................................................................................................................................. 313 
Power Lever Mismatch Check ........................................................................................................................... 313 
Governing RPM Check ....................................................................................................................................... 313 
Solenoid Release Check ..................................................................................................................................... 313 
Ground Solenoid Check ..................................................................................................................................... 313 
Beta Valve Adjustment Check ............................................................................................................................ 313 
Low Pitch Warning Check .................................................................................................................................. 313 
Maximum Power Check ..................................................................................................................................... 313 
Propeller Synchrophaser Functional Check ....................................................................................................... 314 
Continuity Check ................................................................................................................................................ 314 
Governor Operational Check ............................................................................................................................. 315 
Pick‐Up Output Check ........................................................................................................................................ 316 
61‐00‐52‐20  Five‐Blade Swept Turbofan Propellers Maintenance Practices .................................................. 320 
Propeller Removal and Installation ........................................................................................................................ 320 
Propeller De‐Ice and Synchrophaser System Bracketry Installation ...................................................................... 320 
Synchrophaser Target Installation ......................................................................................................................... 321 
Synchrophaser Pick‐Up Installation ....................................................................................................................... 322 
Single or Dual Pick‐Up Installation ..................................................................................................................... 322 
Propeller Controls Nominal Setting ....................................................................................................................... 323 
Beta Arm Clevis Nominal Setting ....................................................................................................................... 323 

Revision AM xviii
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Beta Valve Nominal Setting ............................................................................................................................... 323 
Nf Link Nominal Setting ...................................................................................................................................... 323 
Ground Fine Solenoid Nominal Setting ............................................................................................................. 323 
Propeller Balancing ................................................................................................................................................ 323 
61‐30‐52‐20  Five‐Blade Swept Turbofan Propellers Maintenance De‐Ice Practices ....................................... 328 
Five‐Blade Swept Turbofan Propellers Indicating .................................................................................................. 328 
61‐31‐52‐00  Description and Operation ......................................................................................................... 328 
61‐31‐52‐05  Inspections ................................................................................................................................. 328 
61‐31‐52‐20  Airspeed Indicator Rangemarking ............................................................................................. 328 
300/300LW Equipped with Rockwell Collins’ Pro Line 2 ................................................................................... 328 
300/300LW Equipped with Rockwell Collins’ Pro Line 21 ................................................................................. 328 
300/300LW Equipped with Rockwell Collins’ Fusion ......................................................................................... 328 
300/300LW Equipped with Garmin’s G1000 ..................................................................................................... 328 
B300/B300C Equipped with Rockwell Collins’ Pro Line 2 .................................................................................. 328 
B300/B300C Equipped with Rockwell Collins’ Pro Line 21 ................................................................................ 328 
B300/B300C Equipped with Rockwell Collins’ Fusion ........................................................................................ 328 
B300/B300C Equipped with Gamin’s G1000 ..................................................................................................... 328 
 

Revision AM xix
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

00 Chapter Descriptions
04 Airworthiness Limitations
This chapter details:
Mandatory modifications, replacement and structural inspection requirements for the airframe and
propellers, mandatory replacement time, inspection intervals; and procedures for fuel tanks.
Mandatory replacement time for Electrical Wiring Interconnect System (EWIS) components, limits of
validity of engineering data for structural maintenance, and instructions for continued airworthiness.

05 Time Limits/Maintenance Checks

This chapter contains the minimum requirements for Continued Airworthiness (ICA) for all Raisbeck
Systems as installed on all Beechcraft King Air Series aircraft. Maintenance checks shall be
concurrent with the existing Beechcraft Time Limits and Maintenance Checks including the allowable
time tolerances between checks as described in the applicable King Air Maintenance Manual,
Chapter 05.
Additionally, those operators under the Beechcraft Super King Air 200 Series High Utility Inspection
Program (HUIP) will find provisions that coincide with this program.
Daily Checks are intended as preflight checks for pilots and/or technicians. Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.

11 Placards
This chapter details all interior and exterior placards associated with Raisbeck Systems.

12 Servicing
This chapter details general servicing of Raisbeck Systems.

20 Standard Practices Airframe

This chapter details standard maintenance practices to maintain the aircraft in airworthy condition.

30 Ice and Rain Protection

This chapter details maintenance practices for the ice protection systems on Raisbeck Enhanced
Performance Leading Edges, Ram Air Recovery System, and Raisbeck/Hartzell Propeller Systems.

32 Landing Gear
This chapter details maintenance practices for Raisbeck Fully Enclosed Main Landing Gear Doors on
aircraft equipped with high floatation landing gear.

50 Cargo and Accessory Compartments

This chapter details maintenance practices for Raisbeck Nacelle Wing Lockers and Crown Wing
Lockers.

Revision AM 1
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

51 Standard Practices Structures

This chapter provides information for acceptable repairs and repair limits on Raisbeck Systems for
composite, metallic, and formed components. In general, the repair methods used on all Raisbeck
Systems may be accomplished in accordance with AC43.13-1() Aircraft Inspection and Repair
Manual and AC43.13-2 Aircraft Alterations Manual. The repair information is recommended in
addition to the information given in AC 43.13-1() and AC 43.13-2.

53 Fuselage
This chapter details maintenance practices for Raisbeck Dual Aft Body Strakes.

54 Nacelles/Pylons
This chapter details maintenance practices for Raisbeck Composite Exhaust Stack Fairings and
Stainless Steel Exhaust Stack Fairings.

57 Wings
This chapter details maintenance practices for Raisbeck Enhanced Performance Leading Edges.

61 Propellers
This chapter details maintenance practices on Raisbeck/Hartzell Propeller Systems.

Revision AM 2
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

04 Airworthiness Limitations
04-00-00-01 Mandatory Modification, Replacement, and Structural
Inspection for Airframe Systems
There are no mandatory modification or replacement intervals on any Raisbeck Engineering King Air
airframe systems.

04-61-00-01 Mandatory Modification, Replacement, and Structural

Inspection for Propellers
Maintain Raisbeck/Hartzell Quiet Turbofan, Swept Turbofan Propellers, or Five-Blade Swept
Turbofan Propellers in accordance with the applicable Hartzell Propeller Owner’s Manual and
Logbook, Composite Propeller Blade Field Maintenance and Minor Repair Manual, and the applicable
Beechcraft King Air Maintenance Manual.

04-00-00-02 Mandatory Replacement Time, Inspection Intervals, and

Procedures for Fuel Tanks
There are no Raisbeck Engineering King Air systems that effect any existing fuel tank airworthiness
requirements.

04-00-00-03 Mandatory Replacement Time for EWIS Components

There are no EWIS components associated with any Raisbeck Engineering King Air system.

04-00-00-04 Limits of Validity of Engineering Data for Structural

Maintenance
There are no time or cycle limited components on any Raisbeck Engineering King Air airframe
systems. Components are repaired or replaced when inspection or performance of items reveals a
potentially unsafe condition or performance degradation.
Airworthiness Limitations are stipulated in the applicable Hartzell Propeller Owner’s Manual and
Logbook for time and cycle limited components of Raisbeck/Hartzell propellers.

04-00-00-05 Instructions for Continued Airworthiness

The Airworthiness Limitations section is FAA approved and specifies maintenance required under
§43.16 and §91.403 of the Federal Aviation Regulations, unless an alternative program has been
FAA approved.

Revision AM 3
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05 Time Limit/Maintenance Checks

05-00-00-00 Description
This chapter contains the minimum requirements for Continued Airworthiness (ICA) for all Raisbeck
Systems as installed on all Beechcraft King Air aircraft. Maintenance checks shall be concurrent with
the existing Beechcraft Time Limits and Maintenance Checks including the allowable time tolerances
between checks as described in the applicable King Air Maintenance Manual, Chapter 05.

05-20-00-00 Scheduled Inspection

Daily Checks, Scheduled Inspection Program (Phase Inspection), Fusion Inspection Program
(Detailed Inspection), High Utility Inspection Program (HUIP), Alternate Phase Inspection, and
Biennial Inspection requirements are set forth in this document for individual Raisbeck and
Raisbeck/Hartzell Systems. Inspections are to be accomplished in concurrence with the applicable
Beechcraft King Air Inspection Program time limit and calendar month requirements.
Aircraft structure and components should be sufficiently clean to allow for effective inspection.
Inspections should be performed to a degree to ensure systems and components will remain
serviceable until the next applicable inspection is performed. Ensure that all placards and markings
are in place and legible, especially those listed in the limitations sections of the Airplane Flight Manual
Supplement.

Revision AM 4
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. Daily Checks are not
intended to require a logbook entry. All other Scheduled Inspections are intended for technician’s
entry in the logbook or other appropriate documentation.
Daily Inspection References

ATA
SYSTEM
REFERENCE

Ram Air Recovery System 30-72-00-05

Fully Enclosed Main Landing Gear Doors 32-00-00-05

Nacelle/Crown Wing Lockers 50-00-00-05

Dual Aft Body Strakes 53-00-00-05

Enhanced Performance Leading Edges 57-00-00-05

90 Series Quiet Turbofan Propellers 61-00-10-05

90 Series Swept Turbofan Propellers 61-00-11-05

F90 Quiet Turbofan Propellers 61-00-20-05

100 Series Quiet Turbofan Propellers 61-00-30-05

200 Series Quiet Turbofan Propellers 61-00-40-05

200 Series Swept Turbofan Propellers 61-00-41-05

200 Series Five-Blade Swept Turbofan Propellers 61-00-42-05

300/300LW and B300/B300C Four-Blade Swept 61-00-51-05

Turbofan Propellers

300/300LW and B300/B300C Five-Blade Swept 61-00-52-05

Turbofan Propellers

Revision AM 5
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Phase Inspections
The Beechcraft King Air Phase Inspection Program, for all King Air models, is divided into four (4),
200 hour Phase Inspections. A Complete Inspection cycle is 800 hours or 24 calendar months. Each
consecutive Phase Inspection is accomplished after the previous Phase Inspection. All Special
Inspection and Unscheduled Maintenance Checks shall be accomplished independently of the Phase
Inspection Program as required. Reference Chapter 05-21-00-00 of this manual.
To facilitate scheduling Phase Inspections, Raisbeck Engineering authorizes the inspection interval
tolerances to coincide with the owner’s/operator’s approved maintenance program.

NOTE: Tolerances specified by suppliers, manufactures, DOT regulation, or FAA

regulation take precedence over inspection interval tolerances authorized by
Raisbeck Engineering. Tolerances do not accumulate.

Phase Inspection References

ATA
INSPECTION HOURS
REFERENCE

Phase 1 200 05-20-00-01

Phase 2 400 05-20-00-02

Phase 3 600 05-20-00-03

Phase 4 800 05-20-00-04

NOTE: The Phase 1 through Phase 4 Inspection Checklists includes inspection

items for all Raisbeck, Raisbeck/Hartzell Systems available for all Beechcraft
King Air Models. Some Raisbeck and Raisbeck/Hartzell Systems may not
be applicable to airframe or engine being inspected. Inspect systems as
applicable to engine or airframe.

Revision AM 6
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Fusion Inspections
The Beechcraft King Air Fusion Inspection Program, for King Air Fusion models, is divided into four
(4) 200 hour Detailed Inspections. A complete inspection cycle is 800 hours or 48 calendar months.
Each consecutive Detailed Inspection is accomplished after the previous Detailed Inspection. All
Special Inspection and Unscheduled Maintenance Checks shall be accomplished independently of
the Detailed Inspection Program as required. Reference Chapter 05-21-00-00 of this manual.
To facilitate scheduling Fusion Inspections, Raisbeck Engineering authorizes the inspection interval
tolerances to coincide with owner’s/operator’s approved maintenance program.

NOTE: Tolerances specified by suppliers, manufactures, DOT regulation, or FAA

regulation take precedence over inspection interval tolerances authorized by
Raisbeck Engineering. Tolerances do not accumulate.

Fusion Inspection References

ATA
INSPECTION
REFERENCE

Detailed 1 05-20-00-01

Detailed 2 05-20-00-02

Detailed 3 05-20-00-03

Detailed 4 05-20-00-04

NOTE: The Detailed 1 through Detailed 4 Inspection Checklists includes inspection

items for all Raisbeck, Raisbeck/Hartzell Systems available for all Beechcraft
King Air Models. Some Raisbeck and Raisbeck/Hartzell Systems may not
be applicable to airframe or engine being inspected. Inspect systems as
applicable to engine or airframe.

Revision AM 7
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

HUIP Inspections
Only Beechcraft Super King Air 200 Series aircraft operated for a minimum of 400 hours per year are
eligible for the HUIP.

Transition from the Phase Inspection Program to the HUIP shall be accomplished upon completion of
a complete Phase Inspection Cycle or complete Phase 1 through Phase 4 Inspections. Use the flight
hours and date of the completion of Phase 4 inspection, or complete Phase 1 through Phase 4
Inspections, to establish the correct time for the Routine and Detailed Inspections of the HUIP.

The HUIP, for Beechcraft Super King Air 200 Series are divided into eight (8) inspections, four (4)
Routine Inspections starting at 200 hours, and repeating every 400 hours, alternated with four (4)
Detailed Inspections, starting at 400 hours and repeating every 400 hours. Special Inspection Items
and Unscheduled Maintenance Checks shall be accomplished independently of the HUIP as
required. Reference Chapter 05-21-00-00 of this manual.

To facilitate scheduling Routine and Detailed Inspections, Raisbeck Engineering authorizes the
inspection interval tolerances to coincide with the owner’s/operator’s approved maintenance program.

NOTE: Tolerances specified by suppliers, manufacturers, DOT regulation, or FAA

regulation take precedence over inspection interval tolerances authorized by
Raisbeck Engineering. Tolerances do not accumulate.
HUIP References

ATA
INSPECTION
REFERENCE

Routine 1 through Routine 4 05-20-00-05

Detailed 1 through Detail 4 05-20-00-06

NOTE: The Routine and Detailed Inspection Checklists include inspection items for
all Raisbeck, Raisbeck/Hartzell Systems available for Beechcraft Super King
Air 200 Series. Some Raisbeck and Raisbeck/Hartzell Systems may not be
applicable to the airframe or propeller being inspected. Inspect systems as
applicable to airframe or propeller.

Revision AM 8
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Alternate Phase Inspections

The Beechcraft King Air Alternate Phase Inspection Program for all King Air models, is for operators
flying more than 200 hours but less than 400 hours in 24 months. All Special Inspection and
Unscheduled Maintenance Checks shall be accomplished independently of the Alternate Phase
Inspection Program as required.
Perform scheduled Phase Inspections, Phase 1 and Phase 2, together within 12 months after the
latest inspection. Perform scheduled Phase Inspections, Phase 3 and Phase 4, together within 12
months after completing the Phase 1 and Phase 2 Inspections.

ATA
INSPECTION HOURS
REFERENCE

Phase 1 & 2 200 05-20-00-02

05-20-00-02

Phase 3 & 4 400 05-20-00-03

10-20-00-04

To facilitate scheduling Alternate Phase Inspections, Raisbeck Engineering authorizes the inspection
interval tolerances to coincide with the owner’s/operator’s approved maintenance program. Raisbeck
Engineering recommends that no aircraft exceed 12 months or 200 ±20 flight hours without
completing at least one Phase Inspection. Should an aircraft exceed the limitations of the Alternate
Phase Inspection, the aircraft must complete Phase 1, Phase 2, Phase 3, and Phase 4 Inspections,
or a Complete Inspection to reestablish the aircraft’s inspection cycle.

NOTE: Tolerances specified by suppliers, manufactures, DOT regulation, or FAA

regulation take precedence over inspection interval tolerances authorized by
Raisbeck Engineering. Tolerances do not accumulate.
Biennial Inspections
The Beechcraft King Air Biennial Inspection Program for all King Air models, is for operators flying
less than 200 hours in 24 months is comprised of an Interim Inspection and a Complete Inspection.
An Interim Inspection must be completed at 12 months and every 24 months thereafter. A Complete
Inspection must be completed at 24 months and every 24 months thereafter.

ATA
INSPECTION MONTHS
REFERENCE

Interim 12 Months 05-20-00-07

Complete 24 Months 05-20-00-07

Revision AM 9
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Daily Checklist
Daily Checklist

ATA
SYSTEM
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00

1. No daily checks. N/A

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00

1. No daily checks. N/A

C. FULLY ENCLOSED MAIN LANDING GEAR DOORS LH 32-00-00-00

1. Examine doors and hinges for condition and security. 32-00-00-05

2. Examine actuating mechanisms for condition and security. 32-00-00-05

D. FULLY ENCLOSED MAIN LANDING GEAR DOORS RH 32-00-00-00

1. Examine doors and hinges for condition and security. 32-00-00-05

2. Examine actuating mechanisms for condition and security. 32-00-00-05

E. NACELLE/CROWN WING LOCKERS LH 50-00-00-00

1. Examine locker for condition and security. 50-00-00-05

2. Examine flap fairing for condition and security. 50-00-00-05

3. Ensure door is closed and latched before flight. 50-00-00-05

F. NACELLE/CROWN WING LOCKERS RH 50-00-00-00

1. Examine locker for condition and security. 50-00-00-05

2. Examine flap fairing for condition and security. 50-00-00-05

3. Ensure door is closed and latched before flight. 50-00-00-05

G. DUAL AFT BODY STRAKES LH 53-00-00-00

1. Examine strake for condition and security. 53-00-00-05

2. Examine drain holes for and clear obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00

1. Examine strake for condition and security. 53-00-00-05

2. Examine drain holes for and clear obstructions. 53-00-00-05

Revision AM 10
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Daily Checklist (Continued)

ATA
SYSTEM
REFERENCE

I. EXHAUST FAIRING LH 54-00-00-00

1. Examine fairing for condition and security. 54-00-00-05

J. EXHAUST FAIRING RH 54-00-00-00

1. Examine fairing for condition and security. 54-00-00-05

K. ENHANCED PERFORMANCE LEADING EDGES LH 57-00-00-00

1. Examine the leading and wing to body fairing for condition and security. 57-00-00-05

2. Examine de-ice boot for condition and security. 57-00-00-05

L. ENHANCED PERFORMANCE LEADING EDGES RH 57-00-00-00

1. Examine the leading and wing to body fairing for condition and security. 57-00-00-05

2. Examine de-ice boot for condition and security. 57-00-00-05

M. OUTBOARD WING LH 57-00-00-00

100 SERIES ONLY, B-2 THRU B-89 WITH GROSS WEIGHT INCREASE

1. Examine ballast weight for condition and security. 57-61-30-05

N. OUTBOARD WING RH 57-00-00-00

100 SERIES ONLY, B-2 THRU B-89 WITH GROSS WEIGHT INCREASE

1. Examine ballast weight for condition and security. 57-61-30-05

Revision AM 11
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Daily Checklist (Continued)

ATA
SYSTEM
REFERENCE

O. PROPELLERS LH 61-00-XX*-00
*Use appropriate Subject for aircraft Model and blade design.

90 Series Quiet Turbofan Propellers 61-00-10-05

90 Series Swept Turbofan Propellers 61-00-11-05

F90 Quiet Turbofan Propellers 61-00-20-05

100 Series Quiet Turbofan Propellers 61-00-30-05

200 Series Quiet Turbofan Propellers 61-00-40-05

200 Series Swept Turbofan Propellers 61-00-41-05

200 Series Five-Blade Swept Turbofan Propellers 61-00-42-05

300/300LW, B300/B300C Four-Blade Swept Turbofan Propellers 61-00-51-05

300/300LW, B300/B300C Five-Blade Swept Turbofan Propellers 61-00-52-05

1. Examine spinner and blades for condition and security. 61-00-XX*-05

2. Examine de-ice boots for condition and security. 30-61-XX*-05

P. PROPELLERS RH 61-00-XX*-00
*Use appropriate Subject for aircraft Model and blade design.

90 Series Quiet Turbofan Propellers 61-00-10-05

90 Series Swept Turbofan Propellers 61-00-11-05

F90 Quiet Turbofan Propellers 61-00-20-05

100 Series Quiet Turbofan Propellers 61-00-30-05

200 Series Quiet Turbofan Propellers 61-00-40-05

200 Series Swept Turbofan Propellers 61-00-41-05

200 Series Five-Blade Swept Turbofan Propellers 61-00-42-05

300/300LW, B300/B300C Four-Blade Swept Turbofan Propellers 61-00-51-05

300/300LW, B300/B300C Five-Blade Swept Turbofan Propellers 61-00-52-05

1. Examine spinner and blades for condition and security. 61-00-XX*-05

2. Examine de-ice boots for condition and security. 30-61-XX*-05

Revision AM 12
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Scheduled Inspection Program Phase 1 or Detailed 1

Inspection
05-20-00-01 Phase 1 or Detailed 1 Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 13
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

Revision AM 14
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 53-00-00-05

3. Remove Fairings and examine gasket for condition. 53-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

Revision AM 15
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

M. OUTBOARD WING LH 57-00-00-00

C90A AND C90GT ONLY LJ-1138 THRU -- --
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-3) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

Revision AM 16
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

N. OUTBOARD WING RH 57-00-00-00

C90A AND C90GT ONLY LJ-1138 THRU -- --
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-4) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

O. OUTBOARD WING LH 57-00-00-00

100 SERIES ONLY, B-2 THRU B-89 & B93 WITH -- --
GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

P. OUTBOARD WING RH 57-00-00-00

100 SERIES ONLY, B-2 THRU B-89 & B93 WITH -- --
GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

Revision AM 17
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

Subject 42 200 Series Five-Blade Swept Turbofan

Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

Q. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

R. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

S. ENGINE TRUSS LH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Revision AM 18
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

T. ENGINE TRUSS RH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

U. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program (Phase/Detailed1 &
3).

V. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

Revision AM 19
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-01 Phase 1 or Detailed 1 Inspection Discrepancy Sheet

05-20-00-01 Phase 1 or Detailed 1 Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 20
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Scheduled Inspection Program Phase 2 or Detailed 2

Inspection
05-20-00-02 Phase 2 or Detailed 2 Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1 Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 21
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Examine the Flap Fairing for condition and security 50-00-00-05

of attachment.

Revision AM 22
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Inspect the Flap Fairing for condition and security of 50-00-00-05

attachment.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

Revision AM 23
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination.

Revision AM 24
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

200 Series Five-Blade Swept Turbofan

Subject 42
Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

M. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

N. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect Propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

O. ENGINE TRUSS LH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Revision AM 25
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

P. ENGINE TRUSS RH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Q. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program (Phase/Detailed 2 &
4).

R. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible

3. Complete all necessary logbook entries. --

Revision AM 26
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-02 Phase 2 or Detailed 2 Inspection Discrepancy Sheet

05-20-00-02 Phase 2 or Detailed 2 Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 27
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Scheduled Inspection Program Phase 3 or Detailed 3

Inspection
05-20-00-03 Phase 3 or Detailed 3 Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 28
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

Revision AM 29
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 53-00-00-05

3. Remove Fairings and examine gasket for condition. 53-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

Revision AM 30
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

M. OUTBOARD WING LH 57-00-00-00

C90A AND C90GT ONLY: LJ-1138 THRU -- --
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-3) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

Revision AM 31
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

N. OUTBOARD WING RH 57-00-00-00

C90A AND C90GT ONLY: LJ-1138 THRU -- --
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-4) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

O. OUTBOARD WING LH 57-00-00-00

100 SERIES ONLY: B-2 THRU B-89 AND B93 -- --
WITH GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

P. OUTBOARD WING RH 57-00-00-00

100 SERIES ONLY: B-2 THRU B-89 AND B93 -- --
WITH GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

Revision AM 32
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

200 Series Five-Blade Swept Turbofan

Subject 42
Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

Q. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

R. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

Revision AM 33
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

S. ENGINE TRUSS LH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

T. ENGINE TRUSS RH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

U. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program (Phase/Detailed 1 &
3).

V. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place an 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

Revision AM 34
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-03 Phase 3 or Detailed 3 Inspection Discrepancy Sheet

05-20-00-03 Phase 3 or Detailed 3 Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 35
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Scheduled Inspection Program Phase 4 or Detailed 4

Inspection
05-20-00-04 Phase 4 or Detailed 4 Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1 Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 36
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Examine the Flap Fairing for condition and security 50-00-00-05

of attachment.

Revision AM 37
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Inspect the Flap Fairing for condition and security of 50-00-00-05

attachment.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

Revision AM 38
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination.

Revision AM 39
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

200 Series Five-Blade Swept Turbofan

Subject 42
Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300 Five-Blade Swept

Turbofan Propellers

M. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

N. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect Propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

Revision AM 40
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

O. ENGINE TRUSS LH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

P. ENGINE TRUSS RH 71-00-00-00

200 SERIES, 300/300LW, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around -- --
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Q. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program (Phase/Detailed 2 &
4).

R. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

Revision AM 41
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-04 Phase 4 or Detailed 4 Inspection Discrepancy Sheet

05-20-00-04 Phase 4 or Detailed 4 Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 42
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-05 HUIP Routine Inspection

05-20-00-05 HUIP Routine Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine Diaphragm Seals for condition and 30-70-00-05

security.

2. Examine Bypass Door Seals for condition and 30-72-00-05

security.

3. Examine Particle Separator for condition and 30-72-00-05

security.

4. Examine Fixed Turning Vane for condition and 30-72-00-05

security.

5. Examine Ice Shedder Screen for condition and 30-72-00-05

security.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Examine Diaphragm Seals for condition and 30-70-00-05

security.

2. Examine Bypass Door Seals for condition and 30-72-00-05

security.

3. Examine Particle Separator for condition and 30-72-00-05

security.

4. Examine Fixed Turning Vane for condition and 30-72-00-05

security.

5. Examine Ice Shedder Screen for condition and 30-72-00-05

security.

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine door hinges and door actuating linkage for 32-00-00-05

security and condition.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine door hinges and door actuating linkage for 32-00-00-05

security and condition.

Revision AM 43
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-05 HUIP Routine Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Examine the Flap Fairing for condition and security 50-00-00-05

of attachment.

F. WING LOCKERS RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Examine the Flap Fairing for condition and security 50-00-00-05

of attachment.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security 54-00-00-05

Revision AM 44
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-05 HUIP Routine Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine exterior surface for
delaminations.

3. If exterior delamination detected, use NDT to 57-00-00-05

examine interior surface of cored areas.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine exterior surface for
delaminations.

3. If exterior delamination detected, use NDT to 57-00-00-05

examine interior surface of cored areas.

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

Subject 42 200 Series Five-Blade Swept Turbofan

Propellers

Subject 51 B300/B300C Four-Blade Swept Turbofan

Propellers

Subject 52 B300/B300C Five-Blade Swept Turbofan

Propellers

M. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice boots for condition and 30-61-XX*-05

security.

2. Remove spinner and inspect de-ice boot wiring for 61-00-XX*-05

condition and security.

Revision AM 45
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-05 HUIP Routine Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

N. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect propeller de-ice boots for condition and 30-61-XX*-05

security.

2. Remove spinner and inspect de-ice boot wiring for 61-00-XX*-05

condition and security.

O. ENGINE TRUSS LH 71-00-00-00

200 SERIES, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

P. ENGINE TRUSS RH 71-00-00-00

200 SERIES, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around -- --
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Q. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

R. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
HUIP Inspection Program Routine Inspection

Revision AM 46
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-05 HUIP Routine Inspection Discrepancy Sheet

05-20-00-05 HUIP Routine Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 47
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Aft Bulkhead Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Examine the Aft Bulkhead Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 48
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Detailed Inspection 4 only: Beechcraft

Jack aircraft per the applicable Beechcraft King Air King Air MM
Maintenance Manual and perform a landing gear
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Detailed Inspection 4 only: Beechcraft

Jack aircraft per the applicable Beechcraft King Air King Air MM
Maintenance Manual and perform a landing gear
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Examine the Flap Fairing for condition and security 50-00-00-05

of attachment.

Revision AM 49
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine Hinges for condition and security. 50-00-00-05

5. Inspect the Flap Fairing for condition and security of 50-00-00-05

attachment.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

Revision AM 50
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

3. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

4. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

5. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

6. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

Revision AM 51
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

200 Series Five-Blade Swept Turbofan

Subject 42
Propellers

B300/B300C Four-Blade Swept Turbofan

Subject 51
Propellers

B300/B300C Five-Blade Swept Turbofan

Subject 52
Propellers

M. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

N. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect Propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Inspect Propeller for condition and security. 61-00-XX*-05

Revision AM 52
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

O. ENGINE TRUSS LH 71-00-00-00

200 SERIES, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

P. ENGINE TRUSS RH 71-00-00-00

200 SERIES, B300/B300C -- --
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Q. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

R. FUNCTIONAL CHECKS Beechcraft

-- --
King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
HUIP Inspection Program (Detail 1, 2, 3, or 4).

Revision AM 53
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3, & 4 Discrepancy Sheet

05-20-00-06 HUIP Inspection: Detailed 1, 2, 3 & 4 Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 54
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-07 Alternate Phase Inspection

Reference 05-20-00-01, 05-20-00-02, 05-20-00-03, and 05-20-00-04 Phase Inspections for Alternate
Phase Inspections and Discrepancy Sheets.

05-20-00-08 Biennial: Interim Inspection

05-20-00-08 Biennial: Interim Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Inspect engine inertial anti-icer for proper operation 30-72-00-05

and rigging.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Inspect engine inertial anti-icer for proper operation 30-72-00-05

and rigging.

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for condition, and security.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for condition, and security.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Lockers, Doors, Latches, Hinges, and Flap 50-00-00-05

Fairing for condition and security.

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Lockers, Doors, Latches, Hinges and Flap 50-00-00-05

Fairing for condition and security.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

Revision AM 55
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-08 Biennial: Interim Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Check surface de-ice system for proper operation 30-57-00-05

and cycling.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Check surface de-ice system for proper operation 30-57-00-05

and cycling.

Revision AM 56
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-08 Biennial: Interim Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

Subject 42 200 Series Five-Blade Swept Turbofan

Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

M. PROPELLERS LH 61-00-XX*-00 -- --

1. Check de-ice boots for proper operation and cycling. 30-61-00-05

2. Perform flight idle torque check. 61-00-XX*-05

N. PROPELLERS RH 61-00-XX*-00 -- --

1. Check de-ice boots for proper operation and cycling. 30-61-00-05

2. Perform flight idle torque check. 61-00-XX*-05

Revision AM 57
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-08 Biennial: Interim Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

O. ENGINE TRUSS LH 71-00-00-00 -- --

200 SERIES, 300/300LW, B300/B300C
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

P. ENGINE TRUSS RH 71-00-00-00 -- --

200 SERIES, 300/300LW, B300/B300C
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

Q. FUNCTIONAL CHECKS Beechcraft -- --

King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program.

R. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

Revision AM 58
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-08 Biennial: Interim Inspection Discrepancy Sheet

05-20-00-08 Biennial: Interim Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 59
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection

05-20-00-09 Biennial: Complete Inspection

ATA
SYSTEM MECH INSP
REFERENCE

A. RAM AIR RECOVERY SYSTEM LH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

B. RAM AIR RECOVERY SYSTEM RH 30-00-00-00 -- --

1. Examine the Diaphragm Seals for condition, 30-72-00-05

attachment, and sealing conditions.

2. Examine the Bypass Door Seals for condition, 30-72-00-05

attachment, and sealing conditions. Examine for
freedom of movement and correct adjustment.

3. Examine the Particle Separator for structural 30-72-00-05

condition and attachment. Examine for freedom of
movement and proper travel.

4. Examine the Fixed Turning Vane for structural 30-72-00-05

condition and attachment.

5. Examine the Ice Shedder Screen for condition and 30-72-00-05

attachment.

Revision AM 60
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

C. FULLY ENCLOSED MLG DOORS LH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack Aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

D. FULLY ENCLOSED MLG DOORS RH 32-00-00-00 -- --

1. Examine the door, hinges, and door actuating 32-00-00-05

linkage for wear, condition, and security.

2. Jack Aircraft per the applicable Beechcraft King Air Beechcraft

Maintenance Manual and perform a landing gear King Air MM
retraction test.

3. Examine the door retraction linkage for proper 32-00-00-20

operation and adjustment.

4. Examine the doors for proper fit and security when 32-00-00-20
the landing gear is retracted.

5. Perform a Manual/Emergency landing gear Beechcraft

extension test per the applicable Beechcraft King Air King Air MM
Maintenance Manual.

E. WING LOCKERS LH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

Revision AM 61
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

F. WING LOCKER RH 50-00-00-00 -- --

1. Examine Locker Shell for condition and security. 50-00-00-05

2. Examine Locker Door for condition and security. 50-00-00-05

3. Examine Latches for condition and security. 50-00-00-05

4. Examine the Hinges for condition and security. 50-00-00-05

5. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

G. DUAL AFT BODY STRAKES LH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

H. DUAL AFT BODY STRAKES RH 53-00-00-00 -- --

1. Examine Strake for condition and security. 53-00-00-05

2. Examine drain holes for obstructions. 53-00-00-05

I. EXHAUST FAIRINGS LH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 53-00-00-05

3. Remove Fairings and examine gasket for condition. 53-00-00-05

J. EXHAUST FAIRINGS RH 54-00-00-00 -- --

1. Examine Fairings for condition and security. 54-00-00-05

2. Examine fasteners for condition and security. 54-00-00-05

3. Remove Fairings and examine gasket for condition. 54-00-00-05

Revision AM 62
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

K. ENHANCED PERFORMANCE LEADING EDGE LH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Check surface de-ice system for proper operation 30-57-00-05

and cycling.

3. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

4. Examine the Wing-to-Body fairing for condition and 57-00-00-05

security.

5. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

6. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

7. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

L. ENHANCED PERFORMANCE LEADING EDGE RH 57-00-00-00 -- --

1. Examine the de-ice boot for condition and security. 30-57-00-05

2. Check surface de-ice system for proper operation 30-57-00-05

and cycling.

3. Examine the intercooler duct and gasket for 57-00-00-05

condition and security.

4. Examine the Wing-to-Body Fairing for condition and 57-00-00-05

security.

5. Using Non-destructive Testing (NDT), such as a 57-00-00-05

manual tap test, examine the leading edge for
delamination. Examine both sides of core.

6. Remove the Wing-to-Body Fairing. Inspect the 57-00-00-05

fairing, leading edge, and fuselage for condition and
chafing.

7. Remove the inboard Leading Edge. Inspect the 57-00-00-05

inner surface of the leading edge for condition and
delamination. Inspect the intercooler duct for
condition.

Revision AM 63
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

M. OUTBOARD WING LH 57-00-00-00 -- --

C90A AND C90GT ONLY LJ-1138 THRU
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-3) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

N. OUTBOARD WING RH 57-00-00-00 -- --

C90A AND C90GT ONLY LJ-1138 THRU
LJ-1145 AND LJ-1147 AND AFTER WITH
OPTIONAL GROSS WEIGHT INCREASE

1. Remove the lower Wing Tip Attachment Cover, 57-57-00-05

Panel 20. Inspect the Ballast Weight and Wing Tip 57-61-10-05
Center Rib (000-170012-4) for condition and 57-61-11-05
security.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Re-install the Access Panel, verifying use of correct Beechcraft

hardware. King Air MM

Revision AM 64
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

O. OUTBOARD WING LH 57-00-00-00 -- --

100 SERIES ONLY, B-2 THRU B-89 & B93 WITH
GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

P. OUTBOARD WING RH 57-00-00-00 -- --

100 SERIES ONLY, B-2 THRU B-89 & B93 WITH
GROSS WEIGHT INCREASE

1. Inspect the Ballast Weight for condition and security 57-61-30-05

of attachment.
CAUTION: THE RETAINING HARDWARE IS NON-
MAGNETIC. USE OF MAGNETIC
HARDWARE CAN INTERFERE WITH
THE AIRCRAFT’S NAVIGATION
SYSTEM. IF THE BALLAST WEIGHT IS
REMOVED ENSURE IT IS REINSTALLED
USING THE CORRECT HARDWARE.

2. Examine Flap Fairing for condition and security of 50-00-00-05

attachment.

Revision AM 65
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane Model and
blade design. SYSTEM

61-00-XX*-00

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

Subject 42 200 Series Five-Blade Swept Turbofan

Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

Q. PROPELLERS LH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Check de-ice boots for proper operation and cycling. 30-61-00-05

3. Inspect Propeller for condition and security. 61-00-XX*-05

4. Perform flight idle torque check. 61-00-XX*-05

R. PROPELLERS RH 61-00-XX*-00 -- --

1. Inspect propeller de-ice system for condition and 30-61-00-05

security (spinner removal required).

2. Check de-ice boots for proper operation and cycling. 30-61-00-05

3. Inspect Propeller for condition and security. 61-00-XX*-05

4. Perform flight idle torque check. 61-00-XX*-05

Revision AM 66
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection (Continued)

ATA
SYSTEM MECH INSP
REFERENCE

S. ENGINE TRUSS LH 71-00-00-00 -- --

200 SERIES, 300/300LW, B300/B300C
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

T. ENGINE TRUSS RH 71-00-00-00 -- --

200 SERIES, 300/300LW, B300/B300C
EQUIPPED WITH FIVE-BLADE SWEPT
TURBOFAN PROPELLERS

1. Inspect for cracks, dents, chafing, and corrosion. 71-00-00-05

Special attention should be made to areas around
clamps.

2. Inspect vibration isolators (mounts) for deterioration, 71-00-00-05

damage, and attachment.

U. FUNCTIONAL CHECKS Beechcraft -- --

King Air MM

1. Perform all Operational Inspection items per the Beechcraft

applicable Beechcraft King Air Maintenance Manual, King Air MM
Scheduled Inspection Program (Phase/Detailed1 &
3).

V. POST INSPECTION ITEMS -- -- --

1. Lubricate as necessary. 12-00-00-00

2. Determine that all required placards are in place and 11-00-00-00

legible.

3. Complete all necessary logbook entries. --

Revision AM 67
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-20-00-09 Biennial: Complete Inspection Discrepancy Sheet

05-20-00-09 Biennial: Complete Inspection Discrepancy Sheet

DISCREPANCY CORRECTIVE ACTION MECH INSP

Revision AM 68
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-21-00-00 Special Inspection Maintenance Practices

The following subchapters are arranged as unscheduled maintenance inspection check lists. When
unscheduled maintenance and detailed secondary inspections are necessary due to operations in
conditions which could require unscheduled maintenance, the affected Raisbeck Airframe,
Powerplant, and Accessory Systems shall be inspected in conjunction with the inspection
requirements set forth in the applicable Beechcraft King Air Maintenance Manual for unscheduled
maintenance.
To facilitate scheduling Special Inspections, Raisbeck Engineering authorizes the inspection interval
tolerances to coincide with the owner’s/operator’s approved maintenance program.

NOTE: Tolerances specified by suppliers, manufactures, DOT regulations, or FAA

regulations take precedence over inspection interval tolerances authorized by
Raisbeck. Tolerances do not accumulate.

Revision AM 69
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-32-00-21 Fully Enclosed MLG Doors Special Inspections

Fully Enclosed MLG Doors Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect hinges and retraction linkage for condition. Clean Weekly
atmospheres of high salt with low pressure water and mild detergent. Blow dry with
content dry shop air. Lubricate door hinges and retraction linkage
with Dry Film Lubricant, Type A, Class I or II, Grade 1.

Operation in Inspect hinges and retraction linkage for condition. Clean Weekly
atmospheres of high with low pressure water and mild detergent. Blow dry with
industrial air pollution dry shop air. Lubricate door hinges and retraction linkage
with Dry Film Lubricant, Type A, Class I or II, Grade 1.

Operation in areas of If the aircraft is to be operated in areas of high dust Weekly

high dust content content for an extended period of time, thoroughly clean
the door hinges and retraction linkage with cleaning
solvent. Blow dry with dry shop air. Lubricate door hinges
and retraction linkage with Dry Film Lubricant, Type A,
Class I or II, Grade 1.

Operation in areas of Inspect hinges and retraction linkage for condition. Clean Monthly
high humidity with low pressure water and mild detergent. Blow dry with
dry shop air. Lubricate door hinges and retraction linkage
with Dry Film Lubricant, Type A, Class I or II, Grade 1.

Operation from very soft Inspect hinges and retraction linkage for condition. Clean Weekly
or unusual terrain with low pressure water and mild detergent. Blow dry with
dry shop air. Lubricate door hinges and retraction linkage
with Dry Film Lubricant, Type A, Class I or II, Grade 1.

Hard landing Inspect the landing gear in accordance with Chapter 05- As Required
20-02 of this manual, Items C and D.

Encountering turbulent Inspect the landing gear in accordance with Chapter 05- As Required
air 20-02 of this manual, Items C and D.

Inspection after lightning Inspect area of suspected lighting strike for condition. If As Required
strike damage is found, repair or replace affected components.
Inspect the landing gear in accordance with Chapter 05-
20-00-02 of this manual, Items C and D.

Inspection after sudden N/A N/A

stoppage

Inspection after Inspect the landing gear in accordance with Chapter 05- As Required
deploying landing gear 20-02 of this manual, Items C and D.
above critical speed

Inspection after N/A N/A

deploying the flaps
above critical speed

Revision AM 70
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Fully Enclosed MLG Doors Special Inspections (Continued)

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in or around Inspect hinges and retraction linkage for condition. Clean Weekly
volcanic ash with low pressure water and mild detergent. Blow dry with
dry shop air. Lubricate door hinges and retraction linkage
with Dry Film Lubricant, Type A, Class I or II, Grade 1.

Revision AM 71
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-50-00-21 Wing Lockers Special Inspections

Wing Lockers Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect hinges and latches for condition. Clean with low Weekly
atmospheres of high salt pressure water and mild detergent. Blow dry with dry
content shop air. Lubricate Hinges with Dry Film Lubricant, Type
A, Class I or II, Grade 1.

Operation in Inspect hinges and latches for condition. Clean with low Weekly
atmospheres of high pressure water and mild detergent. Blow dry with dry
industrial air pollution shop air. Lubricate Hinges with Dry Film Lubricant, Type
A, Class I or II, Grade 1.

Operation in areas of If the aircraft is to be operated in areas of high dust Weekly

high dust content content for an extended period of time, thoroughly clean
the hinges with cleaning solvent. Blow dry with dry shop
air. Lubricate hinges with Dry Film Lubricant, Type A,
Class I or II, Grade 1.

Operation in areas of Inspect hinges and latches for condition. Clean with low Monthly
high humidity pressure water and mild detergent. Blow dry with dry
shop air. Lubricate with Dry Film Lubricant, Type A, Class
I or II, Grade 1.

Operation from very soft Inspect lockers for condition and security. Daily
or unusual terrain

Hard landing Inspect lockers for condition and security. Remove locker As Required
as required to inspect for damage to the airframe.

Encountering turbulent Inspect lockers for condition and security. Remove locker As Required
air as required to inspect for damage to the airframe.

Inspection after lightning Inspect area of suspected lighting strike for condition. If As Required
strike damage is found, repair or replace affected components.

Inspection after sudden N/A N/A

stoppage

Inspection after N/A N/A

deploying landing gear
above critical speed

Inspection after Inspect flap fairings for condition and security. As required
deploying the flaps
above critical speed

Operation in or around Inspect lockers for condition and security. Clean with low Weekly
volcanic ash pressure water and mild detergent. Blow dry with dry
shop air. Lubricate Hinges with Dry Film Lubricant, Type
A, Class I or II, Grade 1.

Revision AM 72
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-51-00-00 Time Limits/Maintenance Checks Airframe Systems

There are no time limited components on any Raisbeck King Air airframe systems. All Raisbeck King
Air airframe components are repaired or replaced when inspection or performance of items reveal a
potentially unsafe condition or performance degradation.

05-61-00-00 Time Limits/Maintenance Checks - Propellers

Time limited components of Raisbeck/Hartzell Swept Turbofan Propeller and Quiet Turbofan
Propeller Systems are defined in Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147,
149, or 486 ATA REF 61-00-47, 61-00-49, or 61-00-86 respectively) and the applicable Beechcraft
King Air Maintenance Manual.
Replacement and overhaul of time limited components of Raisbeck/Hartzell Swept Turbofan Propeller
and Quiet Turbofan Propeller Systems shall be accomplished in accordance with Hartzell Propeller
Owner’s Manual and Logbook (Manual No. 147, 149, or 486 ATA REF 61-00-47, 61-00-49, or 61-00-
86 respectively) and the applicable Beechcraft King Air Maintenance Manual.
Repair or replacement of Raisbeck/Hartzell Swept Turbofan Propeller and Quiet Turbofan Propeller
System assemblies and components not specified in this document shall be accomplished in
accordance with Hartzell Manual No. 147 & 149, ATA REF 61-00-47 & 61-00-49 respectively, and the
applicable Beechcraft King Air Maintenance Manual.

Revision AM 73
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-53-00-21 Dual Aft Body Strakes Special Inspections

Dual Aft Body Strakes Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect strakes for condition and security. Clean with low Weekly
atmospheres of high salt pressure water and mild detergent.
content

Operation in Inspect strakes for condition and security. Clean with low Weekly
atmospheres of high pressure water and mild detergent.
industrial air pollution

Operation in areas of Inspect strakes for condition and security. Clean with low Weekly
high dust content pressure water and mild detergent.

Operation in areas of Inspect strakes for condition and security. Clean with low Monthly
high humidity pressure water and mild detergent.

Operation from very soft Inspect strakes for condition and security. Daily
or unusual terrain

Hard landing Inspect for condition and security. As required

Encountering turbulent Inspect for condition and security. As required

air

Inspection after lightning Inspect area of suspected lightning strike for condition and As required
strike security. Repair or replace damaged components as
required.

Inspection after sudden N/A N/A

stoppage

Inspection after N/A N/A

deploying landing gear
above critical speed

Inspection after N/A N/A

deploying the flaps
above critical speed

Operation in or around Inspect strakes for condition and security. Clean with low Weekly
volcanic ash pressure water and mild detergent.

Revision AM 74
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-54-00-21 Exhaust Stack Fairings Special Inspections

Exhaust Stack Fairings Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect fairings for condition and security. Wash with low Weekly
atmospheres of high salt pressure water and mild detergent.
content

Operation in Inspect fairings for condition and security. Wash with low Weekly
atmospheres of high pressure water and mild detergent.
industrial air pollution

Operation in areas of Inspect fairings for condition and security. Wash with low Weekly
high dust content pressure water and mild detergent.

Operation in areas of Inspect fairings for condition and security. Wash with low Weekly
high humidity pressure water and mild detergent.

Operation from very soft Inspect for condition and security. Daily
or unusual terrain

Hard landing Inspect for condition and security. As required

Encountering turbulent Inspect for condition and security. As required

air

Inspection after lightning Inspect area of suspected lightning strike for condition and As required
strike security. Repair or replace damaged components as
required.

Inspection after sudden N/A N/A

stoppage

Inspection after N/A N/A

deploying landing gear
above critical speed

Inspection after N/A N/A

deploying the flaps
above critical speed

Operation in or around Inspect fairings for condition and security. Wash with low Weekly
volcanic ash pressure water and mild detergent.

Revision AM 75
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-57-00-21 Enhanced Performance Leading Edges Special

Inspections
Enhanced Performance Leading Edges Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect leading edges and de-ice boots for condition and Weekly
atmospheres of high salt security. Wash with low pressure water and mild
content detergent.

Operation in Inspect leading edges and de-ice boots for condition and Weekly
atmospheres of high security. Wash with low pressure water and mild
industrial air pollution detergent.

Operation in areas of Inspect leading edges and de-ice boots for condition and Weekly
high dust content security. Wash with low pressure water and mild
detergent.

Operation in areas of Inspect leading edges and de-ice boots for condition and Monthly
high humidity security. Wash with low pressure water and mild
detergent.

Operation from very soft Inspect for condition and security. Daily
or unusual terrain

Hard landing Inspect for condition and security. Remove leading edges As required
as needed to inspect airframe for damage.

Encountering turbulent Inspect for condition and security. Remove leading edges As required
air as needed to inspect airframe for damage.

Inspection after lightning Inspect area of suspected lightning strike for security and As Required
strike condition. Repair or replace damaged components as
required.

Inspection after sudden N/A N/A

stoppage

Inspection after N/A N/A

deploying landing gear
above critical speed

Inspection after N/A N/A

deploying the flaps
above critical speed

Operation in or around Inspect leading edges and de-ice boots for condition and As Required
volcanic ash security. Wash with low pressure water and mild
detergent.

Revision AM 76
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-61-00-21 Swept Turbofan Propellers, Five-Blade Swept Turbofan

Propellers, and Quiet Turbofan Propellers Special
Inspections
Propellers Special Inspections

CONDITION INSPECTION REQUIREMENT

Operation in The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

atmospheres Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
of high salt accordance with the applicable documents:
content Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Operation in The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

atmospheres Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
of high accordance with the applicable documents:
industrial air Beechcraft King Air/Super King Air Maintenance Manual
pollution Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Operation in The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

areas of high Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
dust content accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Operation in The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

areas of high Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
humidity accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Revision AM 77
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Propellers Special Inspections (Continued)

CONDITION INSPECTION REQUIREMENT

Operation from The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan
very soft or Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
unusual terrain accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Hard landing The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan
Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Encountering The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

turbulent air Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Inspection after The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan
lightning strike Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Revision AM 78
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

Propellers Special Inspections (Continued)

CONDITION INSPECTION REQUIREMENT

Inspection after The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan
sudden Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
stoppage accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Inspection after The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan
deploying Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
landing gear accordance with the applicable documents:
above critical Beechcraft King Air/Super King Air Maintenance Manual
speed Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Operation in or The Raisbeck/Hartzell Swept Turbofan Propellers, Five-Blade Swept Turbofan

around Propellers, and Quiet Turbofan Propellers are to be inspected and maintained in
volcanic ash accordance with the applicable documents:
Beechcraft King Air/Super King Air Maintenance Manual
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA REF 61-00-47)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA REF 61-00-86)
Hartzell Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-80)

Revision AM 79
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

05-72-00-21 Ram Air Recovery System Special Inspections

Ram Air Recovery System Special Inspections

INSPECTION
CONDITION INSPECTION REQUIREMENT
INTERVAL

Operation in Inspect components for condition and security. Perform Daily

atmospheres of high salt an external engine wash, to include the Ram Air Recovery
content System Ice Shedder Screen, in accordance with the
maintenance schedule set forth in the applicable Pratt &
Whitney Canada Maintenance Manual.

Operation in Inspect components For condition and security. Perform Daily

atmospheres of high an external engine wash, to include the Ram Air Recovery
industrial air pollution System Ice Shedder Screen, in accordance with the
maintenance schedule set forth in the applicable Pratt &
Whitney Canada Maintenance Manual.

Operation in areas of Inspect components for condition and security. Perform Daily
high dust content an external engine wash, to include the Ram Air Recovery
System Ice Shedder Screen, in accordance with the
maintenance schedule set forth in the applicable Pratt &
Whitney Canada Maintenance Manual.

Operation in areas of Inspect components for condition and security. Perform Daily
high humidity an external engine wash, to include the Ram Air Recovery
System Ice Shedder Screen, in accordance with the
maintenance schedule set forth in the applicable Pratt &
Whitney Canada Maintenance Manual.

Operation from very soft Inspect for condition and security. Daily
or unusual terrain

Hard landing Inspect for condition and security. As required

Encountering turbulent Inspect for condition and security. As required

air

Inspection after lightning Inspect area of suspected lightning strike for security and As Required
strike condition. Repair or replace damaged components as
required.

Operation in or around Inspect components for condition and security. Perform Daily
volcanic ash an external engine wash, to include the Ram Air Recovery
System Ice Shedder Screen, in accordance with the
maintenance schedule set forth in the applicable Pratt &
Whitney Canada Maintenance Manual.

Revision AM 80
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

TABLE 1 Approved Lubricants

Lubricants

TYPE DESCRIPTION

A Dry Film Lubricant

B Grease -100 °F to +300 °F (-73 °C +149 °C) Operating Range

C Silicone Paste

D Oil

CLASS DESCRIPTION

I Aerosol Spray

II Liquid

III Paste

GRADE DESCRIPTION

1 Approved to MIL-L-23398 Specifications

2 Approved to MIL-PRF-23827 Specifications

3 Approved to SAE-AS8660 Specification

4 Proprietary

APPROVED LUBRICANTS

TYPE CLASS GRADE PART NUMBER / DESIGNATION

A I, II 1 LPS 1, Lubri-Bond A, or Equivalent

B III 2 AeroShell 7 or Equivalent

C II 3 Dow Corning DC4 or Equivalent

D II 4 Marvel Mystery Oil

Revision AM 81
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

11 Placards and Markings

11-00-00-00 Description and Operation
This chapter details all interior and exterior Raisbeck Engineering placards and existing placard
rework changes.
TABLE 1 Placard Effectivity

EFFECTIVITY
ELIGIBILITY
CODE

A All King Air and Super King Air models equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers or
Raisbeck/Hartzell Swept Turbofan Propellers or
Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers.
B Super King Air 200, A200, B200, & B200GT Series aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3A/D9383K) or
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3A/D9515K) or
Raisbeck/Hartzell Swept Five-Blade Turbofan Propellers (5D3-NK366A1/91D15B).
C King Air 65-A90, B90, C90, C90A, C90GT, C90GTi, & E90 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) or
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK).
D King Air C90A serial numbers LJ-1063 thru LJ-1137 & LJ-1146 equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and optional
Raisbeck Gross Weight Increase.
E King Air 65-A90, B90, C90, C90A, C90GT, C90GTi, & E90 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and
Raisbeck Gross Weight Increase or
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK) and
Raisbeck Gross Weight Increase
F King Air 65-A90, B90, C90, C90A, & E90 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) without
Autofeather and Raisbeck Magicam installed.
G King Air C90GT, C90GTi aircraft equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK) and
Garmin G1000.
H King Air C90GT, C90GTi & aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and
Collins Pro Line 21 not in compliance with Raisbeck Engineering Service Bulletin
SB-11-BC-01.
J King Air C90, C90A, C90GT, C90GTi, & E90 (serial numbers LJ-502 thru LJ-1062)
aircraft equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK).
K King Air E90 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) or
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK).

Revision AM 82
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

TABLE 1 Placard Effectivity (Continued)

EFFECTIVITY
ELIGIBILITY
CODE

L King Air F90 aircraft equipped with:

Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290SK).
M King Air 100 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and
Raisbeck Gross Weight Increase.
N King Air A100 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and
Raisbeck Gross Weight Increase.
P King Air 100 serial numbers B-2 thru B-89 & B-93 equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K) and
Raisbeck Gross Weight Increase.
R King Air 100 & A100 aircraft equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-D4N-3C/D9290K).
T Super King Air B200 & B200GT Series aircraft equipped with:
Raisbeck/Hartzell Quiet or Swept Turbofan Propellers and
Collins Pro Line 21 not in compliance with Raisbeck Engineering Service Bulletin
SB-13-BC-02.
U Super King Air 200, A200, B200, & B200GT Series aircraft equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3A/D9515K) or
Raisbeck/Hartzell Swept Five-Blade Turbofan Propellers (5D3-NK366A1/91D15B).
V King Air B200GT serial number BY-029 equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3A/D9515K).
W All King Air models equipped with:
Raisbeck Crown Wing Lockers or
Raisbeck Nacelle Wing Lockers.
Y King Air 65-A90, B90, C90, C90A, C90GT, C90GTi, & E90 aircraft equipped with:
Raisbeck Crown Wing Lockers.
AA King Air C90 & C90A equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK) and
Garmin G1000.
AB King Air C90 & C90A equipped with:
Raisbeck/Hartzell Swept Turbofan Propellers (HC-D4N-3C/D9510SK),
PT6A-135A engines and Garmin G1000.
AC King Air C90 or C90A converted to NEXTANT G90XT and equipped with:
Raisbeck/Hartzell Quiet Turbofan Propellers (HC-E4W-3C/D9290K),
Raisbeck Crown Wing Lockers System, Raisbeck Dual Aft Body Strakes,
GE H75-100 engines, and Garmin International G1000.

Revision AM 83
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air Aircraft

TABLE 1 Placard Effectivity (Continued)

EFFECTIVITY
ELIGIBILITY
CODE

AD King Air 300/300LW, B300/B300C equipped with:

Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers, Raisbeck Dual Aft Body
Strakes and Rockwell Collins’ Pro Line 2.
AE King Air B300/B300C equipped with:
Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers, Raisbeck Dual Aft Body
Strakes and Rockwell Collins’ Pro Line 21 or Rockwell Collins’ Fusion or Garmin
G1000.
AF King Air 300/300LW equipped with:
Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers and Rockwell Collins’ Pro-line
21 or Rockwell Collins’ Fusion or Garmin G1000.

Revision AM 84
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-00 FIGURE 1 – PLACARD PART NUMBERS

Revision AM 85
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 Interior Placards and Limitation Markings

This Section details all interior Raisbeck Engineering placards and existing placard rework.
Instrument Panel configuration may vary.

NOTE: G90XT aircraft are C90A aircraft equipped with GE H75-100 engines per
Nextant Aerospace STC SA01902CH.
FIGURE 1; TABLE 1 65-A90, B90, C90, C90A, & E90 Instrument and Pedestal Placards
FIGURE 2; TABLE 2 C90, C90A, C90GT, C90GTi, & G90XT with Garmin G1000
FIGURE 3, TABLE 3 C90GT & C90GTi equipped with Raisbeck/Hartzell Quiet Turbofan
Propellers and Collins Pro Line 21 not in compliance with Raisbeck
Service Bulletin SB-13-BC-02.
FIGURE 4; TABLE 4 C90A serial numbers LJ-1063 thru LJ-1137, & LJ-1146 with optional
Gross Weight Increase. C90 & C90-1 serial numbers LJ-502 thru LJ-
1062 with D9510SK (Swept) Propellers, Airspeed Limitations Placard.
FIGURE 5; TABLE 5 E90 Airspeed Limitations Placard
FIGURE 6; TABLE 6 F90 & F90-1 Airspeed Limitations Placard
FIGURE 7; TABLE 7 65-A90, B90, C90, C90A, C90GT, C90GTi, E90, & G90XT Jacking
Placard
FIGURE 8, TABLE 8 100 & A100 Indicator Placards
FIGURE 9, TABLE 9 100 & A100 Airspeed Limitations Placard
FIGURE 10, TABLE 10 100 & A100 Jacking Placard
FIGURE 11, TABLE 11 200 & A200 Indicator Placards
FIGURE 12, TABLE 12 B200 & B200GT aircraft equipped with Raisbeck/Hartzell Quiet or Swept
Turbofan Propellers and Collins Pro Line 21 not in compliance with
Raisbeck Engineering Service Bulletin SB-13-BC-02.
FIGURE 13, TABLE 13 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell
Five-Blade Turbofan Propellers and Rockwell Collin’s Pro Line 2
FIGURE 14, TABLE 14 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell
Five-Blade Swept Turbofan Propellers and Rockwell Collins’ Pro Line 21
or Garmin’s G1000.
FIGURE 15, TABLE 15 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell
Five-Blade Swept Turbofan Propellers and Rockwell Collins’ Fusion

Revision AM 86
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 1

TABLE 1 65-A90, B90, C90, C90A, & E90 Instrument and Pedestal Placards

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Airspeed Indicator C

2 * Propeller Ammeter C

3 * Propeller Tachometer C

4 * Propeller Torque Meter C

5 REI-1001-3 Indicator Placard F

*Available through Beechcraft or other suitable source.

Revision AM 87
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 2

TABLE 2 C90, C90A, C90GT, C90GTi, & G90XT with Garmin G1000

ITEM PART NUMBER DESCRIPTION EFFECTIVITY

CODE
1 * Propeller Ammeter G

2 REI-1001-3 Indicator Placard G

3 REI-1001-10 Airspeed Placard AB

3 REI-1001-14 Airspeed Placard G, AA

3 REI-1001-16 Airspeed Placard AC

*Available through Beechcraft or other suitable source.

Item 3, centered (where possible), .10 to .25 inch above the pilot’s and co-pilot’s PFD.

Revision AM 88
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 3

TABLE 3 C90GT & C90GTi equipped with Raisbeck/Hartzell Quiet Turbofan Propellers and Collins
Pro Line 21 not in compliance with Raisbeck Service Bulletin SB-13-BC-02.

ITEM PART NUMBER DESCRIPTION EFFECTIVITY

CODE
1 REI-1001-12 Airspeed Placard H

Item 1, Placard REI-1001-12, centered .10 to .25 inch above the pilot’s and co-pilot’s PFD.

Revision AM 89
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 4

TABLE 4 C90A serial numbers LJ-1063 thru LJ-1137, & LJ-1146 with optional Gross Weight Increase.
C90 & C90-1 serial numbers LJ-502 thru LJ-1062 with D9510SK (Swept) Propellers, Airspeed
Limitations Placard.

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Existing Airspeed Limitations Placard J

2 REI-1001-4 Airspeed Limitations Placard D

*Available through Beechcraft of other suitable source.

Item 1, existing Airspeed Limitations Placard, is re-marked as indicated in Figure 4.

Item 2, Placard REI-1001-4, located as indicated in Figure 4.

Revision AM 90
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 5

TABLE 5 E90 Airspeed Limitations Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Existing Airspeed Limitations placard K

*Available through Beechcraft or other suitable source.

Item 1, existing Airspeed Limitations Placard, is re-marked as indicated in Figure 5.

Revision AM 91
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 6

TABLE 6 F90 & F90-1 Airspeed Limitations Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Ammeter L

2 REI-1001-9 Indicator Placard L

*Available through Beechcraft or other suitable source.

Revision AM 92
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 7

TABLE 7 65-A90, B90, C90, C90A, C90GT, C90GTi, E90, & G90XT Jacking Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 REI-1001-5 Jacking Placard E, AC

Revision AM 93
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 8

TABLE 8 100 & A100 Indicator Placards

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Airspeed Indicator M, N

2 * Propeller Ammeter P

3 * Propeller Tachometer M, N

4 * Propeller Torque Meter M, N

5 REI-1001-8 Indicator Placard M, N

*Available through Beechcraft or other suitable source.

Revision AM 94
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 9

TABLE 9 100 & A100 Airspeed Limitations Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Existing Airspeed Limitations Placard N

2 25-0021-1198 Blank Lens N

3 25-0021-1198 Blank Lens N

4 * Low Pitch Indicator placard removed. N

5 * Low Pitch Stop Test Indicator placard removed. N

6 * Low Pitch Indicator placard removed. N

7 * Low Pitch circuit breaker removed. N

8 * Idle Stop placard removed. N

*Available through Beechcraft or other suitable source.

Revision AM 95
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 10

TABLE 10 100 & A100 Jacking Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 REI-1001-6 Jacking Placard M

2 REI-1001-7 Jacking Placard N

Revision AM 96
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 11

TABLE 11 200 & A200 Indicator Placards

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Airspeed Indicator B

2 * Prop Ammeter B

3 REI-1001-2 Indicator Placard B

*Available through Beechcraft or other suitable source.

Revision AM 97
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 12

TABLE 12 B200 & B200GT aircraft equipped with Raisbeck/Hartzell Quiet or Swept Turbofan
Propellers and Collins Pro Line 21 not in compliance with Raisbeck Engineering Service
Bulletin SB-13-BC-02.

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 REI-1001-10 Airspeed Placard T

Revision AM 98
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 13

TABLE 13 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell Five-Blade Turbofan

Propellers and Rockwell Collin’s Pro Line 2

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 * Airspeed Indicator AD

17BC-11-003 Indicator Placard AD

2
17BC-11-401-1 Indicator Placard AF

*Available through Beechcraft or other suitable source.

Revision AM 99
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 14

TABLE 14 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell Five-Blade Swept

Turbofan Propellers and Rockwell Collins’ Pro Line 21 or Garmin’s G1000

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

17BC-11-001 Airspeed Placard AE

1
18BC-11-300-1 Airspeed Placard AF

Revision AM 100
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-10 FIGURE 15

TABLE 15 300/300LW, B300/B300C Aircraft Equipped with Raisbeck/Hartzell Five-Blade Swept

Turbofan Propellers and Rockwell Collins’ Fusion

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

17-BC-11-001 Airspeed Placard AE

1
18BC-11-300-1 Airspeed Placard AF

Revision AM 101
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-11 Exterior Placards and Markings Maintenance Practices

This section details all exterior Raisbeck Engineering Placards.
FIGURE 1, TABLE1 200, A200, B200, & B200GT Elevator Placard
FIGURE 2, TABLE 2 All King Air and Super King Air Models equipped with Nacelle Wing
Lockers or Crown Wing Lockers
FIGURE 3, TABLE 3 All King Air and Super King Air Models equipped with Raisbeck/Hartzell
Quiet Turbofan Propellers, Raisbeck/Hartzell Swept Blade Turbofan
Propellers, or Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers

Revision AM 102
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-11 FIGURE 1

TABLE 1 200, A200, B200, & B200GT Elevator Placard

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 *REI-1001-13 Elevator Trip Placard U

*REI Placard REI-1001-13 located on the inside surface of RH INBD Panel No. 11.

Revision AM 103
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-11 FIGURE 2

TABLE 2 All King Air and Super King Air Models equipped with Nacelle Wing Lockers or Crown Wing
Lockers

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 *85-3520-027 Loading Placard W

85-3520-100 Fuel Placard (White Lettering)

2 Y
85-3520-102 Fuel Placard (Black Lettering)

*Install placard centered between the latches on the interior of the Wing Locker door. Placard legible as viewed
with the door open.

Revision AM 104
 Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

11-00-00-11 FIGURE 3

TABLE 3 All King Air and Super King Air Models equipped with Raisbeck/Hartzell Quiet Turbofan
Propellers or Raisbeck/Hartzell Swept Blade Turbofan Propellers or Raisbeck/Hartzell
Five-Blade Swept Turbofan Propellers

EFFECTIVITY
ITEM PART NUMBER DESCRIPTION
CODE

1 REI-1001-1 Engine Truss Placard A

Revision AM 105
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12 Servicing
12-00-00-00 Description
This chapter details general servicing of the aircraft.

12-00-00-20 Maintenance Practices

TABLE 1 Lubrication Schedule

SYSTEM INTERVAL ATA REFERENCE

200 Hour
or
Ram Air Recovery 12-30-72-20
As required due to operating
conditions.

200 Hour
Fully Enclosed High Flotation or
12-32-00-20
MLG Doors As required due to operating
conditions.

200 Hour
or 12-50-10-20 (Short Skirt)
Wing Lockers
As required due to operating 12-50-11-20 (Long Skirt)
conditions.

Dual Aft Body Strakes N/A 12-53-00-20

200 Hour
or 12-54-10-20 (Stainless)
Exhaust Stack Fairings
As required due to operating 12-54-11-20 (Composite)
conditions.

Enhanced Performance Leading

N/A 12-57-00-20
Edges

Quiet Turbofan Propellers

or 200 Hour
Swept Turbofan Propellers or
12-61-XX*-20
or As required due to operating
Five-Blade Swept Turbofan conditions.
Propellers

Revision AM 106
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

TABLE 1 Lubrication Schedule (Continued)

SYSTEM INTERVAL ATA REFERENCE

PROPELLERS
*Use appropriate Subject for your airplane model
and blade design. SYSTEM

12-61-XX*-20

Subject 10 90 Series Quiet Turbofan Propellers

Subject 11 90 Series Swept Turbofan Propellers

Subject 20 F90 Quiet Turbofan Propellers

Subject 30 100 Series Quiet Turbofan Propellers

Subject 40 200 Series Quiet Turbofan Propellers

Subject 41 200 Series Swept Turbofan Propellers

Subject 42 200 Series Five-Blade Swept Turbofan

Propellers

Subject 51 300/300LW, B300/B300C Four-Blade Swept

Turbofan Propellers

Subject 52 300/300LW, B300/B300C Five-Blade Swept

Turbofan Propellers

Revision AM 107
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

TABLE 2 Approved Lubricants

Lubricants

TYPE DESCRIPTION

A Dry Film Lubricant

B Grease -100 °F +300 °F (-73 °C to +149 °C) Operating Range
C Silicone Paste
D Oil
CLASS DESCRIPTION
I Aerosol Spray
II Liquid
III Paste
GRADE DESCRIPTION
1 Approved to MIL-L-23398 Specifications
2 Approved to MIL-PRF-23827 Specifications
3 Approved to SAE-AS-8660 Specification
4 Proprietary

APPROVED LUBRICANTS

TYPE CLASS GRADE PART NUMBER / DESIGNATION

A I, II 1 LPS 1, Lubri-Bond A, or Equivalent

B III 2 AeroShell 7 or Equivalent

C II 3 Dow Corning DC4 or Equivalent

D II 4 Marvel Mystery Oil

Revision AM 108
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-30-57-20 Surface De-Ice Boot Servicing

The De-ice Boots should be inspected for indications of engine oil after servicing and at the end of
each flight. Remove any oil residue with non-detergent soap and water solution.
Reference the Beechcraft Super King Air 200 Series Maintenance Manual, Chapter 30 for De-ice
Boot care.

12-30-61-20 Propeller De-Ice System Servicing

Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 147, ATA REF 61-00-47)
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Owner’s Manual and Logbook
(Manual No. 486, ATA REF 61-00-86)
Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).

12-30-72-20 Ram Air Recovery System Servicing

Lubricate the Particle Separator Hinge and the Actuator Linkage at 200 hour interval with oil, Type D,
Class II, Grade 4.

12-32-00-20 Fully Enclosed High Flotation MLG Door Servicing

Lubricate the gear door hinges, door links, door roller, and mechanism at the 200 hour intervals with
Dry Film Lubricant, Type A, Class I or II, Grade 1. Before applying lubricant, clean surfaces of all wet
lubrication.

Revision AM 109
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-50-10-20 Short Skirt Wing Locker Servicing

Door Hinges
Reference FIGURE 1
Lubricate with Dry Film Lubricant, Type A, Class I or II, Grade 1.

NOTE: Nacelle Wing Locker door hinges must be lubricated after every cleaning.

Bayonet Latches
Reference FIGURE 2
It is recommended that the procedures given below be accomplished once a year or on an “as-
necessary” basis.
1. Remove the LATCH TRIM PLATE, P/N 85-3520-059, from each latch.
2. With the door open – visually examine internally and externally, the RUBBER GROMMET
(MS35489-38) for any excessive wear. Replace if necessary.
3. Remove old grease and contaminants from pocket with clean, dry, lint free cloth. Cloth may be
wet with MEK or Acetone.
4. Use a standard grease gun with a 2-inch needle attachment to fill the forward end of the latch
pocket with Grease, Type B, Class III, Grade 2. Inject grease at the bottom of the well. Allow it to
fill the complete forward portion of the cavity. Apply a uniform finger pressure to the grease to
force the grease into the cavity. Make sure that all air bubbles are removed, and that grease
completely covers the rubber grommet.
5. Install latch plate and fasteners wet with Sealant, Type A.
If adjustment is necessary, repeat the instructions given below until obtaining satisfactory operation:
1. Loosen the receiver screws to allow restricted movement of the receiver bracket.
2. Close the locker door, and hold/press it firmly to completely compress the bulb seal.
3. Engage the bayonet latch to align the receiver.
4. Retract the latch, open the door, and tighten receiver bracket screws.
5. Close the door and test the latches Cleaning
Cleaning
Clean lockers in accordance with the applicable Beechcraft King Air Maintenance Manual Chapter 20

NOTE: Nacelle Wing Locker door hinges must be lubricated after every cleaning.

Revision AM 110
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-50-10-20 FIGURE 1 SHORT SKIRT WING LOCKER

12-50-10-20 FIGURE 2 BAYONET LATCH

Revision AM 111
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-50-11-20 Long Skirt Wing Locker Servicing

Door Hinges
Reference FIGURE 1
Lubricate with Dry Film Lubricant, Type A, Class I or II, Grade 1.

NOTE: Crown Wing Locker door hinges must be lubricated after every cleaning.

Pin Latches
Reference FIGURE 2
1. Clean the latch pins and receptacles with a clean, oil free cloth.
2. Lubricate the pins with a light coat of Silicone Paste, Type C, Class II, Grade 3.
If adjustment is necessary, repeat the instructions given below until obtaining satisfactory
operation:
1. Loosen the receiver screws only to allow restricted movement of the receiver bracket.
2. Close the locker door, and hold/press it firmly to completely compress the bulb seal.
3. Engage the pin latch to align the receiver.
4. Retract the latch, open the door, and tighten receiver bracket screws.
5. Close the door and test the latches.
Cleaning
Clean lockers in accordance with the applicable Beechcraft King Air Maintenance Manual Chapter 20.

NOTE: Crown Wing Locker door hinges must be lubricated after every cleaning.

Revision AM 112
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-50-11-20 FIGURE 1 LONG SKIRT WING LOCKER

12-50-11-20 FIGURE 2 PIN LATCH

Revision AM 113
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-53-00-20 Dual Aft Body Strake Servicing

Clean the Dual Aft Body Strakes as given in the applicable Beechcraft King Air Maintenance Manual,
Chapter 12. Clear all drain holes of obstructions.

12-54-10-20 Stainless Steel Exhaust Stack Fairing Servicing

Lubricate the fasteners with Dry Film Lubricant, Type A, Class I or II, Grade 1.

12-54-11-20 Composite Exhaust Stack Fairing Servicing

Lubricate the fasteners with Dry Film Lubricant, Type A, Class I or II, Grade 1.

12-57-00-20 Enhanced Performance Leading Edge Servicing

The De-ice Boots should be inspected for indications of engine oil after servicing and at the end of
each flight. Remove any oil residue with non-detergent soap and water solution.
Inspect the inboard leading edges for impact damage. Refer to Chapter 51 of this manual for repairs.

12-61-10-20 Raisbeck/Hartzell Quiet Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-11-20 Raisbeck/Hartzell Swept Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.
12-61-20-20 Raisbeck/Hartzell Quiet Turbofan Propeller Servicing
The Propellers shall be maintained in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-30-20 Raisbeck/Hartzell Quiet Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-40-20 Raisbeck/Hartzell Quiet Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Super Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-41-20 Raisbeck/Hartzell Swept Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Super Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

Revision AM 114
Document No. 85-120
Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as installed on King Air and Super King Air aircraft

12-61-42-20 Raisbeck/Hartzell Five-Blade Swept Turbofan Propeller

Servicing
The Propellers shall be maintained in accordance with the applicable Beechcraft Super King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 486, ATA
REF 61-00-86). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-51-20 Raisbeck/Hartzell Swept Turbofan Propeller Servicing

The Propellers shall be maintained in accordance with the applicable Beechcraft Super King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

12-61-52-20 Raisbeck/Hartzell Five-Blade Swept Turbofan Propeller

Servicing
The Propellers shall be maintained in accordance with the applicable Beechcraft Super King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147, ATA
REF 61-00-47). Reference Chapter 12-30-61-20 of this manual for servicing of the Propeller De-ice
System.

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20 Standard Practices – Airframe

20-00-00-00 Description
This chapter details standard maintenance practices to maintain the aircraft in airworthy condition.

20-01-00-00 Torque Application Information

Unless otherwise stated within this manual, reference the Torque Application Information and
Standard Torque Values within the applicable King Air Maintenance Manual, Chapter 20.

20-02-00-00 Electrostatic Discharge Sensitivity Information

Unless otherwise stated within this manual, reference the Electrostatic Discharge Sensitivity
Information in the applicable Beechcraft King Air Maintenance Manual, Chapter 20.

20-03-00-00 Electrical Bonding Information

Reference Chapter 20 of the applicable Beechcraft King Air Model Maintenance Manual for electrical
bonding information.

20-04-00-00 Anti-static Coating

Reference Chapter 51-20-11-23 of this manual for Anti-Static Coating information.

20-05-00-00 Fastener Locking Device Information

Unless otherwise stated within this manual, reference the Fastener Locking Device Information of the
applicable Beechcraft King Air Maintenance Manual, Chapter 20.

20-06-00-00 Airplane Finish Information

Unless otherwise stated within this manual, reference the Airplane Finish Information of the
applicable Beechcraft King Air Maintenance Manual, Chapter 20.

20-07-00-00 Corrosion Control

Unless otherwise stated within this manual, reference the Corrosion Information of the applicable
Beechcraft King Air Maintenance Manual, Chapter 20.

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30 Ice and Rain Protection

Enhanced Performance Leading Edges
30-57-00-00 Description and Operation
The pneumatic de-ice boots on the Enhanced Performance Leading Edges are flush mounted.
Regulated bleed air pressure and vacuum are cycled to inflate and deflate the boots to prevent the
accumulation of ice.

30-57-00-05 Inspection
The De-ice boots are to be inspected in accordance with the Super King Air 200 Series Maintenance
Manual.

30-57-00-10 Troubleshooting
The Enhanced Performance Leading Edge de-ice boots directly replace the existing de-ice boots of
the inboard leading edges. They do not change or affect the function of the pneumatic de-ice system.
Reference the Beechcraft Super King Air 200 Series Maintenance Manual, Chapters 30, 36, and 37
for troubleshooting procedures.

30-57-00-20 Maintenance Practices

Reference the Beechcraft Super King Air 200 Series Maintenance Manual, Chapters 30 and 36 for
maintenance procedures for the surface de-ice system.
Reference the applicable Goodrich or Ice Shield installation and Maintenance Manuals for de-ice boot
repair and replacement.

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Quiet, Swept, and Five-Blade Swept Turbofan Propellers

30-61-00-00 Description and Operation
The Propeller De-ice System includes: an electrically heated boot for each propeller blade, slip rings,
brush assemblies, timer, control switch, and an ammeter. When the control switch is activated, the
ammeter registers the amount of current (18 to 24 amperes) passing through the system. The
current flows from the timer through the brush assemblies to the slip rings, where it is distributed to
the individual propeller de-ice boots. If the current draw should exceed design limitations, a circuit
breaker integrated into the control switch will cut power to the timer. Heat, produced by the heating
elements in the prop boots, reduces the adhesion of ice on the propeller. Adhesion thus reduced, the
ice is removed by the centrifugal effect of the propeller and the blast of the airstream. The propeller
blades are equipped with single-heating-element de-ice boots. Power to these boots is cycled in 90-
second phases. The first 90-second phase heats all the prop boots on the RH propeller. The second
phase heats all the de-ice boots on the LH propeller. The de-ice timer completes on a full cycle every
three minutes. As the timer moves from one phase to the other, a momentary deflection of the
propeller ammeter needle may be noted.

NOTE: The heating sequences for the De-ice Boots noted in the preceding section
are the sequences which are in evidence during normal operation. However,
due to the fact that the timer does not return to a given point when the control
switch is shutoff, sequential operation may start at any point in the cycle.
Power to the heating elements in the propeller boots is cycled in a
continuous programed sequence.

30-61-00-05 Inspection
Periodic Inspection
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 147, ATA REF 61-00-47)
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Owner’s Manual and Logbook
(Manual No. 486, ATA REF 61-00-86)
Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).

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Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible De-ice Boot parts for surface damage.

30-61-00-10 Troubleshooting
Testing and fault isolation shall be accomplished in accordance with the applicable Beechcraft King
Air Maintenance Manual and the Hartzell maintenance manuals listed in 30-61-00-20, below.

30-61-00-20 Maintenance Practices

Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 147, ATA REF 61-00-47)
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Owner’s Manual and Logbook
(Manual No. 486, ATA REF 61-00-86)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).

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30-61-10-97 90 Series Quiet Turbofan Propellers De-Ice Wiring

Reference TABLE 1 and TABLE 2 for component identification. All diagrams represent the “as
changed” configuration after the installation of Raisbeck/Hartzell Quiet Turbofan Propellers or Swept
Turbofan Propellers. The NEXTANT G90XT does not require modification to its wiring configuration.

NOTE: G90XT aircraft are C90A aircraft equipped with GE H75-100 engines per
Nextant Aerospace STC SA01902CH.
FIGURE 1 65-A90, B90 LJ-76, LJ-114 thru LJ-326
FIGURE 2 B90 LJ-327 thru LJ-501
FIGURE 3 C90 LJ-502 thru LJ-574
FIGURE 4 C90 LJ-575 thru LJ-707
FIGURE 5 C90 LJ-708 thru LJ-953
FIGURE 6 C90 LJ-954 thru LJ-1062
FIGURE 7 C90A LJ-1063 thru LJ-1265
FIGURE 8 C90A, C90GT, C90GTi LJ-1266 and After
FIGURE 9 E90 LW-1 thru LW-208
FIGURE 10 E90 LW-209 thru LW-272
FIGURE 11 E90 LW-273 thru LW-347

30-61-11-97 90 Series Swept Turboprop Propellers De-Ice Wiring

Reference Chapter 30-61-10-97 of this Manual.

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30-61-10-97 FIGURE 1 65-A90, B90 LJ-76, LJ-114 THRU LJ-326

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30-61-10-97 FIGURE 2 B90 LJ-327 THRU LJ-501

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30-61-10-97 FIGURE 3 C90 LJ-502 THRU LJ-574

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30-61-10-97 FIGURE 4 C90 LJ-575 THRU LJ-707

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30-61-10-97 FIGURE 5 C90 LJ-708 THRU LJ-953

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30-61-10-97 FIGURE 6 C90 LJ-954 THRU LJ-1062

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30-61-10-97 FIGURE 7 C90A LJ-1063 THRU LJ-1265

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30-61-10-97 FIGURE 8 C90A, C90GT, C90GTI LJ-1266 AND AFTER

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30-61-10-97 FIGURE 9 E90 LW-1 THRU LW-208

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30-61-10-97 FIGURE 10 E90 LW-209 THRU LW-272

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30-61-10-97 FIGURE 11 E90 LW-273 THRU LW-347

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TABLE 1 90 Series Wiring Diagrams

FIGURE 1 thru FIGURE 6, FIGURE 9 thru FIGURE 11

ITEM DESCRIPTION PART NUMBER MANUFACTURER

7270-1-25
1 Switch/Circuit Breaker or Klixon
270-5-25

2 Ammeter 90-380007-13 Beechcraft

3 Shunt 90-380008-1 Beechcraft

4 Relay MS24187D1 Beechcraft

3E1964-3 Goodrich/UTC
5 Timer or
C45114 McCauley

4E1311-2
6 Brush Block Assembly Goodrich/UTC
Obsolete

7 Modular Brush Block Assembly 3E2044-1 Goodrich/UTC

Universal Replacement Brush 3E2011-10

8 Goodrich/UTC
Module Assembly

TABLE 2 90 Series Wiring Diagrams

FIGURE 7 & FIGURE 8

ITEM DESCRIPTION PART NUMBER MANUFACTURER

F170 Limiter ACH30 Beechcraft

K132 Relay KC-J2A Leach

A151M4 Ammeter 90-380007-13 Beechcraft

R111 Shunt MS91586-1 Beechcraft

3E1964-3
Goodrich/UTC
M125 Timer or
McCauley
C45114

SR1 Modular Brush Block 3E2090-1 Goodrich/UTC

Universal Replacement Brush 3E2011-10

-- Goodrich/UTC
Module Assembly

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30-61-20-97 F90 Series Quiet Turbofan Propellers De-Ice Wiring

Diagrams
Reference TABLE 1 for component identification. All diagrams represent the “as changed”
configuration after the installation of Raisbeck/Hartzell Quiet Turbofan Propellers or Swept Turbofan
Propellers.
FIGURE 1 F90 LA-2 thru LA-55
FIGURE 2 F90 LA-56 thru LA-130

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30-61-20-97 FIGURE 1 F90 LA-2 THRU LA-55

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30-61-20-97 FIGURE 2 F90 LA-56 THRU LA-130

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TABLE 1 F90 Wiring Diagrams

FIGURE 1 & FIGURE 2

ITEM DESCRIPTION PART NUMBER MANUFACTURER

LH and RH Prop De-ice Circuit MS25244-25

1 Commercially Available
Breaker

2 Prop De-ice Control Circuit Breaker MS22073-5 Commercially Available

7270-1-25 OR
3 Main Prop De-ice Circuit Breaker KLIXON
7270-5-25

4 Manual Prop De-ice Control Switch 8812K14 Texas Instruments

5 Shunt MS91586-1 Commercially Available

109-384006-1
6 Ammeter or Beechcraft
109-384006-1

3E1964-3
Goodrich/UTC
7 De-ice Timer or
McCauley
C45114

Inner and Outer Prop De-ice KC-J2A

8 Leach Relay
Manual Override Relay

9 Electric Heat Lockout Relay 50-380048-1 Beechcraft

10 Modular Brush Block Assembly 3E2044-1 Goodrich/UTC

11 Ammeter Select Switch 44A60-03-1-04N Commercially Available

Universal Replacement Modula 3E2011-10

12 Goodrich/UTC
Brush Block Assembly

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30-61-30-97 100 Series Quiet Turbofan Propellers De-Ice Wiring

Diagrams
Reference TABLE 1 for component identification. All diagrams represent the “as changed”
configuration after the installation of Raisbeck/Hartzell Quiet Turbofan Propellers or Swept Turbofan
Propellers.
FIGURE 1 100 B-2 thru B-24
FIGURE 2 100 B-25 thru B-89, B-93
FIGURE 3 A100 B-1, B-90 thru B-92, B-94 thru B-154
FIGURE 4 A100 B-155 thru B-223
FIGURE 5 A100 B-224 thru B-232
FIGURE 6 A100 B-233 and After

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30-61-30-97 FIGURE 1 100 B-2 THRU B-24

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30-61-30-97 FIGURE 2 100 B-25 THRU B-89, B-93

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30-61-30-97 FIGURE 3 A100 B-1, B-90 THRU B-92, B-94 THRU B-154

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30-61-30-97 FIGURE 4 A100 B-155 THRU B-223

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30-61-30-97 FIGURE 5 A100 B-224 THRU B-232

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30-61-30-97 FIGURE 6 A100 B-233 AND AFTER

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TABLE 1 100, A100 Wiring Diagrams

FIGURE 1 & FIGURE 2

ITEM DESCRIPTION PART NUMBER MANUFACTURER

7270-1-25 OR
1 Switch/Circuit Breaker Klixon
7270-5-25

2 Electric Heat Lockout Relay MS24187-D1 Commercially Available

3 Shunt MS91586-1 Commercially Available

4 Ammeter 50-380086-9 Beechcraft

3E1964-3
Goodrich/UTC
5 Timer or
McCauley
C15114

6 Timer Select Relay MS24187-D1 Commercially Available

7 De-ice Fuse MDA30 Commercially Available

4E1311-2
8 Brush Block Assembly Goodrich/UTC
Obsolete

9 Modular Brush Block Assembly 3E2044-1 Goodrich/UTC

Universal Replacement Modular 3E2011-10

10 Goodrich/UTC
Brush Block

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30-61-40-97 200 Series Quiet Turbofan Propellers De-Ice Wiring

Diagrams
Reference TABLE 1 for component identification. All diagrams represent the “as changed”
configuration after the installation of Raisbeck/Hartzell Quiet Turbofan Propellers or Swept Turbofan
Propellers.
FIGURE 1 BB-2 thru BB-828, BB-830 thru BB-853, BB-871 thru BB-873, BB-892, BB-893,
BB-895, BB-912
BL-1 thru BL-29
BT-1 thru BT-22
BN-1
FIGURE 2 BB-829, BB-854 thru BB-870, BB-874 thru BB-891, BB-894, BB-896 thru BB-911,
BB-913 and After
BL-30 and After
BT-23 and After
BN-2 and After
BY-1 and After
BZ-1 and After

30-61-41-97 200 Series Swept Turbofan Propellers De-Ice Wiring

Diagrams
Reference Chapter 30-61-40-97 of this manual.

30-61-42-97 200 Series Five-Blade Swept Turbofan Propellers De-Ice

Wiring Diagrams
Reference Chapter 30-61-40-97 of this manual.

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30-61-40-97 FIGURE 1 200 SERIES: BB-2 THRU BB-828, BB-830 THRU BB-853, BB-871 THRU BB-873, BB-892, BB-893, BB-895, BB-912, BL-1 THRU BL-29, BT-1 THRU BT-22, BN-1

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30-61-40-97 FIGURE 2 200 SERIES: BB-829, BB-854 THRU BB-870, BB-874 THRU BB-891, BB-894, BB-896 THRU BB-911, BB-913 AND AFTER, BL-30 AND AFTER, BT-23 AND AFTER, BN-2 AND AFTER,
BY-1 AND AFTER, BZ-1 AND AFTER

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TABLE 1 200 Series Wiring Diagrams

FIGURE 1 & FIGURE 2

ITEM DESCRIPTION PART NUMBER MANUFACTURER

AS25244-25
LH and RH Prop De-ice Circuit
1 or Commercially Available
Breaker
MS25244-25

Manual Prop De-ice Center Circuit

2 7277-2-5 Texas Instruments
Breaker

Prop De-ice Control Circuit 7270-1-5 OR

3 Klixon
Breaker/Switch 7270-5-25

4 Manual Pop De-ice Control Switch 8812K14 Texas Instruments

90-380007-13 (New)
or
90380007-9
5 Prop De-ice Ammeter Beechcraft
or
101-389017-9
(Modified)

6 Shunt 90-380008-1 Beechcraft

3E1964-3
Goodrich/UTC
7 Prop De-ice Timer or
McCauley
C45114

Inner and Outer Prop De-ice

8 KC-J2A Leach Relay
Manual Override Relay

4E1311-2
9 Brush Block Assembly Goodrich/UTC
OBSOLETE

10 Modular Brush Block Assembly 3E2044-1 Goodrich/UTC

Universal Replacement Brush

11 2E2011-10 Goodrich/UTC
Module Assembly

12 MOV Module 106343 Hartzell

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30-61-50-97 B300/B300C Quiet Turbofan Propellers De-Ice Wiring

Diagrams
This Section intentionally left blank.

30-61-51-97 300/300LW, B300/B300C Four-Blade Swept Turbofan

Propellers De-Ice Wiring Diagrams
Reference the applicable Beechcraft King Air 300 Series Wiring Manual.

30-61-52-97 300/300LW, B300/B300C Five-Blade Swept Turbofan

Propellers De-Ice Wiring Diagrams
Reference the applicable Beechcraft King Air 300 Series Wiring Manual.
FIGURE 1 REMOVED
FIGURE 2 REMOVED
FIGURE 3 REMOVED
FIGURE 4 REMOVED
FIGURE 5 METAL OXIDE VARISTOR (MOV) MODULE WIRING DIAGRAM
FA-2 AND AFTER
FF-1 AND AFTER
FL-1 AND AFTER
FM-1 AND AFTER
FN-1 AND AFTER

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FIGURE
REMOVED

31-61-52-97 FIGURE 1

FIGURE
REMOVED

30-61-52-97 FIGURE 2

FIGURE
REMOVED

30-61-52-97 FIGURE 3

FIGURE
REMOVED

30-61-52-97 FIGURE 4

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30-61-52-97 FIGURE 5 300/300LW, B300/B300C: FA-2 AND AFTER, FF-1 AND AFTER, FL-1 AND AFTER, FM-1 AND AFTER, FN-1 AND AFTER

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Ram Air Recovery System

30-72-00-00 Description and Operation
The Ram Air Recovery system augments the existing inertial ice separation system. A fixed turning
vane and trailing edge flap on the inertial ice vane improves the airflow into the engine inlet.

30-72-00-00 FIGURE 1

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30-72-00-05 Inspection
Periodic Inspections
The maintenance tests on the Raisbeck Ram Air Recovery System should be done at the same time
as the existing Beechcraft maintenance tests as described in the Beechcraft Super King Air 200
Series Maintenance Manual, Chapter 5.
Reference FIGURE 1
1. Examine the Bulb Seals for security and condition.
2. Examine the Diaphragm Seals for security and condition.
3. Examine the Bypass Door Seals for security and condition.
4. Examine the Particle Separator for security and condition.
5. Examine the Fixed Turning Vane for security and condition.
6. Examine the Ice Shedder Screen for security and condition.
Daily Checks
There are no Daily Checks the Ram Air Recovery System.

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30-72-00-05 FIGURE 1

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30-72-00-05 FIGURE 2

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30-72-00-10 Troubleshooting
Perform a functional test of the Bypass Door and Particle Separators in accordance with the
Beechcraft Super King Air 200 Series Maintenance Manual, Chapter 30.

NOTE: The curved turning vane tends to try to deploy the Particle Separator due to
aerodynamic forces. Account for this when adjusting the microswitches for
the annunciator light.
When the Inertial Particle Separators are deployed at high indicated airspeeds, binding in the
Beechcraft actuation mechanism can cause the separator doors to remain deployed as long as the
airspeed is high. This can be caused by parts of the Beechcraft mechanism that are worn, broken, or
binding. Examine components every time the lower cowling is removed or at 200 hour intervals,
whichever occurs first.
There are no approved repairs on any Raisbeck Ram Air Recovery System component. Replace any
damaged or worn components.
1. Disconnect the Particle Separator Actuator Rod and inspect the piano hinge for condition,
security, and freedom of movement.
2. Inspect rod ends for condition, security, and freedom of movement.
3. Adjust the linkage in accordance with Chapter 30-72-00-20 of this manual.

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30-72-00-20 Maintenance Practices

Repair/Replacement
All of the Raisbeck Engineering Ram Air Recovery System components are replaced “On Condition”.
“On Condition” items are to be replaced when inspection or performance of item reveal a potentially
unsafe condition or reduction in performance.
Examples of unsafe conditions are: propagating cracks, enlarged fastener holes that do not meet
minimum edge distance requirements, and/or damaged/missing fasteners. Part distortion and/or
deterioration of seals will affect the system’s performance and should be replaced.
There are no authorized repairs for any Raisbeck Ram Air Recovery component. Replace damaged
components as necessary.
Functional Test/adjustment
Perform a functional test of the Bypass Door and Particle Separator as given in the Beechcraft Super
King Air 200 Series Maintenance Manual, Chapter 30.
Bypass Door Adjustment
Make the adjustment of the Bypass Door as given in the Beechcraft Super King Air 200 Series
Maintenance Manual, Chapter 30. The Bypass Door must have a tight fit in the nacelle opening when
the door is closed to ensure the effectiveness of the Ram Air Recovery System.
Particle Separator Adjustment
1. Adjust the length of the linkage as necessary so that the Particle Separator assembly touches the
entire width of the fixed turning vane.
2. Preload the Particle Separator assembly by turning the linkage adjustment a maximum of one-
quarter (¼) turn.

CAUTION: EXCESSIVE PRELOAD CAN RESULT IN DAMAGE.

3. Secure jam nuts with .032 inch stainless steel lockwire.
4. Cycle the Particle Separator and verify smooth operation and annunciation.
5. Adjust the microswitches as needed for annunciation.

NOTE: The curved turning vane tends to try to deploy the Particle Separator due to
aerodynamic forces. Account for this when adjusting the microswitches for
the annunciator light.

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32 Landing Gear
Fully Enclosed Main Landing Gear Doors
32-00-00-00 Description and Operation
The Raisbeck Engineering High Flotation Gear Door System replaces the high flotation main gear
doors and their related actuation mechanism with new doors and mechanism that completely enclose
the main landing gear when it is retracted.

32-00-00-05 Inspection
Periodic Inspections
The maintenance tests on the Raisbeck Engineering High Flotation Gear Doors shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
applicable Beechcraft Maintenance Manual, Chapter 5.
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine doors, hinges, and mechanism for satisfactory condition.
2. Examine the mechanism attachment for security.

32-00-00-10 Troubleshooting
Reference the applicable Beechcraft King Air Maintenance Manual, Chapter 32, for troubleshooting
the retraction of the Main Landing Gear. Adjust the Fully Enclosed Main Landing Gear Doors per
Chapter 32-00-00-20 of this manual.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

32-00-00-20 Maintenance Practices

Repair/Replacement
All of the Raisbeck Engineering High Flotation Gear Door components are repaired or replaced “On
Condition”. “On Condition” items are to be repaired or replaced when inspection or performance of
items show a potentially unsafe condition or reduction in performance.
Repair and refinish gear door system composite (fiberglass) components as given in the Raisbeck
Structural Inspection and Repair Manual (SIRM).
Repair all other gear door components per AC 43.13 “Acceptable Methods, Techniques, and
Practices Aircraft Inspection and Repair.
Rigging Adjustment 65-90, 65-A90, B90, C90, C90A, C90GT, E90
This section reserved.
Rigging Adjustment 100, A100, B100, F90, 200 Series, B300/B300C
Make the adjustments given below in the sequence given. Each time the door linkage is adjusted,
the over-center dimension, the tire clearance, and the fit of the closed gear doors must be tested.
1. Jack the aircraft per the applicable Beechcraft King Air Maintenance Manual.
2. Adjust the landing gear as given in the applicable Beechcraft King Air Maintenance Manual
Chapter 32.
3. Remove the bolt, washer, nut, and other cotter pin from the clevis, and disconnect the lower
clevis from the plate attached to the clevis. Examine the cam, link, and both clevises for correct
and smooth operation throughout normal travel. Make an adjustment to the clamp-up (torque) of
the pivot bolts.
4. With the gear fully extended and the cam against the door hinge extrusion:
a. Put the upper edge of a straightedge at the centerline of the link mounting bolt and the lower
edge at the centerline of the bolt that attaches the lower clevis to the plate on the door as
shown in FIGURE 1.
b. When each door locks in the open position make sure that the center line of the upper clevis
bolt is not over-center by more than .06 in as measured from the attachment point of the
bottom clevis to the linkage.
5. With the landing gear retracted, adjust the clevis that connects the upper link to the cam until the
door closes for a tight fit.
6. Ensure the actuator roller aligns with the center of the cam slot and does not bottom out when the
doors are closed. Examine for a clearance of .04 to .08 inch between the actuator roller and the
adjusting block of the cam. If necessary, change the position of the adjusting block to get the
correct clearance.
7. Retract the gear as necessary to examine for a minimum clearance of 1.0 inch between the tire
and the door. If the door clearance is satisfactory, retract the gear and make sure that the doors
are correctly closed. If the doors do not close flush or are too tight, adjust the door linkage again
to achieve correct fit. Adjust the upper and lower pivots, or change the location of the slotted
attachment plate on the door.
8. Apply 25 pounds towards the gear at the lower center edge of the door to make sure that the door
linkage is correctly over-centered when open. This ensures that each door is locked open to
withstand the air loads during takeoff and landing. Adjust the door as necessary if the door
closes under the 25 pound load.
9. Operate the landing gear several times to make sure that the doors close correctly when the gear
is retracted, and that they stay open when the gear is extended.

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30-00-00-20 FIGURE 1
Functional Test 65-90, 65-A90, B90, C90, C90A, C90GT, E90
This section reserved.
Functional Test 100, A100, B100, F90, 200 Series, B300/B300C
1. Perform a landing gear retraction test as given in the applicable Beechcraft King Air Maintenance
Manual, Chapter 5.
2. Perform a manual extension of the landing gear as given in the applicable Beechcraft King Air
Maintenance Manual, Chapter 32.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

50 Cargo and Accessory Compartments

Nacelle Wing Lockers
50-00-00-00 Description and Operation
The Raisbeck Engineering Nacelle Wing Locker System and Crown Wing Locker System are
specifically designed to transport long and otherwise unwieldy cargo that presently may not be
possible.

50-00-00-05 Inspection
Periodic Inspections
Conduct the maintenance tests on the Raisbeck Engineering Nacelle and Crown Wing Lockers in
conjunction with the existing Beechcraft maintenance tests as given in the applicable Beechcraft King
Air Maintenance Manual, Chapter 5.
1. Inspect the hinges, latches, seals, and gas struts for condition and operation. Replace as
necessary.
2. Examine Lockers for security of attachment. Repair as necessary.
3. Ensure proper application of anti-static coating to all countersunk screw locations. The bare
metal surface of the large area washers must have direct contact with the anti-static coating of
the locker for the fastener to provide a ground path between the wing locker and the airframe.
For Super King Air Models 200, B200, and B200GT Series Aircraft Equipped with BLR Gurney
Flap:
1. Inspect the BLR Gurney Flaps for security and condition. Inspect the trimmed section of the flap
for deformity, cracking, and finish integrity. Contact BLR for replacement Gurney Flap parts.
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine Lockers for condition.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

50-00-00-20 Maintenance Practices

Short-Skirt Wing Locker Removal
Reference FIGURE 1
1. Open the Wing Locker Door to gain access to the rear attach bolts.
2. Remove the Bolts NAS6204-( ), NAS1104-( ), or AN4-( )A, that mate with permanently mounted
nut plates; two places from the rear attach points of the locker.
3. Remove the screws and countersink washers from the forward edge of the wing locker.
4. Remove the screws from the outboard, inboard, and upper fairings.
5. Lift the locker aft and remove it from the airplane. Record the number of, thickness of, and
position of the Aluminum Spacers (85-3510-125 or -157) that are used between the wing surface
and the locker at the two aft attach points of the locker.
Short-Skirt Wing Locker Installation
Reference FIGURE 1
1. Examine to make sure that rubber Spacers 85-3510-131 are bonded to the wing surface.

NOTE: The rubber Spacers are not intended to support the locker during normal
loading conditions. They are in place to protect the wing skin in the event of
an over-loading.
2. Position the Aluminum Spacers (85-3510-125 or -157) as recorded in Step 5 of the removal
instructions.
3. Place the locker into position on the wing.
4. Install Bolts NAS6204-( ), NAS1104-( ) or AN4-( )A, two places at the rear attach points of the
locker.
5. Install the screws and the countersink washers in the forward edge of the wing locker.
6. Install the screws in the outboard, inboard, and upper fairing.
Long-Skirt Wing Locker Removal
Reference FIGURE 1
1. Remove the screws (NAS514P1032-8) from the Ice Light Plate.
2. Slip the Ice Light Plate through the opening or disconnect and remove the light.
3. Remove the 14 screws (NAS517-3-3) and countersunk washers (A3235-028-193, or
A3235-028-24A) from the inboard and outboard forward edge of the locker.
4. C90 Series only. Remove the 4 screws (NAS517-3-3) from around the fuel fill cut out.
5. Remove the 2 rear attach bolts (NAS1104-20 or AN4-15A) and washers (AN970-4).
6. Move the locker aft and lift and remove it from the airplane. Record the number of, thickness of,
and position of the Aluminum Spacers (85-3510-125 or -157) that are used between the wing
surface and the locker at the two aft attach points of the locker.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Long-Skirt Wing Locker Installation

Reference FIGURE 1
1. Examine to make sure that Spacers 85-3510-131 are bonded to the wing surface.
2. Position the spacers (85-3510-125 or -157) as recorded in Step 6 of the removal instructions.
3. Place the locker into position on the wing.
4. Install the 2 rear attach bolts (NAS1104-20 or AN4-15A) and washers (AN970-4).
5. C90 Series only. Install the 4 screws (NAS517-3-3) from around the fuel fill cut out.

CAUTION: THE LEADING EDGE OF THE LOCKER MUST BE FITTED FIRMLY

DOWN AGAINST THE NACELLE AND FLUSH TO THE FORWARD
FAIRING.
6. Install the 14 screws (NAS517-3-3) and countersunk washers (A3235-028-193, or A3235-028-
24A) from the inboard and outboard forward edge of the locker. Ensure the leading edge of the
locker is fitted firmly down against the nacelle and flush to the forward fairing.
7. Install the Ice Light.
Long-Skirt Wing Locker Removal Factory Installed on B300

NOTE: For lockers that incorporate the optional extended range fuel tank mounts.
Reference FIGURE 1
1. Remove the 6 screws (NAS514P1032-8) from the Ice Light Plate.
2. Slip the Ice Light Plate through the opening or disconnect and remove the light.
3. Remove the 14 screws (NAS517-3-3) and countersunk washers (A3235-028-193, or A3235-028-
24A) from the inboard and outboard forward edge of the locker.
4. Remove the bolts washers bushings, and lock nuts from the aft mounts.
5. Lift the locker aft and lift and remove it from the airplane.
Long-Skirt Wing Locker Installation Factory installed on B300

NOTE: For lockers that incorporate the optional extended range fuel tank mounts.
Reference FIGURE 1
1. Place the locker into position on the wing.
2. Install the bolts washers bushings, and lock nuts in the aft mounts.

CAUTION: THE LEADING EDGE OF THE LOCKER MUST BE FITTED FIRMLY

DOWN AGAINST THE NACELLE AND FLUSH TO THE FORWARD
FAIRING.
3. Install the 14 screws (NAS517-3-3) and countersunk washers (A3235-028-193, or A3235-028-
24A) in the inboard and outboard forward edge of the locker. Ensure the leading edge of the
locker is fitted firmly down against the nacelle and flush to the forward fairing.
4. Install the Ice Light.

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50-00-00-20 FIGURE 1

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Door Seal Replacement

Reference FIGURE 2
1. Remove the latch striker plate.
2. Remove the door seal.
3. Remove the adhesive residue with MEK and a clean, oil free cloth.
4. Starting at the aft, center of the door opening, install the seal using 3M 1300 or 1300L neoprene
adhesive.
5. Allow the adhesive to fully cure and ensure seal contact around the entire periphery of the door
opening.
6. Ensure seal contact around the periphery of the door. Insert a sheet of copier paper between the
door and seal and latch the door. The paper should not be easily pulled out of position. Adjust
the door brackets as necessary to achieve a proper seal.

50-00-00-20 FIGURE 2

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Wing to Locker Seal Replacement

Reference FIGURE 3
1. Remove the locker in accordance with Chapter 52-00-00-20 of this manual.
2. Remove the seal retainers, P/N 85-3510-217 and 85-3510-215 or 85-3510-219 (similar to 85-
3510-217 and 85-3510-215).
3. Remove the old adhesive residue. If the composite is exposed during this process, refinish all
exposed laminate in accordance with Chapter 51-20-11-00 of this manual.
4. Install seals (85-3570) on locker using sealant, PPG P/S 890, PPG PR-1440, or PPG PR-1422.
Trim the forward section of the seal to fit flush with the nacelle and to fit with the retainers. Drill
holes through seal, locker, and retainer (2 places each) and install seal retainer (85-3510-215
inboard and 85-3510-217 outboard) with rivet (NAS1097AD4-4). Countersink rivets and shave
bucked heads flush.

50-00-00-20 FIGURE 3

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Pin Latch Replacement

Reference FIGURE 4
1. Remove six (6) screws (MS24693-C50), washers (NAS1149CN832R), and nuts (MS21083C8).
2. Remove the pin latch using a thin putty knife to separate the fay seal between the door and latch.
Use caution to avoid damaging the fiberglass. Any damage must be repaired before installing the
new latch. Low level heat, not to exceed 165 °F, may be applied to soften the sealant.
3. Remove all sealant and shims from latch well. Refinish latch well surface as required.
4. Install new pin latch, fay sealing with Class B sealant, PPG P/S 890, PPG PR-1440, or PPG PR-
1422. Shim as required to achieve periphery flushness to door +.0/-.125 inch.
5. Reinstall screws (MS24693-C50), washers (NAS1149CN832R), and nuts (MS21083C8).
6. Remove excess sealant and engage pin latch to check for fit and alignment.
7. Adjust the latch receiver as necessary. Reference Bayonet and Pin Latch Receiver Adjustment
(below) and FIGURE 6.

50-00-00-20 FIGURE 4

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Bayonet Latch Replacement

Reference FIGURE 5
1. Remove six (6) screws (MS24693-C27), nuts (NAS679C06), and washers (AN960C6).
2. Remove latch trim plate (85-3520-059).
3. Remove nut (NAS679A08), washer (AN960-8), and screw (AN525-832R26).
4. Remove nut (NAS679A3), washer (AN960-10), and bolt (AN3-16A).
5. Remove latch assembly (H3-1714-2) or (85-3521-7).
6. Clean grease from latch pocket.
7. Inspect grommet (MS35489-38) and replace as necessary.
8. Install new latch assembly (H3-1714-2) or (85-3521-7) with nuts (NAS679A08), washers
(AN960-8), and screws (AN525-832R26), and nuts (NAS679A3), washers (AN960-10), and bolts
(AN3-16A).
9. Use a standard grease gun with a 2-inch needle attachment to fill the forward end of the latch
pocket with Grease, Type B, Class III, Grade 2 (Ref 12-00-00-20, Table 2). Inject grease at the
bottom of the well. Allow it to fill the complete forward portion of the cavity. Apply a uniform
finger pressure to the grease to force the grease into the cavity. Make sure that all air bubbles
are removed and that grease completely covers the rubber grommet.
10. Install latch trim plate with screws (MS24693-C27), nuts (NAS679C06), and washers (AN960C6).

NOTE: All fasteners are installed wet with RTV108.

50-00-00-20 FIGURE 5

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Bayonet and Pin Latch Receiver Adjustment

Reference FIGURE 6
1. Loosen bolts (AN3-3A) and nuts (NAS679A3) enough to allow movement of the adjustment
bracket and hold position.
2. Press clay against the latch receiver and adjustment bracket assembly.
3. Close the door and close latch lever enough for the latch pin (bayonet or pin latch) to leave an
impression in the clay.
4. Move the latch receiver and adjustment bracket assembly to center the latch receiver on the
location of the impression left in the clay.
5. Repeat Steps 2 through 4 as necessary to achieve proper pin engagement.
6. Tighten the nuts and bolts.
7. To check for a proper seal, place a sheet of paper between the door and seal. Shut the door and
close the latches. The paper should hold firm when pulled. Repeat test along the periphery of
the door. Move the latch receiver and adjustment bracket assemblies as necessary to achieve a
proper seal.

50-00-00-20 FIGURE 6

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Gas Spring (85-3520-077) Replacement

Reference FIGURE 7
1. Remove nut (NAS679A4), washers (AN960-416), spacers (NAS43DD4-8), and Bolt (AN4-13A)
from bracket (85-3520-73).
2. Remove gas spring (85-3520-077).
3. Install new gas spring (85-3520-077) in reverse order noting orientation of gas spring.

NOTE: Gas Spring, Part Number 85-3520-077, has been superseded by Gas
Spring, Commercial Part Number C16-26918 (not illustrated in FIGURE 7).
85-3250-077 may be used until stock is exhausted.

Gas Spring (85-3520-098) Replacement

Reference FIGURE 7
1. Remove nut (NAS679A4), washers (AN960-416), and bolt (AN4-13A) from bracket (85-3520-73).
2. Remove gas spring (85-3520-098).
3. Install new gas spring (85-3520-09) in reverse order. Note orientation of gas spring.

NOTE: Gas Spring, Part Number 85-3520-098, has been superseded by Gas
Spring, Commercial Part Number C16-26918 (not illustrated in FIGURE 7).
85-3250-098 may be used until stock is exhausted.

52-00-00-20 FIGURE 7

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Wing Locker Door Hinge Replacement

Reference FIGURE 8
1. Disconnect gas spring from bracket (85-3520-73). Reference Gas Spring (85-3520-077) or (85-
3520-098) Replacement (above).
2. Remove screws (MS24694-S51), washers (NAS1169DD10L), screws (AN525-10R8), bolts (AN3-
4A), and washers (AN970-3) from locker door and hinges (85-3560-1 or 85-3560-2).
3. Remove hinge assembly from locker door.
5. Install new hinges in reverse order, fay sealing with sealant, PPG P/S 890, PPG PR-1440, or
PPG PR-1422. Remove excess squeeze out.

50-00-00-20 FIGURE 8

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

51 Standard Practices and Structures

51-00-00-00 Description
This section provides information for acceptable repairs and repair limits for selected Raisbeck
Systems components. In general, the repair methods used on all Raisbeck Systems may be in
accordance with AC43.13-1A Aircraft Inspection and Repair Manual and AC43.13-2 Aircraft
Alterations Manual. The repair information below is recommended in addition to the information given
in AC43.13-1A and AC43.13-2.
It is the responsibility of the owner or facility performing the work to obtain approval of their particular
repair.

51-00-11-00 Composite Description

This section gives instructions for the repair of fiberglass components made from epoxy resin that is
reinforced with several layers of glass fabric. Some components use a sandwich construction with a
non-metallic core. This section describes two methods of repair – Wet Layup and Prepreg Layup.
The wet layup repair method is acceptable on all components (except on the leading edge for
damage greater than 2 inches in diameter). The wet layup method uses fabric impregnated with
epoxy resin during repair work. This method will cure at room temperature.
The prepreg layup uses the preimpregnated fabric with epoxy resin and requires a control
temperature (250 F) cure with a vacuum pressure. This method must be used for repairs on the
leading edge with damage larger than 2 inches in diameter.

51-11-11-20 Wet Layup Repair Maintenance Practices

The following repairs may be performed on any of the Raisbeck fiberglass components. The repair
size is limited to the ability to keep the component contours (except on the leading edge) where
damage is larger than 2 inches in diameter. The repairs can be round or rectangular with round
corners.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Materials
a. Fabric
Style 181 - Hexcel Corporation
- Burlington Glass Fabrics Company
- J.P. Stevens & Company
- Fiberite West Coast Corporation
b. Parting Film
a. Polyethylene Film - Any sources
b. Polyvinyl Alcohol Film - Reynolds Metals
c. A4000 - Airtech International
d. HS8171 Vac Pack - Richmond Corporation
c. Resin
a. FR40 Resin and 5413C Hardener - Fiberesin Corporation
b. Epocast 50A plus 9816* - Furane Products
c. Epocast 50A plus 946 or 9449 - Furane Products
* 16 to 24 hour cure at room temperature.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

General – Repair And Refinishing Instructions

1. Remove paint approximately 1 inch beyond the repair area. Strip paint with paint stripper (PPG-
Eldorado PR-4028LO [preferred] or PR-2002) or remove by wet sanding, with 220-grit or better
abrasive, until outer layer of resin is lightly abraded over entire surface.
2. Examine the area around the damage for evidence of water, oil, fuel, or other foreign matter.
Examine for delamination around the damage.
a) Delamination can be detected by tapping the skin with a metallic object, such as a half dollar
coin.
b) If the damage to the core material is greater than one (1) inch as shown in Figure 8-3, repair
the damaged core material as shown in 51-11-11-20, FIGURE 6.
3. Trim out the damaged laminates and core, where the core is also damaged. Areas contaminated
by water that cannot be dried out by heating must be removed with the damaged material.
4. Cut the fabric as shown in the applicable repair figure.
5. Cut 2 pieces of parting film approximately 2 inches longer than each fabric ply and tape one piece
of each size film to a smooth flat surface.
6. When the applicable repair preparation work is complete, clean the rework area with oil-free air.
Wipe the surface with a clean cloth moistened with methyl ethyl ketone (MEK).
7. Mix resin as given in the manufacturer’s recommendations and apply to each taped-down piece
of parting film. Put the fabric over the resin and press into resin. Apply resin over top of fabric
and apply the second piece of parting film. Use a roller or a squeegee to press the resin into the
fabric to eliminate any entrapped air.
8. Remove the parting film from the smallest ply and put on the repair area. Smooth the fabric into
place.
9. Use the next largest ply and repeat Steps 8 and 9 until all plies are in position.
10. Cover the entire rework area with a piece of parting film. With a squeegee remove excess resin
form the repair. Air bubbles should be removed with the squeegee. Use caution to not remove
too much resin when removing excess resin or air bubbles.

NOTE: Cure time may be decreased to 2 hours by applying uniform heat (150 F
±100 F) to the part.

11. Allow the repair to completely cure. Remove the parting film. Sand edges to match contour and
fill pinholes with Bostik Epoxy Filler Putty (467-9). Apply Epoxy Surfaces Spray (464-3-1) with
Catalyst-Bostik Finish (CA-142) or Desoto Primer Surfacer (513-009) with Catalyst (910-077).
12. Sand area lightly and wash with Isopropyl Alcohol. Finish with one coat of Class I Primer (MIL-
PRF-23377), Urethane Compatible Primer Yellow Base Desoto #513 X 329 or equivalent.
13. Apply Polyurethane or Epoxy Enamel top coat within 48 hours after primer application.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Repair Instructions for Damaged Laminated Plies

CAUTION: USE GREAT CARE NOT TO DELAMINATE THE OUTSIDE EDGES OF

REPAIR WHEN TRIMMING LAMINATE PLIES.
1. Remove the damaged plies and increase the cutout ½ inch for each ply removed from
undamaged ply out to the surface (Reference 51-11-11-20, FIGURE 1, Section A-A).
2. If damage was through all plies, install a dry fabric ply (peel off ply) or parting film with a metal
backup on the far side of repair during layup and cure. After cure, peel off ply or remove parting
film.

51-11-11-20 FIGURE 1

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Repair Instructions for Damaged Laminated Plies and Core

NOTE: If the core damage is greater than one (1) inch as shown in Figure 8-3, repair
the damaged core material as shown in 51-11-11-20, FIGURE 6.
Accomplish GENERAL REPAIR AND REFINISHING INSTRUCTIONS and
REPAIR INSTRUCTIONS FOR DAMAGED LAMINATED PLIES with the
additional instructions given below to repair damaged laminated plies with
core damage that is less than one (1) inch.
1. Remove core material a minimum of ¼ inch beyond the length of damage.
2. Remove the laminate ply next to the core ½ inch from the edge of the undamaged core.
3. Remove the next ply by cutting it ½ inch further away from the edge of the lower ply (REF 51-11-
11-20, Figure 8, Figure 2, or Figure 3). Repeat process until all plies are removed.
4. Install repair plies and parting film per GENERAL REPAIR AND REFINISHING INSTRUCTIONS,
on lower surface and tape a backup plate to match the contour.
5. Mix the Epocast potting compound per manufacturer’s recommendations and trowel into core
void and level even with the first ply layers (Ref. 51-11-11-20, Figure 8, Figure 2, or Figure 3).
Allow the potting compound to cure tack free.
6. Install upper surface repair plies and allow curing. After cure remove backup plate and parting
film.

51-11-11-20 FIGURE 2

51-11-11-20 FIGURE 3

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51-12-11-20 Prepreg Layup Fiberglass Repair

The repairs given as follows can be accomplished on any of the Raisbeck fiberglass components.
The repair size is limited to the ability to maintain component contours. The repairs may be round or
rectangular with rounded corners.
Materials
a. Fabric (Preimpregnated)
MXB7701/181-150/26040 -Fiberite West Coast Corp.
MXB7230-1581 -Fiberite West Coast Corp.
CE-306/7781 -Ferro Corp.
F-155/7781 -Hexel Corp.
FR-8600/7781 -Fiberesin Corp.

b. Film Adhesive
AF-126 -3M Company
FM-123-2 -American Cyanamid Co.

c. Core (Honeycomb)
HRH-10/0X-3/16-3 -Hexel Corp.
HRH-10/0X-3/16-4 -Hexel Corp.

d. Parting Film
Polyethylene Film -Any sources
Polyvinyl Alcohol Film -Reynolds Metals
A4000 -Airtech International
HS8171 Vac Pak -Richmond Corporation

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General – Repair and Refinishing Instructions

1. Remove paint approximately 1 inch beyond the rework area. Strip paint with paint stripper (PPG-
Eldorado PR-4028LO [preferred] or PR-2002) or remove by wet sanding, with 220-grit or better
abrasive, until outer layer of resin is lightly abraded over entire surface.
2. Examine area in the vicinity of damage for entry of water, oil, fuel or other foreign matter.
Examine for delamination around the damage.

NOTE: Delamination can be detected by tapping the skin with a metallic object, such
as a half dollar coin.
3. Trim out the damaged laminates and core, where the core is also damaged. Areas contaminated
by water that cannot be dried out by heating must be removed with the damaged material.
4. When the applicable repair preparation work is completed, clean the rework area with oil-free air.
Wipe the surface with a clean cloth moistened with MEK (Methyl-Ethyl-Ketone).
5. After repair laminated plies and/or core are assembled, accomplished the bagging procedure as
follows (Ref. 51-12-11-20, Figure 4).
6. Put a dry nylon peel ply over the last repair ply.
7. Space three thermocouples evenly around repair (at the outer edge).
8. Put parting film over the repair layup so the film edges extend 3 inches past repair edge. Put a
surface bleeder over the parting film (dry fabric cloth).
9. Put a heat blanket on the layup. Heat blanket area should be the same or slightly greater than
the parting film.
10. Put several plies of dry fabric breather cloth on the layup. Breather cloth must extend beyond the
parting film and heat blanket. The cloth also must make contact with peel ply.
11. Install an extruded sealing compound around the entire area. Tie in vacuum outlet.
12. Lay vacuum bag material over the entire area and seal edges.
13. Evacuate the space and maintain a minimum of 20 inches of mercury (inHg).
14. Cure the repair by heating repair to 260 F ±10 F. Temperature rise should not be greater than 8
F per minute. Hold at temperature for 90 minutes.
15. Release vacuum pressure after area has cooled to less than 125 F.
16. Remove all equipment and breather plies.
17. Sand edges to match contour and fill pinholes with Bostik Epoxy Filler Putty (467-9). Apply
Epoxy Surfacer Spray (464-3-1) with Catalyst-Bostik Finish (CA-142) or Desoto Primer Surfacer
(513-009) with Catalyst (910-077).
18. Sand area lightly and wash with Isopropyl Alcohol. Finish with one coat of Class I Primer (MIL-
PRF-23377), Urethane Compatible Primer Yellow Base Desoto #513 X 329 or equivalent.
19. Apply Polyurethane or Epoxy Enamel top coat within 48 hours after primer application.

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Repair Instructions for Damage of Laminated Plies

CAUTION: USE CARE NOT TO DELAMINATE THE OUTSIDE EDGES OF REPAIR

WHEN TRIMMING LAMINATE PLIES.
1. Remove the damaged plies and increase the cutout ½ inch for each ply removed from
undamaged ply out to the surface. (Ref. 51-12-11-20, FIGURE 2).
2. If damage was through all plies, install a dry fabric ply (peel off ply) or parting film with a metal
backup on the far side of repair during layup and cure. Repair will require bagging on both
surfaces. After cure, peel off ply or remove parting film.

CAUTION: USE CARE NOT TO DELAMINATE THE OUTSIDE EDGES OF REPAIR

WHEN TRIMMING LAMINATE PLIES.
3. Cut prepreg fabric to size for each ply removed, plus one extra repair ply per 51-12-11-20,
FIGURE 2.
4. Put a layer of adhesive film over the entire area.
5. Remove prepreg fabric polyethylene separator from each fabric path and apply plies, starting with
the smallest.
Repair Instructions for Damage Laminated Ply and Core
1. Remove the core material by trimming normal to the surface.
2. Remove the laminate ply next to the core ½ inch from the edge of the undamaged core.
3. Remove the next ply by cutting it ½ inch further away from the edge of the lower ply (REF
51-12-11-20, FIGURE 3). Repeat process until all plies are removed.
4. Fabricate core plug to fit flush with original core. The plug must overlap and make contact with
surrounding cord material.
5. Wrap core plug edges with adhesive and install.

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51-12-11-20 FIGURE 1

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51-12-11-20 FIGURE 2

51-12-11-20 FIGURE 3

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51-20-11-20 Repainting Fiberglass Components

The following instructions are for repainting all Raisbeck Fiberglass Components, if the paint has
peeled to a depth exposing fiberglass.

CAUTION: FOR LEADING EDGE ONLY: ENSURE THAT THE DEICE BOOT IS
FULLY PROTECTED BY MASKING THE BOOT AREA INCLUDING
SEALANT AROUND EDGES WITH VINYL TAPE. COVER BOOT WITH
VINYL SHEET AND TAPE WITH MASKING TAPE, OVERLAPPING
VINYL TAPE SLIGHTLY.
1. Mask off area to be repainted with vinyl tape.
2. Strip paint with paint stripper (PPG-Eldorado PR-4028LO [preferred] or PR-2002) or remove by
wet sanding, with 22-grit or better abrasive, until outer layer of resin is lightly abraded over entire
surface.

CAUTION: IF STRIPPER IS USED USE ONLY PR-4028LO OR PR-2002. IF

SANDING METHOD IS USED USE EXTREME CAUTION NOT TO
EXPOSE THE GLASS FABRIC.
3. Scrub surface with bristle brush and powder cleanser (Bon Ami) with water.
4. Wet sand lightly and wash with 1.1.1 Trichloroethane (Methyl Chloroform).
5. Fill exterior pinholes, if required, with Bostik Epoxy Filler Putty (467-9). Apply Epoxy Surfacer
Spray (464-3-1) with Catalyst-Bostik Finch (CA-142) or Desoto Primer Surfacer (512-009) with
Catalyst (910-077).
6. Sand lightly and wash with Isopropyl Alcohol.
7. Finish with one coat of Class I Primer (MIL-PRF-23377), Urethane Compatible Primer Yellow
Base Desoto #513-329, or equivalent.
8. After full cure of primer (24 hours at room temperature), a dry tape test to test paint adherence
may be accomplished as follows:
a. Apply 1 inch wide strip of Tape (3M250).
b. Press down firmly with burnisher of stiff putty knife, making sure there are no bubbles.
c. Remove tape with one abrupt jerk; paint should remain on component surface.
9. Apply first top coat of Polyurethane or Epoxy Enamel with 48 hours of primer application.
10. Two coats of Polyurethane of Epoxy Enamel are required. Apply second coat per paint
manufacturer’s recommendations.

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51-20-11-23 Repainting Fiberglass Components With Anti-Static

Treatment
The instructions given below are for the application of paint on Raisbeck Wing Leading Edges with an
anti-static treatment.
Surface Preparation
1. Remove wing leading edges.
2. Protect the deice boot by masking the boot area including sealant around edges with vinyl tape.
Cover entire boot with vinyl sheet and tape with masking tape, overlapping vinyl tape slightly.
3. Strip paint with paint stripper (PPG-Eldorado PR-4028LO [preferred] or PR-2002) or remove by
wet sanding, with 220-grit or better abrasive, until outer layer of resin is lightly abraded over entire
surface.

CAUTION: IF STRIPPER IS USED USE ONLY PR-4028LO OR PR-2002. IF

SANDING METHOD IS USED USE EXTREME CAUTION NOT TO
EXPOSE THE GLASS FABRIC.
4. Fill exterior pin holes, if required, with a static conditioner filler Magna (28-C-1) or equivalent. Use
hand pressure to force conditioner into pin holes.

CAUTION: FILLER SURFACE SHOULD BE USED ONLY TO FILL MINUTE

SURFACE DEFECTS. LARGE AREAS OF FILLER MATERIAL ARE
DETRIMENTAL TO SUBSEQUENT PAINT ADHESION.
5. Fill surface pits and minor depressions, if required, with surface Laminar (X-500), Epocast (156),
or equivalent.
6. Sand surface lightly and clean with naphtha-wet cheesecloth and wipe dry.
Application of Anti-Static Coating
1. Following is a list of anti-static coatings that are to be used.
a. Bostik West, Division of USM Corporation
Base 463-6-14 - Activator Ca-97
b. Desoto Chemical Coatings
Base 528-302 - Activator 910-006
Base 528-305 - Activator 910-464
c. Tempo Paint and Varnish Company
Base 1980-BAS-5A - Catalyst 1980-CAS-5A
2. Apply anti-static coating to a thickness of .0004 to .0008 inch on the entire area including
countersunk fastener holes.

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3. Cure anti-static coating at the desired temperature and time as given below:

Time Between
Time at
Application and Cool Time Total Time
Temp °F Cure Temp
Raised Temp (Minutes) (Minutes)
(Minutes)
(Minutes)
15 210-161 15 15 45
15 160-131 30 15 60
15 130-111 45 15 75
15 110-91 75 15 105
15 90-70 105 15 135

Resistance Measure of Anti-Static Coating

1. Put two 1 inch wide strips of 3M Conductive Adhesive Tape (Copper X-1181 or Aluminum X1170)
1 inch apart on the cured anti-static surface. Press strips firmly against the surface. See 51-20-
11-23, FIGURE 1.
2. With a multimeter measure the resistance between the two metal strips. Multiply the ohms
reading by 10 to give resistance per square. Coating is good if resistance per square is 500,000
ohms or less. If resistance per square is more than 500,000 ohms, apply another coat of anti-
static coating after sanding with 240 grit of finer abrasive paper and cleaning with naphtha-wet
cheesecloth and wiping dry.
3. Reinstall the wing leading edges.

51-20-11-23 FIGURE 1
Top Coating
1. Wipe surface with naphtha moistened cheesecloth and apply Class I Primer (MIL-PRF-23377),
Urethane Compatible Primer Yellow Base Desoto 513 X 329, or equivalent.
2. Apply two (2) coats of Polyurethane of Epoxy Enamel top coat (customer’s option). Apply first top
coat layer within 48 hours of primer application or recondition primer by sanding and a solvent
wipe using either Methyl Chloroform or MEK.

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53 Fuselage
Dual Aft Body Strakes
53-00-00 Description and Operation
The Raisbeck Engineering Dual Aft Body Strakes System incorporates two strakes on the underside
of the aft body, which replaces the single ventral fin. This system is designed and engineered to
streamline the airflow around the aft body, which reduces drag, improves aircraft stability, and
reduces the need for yaw damper.
The strakes can be installed with solid or blind fasteners. After the strakes are located, the ventral fin
is removed. If the customer wants to retain the aft tie-down, the ventral fin may be cut aft of the tie-
down hole.

53-00-00-05 Inspection
Periodic Inspections
The maintenance tests on the Raisbeck Engineering Dual Aft Body Strakes shall be accomplished at
the same time as the existing Beechcraft maintenance tests as given in the applicable Beechcraft
King Air Maintenance Manual, Chapter 5.
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the Strakes for condition. Clear all drain holes of any obstructions.
2. Examine the Strakes for security of attachment.

53-00-00-20 Maintenance Practices

Repair/Replacement
All of the Raisbeck Engineering Dual Aft Body Strake components are replaced “On Condition”. “On
Condition” items are to be replaced when inspection or performance of item show a potentially unsafe
condition or reduction in performance.
Examples of unsafe conditions are: propagating cracks, enlarged fastener holes that do not meet
minimum edge distance requirements, and/or damaged/missing fasteners.
Reference Chapter 51 of this manual for allowable damage limits.

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54 Nacelles/Pylons
Composite and Stainless Steel Exhaust Stack Fairings
54-00-00-00 Description and Operation
The Raisbeck Engineering Exhaust Stack Fairings are designed and engineered to enhance the air
flow around the exhaust stacks, which reduces vibration and subsequent cracking of the stacks. The
enhanced air flow reduces sooting.

54-00-00-05 Inspection
Periodic Inspections
The maintenance tests on the Raisbeck Engineering Composite Exhaust Fairings or Corrosion
Resistant Steel Fairings shall be accomplished at the same time as the existing Beechcraft
maintenance tests as given in the applicable Beechcraft King Air Maintenance Manual, Chapter 5.
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the Exhaust Fairings for condition.
2. Examine the Exhaust Fairings for security of attachment.

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54-00-00-20 Maintenance Practices

Repair/Replacement
All of the Raisbeck Engineering Exhaust Fairing components are repaired or replaced “On Condition”.
“On Condition” items are to be replaced when inspection or performance of item show a potentially
unsafe condition or reduction in performance.
Examples of unsafe conditions are: propagating cracks, enlarged fastener holes that do not meet
minimum edge distance requirements, and/or damaged/missing fasteners.
Composite Fairing Repair
The Composite Exhaust Stack Fairings may be repaired in accordance with Chapter 51 of this
Manual.
Stainless Steel Fairing Repair
Cracks in the Stainless Steel Exhaust Fairings may be repaired by welding.
1. Use a wire brush, sanding, and wire cleaning to remove all contamination in the area to be
welded.
2. Remove cracks by grinding. Use as thin a grinder as possible to minimize width of the gap to be
repaired.
3. Use a dye-penetrant test at the end of the repair area to make sure that the entire crack is
removed.
4. Wire brush and solvent clean.
5. Use the GTAW method and ER 347 filler metal, and weld to get complete penetration of the part.
A copper backing bar with a groove .06-.09 inch deep by a width approximately 1/8 inch wider
than the gap made by grinding will allow welding and minimize distortion and drop through.
6. Examine with dye penetrant to make sure there are no cracks or excessive weld porosity.
7. Grind as necessary to blend the weld into the structure.
8. Corrosion-Resistant Steel (CRES) may be polished for appearance purposes. If parts are
polished with 150-mesh of finer abrasives consisting of alumina (Ao203) or silicon carbide no
further passivation is required. Recommended buffing wheel speeds are 4,500-6,500 surface
feet per minute (SFM) for satin finishes and 7,000-9,000 SFM for gloss finishes. Lea compounds
(6-B-56 and 6-B-602) or equivalent are recommended abrasives. Do not use rouge compounds
on CRES.

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57 Wings
Enhanced Performance Leading Edges
57-00-00-00 Description and Operation
The Raisbeck Engineering Enhanced Performance Leading Edges are designed and engineered to
improve aerodynamic flow over the inboard leading edges. Benefits of the Enhanced Performance
Leading Edges include increased cruise speeds, reduced stall speeds, increased outboard wing life,
more efficient air conditioning through improved intercooler efficiency, excellent low speed flying
qualities, and stall characteristics.

57-00-00-05 Inspection
Periodic Inspection
The maintenance tests on the Raisbeck Engineering Enhanced Performance Leading Edges shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
Beechcraft Super King Air 200 Series Maintenance Manual, Chapter 5.
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the leading edge, intercooler duct, and Wing to Body fairing for condition and
attachment.
2. Examine the de-ice boot for condition and security of attachment.
3. Examine the Intercooler Inlet Abrasion Boot for condition and security of attachment.

57-00-00-20 Maintenance Practices

Repair/Replacement
All the Raisbeck Engineering Enhanced Performance Leading Edge System components are
repaired or replaced “On Condition”. “On Condition” items are to be repaired or replaced when
inspection or performance of items show a potentially unsafe condition or reduction in performance.
Repair the Enhanced Performance Leading Edges in accordance with Chapter 51 of this manual.

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Intercooler Inlet Abrasion Boot Replacement

1. Remove the abrasion boot using a thin putty knife to separate the fay seal between the boot and
the leading edge. Use caution to avoid damaging the fiberglass. Any damage must be repaired
before installing the new boot.
2. Use solvent (3MTM Solvent No. 2 or methyl ethyl ketone (MEK)) to clean adhesive from leading
edge.

CAUTION: PROLONGED EXPOSURE TO STRONG SOLVENTS, SUCH AS MEK,

CAN COMPROMISE THE FINISH AND ENTER THE COMPOSITE
LEADING EDGE, WEAKENING THE COMPOSITE’S MATRIX.
3. Repair any damage to surface and finish before installing new abrasion boot per Chapter 51 of
this manual.
4. Apply 3MTM 1300 or 1300L to mating surfaces of boot and leading edge per manufacturer’s tech
data.
5. Bond boot to leading edge, working out any air bubbles and wrinkles with a rubber roller to
achieve a smooth finish.
6. Trim excess material to allow flush fit of boot into recess of leading edge.
7. Apply conductive edge sealer (Goodrich P/N 74-451-11) to periphery of boot in a .250 inch band.
Overlap edge of abrasion boot and leading edge/de-ice boot .125 inch.

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90 Series Gross Weight Increase

57-57-00-00 Description and Operation
Raisbeck Engineering has increased the Gross Weight of C90 and E90 aircraft to 10,500 lb maximum
takeoff weight and 9,700 lb maximum landing weight.
Prior to the release of Service Bulletin SB-16-BC-01, Rev A, Dated July 18, 2016; C90A, C90B,
C90GT, and C90GTi aircraft, serial numbers LJ-1540 and after required installation of wing ballast
weights to comply with the Raisbeck Engineering 10,500 lb Gross Weight Increase (GWI). Affected
aircraft no longer require wing ballast weights to operate at 10,500 lb gross weight.
Service Bulletin SB-16-BC-01 authorizes the removal of wing ballast weights previously required to
comply with the Raisbeck Engineering 10,500 lb GWI.
All Nextant G90XT aircraft are eligible for the Raisbeck Engineering 10,500 lb GWI.

NOTE: G90XT aircraft are C90A aircraft equipped with GE H75-100 engines per
Nextant Aerospace STC SA01902CH.

NOTE: All 90 series aircraft operating above 10,100 lb must install 10-ply rated main
landing gear tires.

57-57-00-05 Inspections
Periodic Inspection
The maintenance tests on C90A, C90B, C90GT, and C90GTi aircraft equipped with the Raisbeck
Engineering Gross Weight Increase shall be accomplished at the same time as the existing
Beechcraft maintenance tests as given in the Beechcraft King Air 90 Series Maintenance Manual,
Chapter 5.
Reference the aircraft’s records and ensure the proper Raisbeck Engineering Airplane Flight Manual
Supplement has been inserted into the Aircraft Operating Handbook.

NOTE: All 90 series aircraft operating above 10,100 lb must install 10-ply rated main
landing gear tires.

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100/A100 Series Gross Weight Increase with Quiet Turbofan Propellers

57-61-30-00 Description and Operation
The Takeoff Gross Weights of both the 100 and A100 are increased. To facilitate this increase,
ballast weights must be installed on the wing.
The Landing Weight of the 100 is increased and the Zero Fuel Weight of the A100 is increased. To
facilitate this capability, moment-relieving weights are attached to the wing of the 100/A100, while VMO
has been reduced to ensure no degradation in the structural integrity of fatigue life of the aircraft.

57-61-30-05 Inspections
Periodic Inspection
The maintenance tests on Beechcraft King Air 100 and A100 Series aircraft equipped with the
Raisbeck Engineering Gross Weight Increase shall be accomplished at the same time as the existing
Beechcraft maintenance tests as given in the Beechcraft King Air 100 Series Maintenance Manual,
Chapter 5.
Daily Checks
Check Wing Ballast Weights for condition and security of attachment.

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61 Propellers
C90, E90 Series Propellers
61-00-10-00 Quiet Turbofan Propellers Description and Operation
Each engine is equipped with a Raisbeck/Hartzell Quiet Turbofan, four-blade, full feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down. Low pitch propeller position is determined by a mechanically
monitored hydraulic stop. The propeller servo piston is connected by four spring-loaded sliding rods
to the slip ring mounted behind the propeller. Movement is transferred through the propeller
reversing lever to the Beta valve of the governor. When the propeller is rotating at a speed lower
than that selected on its governor, the governor pump provides oil pressure to the servo piston and
decreases the pitch of the propeller blades until the feedback of motion from the slip ring pulls the
Beta valve into position blocking the supply of oil to the propeller, thus preventing further pitch
changes. Throughout this and referenced Beechcraft documentation, the term "Constant Speed
Governor", “Propeller Governor" and "Primary Governor" are used interchangeably to refer to the
same mounted propeller speed control unit.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Quiet Turbofan, four-bladed Propellers (HC-D4N-3C/D9290K) have a full
feathered angle of 84.5 degrees ±.5 degree at the 30-inch station, a mechanical reverse pitch stop of
-9.0 degrees ±.5 degree, and a low pitch stop of 20.1 degrees ±.1 degree.

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61-00-11-00 Swept Turbofan Propellers Description and Operation

Each engine is equipped with a Raisbeck/Hartzell Swept Turbofan, four-blade, full feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down. Low pitch propeller position is determined by a mechanically
monitored hydraulic stop. The propeller servo piston is connected by four spring-loaded sliding rods
to the slip ring mounted behind the propeller. Movement is transferred through the propeller
reversing lever to the Beta valve of the governor. When the propeller is rotating at a speed lower
than that selected on its governor, the governor pump provides oil pressure to the servo piston and
decreases the pitch of the propeller blades until the feedback of motion from the slip ring pulls the
Beta valve into position blocking the supply of oil to the propeller, thus preventing further pitch
changes. Throughout this and referenced Beechcraft documentation, the term "Constant Speed
Governor", “Propeller Governor" and "Primary Governor" are used interchangeably to refer to the
same mounted propeller speed control unit.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Swept Turbofan, four-bladed Propellers (HC-04N-3C/09510SK) have a full
feathered angle of 86.7 degrees ±.5 degree at the 30-inch station, a mechanical reverse pitch stop of
-10 degrees ±.5 degree, and a low pitch stop of 18.6 degrees ±.1 degree.

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61-00-10-05 Quiet Turbofan Propellers Inspection

Periodic Inspections
The maintenance tests on the Raisbeck Engineering Quiet Turbofan Propellers and Swept Turbofan
Propellers shall be accomplished at the same time as the existing Beechcraft maintenance tests as
given in the applicable Beechcraft King Air Maintenance Manual, Chapter 5.
The Propellers and De-ice Systems shall be maintained in accordance with the Beechcraft King Air
90 Series Maintenance Manual 90-590012-3, Hartzell maintenance manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Examine the blades for scratches and gouges in the leading edge or trailing edge or on blade
face and camber surfaces. See Hartzell Manual No. 149, ATA REF 61-00-49, for damage types
and allowances.

61-00-11-05 Swept Turbofan Propellers Inspection

Reference Chapter 61-00-10-05 of this manual.

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61-00-00-10 Quiet and Swept Turbofan Propellers Troubleshooting

Testing and fault isolation shall be accomplished in accordance with the Beechcraft King Air 90
Series Maintenance Manual and the Hartzell maintenance manuals listed above.

61-00-00-20 Quiet Turbofan Propellers Maintenance Practices

The following maintenance practices shall be accomplished in accordance with the Beechcraft King
Air 90 Series Maintenance Manual, Hartzell Propeller Owner’s Manual and Logbook (Manual No.
149, ATA REF 61-00-49), Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA
REF 30-61-80).
Propeller Care
Blade Damage
Removal
Installation
Dynamic Balancing
Dynamic Balancing Test Preparation
Dynamic Balancing Test Procedure
Dynamic Balancing Flight Test
Dynamic Balancing Test Recovery
Spinner Dome Installation
Spinner Dome Removal

61-00-11-20 Swept Turbofan Propellers Maintenance Practices

Reference Chapter 61-00-00-20 of this manual.

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Engine and Propeller Indicating

61-31-10-00 Description and Operation Quiet Turbofan Propellers
Airspeed Indicators, Propeller Tachometers, Propeller Torque Meters, and Propeller De-Ice
ammeters are re-rangemarked upon installation of Raisbeck/Hartzell Quiet Turbofan and Swept
Turbofan Propellers. Changes to the range marking of the affected instruments are detailed in
Chapter 61-31-10-20 of this manual.

61-31-10-05 Inspections Quiet Turbofan Propellers

Verify that all instruments are properly marked as indicated in Chapters 61-31-10-20 and 61-31-11-20
of this manual.

61-31-10-20 Maintenance Practices Quiet Turbofan Propellers

61-31-10-20 TABLE 1

TCDS Marketing
Serial Number Range
Model Model

C90 LJ-502 thru LJ-985, LJ-987 thru LJ-995, and LJ-997 thru LJ-1010
C90
C90-1 LJ-986, LJ-996, and LJ-1011 thru LJ-1062

LJ-1063 thru LJ-1287, LJ-1289 thru LJ-1294, LJ-1296 thru LJ-1301,

C90A
LJ-1304, LJ-1309, LJ-1310, LJ-1313, LJ-1317, and LJ-1319

LJ-1288, LJ-1295, LJ-1302, LJ-1303, LJ-1305 thru LJ-1309, LJ-1311,

LJ-1312, LJ-1314 thru LJ-1316, LJ-1318, LJ-1320 thru LJ-1366, LJ-
1368 thru LJ-1372, LJ-1374 thru LJ-1376, LJ-1378 thru LJ-1383, LJ-
C90A C90B 1385, LJ-1387, LJ-1388, LJ-1390 thru LJ-1393, LJ-1395, LJ-1396, LJ-
1398 thru LJ-1402, LJ-1404 thru LJ-1410, LJ-1412 thru LJ-1424, LJ-
1426 thru LJ-1430, LJ-1432 thru LJ-1497, LJ-1499 thru LJ-1537, LJ-
1539 thru LJ-1726, LJ-1728 thru LJ-1753, and LJ-1755

LJ-1367, LJ-1373, LJ-1377, LJ-1384, LJ-1386, LJ-1389, LJ-1394, LJ-

C90SE
1397, LJ-1403, LJ-1411, LJ-1425, LJ-1431, LJ-1498, and LJ-1538

C90GT C90GT LJ-1727, LJ-1754, LJ-1756 thru LJ-1846, and LJ-1848 thru LJ-1852

LJ-1847, LJ-1853 thru LJ-1963, LJ-1965, LJ-1967, and LJ-1969 thru

C90GTi
LJ-1976
C90GTi
C90GTx LJ-1964, LJ-1966, LJ-1968, and LJ-1977 and after

E90 E90 LW-1 thru LW-347

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Airspeed Indicator Range Markings

Reference TABLE 1 for aircraft identification. Reference TABLE 2 and TABLE 3 to verify proper VMCA
range marking of the airspeed indicators.
Identify re-rangemarked indicators with Placard REI-1001-3. Reference Chapter 11-00-00-10 of this
manual.
For C90A aircraft, serial numbers LJ-1063 thru LJ-1137 & LJ-1146, operating above 9,650 lb VMO is
208 KCAS. Raisbeck has created a Dual VMO Indicator, P/N 200-3101-1, for this serial number range
that allows operation at two different airspeed limitations based on aircraft weight. Placard REI-1001-
4 must be installed on the Overhead Light Panel on these serial number range aircraft. Reference
Chapter 11-00-00-10, FIGURE 4 of this manual.
C90 aircraft, serial numbers LJ-502 thru LJ-1062 equipped with D9510SK (Swept Turbofan
Propellers), must re-mark the Airspeed Limitations Placard. Reference 11-00-00-10, FIGURE 4 of
this manual.
61-31-10-20 TABLE 2

AIRCRAFT EQUIPPED WITH OEM ENGINES

VMCA
Market
TCDS Quiet Turbofan Swept Turbofan
ing
Model Propellers Propellers
Model
D9290K D9510SK

KIAS KCAS KIAS KCAS

E90 E90 --- 92 --- 93

C90 --- 92 --- 94

C90
C90-1 --- 92 --- 94

C90A 90 92 93 94

C90A C90B 90 92 93 94

C90SE 90 92 93 94

C90G C90G
90 92 91 93
T T
C90G
C90G 90 92 91 93
Ti
Ti
C90G
-- -- 91 --
Tx

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61-31-10-20 TABLE 3

AIRCRAFT EQUIPPED WITH PT6A-135/135A AFTERMARKET ENGINES

VMCA

Quiet Turbofan Swept Turbofan

TCDS Marketing
Propellers Propellers
Model Model
D9290K D9510SK

KIAS KCAS KIAS KCAS

E90 E90 --- 92 --- 93

C90 --- 92 --- 93

C90
C90-1 --- 92 --- 93

C90A 90 92 91 93

C90A C90B 90 92 91 93

C90SE 90 92 91 93

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Propeller Tachometers Range Markings

The upper RPM limit may be reduced and the normal operating range shifted or expanded upon
Installation of Raisbeck/Hartzell Turbofan Propellers. Reference 61-31-10-20 TABLE 1 for aircraft
identification. Reference 61-31-10-20 TABLE 4 for proper Propeller Tachometer range marking.
Should a Propeller Tachometer need to be replaced, ensure proper range marking as given in
61-31-10-20, TABLE 4, and identify the indicator with Placard REI-1001-3.
61-31-10-20 TABLE 4

GREEN RED RADIAL

MODEL
BAND (Maximum)

King Air 65-A90 airplanes equipped with PT6A-28 engines per STC
SA822SO

King Air B90/C90 airplanes equipped with PT6A-34 engines per STC
SA3501SW
1,600 to 1,900 1,900
King Air E90 airplanes

King Air C90, C90GT, & E90 Airplanes equipped with PT6A-135A
engines rigged at 1900 RPM

King Air 65-A90 not modified per FAA Type Data Sheet Note 17 or 19

King Air 65-A90/B90 modified per FAA Type Data Sheet Note 17 or
19 1,600 to 2,200
2,200
King Air C90 and C90A airplanes (serial numbers LJ-527 thru
LJ-1360, and LJ-1362)

King Air C90A (serial numbers LJ-1367 and on, and model C90SE
1,100 to 2,200
airplanes)

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Torque Meters Range Markings

The propeller torque Red Radial (maximum torque) may increase and the propeller torque Green
Band (normal operation range) may shift upon installation of Raisbeck/Hartzell Quiet Turbofan or
Swept Blade Propellers. Reference 61-31-10-20 TABLE 1 for aircraft identification. Reference 61-
31-10-20 TABLE 5 for proper Propeller Torque Meter range marking.
Should a Propeller Torque Meter need to be replaced, ensure proper range marking as given in 61-
31-10-20, TABLE 5, and identify the indicator with Placard REI-1001-3.
61-31-10-20 TABLE 5

GREEN RED RADIAL

MODEL
BAND (Maximum)

*King Air 65-A90/B90 modified per FAA Type Data Sheet Note 17 or
400 to 1,192 1,192
19

King Air 65-A90 not modified per FAA Type Data Sheet Note 17 or 19
400 to 1,315 1,315
*King Air C90 and C90A airplanes

King Air 65-A90 airplanes equipped with PT6A-28 engines per STC
400 to 1,520 1,520
SA822SO

King Air B90/C90 airplanes equipped with PT6A-34 engines per STC
SA3501SW

King Air E90 airplanes

400 to 1,520 1,520
King Air C90, C90GT, & E90 Airplanes equipped with PT6A-135A
engines rigged at 1,900 RPM

King Air 65-A90 airplanes equipped with PT6A-28 engines per STC
SA822SO

King Air C90, C90GT, & E90 Airplanes equipped with PT6A-135A
400 to 1,650 1,650
engines rigged at 1,750 RPM

*The range markings on these torque meters were not changed, and the above placard is not installed.
This data is given for reference only.

Propeller De-Ice Ammeters Range Markings Quiet Turbofan Propellers and Swept Turbofan
Propellers
On aircraft previously equipped with 3 bladed propellers, the propeller de-ice ammeters green arc is
re-marked for 18 to 24 amp upon installation of Raisbeck/Hartzell Quiet Turbofan or Swept Blade
Propellers. If a replacement propeller de-ice ammeter needs to be re-range marked, identify the
indicator with REI placard, REI-1001-3.
OEM Propeller De-ice Ammeters with the Green Arc originally marked for 18 to 24 amperes are not
identified with Placard, REI-1001-3.

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61-31-11-00 Description and Operation Swept Turbofan Propellers

Reference Chapter 61-31-10-00 of this manual.

61-31-11-05 Inspections Swept Turbofan Propellers

Reference Chapter 61-31-10-05 of this manual.

61-31-11-20 Maintenance Practices Swept Turbofan Propellers

Airspeed Indicator Range Markings
For C90A, C90GT, & C90GTi aircraft equipped with Garmin International G1000 per STC
SA01456WI-D and Raisbeck/Hartzell Swept Turbofan Propellers (D9510SK) per STC SA3595MM,
install Placard REI-1001-14 (Reference 11-00-00-10, FIGURE 2) or comply with Garmin Service
Bulletin No. 1414 to display the correct airspeed (Reference Raisbeck Service Bulletin SB-15-BC-01).

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Engine and Propeller Controls

61-76-00-20 Quiet Turbofan Propellers and Swept Turbofan Propellers
Maintenance Practices
61-76-00-20 TABLE 1

TCDS Marketing
Serial Number Ranges
Model Model

C90 LJ-502 thru LJ-985, LJ-987 thru LJ-995, and LJ-997 thru LJ-1010
C90
C90-1 LJ-986, LJ-996, and LJ-1011 thru LJ-1062

LJ-1063 thru LJ-1287, LJ-1289 thru LJ-1294, LJ-1296 thru LJ-1301,

C90A
LJ-1304, LJ-1309, LJ-1310, LJ-1313, LJ-1317, and LJ-1319

LJ-1288, LJ-1295, LJ-1302, LJ-1303, LJ-1305 thru LJ-1309, LJ-1311,

LJ-1312, LJ-1314 thru LJ-1316, LJ-1318, LJ-1320 thru LJ-1366, LJ-
1368 thru LJ-1372, LJ-1374 thru LJ-1376, LJ-1378 thru LJ-1383, LJ-
C90A C90B 1385, LJ-1387, LJ-1388, LJ-1390 thru LJ-1393, LJ-1395, LJ-1396, LJ-
1398 thru LJ-1402, LJ-1404 thru LJ-1410, LJ-1412 thru LJ-1424, LJ-
1426 thru LJ-1430, LJ-1432 thru LJ-1497, LJ-1499 thru LJ-1537, LJ-
1539 thru LJ-1726, LJ-1728 thru LJ-1753, and LJ-1755

LJ-1367, LJ-1373, LJ-1377, LJ-1384, LJ-1386, LJ-1389, LJ-1394, LJ-

C90SE
1397, LJ-1403, LJ-1411, LJ-1425, LJ-1431, LJ-1498, and LJ-1538

C90GT C90GT LJ-1727, LJ-1754, LJ-1756 thru LJ-1846, and LJ-1848 thru LJ-1852

LJ-1847, LJ-1853 thru LJ-1963, LJ-1965, LJ-1967, and LJ-1969 thru

C90GTi
LJ-1976
C90GTi
C90GTx LJ-1964, LJ-1966, LJ-1968, and LJ-1977 and after

E90 E90 LW-1 thru LW-347

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Torque Chart A C90, C90A, & E90 aircraft.

Torque Chart B Inactive. Contact Raisbeck Engineering.
Torque Chart C Aircraft equipped without autofeather and Raisbeck Magicam installed.
Torque Chart D Aircraft equipped with Swept Turbofan Propellers.
Torque Chart E G90XT.

NOTE: G90XT aircraft are C90A aircraft modified per Nextant Aerospace STC
SA01902CH.
Torque Chart F 90 series aircraft equipped with PT6A-28 engines and Quiet Turbofan Propellers
(Engine Performance and Data Plate Speed Test)
Ground Run/Low Pitch Torque Check C90, C90A, & E90 Aircraft Quiet Turbofan Propellers
Reference TABLE 1 for aircraft identification and TORQUE CHART A.

NOTE: If this test is not done in zero-wind conditions, take an average of the upwind
and downwind readings to get valid results.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,100

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
With the propeller levers completely forward, advance the cockpit power lever for the engine until the
propeller reaches 1,800 RPM. The torquemeter reading for the engine must be +20/-0 lb-ft from the
maximum value shown by the pressure altitude and temperature conversion graphs, for the ambient
conditions that the engine is operating in. Do this test again for the other engine. The difference
between torquemeter readings on the engines should not exceed 20 lb-ft.
If the torque meter readings are not correct as shown in the graph, or if the difference between the
Left and Right engines exceeds 20 lb-ft, do the adjustments given below:
Adjust the stop (Beta) nut on each of the four pitch stop rods for the propeller. All four nuts must be
adjusted to an identical position. One flat of rotation on the Beta nuts (clockwise to increase,
counterclockwise to decrease) changes engine torque approximately 20 lb-ft. Adjust the Beta nuts as
necessary to get the engine to operate within the prescribed limits. Do not use the Beta Valve for this
adjustment.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULLY FORWARD
POWER LEVER SET FOR 1,800 RPM

61-76-00-20 TORQUE CHART A

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Ground Run/Low Pitch Torque: Blackhawk or 1,750 RPM Installations.

Inactive. Contact Raisbeck Engineering.

61-76-00-20 TORQUE CHART B

TORQUE CHART B inactive. Contact Raisbeck Engineering.

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Ground Run/Low Pitch Torque Check Aircraft Equipped with Raisbeck Magicam
Reference TABLE 1 for aircraft identification and TORQUE CHART C.

NOTE: If this test is not done in zero-wind conditions, take an average of the upwind
and downwind readings to get valid results.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,100

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
With the propeller levers completely forward, advance the cockpit power lever for the engine until the
propeller reaches 1,800 RPM. The torquemeter reading for the engine must be +20/-0 lb-ft from the
maximum value shown by the pressure altitude and temperature conversion graphs, for the ambient
conditions that the engine is operating in. Do this test again for the other engine. The difference
between torquemeter readings on the engines should not exceed 20 lb-ft.
If the torque meter readings are not correct as shown in the graph, or if the difference between the
Left and Right engines exceeds 20 lb-ft, do the adjustments given below:
Adjust the stop (Beta) nut on each of the four pitch stop rods for the propeller. All four nuts must be
adjusted to an identical position. One flat of rotation on the Beta nuts (clockwise to increase,
counterclockwise to decrease) changes engine torque approximately 20 lb-ft. Adjust the Beta nuts as
necessary to get the engine to operate within the prescribed limits. Do not use the Beta Valve for this
adjustment.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULL FORWARD
POWER LEVER SET FOR 1,800 PROPELLER RPM
‐40 AMBIENT TEMPERATURE ~ °C

‐30

‐20

‐10

10

20

30

40

50
0
900
850
800
750
TORQUE @ 1,800 RPM ~ LB‐FT
700
650
600
550
500
450

61-76-00-20 TORQUE CHART C

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Ground Run/Low Pitch Torque Check Aircraft Equipped with Swept Turbofan Propellers
Reference TABLE 1 for aircraft identification and TORQUE CHART D.

NOTE: If this test is not done in zero-wind conditions, take an average of the upwind
and downwind readings to get valid results.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,100

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.

(With Collins Pro Line 21 per STC SA11134SC installed):

STABILIZED GROUND OPERATION BETWEEN 500 AND 1,100
PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
500 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
With the propeller levers completely forward, advance the cockpit power lever for the engine until the
propeller reaches 1,800 RPM. The torque meter reading for the engine must be +20/-0 lb-ft from the
maximum value shown by the pressure altitude and temperature conversion graphs, for the ambient
conditions that the engine is operating in. Do this test again for the other engine. The difference
between torque meter readings on the engines should not exceed 20 lb-ft.
If the torque meter readings are not correct as shown in the graph, or if the difference between the
Left and Right engines exceeds 20 lb-ft, do the adjustments given below:
Adjust the stop (Beta) nut on each of the four pitch stop rods for the propeller. All four nuts must be
adjusted to an identical position. One flat of rotation on the Beta nuts (clockwise to increase,
counterclockwise to decrease) changes engine torque approximately 20 lb-ft. Adjust the Beta nuts as
necessary to get the engine to operate within the prescribed limits. Do not use the Beta Valve for this
adjustment.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULL FORWARD
POWER LEVER SET FOR 1,800 PROPELLER RPM

‐40 AMBIENT TEMPURATURE ~ °C

‐30

‐20

‐10

10

20

30

40

50
0
550
500
450
TORQUE @ 1,800 RPM ~ LB‐FT
400
350
300

61-76-00-20 TORQUE CHART D

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Ground Run/Low Pitch Torque Check G90XT Aircraft Equipped with HC-E4W-3/D9290K Quiet
Turbofan Propellers

NOTE: G90XT aircraft are C90A aircraft modified per Nextant Aerospace STC
SA01902CH.
Reference TABLE 1 for aircraft identification and TORQUE CHART E.

NOTE: If this test is not done in zero-wind conditions, take an average of the upwind
and downwind readings to get valid results.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,100

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
1. With the propeller levers fully forward, advance the cockpit power lever for the engine until
the propeller reaches 1,800 RPM. The torque meter reading for the engine must not
exceed and should be within 1.8% of the value designated by the pressure altitude and
temperature conversion graph Chart A, for the ambient conditions under which the engine
is operating. Repeat this check on the other engine. The difference between torque-meter
readings on the engines should not exceed .9%. If the torque meter readings do not fall
within the limitations described by the graph, or if the difference between the LH and RH
engines exceeds .9%, the following adjustments are required:

CAUTION: HOLD STUDS WHEN TURNING BETA NUTS.

a. When the torque change required rig an engine within the design limits does
not exceed .9%, disconnect the fuel topping governor inner connecting rod,
and disconnect the control cable rear clevis from the Beta control cam.
Adjust the clevis in or out until engine torque is within the prescribed limits
and the torque of each engine is the same, then reconnect the inner
connecting rod and the rear clevis.

b. When the torque change required to bring an engine within the prescribed
limits exceeds .9%, adjustment of the stop (Beta) nut on each of the four low
pitch stop rods for the propeller is required. All four nuts must be adjusted to
an identical setting (see FIGURE 3). One flat of rotation on the Beta nuts
(clockwise to increase or counterclockwise to decrease) changes engine
torque approximately .7%. Adjust the Beta nuts as necessary to bring the
engine within the prescribed limits.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULL FORWARD
POWER LEVER SET FOR 1,800 PROPELLER RPM

61-76-00-20 TORQUE CHART E

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Engine Performance and Data Plate Speed Test

This performance and speed test applies to 90 series airplanes that are equipped with PT6A-28
engines and Quiet Turbofan Propellers.
When equipped with the Raisbeck Engineering Quiet Turbofan Propellers, the revised maximum
takeoff RPM for the 90 series airplanes equipped with the PT6A-28 engines is 1,900 RPM.
Perform an Engine Ground Test in accordance with the Beechcraft King Air 90 Series Maintenance
Manual. Adjust the torque referencing TORQUE CHART F.

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61-76-00-20 TORQUE CHART F

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Functional Test Magicam Adjustment Quiet Turbofan Propellers

1. If equipped with Magicam, use the data given below with the data given in the Beechcraft King Air
Maintenance Manual Subject 76-00-00 to couple the Magicam to the fuel control:
a. The normal 90 degree measurement is greater with the Magicam Adjust so that engine power
lever/Magicam follower pin is aligned with scribed line on Magicam.
b. The alignment of the power control lever shaft, lever connecting bolt and pin will be in a
straight line.
2. Adjust the beta cable clevis to the Magicam as given below:
a. Remove the attach bolt for the Beta cable clevis.
b. Advance the throttle lever to ¾ of the full travel.
c. Adjust the beta cable clevis to a slip fit.
d. Put the throttle to idle. The beta cable clevis should be pulled aft by the Magicam .125 to
.250 inch.
e. Install the attach bolt and nut of the Beta cable clevis.

61-76-00-20 FIGURE 1

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Low Idle Adjustment Aircraft with Magicam Quiet Turbofan Propellers

Set the condition lever at low idle and the power lever at idle, then set the propeller at 1,100 +50/-0
RPM. The tachometer will show between 56% to 58% gas generator (N1). Shorten (to increase
RPM) or lengthen (to decrease RPM) the throttle flexible cable rod-end where it attaches to the
engine power lever, while the power lever in cockpit is against its low-idle stop. This will move the
Magicam follower pin, and the Beta Valve, without a change to N1 affecting the 1,800 RPM low-pitch
setting.
Low Idle Adjustment Aircraft without Magicam Quiet and Swept Turbofan Propellers
Reference the Beechcraft King Air 90 Series Maintenance Manual adjust the low idle up or down to
achieve 1,100 RPM +50/-0 RPM.
Takeoff RPM Quiet Turbofan Propellers and Swept Turbofan Propellers
The maximum takeoff RPM limit may require adjustment upon installation of Raisbeck/Hartzell Quiet
Turbofan or Swept Turbofan Propellers. Constant Speed Governors and Overspeed Governors that
have had the maximum takeoff RPM and/or the Normal Operating Range RPM adjusted in
accordance with FAA STC SA3593NM are identified with a letter as a prefix of the part number
stamped into the governor data plate. OEM and STC engine installations with the governors rigged
for 1,900 RPM takeoff do not require the governors to be adjusted and are not stamped with a letter
prefix on the governor data plate.
Reference 61-76-00-20, Table 2 for letter prefixes.

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61-76-00-20 TABLE 2

CONSTANT SPEED GOVERNOR IDENTIFICATION

MAXIMUM TAKEOFF NORMAL OPERATING RANGE

GOVERNOR P/N
PROPELLER RPM PROPELLER RPM
PREFIX
IDENTIFIER
WAS: IS: WAS: IS:

2,200 2,200 1,800 to 2,200 1,600 to 2,200 R

2,200 1,900 1,800 to 2,200 1,600 to 1,900 S

2,200 2,000 1,800 to 2,200 1,600 to 2,000 T

1,900 1,900 1,900 MAX *1,900 MAX NONE

R Indicates no change in MAX RPM.

Expands Normal Operating Range from (1,800 to 2,200 RPM) to (1,600 to 2,200 RPM).
S Indicates 1,900 MAX RPM as adjusted per STC SA3593NM.
Normal Operating Range shifts from (1,800 to 2,200 RPM) to (1,600 to 1,900 RPM).
T Indicates 2,000 MAX RPM as adjusted per STC SA3593NM.
Normal Operating Range shifts form (1,800 to 2,200 RPM) to (1,600 to 2,000 RPM).
* No adjustment is made to governors on OEM or STC installed engines already rigged for
1,900 MAX takeoff RPM.

OVERSPEED GOVERNOR IDENTIFICATION

MAXIMUM PROPELLER RPM GOVERNOR P/N

PREFIX
WAS: IS: IDENTIFIER

2,200 *2,200 NONE

2,200 1,900 S

2,200 2,000 T

1,900 **1,900 NONE

S Indicates the MAX takeoff RPM has been reduced from 2,200 to 1,900 RPM.
T Indicates the MAX takeoff RPM has been reduced from 2,200 to 2,000 RPM.
* No adjustment has been made to the OEM engine installation rigged for 2,200 MAX takeoff RPM.
** No adjustment is made to governors on OEM or STC installed engines already rigged for
1,900 MAX takeoff RPM.

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1,600 RPM Cruise Functional Test and Adjustment C90, C90A, C90B, and E90 Quiet Turbofan
Propellers and Swept Turbofan Propellers
1. Advance to 1,600 RPM with both propeller levers before they touch the feather detents in the
throttle quadrant.
2. Advance to full takeoff RPM with the propeller levers before they touch the forward mechanical
stops in the throttle quadrant.
To achieve the adjustments given above, shorten or lengthen the propeller cable rod ends at their
attach points on the propeller governors. In extreme cases, where more governor throw is necessary
in the same physical propeller lever quadrant throw, remove the radius arm of the propeller governor,
and install it on its shaft at a more acute angle as measured from the propeller control cable. See the
proper Beechcraft Maintenance Manual for all other adjustment procedures, such as ‘REVERSE-
NOT-READY” micro switches.
1,600 RPM Cruise Feathering Adjustment C90, C90A, C90B, and E90 Quiet Turbofan Propellers
and Swept Turbofan Propellers
Advance the propeller lever to the Full High RPM position and advance the power lever to get 1,800
RPM. Pull the propeller lever back past the detent (Feather Position) and observe the RPM at the
start of feather. This RPM should be 1,500 ±25 RPM. Adjust the feathering lift rod on the Constant
Speed Governor as necessary (clockwise to reduce the RPM for the start of feather).
Should a governor need to be replaced, adjust the governor in accordance with 61-76-00-20,
Constant Speed Governor Adjustment Quiet Turbofan Propeller and Swept Turbofan Propellers
Section of this manual as applicable.
Constant Speed Governor Adjustment Quiet Turbofan Propellers and Swept Turbofan
Propellers
The maximum (MAX) propeller RPM setting of the Constant Speed Governors may require
adjustment upon installation of Raisbeck/Hartzell Quiet Turbofan or Swept Turbofan Propellers. The
Normal Operating RPM Range may also require adjustment. OEM and STC Engine installations that
are rigged for 1,900 MAX Takeoff RPM by the Manufacturer or Engine STC Holder do not require the
MAX Takeoff RPM or Normal Operating Range RPM be adjusted.
Reference the aircraft’s records for Engine identification.
Reference 61-76-00-20 TABLE 1 for aircraft identification.
Reference 61-76-00-20 TABLE 2 for applicable Constant Speed Governor identification, MAX Takeoff
RPM setting, and Normal Operating Range RPM setting.
Reference 61-76-00-20 1,600 RPM Cruise Feathering Adjustment Quiet Turbofan and Swept
Turbofan Propellers for Normal Operating Range adjustment procedures.
The following steps are for adjusting the Maximum Takeoff RPM and Normal Operating Range
(cruise RPM) for a Constant Speed Governor that has not been previously adjusted in accordance
with FAA STC SA3593NM. Identify the adjusted governor with the appropriate letter stamp in the
prefix of the part number on the governor data plate. Reference 61-76-00-20 TABLE 2, and 61-76-
00-20 TABLE 3.
Adjust the governor as applicable in following Sections, 61-76-00-20:
Constant Speed Governors adjusted from 2,200 to 1,900 MAX Takeoff RPM and 1,600 to 1,900
RPM Normal Operating Range
Constant Speed Governors adjusted from 2,200 to 2,000 MAX Takeoff RPM and 1,600 to 2,000
RPM Normal Operating Range
Constant Speed Governors 2,200 MAX Takeoff RPM and 1,600 to 2,200 RPM Normal Operating
Range

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Constant Speed Governors adjusted from 2,200 to 1,900 MAX Takeoff RPM and 1,600 to 1,900
RPM Normal Operating Range
1. Mark the location of the outer arm (Control Lever) and inner arm (Speed Setting Stop Assembly).
2. Remove the outer arm.
3. Remove the spiral retaining spring (“Spirolox®”).
4. Remove the inner arm and rotate it four (4) serrations clockwise as viewed from the top. Install
the inner arm with the spiral retaining spring.
5. Install the outer arm four (4) serrations clockwise as viewed from the top. Torque the control
lever clamping screw to 33-38 lb-in.
6. Install stainless steel safety wire on the inner and outer arms.
7. Turn the Feathering Lift Rod clockwise approximately ½ turn.
8. Attach the push-pull control rod to the outer arm.
As an option, the Constant Speed Governor can be adjusted by an appropriate Woodward service
center. Reference 61-76-00-20, TABLE 3.
Constant Speed Governors adjusted from 2,200 to 2,000 MAX Takeoff RPM and 1,600 to 2,000
RPM Normal Operating Range
1. Turn the Feather Stop Screw out three (3) turns.
2. Turn the feathering lift rod screw in approximately ½ turn.
3. Reset the control lever on the stop bracket one serration clockwise. Torque the control lever
clamping screw to 33-38 lb-in.
4. Adjust the push-pull rod end at the governor to ensure proper travel at the quadrant in the cockpit.
REVERSE-NOT- READY light should extinguish at full forward (low pitch) propeller lever position.
The lever should not hit the quadrant feather detent at 1,600 RPM lever position.
As an option, the Constant Speed Governor can be adjusted by an appropriate Woodward service
center. Reference 61-76-00-20, TABLE 3.
Constant Speed Governors 2,200 MAX Takeoff RPM and 1,600 to 2,200 RPM Normal Operating
Range
1. Turn the Feather Stop Screw out three (3) turns.
2. Turn the feathering lift rod screw in approximately ½ turn.
3. Reset the control lever on the stop bracket one serration clockwise. Torque the control lever
clamping screw to 33-38 lb-in.
4. Adjust the push-pull rod end at the governor to ensure proper travel at the quadrant in the cockpit.
REVERSE-NOT- READY light should extinguish at full forward (low pitch) propeller lever position.
The lever should not hit the quadrant feather detent at 1,600 RPM lever position.
As an option, the Constant Speed Governor can be adjusted by an appropriate Woodward service
center. Reference 61-76-00-20, TABLE 3.

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61-76-00-20 TABLE 3

CONSTANT SPEED GOVERNORS ADJUSTED FROM 2,200 TO 1,900 MAX TAKEOFF RPM
AND 1,600 TO 1,900 RPM NORMAL OPERATING RANGE

WAS: IS:

8210-002 S8210-002
Governor Model No.
8210-025* S8210-025*

MAX Propeller RPM 2,200 1,900

MAX Governor RPM 4,200** 3,627**

Approximate Start of Feather at Propeller RPM 1,600 1,490

Approximate Start of Feather at Governor RPM 3,055 2,844

CONSTANT SPEED GOVERNORS ADJUSTED FROM 2,200 TO 2,000 MAX TAKEOFF RPM
AND 1,600 TO 2,000 RPM NORMAL OPERATING RANGE

WAS IS

8120-002 T8210-002
Governor Model No.
8210-025* T8210-025*

MAX Propeller RPM 2,200 2,000

MAX Governor RPM 4,200*** 3,818***

Approximate Start of Feather at Propeller RPM 1,600 1,490

Approximate Start of Feather at Governor RPM 3,055 2,844

CONSTANT SPEED GOVERNORS 2,200 MAX TAKEOFF RPM

AND 1,600 TO 2,200 NORMAL OPERATING RANGE

WAS IS
8210-002 R8210-002
Governor Model No.
8210-025* R8210-025*

MAX Propeller RPM 2,200 2,200

MAX Governor RPM 4,200 4,200

Approximate Start of Feather at Propeller RPM 1,600 1,490

Approximate Start of Feather at Propeller RPM 3,055 2,844

*8210-002 and 8210-025 are equivalent except for the synchrophaser coil which is not affected by this
adjustment.
**Add 46 RPM for bench adjustment to 4,246 and 3,673 RPM.
***Add 46 RPM for bench adjustment to 4,246 and 3,864 RPM.

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Overspeed Governor Operational Test for Quiet Turbofan Propellers and Swept Turbofan
Propellers

CAUTION: DO NOT EXCEED THE ENGINE TORQUE OR ITT LIMITS DURING

THIS TEST.
With the Propeller Levers in the full HIGH RPM position, set the Power Levers to 1,600 propeller
RPM. Hold the Governor Test Switch ON and advance the Power Levers fully forward. When the
governor is operating correctly, it will hold the propeller RPM to the values in 61-76-00-20, TABLE 4.
Adjust the Overspeed Governor as necessary using the adjustment screw on top of the governor.
One turn equals approximately 195 RPM.
61-76-00-20 TABLE 4

RPM RPM
MODEL PREFIX
Test Switch ON Test Switch OFF

King Air 65-A90 equipped with PT6A-

1,650 to 1,850 1,900 ‘S’
28 engines per STC SA822SO

King Air 65-A90 not modified per FAA

1,750 to 1,950 2,000 ‘T’
Type Data Sheet Note 17 or 19

* King Air 65-A90/B90 modified per 1,900 to 2,100 2,200 None

FAA Type Data Sheet Note 17 or 19

King Air B90/C90 equipped with PT6A-

1,650 to 1,850 1,900 ‘S’
34 engines per STC SA3501SW

* King Air C90 and C90A airplanes 1,900 to 2,100 2,200 None

King Air E90 airplanes 1,650 to 1,850 1,900 ‘S’

King Air C90 Series and E90 equipped

with OEM or STC engines rigged for 1,650 to 1,850 1,900 None
1,900 maximum propeller RPM
* The maximum RPM setting of these governors is not adjusted per STC
SA3593NM and do not have a letter stamp in the prefix of the part number.

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Reverse Not Ready Light Adjustment

This adjustment is for Aircraft Equipped with PT6A-135A Engines and Quiet Turbofan Propellers or
Swept Turbofan Propellers.

CAUTION: OBSERVE THE STANDARD FIRE AND PROPELLER SAFETY

PRECAUTIONS. MAKE SURE THAT THE AREA AROUND THE
AIRPLANE AND ENGINES IS CLEAR BEFORE STARTING THE
ENGINES.
The switches for the PROP REVERSE NOT READY LIGHT in the annunciation panel are installed in
the pedestal that is next to the ball cranks for the propeller lever. Gain access to the switches
through the cover on the left side of the pedestal.
1. Place the control switch for the landing gear in the DOWN position. Place the propeller control
levers in the full high RPM (low pitch) position. Move the power lever to 1,900 RPM.
2. Adjust each switch in its mounting slot so that the PROP REVERSE NOT READY light (amber in
color) is illuminated when the propeller lever for the related switch is set for 1,875 RPM.

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Synchrophaser Target-Screw Installation Configuration 1

Reference FIGURE 2 and 4
1. Install screws (2E1377) in the pre-tapped holes in the slip ring outer surface with Loctite “C” and
torque to 2-3 lb-in as follows:
a. Left Engine Propeller - four (4) screws aligned with blade centerlines.
b. Right Engine Propeller - four (4) screws 65 degrees counterclockwise from blade centerline
as viewed from rear.
Synchrophaser Multiple Target Bracket Rework and Installation Configuration 2
Reference FIGURE 2 and 4
1. Install Target Brackets (90-960028-3) with bolts (AN3-5A), lock washers (MS35335-32), washers
(AN96010L) and nuts (MS21043-3) s as follows:
a. Left Engine Propeller - Four (4) brackets 5 degrees counterclockwise from blade centerline
as viewed from rear, in drilled holes 7.35 inches radius from hub centerline.
b. Right Engine Propeller - Four (4) screws 20 degrees clockwise from blade centerline as
viewed from rear, in drilled holes 7.35 inches radius from hub centerline. Re-install retained
counterweights.
Synchrophaser Single Target Bracket Rework and Installation Configuration 3
Reference FIGURE 2 and 4
1. Install Target Brackets (90-960028-3) with bolts (AN3-5A), lock washers (MS35335-32), washers
(AN96010L), and nuts (MS21043-3) as follows.
a. Left Engine Propeller - One (1) bracket 5 degrees counterclockwise from blade centerline as
viewed from rear, in drilled holes 7.35 inches from hub centerline.
b. Right Engine Propeller - One (1) bracket 20 degrees clockwise from blade centerline as
viewed from rear, in drilled holes 7.35 inches radius from hub centerline.
2. Install Counterweight (90-960028-5) on the spinner bulkhead 180 degrees from target.
Synchrophaser Target Rework and Installation Configuration 4
Reference TABLE 1 for aircraft identification and FIGURES 2, 3, and 4 for the applicable
configuration.
1 Bend target (90-960028-3) from 90 degrees to approximately 80 degrees as shown.
2. Install one (1) Target Bracket (90-960028-3 as reworked) on the aft side of each spinner. Install
bracket with bolt (AN3-5A), lock washer (MS35335-32), washer (AN96010L), and nut
(MS21043-3). Position Target Brackets for left and right propellers as follows:
a. Left Engine Propeller - One (1) bracket 5 degrees counterclockwise from blade centerline as
viewed from rear, in drilled holes 7.35 inches from hub centerline.
b. Right Engine Propeller - One (1) bracket 20 degrees clockwise from blade centerline as
viewed from rear, in drilled holes 7.35 inches radius from hub centerline.
3. Install Counterweight (90-960028-5) on the spinner bulkhead 180 degrees from target.
Reference the Beechcraft King Air 90 Series Maintenance Manual for static and dynamic balancing
procedures.

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Synchrophaser Target-Screw Installation Configuration 5

Reference TABLE 1 for aircraft identification and FIGURES 2, 3, and 4 for the applicable
configuration.
1. Install screws (3360-078) with nuts (MS21043-06) and washers (AN960C6L) in the spinner
bulkhead as follows:
a. The left engine propeller synchrophaser target screw is installed at 7.26 inches from the
centerline of the hub and 5 degrees counterclockwise from blade centerline and viewed from
the rear.
b. The right engine propeller synchrophaser target screw is installed at 7.26 inches from the
centerline of the hub and 20 degrees clockwise from blade centerline and viewed from the
rear.
Reference the Beechcraft King Air 90 Series Maintenance Manual for static and dynamic balancing
procedures.
Brush Block Mounting Bracket Rework and Installation C90 Series & E90
Should it become necessary to replace the De-ice Brush Block Mounting Bracket, reference FIGURE
5 and the steps provided below:
1. Remove the Brush Block Mounting Bracket in accordance with the Beechcraft King Air 90 Series
Maintenance Manual.
2. Trim .20 inch from the front edge of the de-ice brush block bracket and elongate the slots .20 inch
aft. Break all sharp edges and treat bare metal with primer.
3. Install the Brush Block Mounting Bracket in accordance with the Beechcraft King Air 90 Series
Maintenance Manual.
Synchrophaser Magnetic Target Pickup Bracket Rework and Installation
Should it become necessary to replace the Prop Sync Magnetic Pick-up Bracket, reference FIGURE
5 and the steps provided below:
1. Remove the Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft
King Air 90 Series Maintenance Manual.
2. Trim Magnetic Target Bracket, P/N 90-960028-1, as needed to clear the spinner bulkhead. Break
all sharp edges and treat bare metal with primer.
3. Reinstall Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft King
Air 90 Series Maintenance Manual.
Pick-up Brackets P/N 92-2502-1 and 101-960116-1 do not require rework and are to be installed in
accordance with the Beechcraft King Air 90 Series Maintenance Manual.

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61-76-00-00 FIGURE 2

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61-76-00-20 FIGURE 3

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61-76-00-20 FIGURE 4

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61-76-00-20 FIGURE 5

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F90 Quiet Turbofan Propellers

61-00-20-00 Description and Operation
Each engine is equipped with a Raisbeck/Hartzell Quiet Turbofan, four-blade, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gearbox. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, put the blades into the low RPM (high pitch) position and into the feathered position.
Governor-boosted engine oil pressure puts the propeller into the high RPM (low pitch) hydraulic stop,
and into the reverse position. The propellers have no low RPM (high pitch) stops; this allows the
blades to feather after the engine is shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
Reversing propeller-setting is changed to full feathered angle of 86 degrees at the 30-inch station and
mechanical reverse pitch stop of -10.5 degrees ±.5 degree. Low pitch propeller position is
determined by a hydraulic stop that is mechanically monitored. The propeller servo piston is
connected by four spring-loaded sliding rods to the slip ring. The slip ring is installed behind the
propeller. Motion is transferred through the propeller-reversing lever to the Beta valve of the
governor. The initial forward motion of the Beta valve blocks off the flow of oil to the propeller.
Further forward motion causes oil to flow from the propeller at a flow rate that is less than that
selected on the governor. The governor pump provides oil pressure to the servo piston and
decreases the pitch of the propeller blades until the feedback of motion from the slip ring pulls the
Beta valve into a position that stops the supply of oil to the propeller, thus preventing further pitch
changes.

61-00-20-05 Inspection
Periodic Inspections
The maintenance tests on the Raisbeck Engineering Quiet Turbofan Propellers shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
applicable Beechcraft King Air Maintenance Manual, Chapter 5.
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).

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Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Examine the blades for scratches and gouges in the leading edge or trailing edge or on blade
face and camber surfaces.

61-00-20-10 Troubleshooting
Testing and fault isolation shall be accomplished in accordance with the Beechcraft King Air F90
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49), Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-
80).

61-00-20-20 Maintenance Practices

Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149, ATA
REF 61-00-49), Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA REF 30-61-
80).
Propeller Care
Blade Damage
Removal
Installation Dynamic Balancing
Balancing Test Preparation
Dynamic Balancing Test Procedure
Dynamic Balancing Ground Check
Dynamic Balancing Flight Test
Dynamic Balancing Test Recovery
Spinner Dome Removal
Spinner Dome Installation

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Engine and Propeller Indicating

61-31-20-00 Description and Operation
Changes to the airspeed and engine indicating instrumentation are defined in the following.

61-31-20-20 Maintenance Practices

Airspeed Indicators
No change.
Propeller Tachometers
No change.
Torquemeter
No change.
Ammeters
The ammeter is rangemarked with a green arc from 18 to 24 amperes. Identify the remarked
indicator with Placard REI 1001-9.

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Engine and Propeller Controls

61-76-20-20 Maintenance Practices
Ground Run/Low Pitch Torque Check
Reference TORQUE CHART A

NOTE: If this test is not done in zero-wind conditions, take an average of the upwind
and downwind readings to get valid results.
With the propeller levers completely forward, advance the cockpit power lever for the engine until the
propeller reaches 1,800 RPM (1,700 RPM if equipped with PT6A-135A engines and rigged at 1,750
RPM). The torque meter reading for the engine must be +20/-0 lb-ft from the maximum value shown
by the pressure altitude and temperature conversion graphs, for the ambient conditions that the
engine is operating in. Do this test again for the other engine. The difference between torquemeter
readings on the engines should not exceed 20 lb-ft.
If the torque meter readings are not correct as shown in the graph, or if the difference between the
Left and Right engines exceeds 20 lb-ft, perform the adjustments given below:
Adjust the stop (Beta) nut on each of the four pitch stop rods for the propeller. All four nuts must be
adjusted to an identical position. One flat of rotation on the Beta nuts (clockwise to increase,
counterclockwise to decrease) changes engine torque approximately 20 lb-ft. Adjust the Beta nuts as
necessary to obtain engine operation within the prescribed limits. Do not use the Beta Valve for this
adjustment.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULL FORWARD
POWER LEVER SET FOR 1,800 PROPELLER RPM

AMBIENT TEMPERATURE ~ °C
‐50

‐40

‐30

‐20

‐10

10

20

30

40

50
0
700
650
600
550
TORQUE @ 1,800 RPM ~ LB‐FT
500
450
400
350
300
250

61-76-20-20 TORQUE CHART A

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Low Idle Adjustment

Set the condition lever at low idle and the power level at idle, then set the propeller at 1,150 +50/-0
RPM. The tachometer should read between 60-63% gas generator (N1). Perform adjustment per
Beechcraft King Air F90 Maintenance Manual Subject 76-00-000.
High Idle Adjustment
Adjust as given in the Beechcraft King Air F90 Maintenance Manual, Chapter 76.
Constant Speed Governors
Check the operation as given in the Beechcraft King Air F90 Maintenance Manual, Chapter 61.
Overspeed Governors
Check the operation as given in the Beechcraft King Air F90 Maintenance Manual, Chapter 61.
Reversing System
Set maximum N1 RPM settings as given in the Beechcraft King Air F90 Maintenance Manual,
Chapter 61.
Fuel Lever Cutoff Adjustment
Rig the fuel lever cutoff adjustment as given in the Beechcraft King Air F90 Maintenance Manual,
Chapter 76.
Synchrophaser Target Installation LA-2 thru LA-99, LA-101
Reference FIGURE 1 and FIGURE 2
1. Apply Loctite “C” and install screws (2E1377) in the pre-tapped holes in the outer surface of the
slip ring. Torque these screws to 2 -3 pound-inches. These screws are located as given below:
Reference FIGURE 1 and FIGURE 2.
a) Left Engine Propeller – Four (4) screws aligned with the blade centerlines.
b) Right Engine Propeller – Four (4) screws at 65 degrees counterclockwise from the blade
centerlines as viewed from the rear.
Synchrophaser Target Installation LA-100, LA-102 thru LA-201
Reference FIGURE 1 and FIGURE 2
1. Bend the Target Brackets (closed angle) from 90 degrees to approximately 80 degrees as shown.
2. Install the Target Brackets on the aft side of each spinner. Install each bracket with bolt
(AN3-5A), lock washer (MS35335-32) between the bracket and the aft face of spinner bulkhead,
with washer (AN96010L) and nut (MS21043-3) on the forward face of the spinner bulkhead.
Position the Target Brackets for left and right propellers as given below:
a) Left Propeller - four (4) brackets 5 degrees counterclockwise from the blade centerline as
viewed from the rear, in pre-drilled holes 7.35 inches from the hub centerline.
b) Right Propeller - four (4) brackets 20 degrees clockwise from the blade centerline as viewed
from the rear, in pre-drilled holes 7.35 inches from the hub centerline.

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Target-Single Bracket Changes and Installation LA-202 through LA-236

Reference FIGURE 1 and FIGURE 2
1. Bend the Target Brackets (Beechcraft P/N 90-960028-9) or new Target Brackets (90-960028-15)
(closed angle) from 90 degrees to approximately 80 degrees as shown.
2. Install one (1) new or reworked Target Bracket (Beechcraft P/N 90-960028-9 or -15) on the aft
face of each spinner bulkhead. Install bracket with bolt (AN3-5A), with the lock washer
(MS35335-32) between the bracket and the aft face of the spinner bulkhead, with washer
(AN96010L) and nut (MS21043-3) on the forward face of spinner bulkhead as shown. Position
the Target Brackets for the left and the right propeller given below:
a) Left Propeller: One (1) bracket 5 degrees counterclockwise from the blade centerline as
viewed from the rear, in pre drilled hole 7.35 inches from the hub centerline.
b) Right Propeller: One (1) screw 20 degrees clockwise from the blade centerline as viewed
from the rear, in pre drilled hole 7.35 inches from the hub centerline.
3. Install the counterweights on the spinner bulkhead 180 degrees from the target.
Brush Block Mounting Bracket Rework and Installation
Should it become necessary to replace the De-ice Brush Block Mounting Bracket, reference FIGURE
2 and the steps provided below:
1. Remove the Brush Block Mounting Bracket in accordance with the Beechcraft King Air F90
Maintenance Manual.
2. Trim .125 inch from the front edge of the existing de-ice brush mounting bracket and make the
slots .125 inch longer. Break all sharp edges and treat bare metal with primer.
3. Reinstall the Brush Block Mounting Bracket in accordance with the Beechcraft King Air F90
Maintenance Manual.
Synchrophaser Magnetic Target Pick-Up Bracket Rework and Installation
Should it become necessary to replace the Prop Sync Magnetic Pick-up Bracket, remove and discard
the old bracket. Reference FIGURE 2 and the steps below.
1. Remove the Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft
King Air F90 Maintenance Manual.
2. Trim the front edge of the new bracket, P/N 90-960028-1 as necessary to clear the spinner
bulkhead. Break sharp edges and treat all bare metal with primer.
3. Reinstall the Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft
King Air F90 Maintenance Manual. Install the magnetic pick-up with the jam nut on the outside of
the bracket to increase the adjustment length of the magnetic pick-up.

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61-76-20-20 FIGURE 1

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61-76-20-20 FIGURE 2

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100/A100 Quiet Turbofan Propellers

61-00-30-00 Description and Operation
Each engine is equipped with a Raisbeck/Hartzell Quiet Turbofan, four-blade, full feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
Low pitch propeller position is determined by a mechanical monitored hydraulic stop. The propeller
servo piston is connected by four spring-loaded sliding rods to the slip ring mounted behind the
propeller. Movement is transferred through the propeller reversing lever to the Beta valve of the
governor. The initial forward motion of the Beta valve blocks off the flow of oil to the propeller.
Further motion forward dumps the oil from the propeller at a speed lower than that selected on the
governor. The governor pump provides oil pressure to the servo piston and decreases the pitch of
the propeller blades until the feedback of motion from the slip ring pulls the Beta valve into a position
blocking the supply of oil to the propeller, thus preventing further pitch changes. Throughout this and
referenced Beechcraft documentation, the term "Constant Speed Governor", "Propeller Governor",
and "Primary Governor" are used interchangeable to refer to the same engine mounted propeller
speed control unit.

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61-00-30-05 Inspection
Inspections
The maintenance tests on the Raisbeck Engineering Quiet Turbofan Propellers shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
applicable Beechcraft King Air Maintenance Manual, Chapter 5.
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions; and
technical information for the components supplied by Hartzell Propeller Inc.; can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Visually inspect the entire blade (lead, trail, face, and camber sides) for nicks, gouges, and
cracks. See Hartzell Manual No. 149, ATA REF 61-00-49 for damage types and allowances.

61-00-30-10 Troubleshooting
Testing and fault isolation shall be accomplished in accordance with the Beechcraft King Air 100
Series Maintenance Manual and the Hartzell maintenance manuals listed above.

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61-00-30-20 Maintenance Practices

The following maintenance practices shall be accomplished in accordance with the Beechcraft King
Air 100 Series Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual
No. 149, ATA REF 61-00-49), Hartzell Propeller Ice Protection System Manual (Manual No. 180, ATA
REF 30-61-80).
Propeller Care
Removal
Installation
Dynamic Balancing
Dynamic Balancing Test Prep
Dynamic Balancing Test Procedure
Dynamic Balancing Ground Check
Dynamic Balancing Flight Test
Dynamic Balancing Test Recovery
Spinner Dome Removal
Spinner Dome Installation

Engine and Propeller Indicating

61-31-30-00 Description and Operation
Changes to the airspeed and engine indicating instrumentation are defined in this section.

61-31-30-05 Inspections
Verify that all instruments are properly rangemarked as indicated in 61-31-30-20 of this manual.

61-31-30-20 Maintenance Practices

The Airspeed Indicators, Propeller Tachometers, Torque meters, and Propeller De-ice Ammeters
(Model 100 only), are re-rangemarked upon installation of Raisbeck/Hartzell Quiet Turbofan
Propellers. If an instrument needs to be replaced, rangemark it as described in this section.

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Airspeed Indicators
Remove the red radial VMO at 226 knots, and the green arc between 208 knots and 226 knots.
Add red radial VMO at 208 knots.
If the instrument is equipped with a MAX Allowable pointer (Barber Pole), this needs to be re-
calibrated to the new speeds (208 knots to 20,300 feet, decrease 4 knots per thousand feet
above 20,300 ft).
Identify reworked indicators with Placard REI-1001-8.
Propeller Tachometers
Extend the green band from 1,600 RPM to 1,800 RPM. Add red radial at 2,000 RPM, and
remove red radial at 2,200 RPM.
Identify reworked propeller tachometers with Placard REI-1001-8.
Torque Meters
Extend the green band from 1,628 to 1,786 lb-ft. Remove red radial at 1,628 lb-ft. and add a red
radial at 1,786 lb-ft.
Identify reworked indicators with Placard REI-1001-8.
Propeller De-Ice Ammeters Model 100 Only
Extend the green band from 14-18 amperes to 18-24 amperes.
Identify reworked ammeter with Placard REI-1001-8.

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Engine and Propeller Controls

61-76-30-20 Maintenance Practices
Ground Run Power Symmetry and Low Pitch Torque Check
Reference TORQUE CHART A
If this test is not done in zero-wind conditions, take an average of the upwind and downwind readings
to get valid results.
With the propeller levers fully forward, advance the cockpit power lever until the propeller reaches
1,800 RPM. The torque meter reading for the engine should within 40 lb-ft of the value specified by
the pressure altitude and temperature conversion chart (+20/-0 lb-ft).
Repeat this test on the other engine. The difference between the torque meter readings on the
engines should not exceed 20 lb-ft. If the torque meter readings do not fall within the limitations
described above, or the difference between the engines exceeds 20 lb-ft, make the adjustments given
below:
Adjust the stop (Beta) nut on each of the four pitch stop rods for the propeller. All four nuts must be
adjusted to an identical setting. One flat of rotation on the Beta nuts (clockwise to increase;
counterclockwise to decrease) changes engine torque approximately 20 lb-ft. Adjust the Beta nuts as
necessary to bring the engine within the prescribed limits.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULL FORWARD
POWER LEVER SET FOR 1,800 PROPELLER RPM

AMBIENT TEMPERATURE ~ °C
‐40

‐30

‐20

‐10

10

20

30

40

50
0
550
500
450
TORQUE @ 1,800 RPM ~ LB‐FT
400
350
300

61-76-30-20 TORQUE CHART A

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Low Idle Adjustment

Adjust low-idle up or down to achieve propeller RPM of 1,100 +50/0 RPM.

Propeller Autofeathering System (if installed)

Check autofeather operation (Ref. Beechcraft King Air 100 Series Maintenance Manual, Subject
61-21-00).

Constant Speed Governor Adjustment

The Constant Speed Governor is adjusted upon installation of Raisbeck/Hartzell Quiet Turbofan
Propellers. When installing a governor that has not been adjusted in accordance with STC
SA5661NM, the following steps must be accomplished. Reference 61-76-30-20 TABLE 1, and
61-76-30-20 FIGURE 1.
1. Mark the location of the Control Lever and Stop Assembly.
2. Remove the Control Arm.
3. Rotate the Stop Assembly approximately four (4) serrations clockwise, as viewed from the top.
4. Reinstall the Control Lever four (4) serrations clockwise, as viewed from the top.
5. Torque the Stop Assembly and Control Lever clamping bolts to 33-38 lb-in and safety wire.
6. Turn the Feathering Lift Rod adjustment screw in, clockwise as viewed from the top,
approximately ½.
7. Remove the Constant Speed Governor data plate and re-identify using a steel ‘T’ stamp.
Reinstall the data plate.
Alternately, the governor may be sent to an approved Woodward Service Center and adjusted.
Reference 61-76-30-20-00, TABLE 1.
61-76-30-20 TABLE 1

WAS IS

8210-002 T8210-002
GOVERNOR MODEL NO. 8210-0025* T8210-025*
8210-003** T8212-003**

MAX PROPELLER RPM 2,200 2,000

MAX GOVERNOR RPM 4,200*** 3,818***

APPROX. START OF FEATHER AT PROPELLER RPM 1,600 1,490

APPROX. START OF FEATHER AT GOVERNOR RPM 3,055 2,844

* 8210-002 and 8210-025 are equivalent except for the synchrophaser coil which is not
affected by this adjustment.
** Model A100 only.
*** Add 46 RPM for bench setting to 4,246 and 3,864 RPM respectively.

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61-76-30-20 FIGURE 1
Feathering Test and Adjustment
1. Advance the propeller lever to the Full High RPM position and advance the power lever to get
1,800 RPM.
2. Pull the propeller lever back past the detent (Feather Position) and observe the RPM at the start
of feather. The RPM should be 1,500 RPM ±25 RPM.
3. Adjust the feathering lift rod on the Constant Speed Governor as necessary. Adjust clockwise to
reduce the RPM for the start of feather.

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Overspeed Governor Adjustment

The MAX propeller RPM is reduced from 2,200 RPM to 2,000 RPM upon installation of Raisbeck/
Hartzell Quiet Turbofan Propellers. To facilitate this, the Overspeed Governor is adjusted to 2,100
RPM. Should the Overspeed Governor need to be replaced with one that has not been adjusted in
accordance with STC SA5661NM, the following steps must be accomplished.
1. Adjust the Overspeed Governor down 188 RPM by turning the adjustment screw on top of the
governor counter-clockwise slightly less than one (1) turn. One turn equals approximately 195
RPM.
2. Identify the adjusted governor with a “T” stamp in the prefix of the part number on the data plate.
Overspeed Governor Operational Check
1. Set the power levers to 1,700 RPM with the propeller control in the Full High RPM positon.
2. Hold the Overspeed Governor Test switch ON and advance the power levers to increase the
RPM. The tachometer will show 1,750 RPM to 1,950 RPM when the Overspeed Governor is
operating correctly.
3. If necessary, adjust the governor in accordance with 61-76-30-20, Overspeed Governor
Adjustment section in this manual.
Reverse Not Ready Light Switch Adjustment
(B-1 and after)

CAUTION: OBSERVE STANDARD FIRE AND PROPELLER SAFETY

PRECAUTIONS. MAKE SURE RAMP IS CLEAR BEFORE STARTING
ENGINES.
Refer to Beechcraft King Air Operator Manual and start engines. Accomplish the checks and
adjustments as follows:
1. The switches for the PROP REVERSE NOT READY light in the annunciation panel are mounted
in the pedestal adjacent to the propeller lever ball cranks. Access to the switches is through the
cover on the left side of the pedestal. Adjust the switches as follows:
2. With the landing control switch in the DOWN position and the propeller control levers in the full
high RPM (low pitch) position, advance the power lever to obtain 2,000 RPM. Adjust each
switch in its mounting slot so that the PROP REVERSE NOT READY LIGHT (amber) illuminates
at the point when the propeller lever for that switch is set to obtain 1,875 RPM.
3. Retard the power lever to FLIGHT IDLE, perform the engine shutdown check, and stop the
engines as described in the applicable King Air Operators Manual.
Synchrophaser Target Installation
Reference FIGURE 1
Apply Loctite “C” and install screws (2E1377) in the pre-tapped holes in the outer surface of the slip-
ring. Torque these screws to 2-3 pound-inches. These screws are located as given below:
Left Engine Propeller – Four (4) screws aligned with the blade centerlines.
Right Engine Propeller – Four (4) screws at 65 degrees counterclockwise from the blade centerlines
as viewed from the rear.

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Brush Block Mounting Bracket Rework and Installation

Should it become necessary to replace the De-ice Brush Block Mounting Bracket, reference FIGURE
2 and the steps provided below:
1. Remove the Brush Block Mounting Bracket in accordance with the Beechcraft King Air 100 Series
Maintenance Manual.
2. Trim .20 inch from the front edge of the existing de-ice brush mounting bracket and make the
slots .20 inch longer. Break all sharp edges and treat bare metal with primer.
3. Reinstall the Brush Block Mounting Bracket in accordance with the Beechcraft King Air 100
Series Maintenance Manual.
Synchrophaser Magnetic Target Pick-up Bracket Rework and Installation
Should it become necessary to replace the Prop Sync Magnetic Pick-up Bracket, remove and discard
the old bracket. Reference FIGURE 2 and the steps below.
1. Remove the Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft
King Air 100 Series Maintenance Manual.
2. Trim the front edge of the new bracket, P/N 90-960028-1 as necessary to clear the spinner
bulkhead. Break all sharp edges and treat all bare metal with primer.
3. Reinstall the Synchrophaser Magnetic Target Pick-up Bracket in accordance with the Beechcraft
King Air 100 Series Maintenance Manual. Install the magnetic pick-up with the jam nut on the
outside of the bracket to increase the adjustment length of the magnetic pick-up.

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61-76-30-20 FIGURE 2

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61-76-30-97 Engine and Propeller Controls Wiring

The Following changes have been made to the Secondary Low Pitch Stop System on Model A100
aircraft only, serial numbers B-1, B-90 thru B-92, and B-94 and after. The wiring diagrams represent
the “as changed” configuration of the aircraft.
Reference FIGURES 1 thru 4
FIGURE 1 Low Pitch Solenoid A100 only
FIGURE 2 Prop Governor Test Flight Idle Stop B-1, B-90 thru B-92, B-94 thru B-231
FIGURE 3 Prop Governor Test and Flight Idle Stop B-232 and After
FIGURE 4 Propeller Low Pitch Indicator B-1, B-90 thru B-92, B-94 and After
Low Pitch Solenoid A100 Only
1. Cut, cap, and stow wires K25D18 and K36A18N at the Low Pitch Solenoid in accordance with
AC43.13.
2. Remove and discard the Solenoid Plug, MS3106A10SL4S, and the Suppression Diode.
3. Cap the solenoid connector with cover MS25043-10D or MS25043-10DA.
Low Pitch Indicator Switch A100 Only
1. Cut, cap, and stow wires, K72D20, K74A20N, W82C20, and W82D20 at the Low Pitch Indicator
Switch in accordance with AC43.13.
2. Optional, remove and discard the Low Pitch Indicator Switch, P/N 100-369013-1.
Low Pitch Proximity Switch A100 Only
1. Cut, cap, and stow the yellow and blue wires at the Proximity Switch Sensor in accordance with
AC43.13.
2. Optional, remove and discard the Proximity Switch Sensor, P/N 1-889-15.

61-76-30-97 FIGURE 1

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61-76-30-20 FIGURE 2

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-30-20 FIGURE 3

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-30-20 FIGURE 4

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Super King Air 200 Series Propellers

Super King Air “200 Series” includes the following King Air Models and Military Models: 200, 200C,
200T, 200CT, A200 (C-12A & C-12C), A200C (UC-12B), A200CT (C-12D, C-12F, FWC-12D, RC-
12D, RC-12G, RC-12H, RC-12K, RC-12P, and RC-12Q), B200, B200C, B200C (C-12F, C-12R, UC-
12F, and UC-12M), B200T, B200CT, B200GT, and B200CGT.

61-00-40-00 Quiet Turbofan Propellers Description and Operation

Each engine is equipped with a Raisbeck/Hartzell Quiet Turbofan, four-blade, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Quiet Turbofan, four-blade propellers (HC-D4N-3A/D9383K) have a full
feathered angle of 86 degrees at the 30-inch station and mechanical reverse pitch stop of -10.5
degrees ±.5 degree.

61-00-41-00 Swept Turbofan Propellers Description and Operation

Each engine is equipped with a Raisbeck/Hartzell Swept Turbofan, four-blade, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Swept Turbofan Propellers (HC-04N-3A/D9515K) have a full feathered angle
of 84.2 degrees at the 30-inch station and mechanical reverse pitch stop of -10.3 degrees ±.5 degree.

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61-00-42-00 Five-Blade Swept Turbofan Propellers Description and

Operation
Each engine is equipped with a Raisbeck/Hartzell Swept Turbofan, five-blade, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers (5D3-NK366A1/91D15B) have a full
feathered angle of 85.7 degrees at the 30-inch station and mechanical reverse pitch stop of -8.0
degrees.

61-00-40-05 Quiet Turbofan Propellers Inspection

Periodic Inspections
The maintenance tests on the Raisbeck Engineering Quiet Turbofan or Swept Turbofan or Five-Blade
Swept Turbofan Propellers shall be accomplished at the same time as the existing Beechcraft
maintenance tests as given in the Beechcraft Super King Air 200 Maintenance Manual, Chapter 5.
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Hartzell Propeller Owner’s Manual and Logbook
(Manual No. 486, ATA REF 61-00-86)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Visually inspect the entire blade (lead, trail, face, and camber sides) for nicks, gouges, and
cracks. For damage types and allowances see Hartzell Manual No. 149, ATA REF 61-00-49 for
Quiet and Swept Turbofan Propellers and Hartzell Manual No. 486, ATA REF 61-00-86 for Five-
Blade Swept Turbofan Propellers.

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61-00-41-05 Swept Turbofan Propellers Inspection

Reference Chapter 61-00-40-05 of this manual.

61-00-42-05 Five-Blade Swept Turbofan Propellers Inspection

Reference Chapter 61-00-40-05 of this manual.

61-00-40-10 Quiet Turbofan Propellers Troubleshooting

Testing and fault isolation shall be accomplished in accordance with the Beechcraft Super King Air
200 Series Maintenance Manual and Hartzell maintenance manuals listed above.

61-00-41-10 Swept Turbofan Propellers Troubleshooting

Reference Chapter 61-00-40-10 of this manual.

61-00-42-10 Five-Blade Swept Turbofan Propellers Troubleshooting

Testing and fault isolation shall be accomplished in accordance with the Beechcraft Super King Air
200 Series Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook (Manual No.
486).

61-00-40-20 Quiet Turbofan Propellers Maintenance Practices

The following maintenance practices shall be accomplished in accordance with the Beechcraft Super
King Air 200 Series Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49), Hartzell Propeller Ice Protection System Manual (Manual No.
180, ATA REF 30-61-80).
Propeller Care
Blade Damage
Removal
Installation
Dynamic Balancing
Dynamic Balancing Ground Check
Dynamic Balancing Flight Test
Dynamic Balancing Test Recovery
Spinner Dome Removal
Spinner Dome Installation

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61-00-41-20 Swept Turbofan Propellers Maintenance Practices

Reference Chapter 61-00-40-20 of this manual.

61-00-42-20 Five-Blade Swept Turbofan Propellers Maintenance

Practices
The following maintenance practices shall be accomplished in accordance with the Beechcraft Super
King Air 200 Series Maintenance Manual and Hartzell Propeller Owner’s Manual and Logbook
(Manual No. 486, ATA REF 61-00-86), Hartzell Propeller Ice Protection System Manual (Manual No.
180, ATA REF 30-61-80).
Propeller Care
Blade Damage
Removal
Installation
Dynamic Balancing
Dynamic Balancing Ground Check
Dynamic Balancing Flight Test
Dynamic Balancing Test Recovery
Spinner Dome Removal
Spinner Dome Installation

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Flight Controls Swept Turbofan Propellers

61-27-40-05 Flight Controls Inspection Quiet Turbofan Propellers
This section intentionally left blank.

61-27-41-05 Flight Controls Inspections Swept Turbofan Propellers

Verify that the warning placard is installed. Reference 61-27-41-20 of this manual.

61-27-42-05 Flight Controls Inspections Five-Blade Swept Turbofan

Propellers
Reference Section 61-27-41-05 of this manual.

61-27-40-20 Flight Controls Maintenance Practices Quiet Turbofan

Propellers
This section intentionally left blank.

61-27-41-20 Flight Controls Maintenance Practices Swept Turbofan

Propellers
CAUTION: THIS SECTION ONLY APPLICABLE TO AIRCRAFT EQUIPPED WITH
RAISBECK/HARTZELL SWEPT TURBOFAN PROPELLERS HC-D4N-
3A/D9515K OR FIVE-BLADE SWEPT TURBOFAN PROPELLERS 5D3-
NK366A1/91D15B.

NOTE: All work to be accomplished in accordance with the Beechcraft Super King
Air 200 Series Maintenance Manual.
1. Perform CHECKING ELEVATOR TAB FREE PLAY inspection per the Beechcraft Maintenance
Manual and correct any discrepancies.
2. Perform an ELEVATOR TRIM TAB RIGGING procedure per the Beechcraft Maintenance Manual,
except adjust the elevator tab for a deflection of 15 degrees +1/-0 degree DOWN from neutral, in
lieu of the value specified by the MM. All other settings are per the Maintenance Manual.
3. Perform an ELEVATOR TAB INDICATOR ADJUSTMENT procedure per the Beechcraft
Maintenance Manual. Adjust indicator if required.
4. Perform an ELEVATOR TRIM INDICATOR SCALE MARKINGS procedure per the Beechcraft
Maintenance Manual. Remark indicator if required.
For BB-1 thru BB-13, contact Raisbeck Engineering.
1. Remove the right-hand inboard number 11 access panel from the lower side of the horizontal
stabilizer (see picture of location below). This panel allows access to the Elevator Tab Cable
Down Stop (and turnbuckle).
2. Install Placard (P/N REI-1001-13) to the INSIDE surface of the number 11 access panel (see
picture of Placard below), taking care to prepare the surface per steps 2.a & 2.b below.
a. Before applying the placard, clean the INSIDE surface of the access panel with a 2 to 1
mixture of water and isopropyl alcohol. Do not use soaps or other cleaners with lotions or
creams, as they will leave a residue.
b. Saturate a clean paper towel with a solvent-based cleaner and wipe the access panel
surface. Be certain to follow all manufacturers’ safety guidelines when using any solvent.
Dry the surface with a lint-free paper towel before the solvent evaporates.
3. Re-install the number 11 access panel.

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61-27-41-20 FIGURE 1

61-27-42-20 Flight Controls Maintenance Practices Five-Blade Swept

Turbofan Propellers
Reference Section 61-27-41-20 of this manual.

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Engine and Propeller Indicating

61-31-40-00 Description and Operation Quiet Turbofan Propellers
Changes to the airspeed and engine and propeller indicating instruments are defined in this section.

61-31-41-00 Description and Operation Swept Turbofan Propellers

Changes to the airspeed and engine and propeller indicating instruments are defined in this section.

61-31-42-00 Description and Operation Five-Blade Swept Turbofan

Propellers
Changes to the airspeed and engine and propeller indicating instruments are defined in this section.

61-31-40-05 Inspections Quiet Turbofan Propellers

Verify that all instruments are properly rangemarked as indicated in Chapter 61-31-40 of this manual.

61-31-41-05 Inspections Swept Turbofan Propellers

Verify that all instruments are properly rangemarked as indicated in Chapter 61-31-41 of this manual.

61-31-42-05 Inspections Five-Blade Swept Turbofan Propellers

Verify that all instruments are properly rangemarked as indicated in Chapter 61-31-42 of this manual.

61-31-40-20 Maintenance Practices Quiet Turbofan Propellers

The engine and propeller instruments are to be rangemarked as indicated in this section.

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Airspeed Indicators Aircraft equipped with Rockwell Collins Pro Line 21

NOTE: Model 200 and A200 Series aircraft indicate airspeed in KCAS.
Model B200 Series aircraft indicate airspeed in KIAS.

Reference TABLE 1
1. Determine the part number of the installed Adaptive Flight Display (AFD) model AFD-3010 or
AFD-3010E.
61-31-40-20 TABLE 1

AFD P/N Aircraft Collins Beechcraft AFD P/N Aircraft Collins Beechcraft

Installed Model SB Report* Installed Model SB Report*

1084-051 B200 521 Rev 2/3 1084-353 B200GT 546 Rev 3

1084-053 B200 521 Rev 2/3 1084-354 B200GT -- Rev 3

1084-351 B200 -- Rev 2/3 1084-355 B200GT -- Rev 3

1084-352 B200 -- Rev 2/3 1084-358 B200GT -- Rev 3

1084-353 B200 -- Rev 2/3 1084-359 B200GT -- Rev 3

1084-354 B200 -- Rev 3 1084-360 B200GT -- Rev 3

1084-358 B200 -- Rev 3 1753-353 B200GT 546 Rev 3

1753-351 B200 -- Rev 2/3 1753-354 B200GT -- Rev 3

1753-352 B200 -- Rev 2/3 1753-355 B200GT -- Rev 3

1753-353 B200 -- Rev 2/3 1753-358 B200GT -- Rev 3

1753-354 B200 -- Rev 3 1753-359 B200GT -- Rev 3

1753-358 B200 -- Rev 3 1753-360 B200GT -- Rev 3

(* or latest approved revision)
2. If the installed AFD model requires a Collins Service Bulletin (SB) per TABLE 1, remove and ship
to a Collins authorized repair station for rework. The unit will return with a new part number.
3. The AFD must be pin strapped to display the correct limitations for Raisbeck equipped aircraft.
Determine pin strapping by the Raisbeck STCs that are incorporated into the aircraft. The proper
pin strapping is referenced in Beechcraft Report 200E261947. Carefully follow these instructions
to determine how to pin strap the corresponding Collins AFD model.
4. Modify the existing wiring per Beechcraft Report 200E261947 and the manufacturer's approved
maintenance manual.

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Airspeed Indicators
For model 200 and A200 airplanes, remove the red radial (VMCA) at 91 knots and replace with red
radial (VMCA) at 96 knots.
For model B200 series airplanes previously equipped with the hub and propeller combinations listed
below, and for model B200 series airplanes within serial number range: BB-1439, BB-1444 and after
[except Special Editions], and BL-139 and after, remove the red radial (VMCA) at 86 knots and replace
with red radial (VMCA) at 91 knots.
2 ea. Hartzell HC-B3TN-3G (3N) hubs, 3-bladed propeller
2 ea. Hartzell HC-E4N-3G hubs, D9390SK-1R 4-bladed propeller
2 ea. McCauley 4HFR34C754 hubs, 4-bladed propeller
2 ea. McCauley 4HFR34C771 hubs, 4-bladed propeller
2 ea. McCauley 3GFR34C702 hubs, 3-bladed propeller
Identify the re-marked indicators with Placard REI-1001-2.
Propeller Tachometers
No change.
Torque meters
No change.
Ammeters

NOTE: As customer option, the existing ammeter can be replaced with Beechcraft
ammeter (101-389017-13).

Rangemark the green arc from (14 to 18) amperes to (18 to 24) amperes. Identify the re-marked
indicator with Placard REI-1001-2.

61-31-41-20 Maintenance Practices Swept Turbofan Propellers

Reference Section 61-31-42-20 of this manual.

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61-31-42-20 Maintenance Practices Five-Blade Swept Turbofan

Propellers
The engine and propeller instruments are to be rangemarked as indicated in this section.

NOTE: Model 200 and A200 series aircraft indicate airspeed in KIAS but their
limitation markings are located at the markings’ respective KCAS values.
Model B200 and B200GT series aircraft indicate airspeed in KIAS and their
limitation markings are located at the markings’ respective KIAS values.
Model B200GT series aircraft are factory equipped with Rockwell Collins Pro
Line 21 (see section 5.1) or Pro Line Fusion (see section 5.3).

Aircraft Equipped with Rockwell Collins Pro Line 21 – OEM

Reference TABLE 1
1. If installed, remove placard P/N BLR-PL200 from above pilot’s and co-pilot’s PFD:

DISREGARD VMCA RED LINE

VMCA = 92 KIAS
P/N BLR-PL200

2. Referencing TABLE 1, determine the part number of your Adaptive Flight Display (AFD) model
AFD-3010 or AFD-3010E.

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61-31-42-20 TABLE 1
AFD P/N AIRCRAFT COLLINS BEECHCRAFT
INSTALLED MODEL SB REPORT*
1084-051 B200 521 Rev 2/3
1084-053 B200 521 Rev 2/3
1084-351 B200 -- Rev 2/3
1084-352 B200 -- Rev 2/3
1084-353 B200 -- Rev 2/3
1084-354 B200 -- Rev 3
1084-358 B200 -- Rev 3
1753-351 B200 -- Rev 2/3
1753-352 B200 -- Rev 2/3
1753-353 B200 -- Rev 2/3
1753-354 B200 -- Rev 3
1753-358 B200 -- Rev 3
1084-353 B200GT 546 Rev 3
1084-354 B200GT -- Rev 3
1084-355 B200GT -- Rev 3
1084-358 B200GT -- Rev 3
1084-359 B200GT -- Rev 3
1084-360 B200GT -- Rev 3
1753-353 B200GT 546 Rev 3
1753-354 B200GT -- Rev 3
1753-355 B200GT -- Rev 3
1753-358 B200GT -- Rev 3
1753-359 B200GT -- Rev 3
1753-360 B200GT -- Rev 3
* Or latest approved revision.
3. If your AFD model requires a Rockwell Collins Service Bulletin (SB) per TABLE 1, remove and
ship to a Rockwell Collins authorized repair station for rework. The unit will return with a new part
number.
4. Your AFD must be pin strapped to display the correct limitations for your Raisbeck equipped
aircraft. Determine pin strapping by the Raisbeck STCs that are incorporated into the aircraft.
The proper pin strapping is referenced in Beechcraft Report 200E261947. Follow these
instructions to determine how to pin strap your Rockwell Collins AFD model.
5. Modify the existing wiring per Beechcraft Report 200E261947 and the manufacturer's approved
maintenance manual.
Aircraft Equipped with Rockwell Collins Pro Line 21 – Aftermarket
1. Configure your Pro Line 21 installation per BHE & Associates STC SA11133SC, with instructions
for the Raisbeck/Hartzell Swept Turbofan Propellers (D9515K).

NOTE: Raisbeck/Hartzell Composite Five-Blade Swept Turbofan Propellers

(91D15B) have the same limitations as Raisbeck/Hartzell Aluminum Swept
Turbofan Propeller (D9515K) and therefore the BHE & Associates STC
instructions are applicable.

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Aircraft Equipped with Rockwell Collins Pro Line Fusion – OEM

1. If installed, remove BLR-PL200 Placard from above pilot’s and co-pilot’s PFD:

DISREGARD VMCA RED LINE

VMCA = 92 KIAS
P/N BLR-PL200

2. Configure your Beechcraft factory “off the line” Pro Line Fusion installation per Textron Aviation
Fusion Maintenance Manual (document 434-590168-0009) with instructions for enabling either:
a) Sub-type 14 “B200GT W/ RAISBECK PROP MOD” for non-EPIC equipped aircraft.
b) Sub-type 41 “B200GT RAISBECK EPIC PLATINUM” for EPIC Platinum equipped aircraft.
Aircraft Equipped with Rockwell Collins Pro Line Fusion – Aftermarket
1. Configure your Pro Line Fusion installation per BHE & Associates STC SA11136SC or
Rockwell Collins STC SA01769WI with instructions for the Raisbeck D9515K (Swept
Turbofan Propeller) configuration.

NOTE: Raisbeck/Hartzell Composite Five-Blade Swept Turbofan Propellers

(91D15B) have the same limitations as Raisbeck Hartzell Aluminum Swept
Turbofan Propellers (D9515K) and therefore the BHE & Associate or
Rockwell Collins STC instructions are applicable.

Aircraft Equipped with Garmin International G1000

1. Configure your G1000 installation per Garmin International STC SA01535WI-D, with instructions
for the Raisbeck D9515K (Swept Turbofan Propeller) configuration.

NOTE: Raisbeck/Hartzell Composite Five-Blade Swept Turbofan Propellers

(91D15B) have the same limitations as t Raisbeck/Hartzell Aluminum Swept
Blade Turbofan Propellers (D9515K) and therefore the Garmin STC
instructions are applicable.
Model 200 and A200 Series Airspeed Indicator Rework
1. Remove the airspeed indicators and route them to an instrument repair shop for the following
rework:
a) For 200 and A200 series aircraft, remove the red radial (VMCA) at 91 knots and replace with
red radial (VMCA) at 96 knots.
b) Install REI-1001-2 Placard on the reworked instrument’s housing.
c) Reinstall the airspeed indicators and perform pitot static system leak check (Ref. Beechcraft
King Air 200 Series Maintenance Manual, Subject 34-00-00).

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Model B200 Series Airspeed Indicator Rework

1. For B200 series aircraft previously equipped with the hub and propeller combinations listed
below, and for B200 series aircraft within serial number range BB-1439, BB-1444 and after
[except Special Editions], and BL-139 and after, remove the red radial (VMCA) at 86 knots and
replace with a red radial (VMCA) at 91 knots.
2 ea. Hartzell HC-B3TN-3G (3N) hubs, 3-bladed propeller
2 ea. Hartzell HC-E4N-3G hubs, D9390SK-1R 4-bladed propeller
2 ea. McCauley 4HFR34C754 hubs, 4-bladed propeller
2 ea. McCauley 4HFR34C771 hubs, 4-bladed propeller
2 ea. McCauley 3GFR34C702 hubs, 3-bladed propeller
a) Install REI-1001-2 Placard on the reworked instrument’s housing.
b) Reinstall the airspeed indicators and perform pitot static system leak check. (Ref. Beechcraft
King Air 200 Series Maintenance Manual, Subject 34-00-00).
Propeller Ammeter Rework/Replacement
1. Remove the Propeller De-Ice Ammeter and route to an instrument repair shop for rework.
a) Change the green arc from (14 to 18) amperes to (18 to 24) amperes.
b) Install REI-1001-2 Placard on the instrument’s housing.

NOTE: The existing Ammeter may be replaced with Beechcraft Ammeter

(P/N 101-389017) with no rework required.

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Engine and Propeller Controls

61-76-40-20 Maintenance Practices Quiet Turbofan Propellers
Ground Run Power Symmetry and Low Pitch Torque Check

CAUTION: STABILIZED GROUND OPERATION WITHIN THE PROPELLER

RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER
STRESSES AND RESULT IN FATIGUE DAMAGE TO THE
PROPELLER. THIS DAMAGE CAN LEAD TO A REDUCED
PROPELLER FATIGUE LIFE, PROPELLER FAILURE, AND LOSS OF
CONTROL OF THE AIRPLANE. THE PROPELLER RESTRICTED RPM
RANGE IS DEFINED IN THE AIRPLANE FLIGHT MANUAL. CONTACT
HARTZELL PROPELLER FOR CORRECTIVE ACTIONS IF A
PROPELLER RESTRICTION OR LIMITATION IS VIOLATED.
RESTRICTED RANGE IS CONTINUOUS OPERATION BETWEEN 400
AND 1,150 PROPELLER RPM.

CAUTION: OBSERVE STANDARD FIRE AND PROPELLER SAFETY

PRECAUTIONS. MAKE SURE RAMP IS CLEAR BEFORE STARTING
ENGINES.

Refer to the appropriate sections of the Beechcraft Super King Air Pilot’s Operating Handbook and
start engines. Accomplish the checks and adjustments as follows:
Torque Chart A for models 200 and B200.
Torque Chart B for model A200, serial numbers BC-1 and after, BD-1 and after, BP-1, BP-19 thru
BP-22, and BP-24 and after.

NOTE: If this check is not being performed under zero wind conditions, take an
average of the upwind and downwind readings to obtain valid results.
With the propeller levers fully forward, advance the cockpit power lever for the engine until the
propeller reaches 1,800 RPM. The torque meter reading for the engine must not exceed and should
be within 40 lb-ft of the value designated by the pressure altitude and temperature conversion graph
CHART A, or must not exceed and should be within 1.8% of the value designated by the pressure
altitude and temperature conversion graph CHART B, for the ambient conditions under which the
engine is operating. Repeat this check on the other engine. The difference between torque-meter
readings on the engines should not exceed 20 lb-ft (CHART A), or .9% (CHART B). If the torque
meter readings do not fall within the limitations described by the graph or if the difference between the
LH and RH engines exceeds 20 lb-ft (CHART A), or .9% (CHART B), the following adjustments are
required:
When the torque change required to bring an engine within the design limits does not exceed 20 lb-ft
(CHART A), or .9% (CHART B), disconnect the fuel topping governor inner connecting rod and
disconnect the control cable rear clevis from the Beta control cam. Adjust the clevis in or out until
engine torque is within the prescribed limits and the torque of each engine is the same, then
reconnect the inner connecting rod and the rear clevis.
When the torque change required to bring an engine within the prescribed limits exceeds 20 lb-ft
(CHART A), or .9% (CHART B), adjustment of the stop (Beta) nut on each of the four low pitch stop
rods for the propeller is required. All four nuts must be adjusted to an identical setting. One flat of
rotation on the Beta nuts (clockwise to increase or counterclockwise to decrease) changes engine
torque approximately 15 lb-ft (CHART A), or .7% (CHART B). Adjust the Beta nuts as necessary to
bring the engine within the prescribed limits.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULLY FORWARD
POWER LEVER SET FOR 1,800 RPM
AMBIENT TEMPERATURE  ~ °C
‐50

‐40

‐30

‐20

‐10

10

20

30

40

50
0
800
750
700
650
TORQUE @ 1,800 RPM ~ LB‐FT
600
550
500
450
400
350

61-76-40-20 TORQUE CHART A

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULLY FORWARD
POWER LEVER SET FOR 1,800 RPM

61-76-40-20 TORQUE CHART B

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Low Idle Adjustment

Set the condition lever at LOW IDLE and the power level at IDLE. Adjust N1 to achieve a propeller
speed of 1,150 RPM +50/-0 RPM. Perform adjustment per Beechcraft Super King Air 200 Series
Maintenance Manual, Chapter 76.
Constant Speed Governor Adjustment
Perform a functional test of the Constant Speed Governors per Beechcraft Super King Air 200 Series
Maintenance Manual, Chapter 61.
Overspeed Governor Operational Test
Perform an operational test of the Overspeed Governor per Beechcraft Super King Air 200 Series
Maintenance Manual, Chapter 61.
Feathering Adjustment
Adjust autofeather power switch as required per Beechcraft Super King Air 200 Series Maintenance
Manual, Chapter 61.

CAUTION: CONTINUOUS OPERATION BETWEEN 400 AND 1,150 RPM MAY

CAUSE DAMAGE TO PROPELLER.

NOTE: If ground check of the autofeather system is unsatisfactory, the problem may
be that the low pitch stops (propeller blade angles) are too coarse. In this
case, reset the low pitch stops so that the minimum torque value allowed at
1,800 RPM is utilized. This will require lowering low idle (N1) to reduce
propeller idle to 1,150 RPM, reducing torque at low idle.

NOTE: Concerning early model 200 aircraft, serial numbers BB-2 thru BB-733, BB-
735 thru BB-792, BB-794 thru BB-828, BB-830 thru BB-853, BB-871 thru BB-
873, BB-892, BB-893, BB-912, BL-1 thru BL-36, BN-1, and BT-1 thru BT-22:
If ground check of the autofeather system is unsatisfactory, the problem may
be due to the higher oil pressure associated with the four-bladed propeller
tripping the pressure switch prematurely. Raisbeck Engineering Service
Bulletin SB-06-02 provides for replacement of the stock pressure switch with
an approved alternate pressure switch with a higher tripping pressure.

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Synchrophaser Target Screw Installation

Reference FIGURE 1 thru 4
1. Install screws (2E1377) in the pre-threaded holes of the bulkhead with Loctite “C” and torque to
32-48 oz-in as follows:
a) Left Spinner Aft Bulkhead - Four (4) screws aligned with blade centerlines.
b) Right Spinner Aft Bulkhead - Four (4) screws 65 degrees counterclockwise from blade
centerlines as viewed from rear.

Synchrophaser Single Target Installation

Reference FIGURE 1 thru 4

NOTE: Raisbeck Target Bracket P/N 08BC-72-400-1 is a direct replacement for

Beechcraft Target Bracket P/N 90-960028-3. Target Bracket P/N 08BC-72-
400-1 is set at 80 degrees.

NOTE: Beechcraft Service Bulletin 2115 installs an improved Target Bracket

(Beechcraft P/N 90-960028-11).

1. Bend Target Brackets (Beech P/N 90-960028-3) or new Target Brackets (90-960028-11) (closed
angle) from 90 degrees to approximately 80 degrees.
2. Install one (1) new or reworked Target Bracket (Beech P/N 90-960028-3 or -11) on the aft side of
the spinner aft bulkhead. Install each bracket with bolt (AN3-5A), positioning the lock washer
(MS35335-32) between bracket and aft side of spinner aft bulkhead, with washer (AN96010L)
and nut (MS21043-3) on the forward side of spinner aft bulkhead. Position Target Brackets for
left and right propeller as follows:
a) Left Spinner Aft Bulkhead - One (1) bracket 5 degrees counterclockwise from blade
centerline as viewed from rear, in pre-drilled holes R7.261 inches from hub centerline.
b) Right Spinner Aft Bulkhead - One (1) bracket 20 degrees clockwise from blade centerline as
viewed from rear, in pre-drilled holes R7.261 inches from hub centerline.
3. Torque nuts 20 to 25 lb-in above nut running torque.
4. Reinstall retained counterweight on spinner aft bulkhead 180 degrees from target in pre-drilled
hole as shown in FIGURE 3. Torque nut 20 to 25 lb-in above nut running torque.

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Synchrophaser Multiple Target Installation

Reference FIGURES 1 thru 4

NOTE: Raisbeck Target Bracket P/N 08BC-72-400-1 is a direct replacement for

Beechcraft Target Bracket P/N 90-960028-3. Target Bracket P/N
08BC-72-400-1 is set at 80 degrees.

1. Bend the Beechcraft P/N (90-960028-3) Target Brackets (closed angle) from 90 degrees to
approximately 80 degrees.
2. Install Target Brackets (Beech P/N 90960028-3 (as reworked) on the aft side of the spinner aft
bulkhead. Install each bracket with bolt (AN3-5A), positioning the lock washer (MS35335-32)
between bracket and aft side of spinner aft bulkhead, with washer (AN96010L) and nut
(MS21043-3) on the forward side of spinner aft bulkhead. Position Target Brackets for left and
right propellers as follows:
a) Left Spinner Aft Bulkhead - four (4) brackets 5 degrees counterclockwise from blade
centerline as viewed from rear, in pre-drilled holes R7.261 inches from hub centerline.
b) Right Spinner Aft Bulkhead - four (4) brackets 20 degrees clockwise from blade centerline as
viewed from rear, in pre-drilled holes R7.261 inches from hub centerline.
3. Torque nuts 20-25 lb-in above nut running torque.

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De-Ice Brush Block Bracket Rework and Installation

Should it become necessary to replace the De-ice Brush Block Bracket reference FIGURE 4 and the
steps provided below:
1. Remove the Brush Block Bracket and its associated hardware in accordance with the Beechcraft
Super King Air 200 Series Maintenance Manual.
2. Trim .125 inch from the front edge of the new de-ice brush mounting bracket and elongate the
brush retention slots .125 inch aft. Break all sharp edges and treat all bare metal surfaces with
primer.
3. Install the Brush Block Bracket and its associated hardware in accordance with the Beechcraft
Super King Air 200 Series Maintenance Manual.
Synchrophaser and Dynamic Balancing Pick-up Bracket Rework and Installation
Should it become necessary to replace the Synchrophaser and Dynamic Balancing Pick-up Bracket,
reference FIGURE 4 and the steps provided below:
1. Remove the Synchrophaser or Synchrophaser and Dynamic Balancing Pick-up Bracket and
associated hardware in accordance with the Beechcraft Super King Air 200 Series Maintenance
Manual.
2. Synchrophaser Pick-up Bracket, P/N 90-960028-1, trim .75 inch to clear the spinner bulkhead.
Break sharp edges and treat all bare metal surfaces with primer.
3. Reinstall the Synchrophaser or Synchrophaser and Dynamic Balancing Pick-up Bracket and
associated hardware in accordance with the Beechcraft Super King Air 200 Series Maintenance
Manual.

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61-76-40-20 FIGURE 1

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61-76-40-20 FIGURE 2

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61-76-40-20 FIGURE 3

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61-76-40-20 FIGURE 4

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-41-20 Maintenance Practices Swept Turbofan Propellers

Reference Section 61-76-40-20 of this manual.

61-76-42-20 Maintenance Practices Five-Blade Swept Turbofan

Propellers
Power Symmetry and Low Pitch Torque Check

CAUTION: STABILIZED GROUND OPERATION BETWEEN 700 AND 1,150 RPM

IS PROHIBITED.

CAUTION: FOR COLLINS PRO LINE 21 OR PRO LINE FUSION EQUIPPED

AIRCRAFT ONLY:
STABILIZED GROUND OPERATION BETWEEN 400 AND 1,150 RPM
IS PROHIBITED.
1. Position aircraft into the wind.
2. Advance Propeller Lever full forward.
3. Advance Power Lever to obtain exactly 1,800 RPM and record the following:
Outside Air Temperature ________________ °C
Pressure Altitude ________________ ft
Target Torque ________________ lb-ft or % Torque
Left Engine Torque ________________ lb-ft or % Torque
Right Engine Torque ________________ lb-ft or % Torque
Engine Torque Difference ________________ lb-ft or % Torque

CAUTION: USE CHART A FOR MODEL 200, B200, AND B200GT SERIES
TORQUE SETTING VALUES. USE CHART B FOR MODEL A200
SERIES TORQUE SETTING VALUES.
4. Reference appropriate Torque Chart. The torque must be within 40 lb-ft or 2.0% of target torque.
The torque differential between the left and right engines must not exceed 20 lb-ft or 1.0%. If
torque or torque differentials do not fall within tolerances, adjust per the following steps.
a. Adjust the Beta Nuts on each of the three (3) Low Pitch Stop Rods on the propeller. All 3
nuts must be adjusted identically. Clockwise (in) to increase torque. Counterclockwise (out)
to decrease torque. Turning each nut 1 flat equals approximately 20 lb-ft or 1.0% torque.

CAUTION: DO NOT TURN THE LOW PITCH STOP RODS WHILE ADJUSTING
THE BETA NUTS.

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ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULLY FORWARD
POWER LEVER SET FOR 1,800 RPM

CAUTION: STABILIZED GROUND OPERATION BETWEEN 700 AND 1,150 RPM

IS PROHIBITED.

CAUTION: FOR COLLINS PRO LINE 21 OR PRO LINE FUSION EQUIPPED

AIRCRAFT ONLY:
STABILIZED GROUND OPERATION BETWEEN 400 AND 1,150 RPM
IS PROHIBITED.

60

50

40

30

20
AMBIENT TEMPERATURE °C

10

‐10

‐20

‐30

‐40

‐50

‐60
820 770 720 670 620 570 520 470 420 370
LB‐FT TORQUE @ 1,800 RPM

61-76-42-20 TORQUE CHART A

Model 200, B200, and B200GT Series
1. Set Low-Pitch stops to produce these torque values at 1,800 RPM.
2. Adjust N1 to achieve an N2 of 1,150 RPM +50/-0 RPM.
3. Verify propeller RPM at Ground Idle is 1,150 RPM +50/-0 RPM.

Revision AM 277
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Raisbeck Systems as Installed on King Air and Super King Air aircraft

ASSOCIATED CONDITIONS
PROPELLER LEVER SET FULLY FORWARD
POWER LEVER SET FOR 1,800 RPM

CAUTION: STABILIZED GROUND OPERATION BETWEEN 700 AND 1,150 RPM

IS PROHIBITED.

CAUTION: FOR COLLINS PRO LINE 21 OR PRO LINE FUSION EQUIPPED

AIRCRAFT ONLY:
STABILIZED GROUND OPERATION BETWEEN 400 AND 1,150 RPM
IS PROHIBITED.

60

50

40

30

20
AMBIENT TEMPURATURE °C

10

‐10

‐20

‐30

‐40

‐50

‐60
37 35 33 31 29 27 25 23 21 19 17
% TORQUE @ 1,800 RPM

61-76-42-20 TORQUE CHART B

Model A200 BC-1 & after, BD-1 & after, BP-1, BP-19 thru BP-22, and BP-24 & after
1. Set Low-Pitch stops to produce these torque values at 1,800 RPM.
2. Adjust N1 to achieve an N2 of 1,150 RPM +50/-0 RPM.
3. Verify propeller RPM at Ground Idle is 1,150 RPM +50/-0 RPM.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Low Idle Check

CAUTION: STABILIZED GROUND OPERATION BETWEEN 700 AND 1,150 RPM

IS PROHIBITED.

CAUTION: FOR COLLINS PRO LINE 21 OR PRO LINE FUSION EQUIPPED

AIRCRAFT ONLY:
STABILIZED GROUND OPERATION BETWEEN 400 AND 1,150 RPM
IS PROHIBITED.
Set the condition lever at low idle and the power lever at idle. Adjust low idle per applicable King Air
200 Series Maintenance Manual, except adjust N1 (gas generator RPM) to achieve an N2 (propeller
RPM) of 1,150 +50/-0 RPM.
High Idle Check
Adjust high idle in accordance with the applicable Beechcraft King Air 200 Series Maintenance
Manual.
Fuel Cutoff Lever Adjustment
Adjust in accordance with the applicable Beechcraft King Air 200 Series Maintenance Manual.
Propeller Autofeathering System Check

CAUTION: STABILIZED GROUND OPERATION BETWEEN 700 AND 1,150 RPM

IS PROHIBITED.

CAUTION: FOR COLLINS PRO LINE 21 OR PRO LINE FUSION EQUIPPED

AIRCRAFT ONLY:
STABILIZED GROUND OPERATION BETWEEN 400 AND 1,150 RPM
IS PROHIBITED.
Check and adjust autofeather power switch in accordance with the applicable Beechcraft King Air 200
Series Maintenance Manual.

NOTE: If ground check of the autofeather system is unsatisfactory, the problem may
be that the low pitch stops (propeller blade angles) are too coarse. In this
case, reset the low pitch stops so that the minimum torque value allowed at
1,800 RPM is utilized. This will require lowering low idle N1 to reduce
propeller idle (N2) RPM to 1,150, reducing torque at low idle.

NOTE: Concerning early Model 200 aircraft, serial numbers BB-2 thru BB-733, BB-
735 thru BB-792, BB-794 thru BB-828, BB-830 thru BB-853, BB-871 thru BB-
873, BB-892, BB-893, BB-912, BL-1 thru BL-36, BN-1, and BT1 thru BT-22:
If ground check of the autofeather system is unsatisfactory, the problem may
be due to the higher oil pressure associated with the four-bladed propeller
tripping the pressure switch prematurely. Raisbeck Engineering Service
Bulletin No. 06-02 provides for replacement of the stock pressure switch with
an approved alternate pressure switch with a higher tripping pressure.

Governor Operational Check

Check the operation in accordance with the applicable Beechcraft King Air 200 Series Maintenance
Manual.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Propeller Synchrophaser Functional Check

Perform a functional check of the propeller Synchrophaser System in accordance with the applicable
Beechcraft King Air 200 Series Maintenance Manual.
Synchrophaser Target and Pick-Up Installation
Reference FIGURE 1 thru FIGURE 4

NOTE: If using salvaged hardware, ensure locking feature of any nuts fully engage.
Replace as necessary.

Type I Synchrophaser Targets

Reference FIGURE 1
1. Install Synchrophaser Targets as shown.
a) Left Spinner Aft Bulkhead – Install Target (P/N 3360-078) 8.5 degrees, R 6.00 inches
clockwise from Blade No. 1 (REF) centerline (as viewed from the rear). Install three (3)
additional Targets 90 degrees, 180 degrees, and 270 degrees from Blade No. 1 (REF) Target
installation.
b) Right Spinner Aft Bulkhead – Install Target (P/N 3360-078) 16.5 degrees, R6.00 inches
counterclockwise from Blade No. 1 (REF) centerline (as viewed from the rear). Install three
(3) additional Targets 90 degrees, 180 degrees, and 270 degrees from Blade No. 1 (REF)
centerline (as viewed from the rear).
Type II Synchrophaser Target and Balance Weight
Reference FIGURE 2
1. Install Synchrophaser Targets as shown.
a. Left Spinner Aft Bulkhead – Install Target (P/N 3360-078) 8.5 degrees clockwise from Blade
No. 1 centerline (as viewed from the rear). Install salvaged Balance Weight(s) (P/N 90-
960028-23) approximately 180 degrees, R7.26 inches from Target.
b. Right Spinner Aft Bulkhead – Install Target (P/N 3360-078) 16.5 degrees, R6.00 from Blade
No.1 centerline (as viewed from the rear. Install Balance Weight (P/N 90-960028-23)
approximately 180 degrees, R7.26 inches from Target.
Propeller De-Ice Brush Block Bracket Installation
Reference FIGURE 3 and FIGURE 4

NOTE: Early model aircraft Brush Block Brackets are installed at approximately the
5 o’clock position as viewed from the front of the engine. Late model aircraft
Brush Block Brackets are installed at the 9 o’clock position as viewed from
the front of the engine. No rework or replacement of late model Brush Block
Brackets (Beechcraft P/N 101-960115-1) is necessary.
1. Rework and Install Brush Block Brackets as applicable.
a) Trim Brush Block Bracket (Beechcraft P/N 50-910584-33) as shown. Treat all bare metal
edges with primer. Install bracket at the 5 o’clock position (as viewed from the front of the
engine).
b) Install Brush Block Bracket (Raisbeck P/N 15BC-71-200-1) at the 5 o’clock position (as
viewed from the front of the engine).
c) Install Brush Block Bracket (Beechcraft P/N 101-960115-1) at the 9 o’clock position (as
viewed from the front of the engine) in accordance with the applicable Beechcraft King Air
200 Series Maintenance Manual.

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Synchrophaser Pick-Up Installation

Reference FIGURE 3 and FIGURE 4
1. Install Pick-Up Brackets as applicable.
a) Install Raisbeck Pick-Up Bracket (P/N 19BC-61-200-1) on Brush Block Bracket (Raisbeck
P/N 15BC-71-200-1) or Brush Block Bracket (Beechcraft P/N 50-910584-33) as shown.
b) Install Pick-Up Bracket (Raisbeck P/N 19BC-61-200-3) on Brush Block Bracket (Beechcraft
P/N 101-960115-1) as shown.
2. Install Magnetic Pick-Ups (P/N 213181) on Pick-Up Bracket (Raisbeck P/N 19BC-61-200-1 or
19BC-61-200-3) as shown.
3. Install Jam Nuts (P/N 101-960116-3) on Targets (P/N 213181).
4. Adjust the gap between the Magnetic Targets and Pick-Ups in accordance with the applicable
Beechcraft King Air 200 Series Maintenance Manual.
Propeller Brush Block Installation
Reference FIGURE 3 and FIGURE 4
1. Install Brush Bock Assemblies as applicable.
a) Install Brush Block Assembly (P/N 3H2090-1) and MOV Bracket (P/N 105070) on Brush
Block Bracket (Raisbeck P/N 15BC-71-200-1 or Beechcraft P/N 50-910584-33) as shown.
b) Install Brush Block Assembly (P/N 3H2090-1) on Brush Block Bracket (Beechcraft P/N 101-
960115-1) as shown.
Metal Oxide Varistor (MOV) Module Installation
1. Install MOV Module as applicable.
a) Install MOV Module (P/N 106343) on Bracket (P/N 105070) as shown.
b) Install MOV Module Bracket (P/N 103648) on engine as shown. Install Clamp (P/N
MS21919WDG13) on Bracket (P/N 103648) as shown. Install MOV Module (P/N 106343) on
Bracket (P/N 103648) as shown.

Revision AM 281
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Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-42-20 FIGURE 1

Revision AM 282
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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-42-20 FIGURE 2

Revision AM 283
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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-42-20 FIGURE 3

Revision AM 284
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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-76-42-20 FIGURE 4

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Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

Super King Air 300/300LW, B300/B300C Propellers

61-00-51-00 Four-Blade Swept Turbofan Propellers Description and
Operation
Each engine is equipped with a Raisbeck/Hartzell Swept Turbofan, four-blade, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

NOTE: During in-flight engine shut down, the feathered propeller may exhibit slight
rotation. Reference the applicable Pratt & Whitney Canada Maintenance
Manual for inspection and maintenance requirements for engine out,
propeller windmilling greater than 20 RPM and engine oil loss during in flight
engine shut down.
The Raisbeck/Hartzell Four-Blade Swept Turbofan Propellers (HC-E4P-3K/E10479SK) have a full
feathered angle of 78.0 degrees ±.5 degree at the 42-inch station, a mechanical reverse pitch stop of
-14.0 degrees ±.5 degree, and a low pitch stop of 17.1 degrees ±.1 degree.

Revision AM 286
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-00-51-05 Four-Blade Swept Turbofan Propellers Inspection

Periodic Inspections
The maintenance tests on the Raisbeck Engineering Four-Blade Swept Turbofan Propellers shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual, Chapter 5.
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 149, ATA REF 61-00-49)
Propeller Ice Protection System Manual
(Manual No. 180, ATA REF 30-61-80)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Visually inspect the entire blade (lead, trail, face, and camber sides) for nicks, gouges, and
cracks. See Hartzell Manual No. 149, ATA REF 61-00-49 for damage types and allowances.

Revision AM 287
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Maintenance Manual and
Instructions for Continued Airworthiness for
Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-00-51-10 Four-Blade Swept Turbofan Propellers Checks and Fault

Isolation
Unless otherwise stated, testing and fault isolation shall be accomplished in accordance with the
Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual and Hartzell
maintenance manuals listed above.
Power Symmetry and Low Pitch Torque Check
300/300LW Serial Number FA-2 and After and FF-1 and After

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
1. Position aircraft into the wind.
2. Advance Propeller Lever full forward.
3. Advance Power Lever to obtain exactly 1,500 RPM and record the following:
Outside Air Temperature ________________ °C
Pressure Altitude ________________ ft
Target Torque ________________ lb-ft
Left Engine Torque ________________ lb-ft
Right Engine Torque ________________ lb-ft
Engine Torque Difference ________________ lb-ft
4. Reference Torque Chart A. The torque must be within 2.0% of target torque. Torque the
differential between the left and right engines must not exceed 1.0%. If torque or torque
differentials do not fall within tolerances, adjust per following steps.
5. Coarse adjustment (torque adjustment greater than 2.0%). Use this adjustment to bring the
torque of each propeller to within 2.0% of target torque.
a. Adjust the Beta Nuts on each of the four (4) Low Pitch Stop Rods on the propeller. All 4 nuts
must be adjusted identically. Clockwise (in) to increase torque. Counterclockwise (out) to
decrease torque. Turning each nut 1 flat equals approximately .5% torque.

CAUTION: DO NOT TURN THE LOW PITCH STOP RODS WHILE ADJUSTING
THE BETA NUTS.
6. Fine adjustment (torque adjustment 2.0% or less). Use this adjustment to bring the torque of
each engine to within 1.0% of each other.
a. Adjust the Torque Adjusting Screw at the forward end of the Reversing Cable. Clockwise (in)
to decrease torque. Counterclockwise (out) to increase torque. One half turn equals
approximately 1.0% torque.

Revision AM 288
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Raisbeck Systems as Installed on King Air and Super King Air aircraft

RAISBECK/HARTZELL FOUR-BLADE SWEPT

TURBOFAN PROPELLER LOW-PITCH TORQUE CHART
CHART A
Models 300/300LW
Set Low-Pitch stops to produce these torque values at 1,500 RPM.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050 RPM

IS PROHIBITED.

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B300 Serial Number FL-1 and After

B300C Serial Number FM-1 and After

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
1. Position aircraft into the wind.
2. Advance Propeller Lever full forward.
3. Advance Power Lever to obtain exactly 1,500 RPM and record the following:
Outside Air Temperature ____________ °C
Pressure Altitude ____________ ft
Target Torque ____________ lb-ft
Left Engine Torque ____________ lb-ft
Right Engine Torque ____________ lb-ft
Engine Torque Difference ____________ lb-ft
4. Reference Torque Chart B. The torque must be within 2.0% of target torque. Torque the
differential between the left and right engines must not exceed 1.0%. If torque or torque
differentials do not fall within tolerances, adjust per following steps.
5. Coarse adjustment (torque adjustment greater than 2.0%). Use this adjustment to bring the
torque of each propeller to within 2.0% of target torque.
a. Adjust the Beta Nuts on each of the four (4) Low Pitch Stop Rods on the propeller. All 4 nuts
must be adjusted identically. Clockwise (in) to increase torque. Counterclockwise (out) to
decrease torque. Turning each nut 1 flat equals approximately .5% torque.

CAUTION: DO NOT TURN THE LOW PITCH STOP RODS WHILE ADJUSTING
THE BETA NUTS.
6. Fine adjustment (torque adjustment 2.0% or less). Use this adjustment to bring the torque of
each engine to within 1.0% of each other.
a. Adjust the Torque Adjusting Screw at the forward end of the Reversing Cable. Clockwise (in)
to decrease torque. Counterclockwise (out) to increase torque. One half turn equals
approximately 1.0% torque.

Revision AM 290
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Maintenance Manual and
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Raisbeck Systems as Installed on King Air and Super King Air aircraft

RAISBECK/HARTZELL FOUR-BLADE SWEPT

TURBOFAN PROPELLER LOW-PITCH TORQUE CHART
CHART B
Models B300/B300C
Set Low-Pitch stops to produce these torque values at 1,500 RPM.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050 RPM

IS PROHIBITED.

Outside Air Temperature - °C

60

Raisbeck SKA 300 Flight Idle Graph Rev 1.JNB

P
55   RESS
UR
E
 -5000 AL
TI
FT TU
DE
-F
EE
T
50

-30
  00
FT

-20
45   00
FT
 
-10
ISA
Percent Torque at 1500 Propeller RPM

-10
00
ISA

FT
0

 
+1

SE
AL
ISA

 
20
EV
10 EL
+

40 00
ISA

FT

20
00
FT

300
35
  0F
T
400
0F
T

500
0 FT
30 600
0 FT

700
0 FT
800
0FT
25 900
0 FT
10,00
0 FT

12,00
0 FT

20
15,000
FT

15

-50 -40 -30 -20 -10 0 10 20 30 40 50

Revision AM 291
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Low Idle Check

The following steps set N1 (Gas Generator RPM) and N2 (Propeller RPM) at idle.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.

WARNING: STABILIZED GROUND OPERATION WITHIN THE PROPELLER

RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER
STRESSES AND RESULT IN FATIGUE DAMAGE TO THE
PROPELLER AND RESULT IN PROPELLER FAILURE AND LOSS OF
CONTROL OF THE AIRCRAFT.
1. Position Power Lever against the IDLE detent.
2. Position Condition Lever in the LOW IDLE position.
N1 should be between 62% - 65% in this configuration. Adjust as need as follows.
a. Loosen Fuel Control Unit (FCU) lever clamp screw.
b. To increase N1 loosen upper idle adjustment screw and tighten the lower adjustment screw
equally.
To decrease N1, loosen lower idle adjustment screw and tighten the upper idle adjustment screw
equally.
One-sixth of a turn of each screw equals approximately 3.5% change in N1.
c. Tighten FCU lever clamp screw.
3. With N1 set at 62%, N2 should be1,050 +50/-0 RPM. Adjust Ground Idle Solenoid as necessary
to set N2 to 1,050 +50/-0 RPM.
a. Loosen bolts on Ground Idle Solenoid Bracket securing solenoid. Do not loosen bolts
securing bracket to the Reversing Cable.
To increase N2, move Ground Idle Solenoid aft. This will increase pull on Beta Valve when
solenoid is energized, flattening the blade angle.
To decrease N2, move Ground Idle Solenoid forward. This will decrease pull on Beta Valve when
solenoid is energized, resulting in a coarser blade angle.
b. Tighten bolts securing the Ground Idle Solenoid.
4. Adjust taxi speed characteristics as follows.
a. Observing N1 and N2 limitations, adjust Beta Valve Ground Fine Solenoid pull and N1 Low Idle
in concert to tailor taxi characteristics.
Decreasing pull on the Beta Valve and increasing N1 will result in a faster taxi speed.
Increasing pull on the Beta Valve and decreasing N1 will result in a slower taxi speed.
Dead Band Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
High Idle Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Maximum Reverse Check

1. Position Power Lever to the full REVERSE position. N1 should be 84 - 86%.
2. Adjust N1 by turning Reverse Stop Screw in to increase RPM or out to decrease RPM. One half
turn equals approximately 2.7% N1.
When moving Power Lever through ground fine, observe that N2 rises. If there is a slight
decrease in N2 just before going into the reverse detent, it indicates that the propellers are going
into reverse too soon. Adjust as necessary.
a. Measure and record Beta Valve Depth.
b. Remove aft Beta Clevis from Reversing Cam and reinstall it one hole lower than its original
position.
c. Adjust the Rear Clevis to obtain the Beta Valve Depth recorded in Step a. The Torque
Adjusting Screw may be used for fine adjustment of Beta Valve depth.
d. Repeat Steps b and c as necessary to eliminate drop in N2 when the Power Levers pass
through ground fine.

NOTE: If necessary to make this adjustment, repeat Power Symetry and Low Pitch
Torque Check and Low Idle Check.

Power Lever Mismatch Check

Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Governing RPM Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Solenoid Release Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Ground Solenoid Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Beta Valve Adjustment Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Low Pitch Warning Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Maximum Power Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.

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Propeller Synchrophaser Functional Check

1. Start engines and place propeller levers in the HIGH IDLE position. Increase N2 to 1,700 RPM on
both propellers.
2. Retard the propellers levers to reduce N2 to 1,500 RPM on both propellers.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

3. Turn synchrophaser to the ON position.
4. Using the propeller lever, increase N2 of the left propeller slightly and verify that the
synchrophaser system increased N2 of the right propeller to match.
5. If this check is not satisfactory, turn the synchrophaser off and repeat Steps 1 thru 4 to confirm
result. Continue to Step 5 if result is satisfactory.
6. Continue increasing N2 with the propeller lever until synchronization is lost and record that RPM.
7. Using the propeller lever, slowly decrease N2 on the left engine below that of the right engine until
synchronization is lost and record that RPM.
8. The difference between the RPM recorded in Steps 5 and 6, where synchronization was lost
should be at least 23 to 27 RPM. Satisfactory results indicate the right propeller governor is
responding to commands from the control box and the control box is functioning properly. If the
Synchrophaser Functional Check was not satisfactory, perform the Continuity.
Continuity Check
1. Turn the Battery Master Switch OFF and open the Synchrophaser Circuit Breaker.
2. Remove the connector from the Control Box.
3. Reference FIGURE 1 and verify connector plug configuration.
4. Perform continuity checks indicated in TABLE 1 thru 3.

NOTE: Readings in TABLES 1 thru 3 may be as much as 20% higher during heat
soak, after engine shut-down.
5. After continuity checks, close the Synchrophaser Circuit Breaker and turn the Battery Master
Switch ON. Check for voltage between pins A and B. Turn Battery Master Switch OFF and open
Synchrophaser Circuit Breaker.

CAUTION: DO NOT CONNECT THE CONNECTOR PLUG TO THE CONTROL BOX

BEFORE TURNING BATTERY MASTER SWITCH OFF AND OPENING
SYNCHROPHASER CIRCUIT BREAKER.
6. Correct and wiring discrepancies revealed in Steps 1 thru 5. Replace any component that failed
the resistance checks as specified in CHART 1 thru 3 and repeat Steps 1 thru 5 to verify no
discrepancies remain.
7. If no faults were found, restore the Synchronization System and perform the Governor
Operational Check.

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Governor Operational Check

1. Connect breakout box between plug P151 of the aircraft wiring harness and Synchrophaser
Control Box (P/N 2136696 or 213765).

NOTE: Breakout Box T18BC-61-000-1 may be fabricated referencing FIGURE 2.

2. Start engines and set the propeller levers in HIGH. Increase N2 to 1,700 RPM.
3. Using the propeller levers, reduce N2 to 1,500 RPM to verify the propellers are being controlled
by the governors.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

4. Install a jumper between pins R and A. Close the control switch. N2 of the right propeller should
increase.
5. Open the control switch and remove the jumper.
6. Install a jumper between pins L and A. Close the control switch. N2 of the left propeller should
increase.
7. Open the control switch and remove the jumper.
Failure of either governor indicates:
a. No voltage from the control box (pins K and J).
b. Fault in the governor.
8. If there is no N2 increase in Step 4 or 6, check resistance between pins B and J or B and K of the
Control Box. There should be approximately 800 ohm of resistance. This indicates that the 3.9
ohm resistor is functional. Some Control Boxes have an automatic resetting resistor that will
reset when power is removed from the Control Box.
9. If no faults were found, perform the Pick-Up Output Check.

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Pick-Up Output Check

In order to check the Pick-Up voltage output, an oscilloscope is needed to display the output
waveform and measure peak to peak voltages. Reference FIGURE 3.
1. Turn the Battery Master Switch OFF and open the Synchrophaser Circuit Breaker.
2. Disconnect the connector plug from the Control Box.
3. Connect the oscilloscope:
4. Between pins D and E, left Pick-Up.
5. Between pins C and G, right Pick-Up.
6. Start the engines and adjust N2 to 1,700 RPM.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

7. Observe the wave form generated by the Pick-Ups. The wave forms should depart and rise
smoothly from the baseline to positive peak, drop off to negative peak, and return smoothly to
baseline. The ascending and descending sides of the peaks should be symmetrical, with no
secondary peaks. Reference FIGURE 6 for waveform and fault diagnostics.
8. Record peak to peak voltage of the left and right Pick-Ups. The output voltage should be
between 2 and 4 volts.
9. Adjust the gap between the Targets and Pick-Ups to obtain matching output voltage between the
left and right Pick-Ups. The output voltage should match to within .5 volt, necessary to maintain
the 1 volt variation from left to right for proper Control Box function.
Moving the Pick-Up away from the Target will decrease output voltage.
Moving the Pick-Up towards the Target will increase the output voltage.
.007 inch adjustment equals approximately .5 volt.
10. After final adjustment, torque the Pick-Up locknuts to a maximum of 25 lb-in and secure with
lockwire.
Ensure the Battery Master Switch is OFF and the Synchrophaser Circuit Breaker is open before
reconnecting the connector plug to the Control Box.

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61-00-51-10 FIGURE 1

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61-00-51-10 FIGURE 2

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61-00-51-10 FIGURE 3

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61-00-51-20 Four-Blade Swept Turbofan Propellers Maintenance

Practices
Propeller Removal and Installation
Reference the applicable Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual
and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 149) for propeller removal and
installation. Reference FIGURE 4 for External Beta System Decompression Tool (T85-1500,
85-1500-0001T, 85-1500-0002T, or equivalent) general arrangement
Propeller De-Ice and Synchrophaser System Bracketry Installation
300/300LW Serial Number FA-2 thru FA-218, FA-1 and After
B300 Serial Number FL-1 thru FL-35
Reference FIGURE 1
1. Install Pick-Up brackets (P/N 18BC-61-300-1) on Brush Block Bracket (P/N 50-910584-51) with
Bolts (P/N 130909B15), Washers (P/N AN960-10L) and Nuts (P/N NAS679-3A).
2. Install Synchrophaser Pick-Up (P/N 213181) with Lock Nut (P/N 1133-877) on Bracket (P/N18BC-
61-300-1). Adjust Pick-Up as follows:
300/300LW Serial Number FA-219 and After
B300 Serial Number FL-36 and After
B300C Serial Number FM-1 and After
No bracketry changes are made to the OEM installation.
Synchrophaser Target Installation
300/300LW Serial Number FA-2 thru FA-218, FF-1 and After
B300 Serial Number FL-1 thru FL-35
Reference Figure 2
1. Weigh each Target (P/N 14BC-61-400-5) and attaching hardware (Bolt P/N 130909B15, Washer
P/N AN960-10L, and Nut P/N MS21043-3).
Optional installation – Magnetic Target (P/N 3360-078) may be installed on Bracket
(P/N 14BC-61-400-4) with Washer (P/N NAS1149CN616R) and Nut (P/N MS21043-06).

NOTE: If using salvaged attaching hardware, ensure locking feature of Nut (P/N
MS21043-06) fully engages. Replace as necessary.
2. Temporarily assemble Counterweights (P/N 90-960028-5) and Bolts (P/N 130909B15) to equal
the corresponding Target Assembly installation weight recorded in Step 1. Reference the Static
and Dynamic Balance Chapter of Hartzell Standard Practices Manual 202A for alternate
counterweights and attaching hardware.
3. Install Targets and corresponding counterweights as shown.
a. LH propeller – install Target 5 degrees counter-clockwise from blade centerline, as viewed
from rear, in pre-drilled hole approximately R6.96 inches from hub centerline. Install
corresponding Counterweight 180 degrees opposite from Target in pre-drilled hole
approximately R8.11 inches from hub centerline.
b. RH propeller – install Target 20 degrees clockwise from blade centerline, as viewed from
rear, in pre-drilled hole approximately R6.96 inches from hub centerline. Install
corresponding Counterweight 180 degrees opposite from Target in pre-drilled hole
approximately R8.11 inches from hub centerline.

NOTE: If using salvaged attaching hardware, ensure locking feature of Nuts (P/N
MS21043-3 and MS21043-06) fully engage. Replace as necessary.

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300/300LW Serial Number FA-219 and After

B300 Serial Number FL-36 and After
B300C Serial Number FM-1 and After

Reference FIGURE 2
1. Install Magnetic Targets (P/N 3360-078, salvaged) on Brackets (P/N 14BC-61-400-5) with
Washers (P/N NAS1149CN616R) and Nuts (P/N MS21043-06) as shown in FIGURE 2.
2. Weigh each Target Assembly and attaching hardware (Bolts, P/N 130909B15; Washers, P/N
NAS1149F0332P; and Nuts, P/N MS21043-3). Record results for Counterweight installation.
3. Temporarily assemble Counterweights (P/N 90-960028-5) and Bolts (P/N 130909B15) to equal
the corresponding Target Assembly installation weight recorded in Step 1. Reference the Static
and Dynamic Balance Chapter of Hartzell Standard Practices Manual 202A for alternate
counterweights and attaching hardware.
4. Install Target Assemblies and corresponding Counterweights as shown.
a. LH propeller – install Target 5 degrees counter-clockwise from blade centerline, as viewed
from rear, in pre-drilled hole approximately R6.96 inches from hub centerline. Install
corresponding Counterweight 180 degrees opposite from Target in pre-drilled hole
approximately R8.11 inches from hub centerline.
b. RH propeller – install Target 20 degrees clockwise from blade centerline, as viewed from
rear, in pre-drilled hole approximately R6.96 inches from hub centerline. Install
corresponding Counterweight 180 degrees opposite from Target in pre-drilled hole
approximately R8.11 inches from hub centerline.

NOTE: If using salvaged attaching hardware, ensure locking feature of Nuts (P/N
MS21043-3 and MS210-43-06) fully engage. Replace as necessary.

Synchrophaser Pick-Up Installation

1. Adjust Pick-Up to provide an initial clearance between the Target and Pick-Up. The Target
should pass across the center of the Pick-Up, with the face of the Target and Pick-Up parallel.
Aircraft with Magnetic Target - .10 inch.
Aircraft with Ferrous Target - .04 inch.

NOTE: This is an initial setting only. Additional adjustments may be necessary.

Reference 61-00-51-10.
Propeller Balancing
Dynamically balancing the propellers is recommended to reduce vibrations that may be caused by a
rotating system (propeller and engine). Reference Hartzell Propeller Owner’s Manual and Logbook
(Manual No. 149).

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Propeller Controls Nominal Setting

Reference FIGURE 3 for Propeller Controls nominal position.

NOTE: The following steps are initial settings. Additional adjustments may be
needed. Reference 61-00-51-10.

Beta Arm Clevis Nominal Setting

1. Install the Beta Arm and Carbon Block.
2. Set the distance from the end of the Clevis to the Beta Arm to 0.55 inch as shown.
Beta Valve Nominal Setting
Set Beta Valve depth so chamfer is evenly divided by forward face of cap nut.
Nf Link Nominal Setting
Set the gap between the bottom of the Nf Link and the jam nut to .090 to .110 inch as shown.
Ground Fine Solenoid Nominal Setting
Set Ground Fine Solenoid Bracket to affixed position of 2.5 inches. Set Ground Fine Solenoid “Pull”
dimension to .30 to .36 inch as shown.

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61-00-51-20 FIGURE 1

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61-00-51-20 FIGURE 2

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61-00-51-20 FIGURE 3

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61-00-51-20 FIGURE 4

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

61-30-51-20 Four-Blade Swept Turbofan Propellers De-Icing System

Maintenance Practices
Reference 61-00-51-20 FIGURE 1 for De-Ice Brush Block Assembly installation.
1. Install Brush Block Assembly (P/N 3E2090-1).
2. Adjust Brush Block Assembly in accordance with the Beechcraft Super King Air 300/300LW or
B300/B300C Maintenance Manual.

61-00-52-00 Five-Blade Swept Turbofan Propellers Description and

Operation
Each engine is equipped with a Raisbeck/Hartzell Five-Blade Swept Turbofan, full-feathering,
constant-speed, counterweighted, reversing, variable-pitch propeller mounted on the output shaft of
the reduction gear box. The propeller pitch and speed are controlled by engine oil pressure, through
single-action, engine-driven propeller governors. Centrifugal counterweights, assisted by a feathering
spring, move the blades toward the low RPM (high pitch) position and into the feathered position.
Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop
and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to
feather after engine shut down.

61-00-52-05 Five-Blade Swept Turbofan Propellers Inspection

Periodic Inspections
The maintenance tests on the Raisbeck/Hartzell Five-Blade Swept Turbofan Propellers shall be
accomplished at the same time as the existing Beechcraft maintenance tests as given in the
Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual, Chapter 5.
Maintain the Propellers and De-ice Systems in accordance with the applicable Beechcraft King Air
Maintenance Manual and Hartzell system and component manuals listed below.
Ice protection system components supplied by Hartzell Propeller Inc. Applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc. can be found in the
following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com.
Propeller Owner’s Manual and Logbook
(Manual No. 147, ATA REF 61-00-47)
Composite Propeller Blade Field Maintenance and Minor Repair Manual
(Manual No. 170, ATA REF 61-13-70)
Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by
the applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
Daily Checks
Daily Checks are intended as preflight checks for pilots and/or technicians. The Daily Checks are not
intended to require a logbook entry. All other periodic inspections are intended for technician’s entry
in the logbook or other appropriate documentation.
1. Examine the visible hub parts for surface damage.
2. Look for evidence of grease and/or oil leaks.
3. Visually inspect the entire blade (lead, trail, face, and camber sides) for nicks, gouges, and
cracks. See Hartzell Manual No. 170, ATA REF 61-13-70 for damage types and allowances.

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61-00-52-10 Five-Blade Swept Turbofan Propellers Checks and Fault

Isolation
Unless otherwise stated, testing and fault isolation shall be accomplished in accordance with the
Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual and Hartzell
maintenance manuals listed above.
Power Symmetry and Low Pitch Torque Check
300/300LW Serial Number FA-2 and After, Serial Number, FF-1 and After

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
1. Position aircraft into the wind.
2. Advance Propeller Lever full forward.
3. Advance Power Lever to obtain 1,500 RPM and record the following.
Outside Air Temperature ____________ °C
Pressure Altitude ____________ ft
Target Torque ____________ lb-ft
Left Engine Torque ____________ lb-ft
Right Engine Torque ____________ lb-ft
Engine Torque Difference ____________ lb-ft
4. Reference the Torque Chart A. The torque must be within 2.0% of target torque. Torque
differential between the left and right engines must not exceed 1.0%. If torque or torque
differentials do not fall within tolerances, adjust per following steps.
5. Coarse adjustment (torque adjustment greater than 2.0%). Use this adjustment to bring the
torque of each propeller to within 2.0% of target torque.
a. Adjust the Beta Nuts on each of the three (3) Low Pitch Stop Rods on the propeller. All 3
nuts must be adjusted identically. Clockwise (in) to increase torque. Counterclockwise (out)
to decrease torque. Turning each nut 1 flat equals approximately 1.0% torque.

CAUTION: DO NOT TURN THE LOW PITCH STOP RODS WHILE ADJUSTING
THE BETA NUTS.
6. Fine adjustment (torque adjustment 2.0% or less). Use this adjustment to bring the torque of
each engine to within 1.0% of each other.
a. Adjust the Torque Adjusting Screw at the forward end of the Reversing Cable. Clockwise (in)
to decrease torque. Counterclockwise (out) to increase torque.

Revision AM 308
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RAISBECK/HARTZELL FIVE-BLADE SWEPT

TURBOFAN PROPELLER LOW-PITCH TORQUE CHART
Models 300/300LW
CHART A
Set Low-Pitch stops to produce these torque values at 1,500 RPM.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050 RPM

IS PROHIBITED.

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B300 Serial Number FL-1 and After

B300C Serial Number FM-1 and After

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050

PROPELLER RPM IS PROHIBITED. OPERATION BETWEEN 0 AND
400 PROPELLER RPM IS PERMISSIBLE ONLY WITH PROPELLER
FEATHERED.
1. Position aircraft into the wind.
2. Advance Propeller Lever full forward.
3. Advance Power Lever to obtain 1,500 RPM and record the following.
Outside Air Temperature ____________ °C
Pressure Altitude ____________ ft
Target Torque ____________ lb-ft
Left Engine Torque ____________ lb-ft
Right Engine Torque ____________ lb-ft
Engine Torque Difference ____________ lb-ft
4. Reference Torque Chart B. The torque must be within 2.0% of target torque. Torque the
differential between the left and right engines must not exceed 1.0%. If torque or torque
differentials do not fall within tolerances, adjust per following steps.
5. Coarse adjustment (torque adjustment greater than 2.0%). Use this adjustment to bring the
torque of each propeller to within 2.0% of target torque.
a. Adjust the Beta Nuts on each of the three (3) Low Pitch Stop Rods on the propeller. All 3
nuts must be adjusted identically. Clockwise (in) to increase torque. Counterclockwise (out)
to decrease torque. Turning each nut 1 flat equals approximately 0.5% torque.

CAUTION: DO NOT TURN THE LOW PITCH STOP RODS WHILE ADJUSTING
THE BETA NUTS.
6. Fine adjustment (torque adjustment 2.0% or less). Use this adjustment to bring the torque of
each engine to within 1.0% of each other.
a. Adjust the Torque Adjusting Screw at the forward end of the Reversing Cable. Clockwise (in)
to decrease torque. Counterclockwise (out) to increase torque. One half turn equals
approximately 1.0% torque.

Revision AM 310
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RAISBECK/HARTZELL FIVE-BLADE SWEPT

TURBOFAN PROPELLER LOW-PITCH TORQUE CHART
CHART B
Models B300/B300C
Set Low-Pitch stops to produce these torque values at 1,500 RPM.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050 RPM

IS PROHIBITED.

Outside Air Temperature - °C

60

Raisbeck SKA 300 Flight Idle Graph Rev 1.JNB

P
55   RESS
UR
E
 -5000 AL
TI
FT TU
DE
-F
EE
T
50

-30
00
PERCENT TORQUE AT 1500 PROPELLER RPM

FT

-20
45 00
FT
 
-10
ISA

-10
00
ISA

FT
  0
+1
SE
AL
ISA

 
+20
EV
40 10 EL
  00
FT
ISA

 2000 FT
300
35
  0F
T
400
  0F
T

500
0 FT
30 600
0 FT

700
0 FT
800
0 FT

25 900
0 FT
10,0
00 F
T

12,00
0 FT

20
15,000
FT

15

-50 -40 -30 -20 -10 0 10 20 30 40 50

 

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Low Idle Check

The following steps set N1 (Gas Generator RPM) and N2 (Propeller RPM) at idle.

CAUTION: STABILIZED GROUND OPERATION BETWEEN 400 AND 1,050 RPM

IS PROHIBITED. OPERATION BETWEEN 0 AND 400 PROPELLER
RPM IS PERMISSIBLE ONLY WITH PROPELLER FEATHERED.

WARNING: STABILIZED GROUND OPERATION WITHIN THE PROPELLER

RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER
STRESSES AND RESULT IN PROPELLER FAILURE AND LOSS OF
CONTROL OF THE AIRCRAFT.
1. Position Power Lever against the IDLE detent.
2. Position Condition Lever in the LOW IDLE position.
N1 should be between 62% - 65% in this configuration. Adjust as needed as follows.
a. Loosen Fuel Control Unit (FCU) lever clamp screw.
b. To increase N1, loosen upper idle adjustment screw and tighten the lower idle adjustment
screw equally.
To decrease N1, loosen lower idle adjustment screw and tighten the upper idle adjustment screw
equally. One-sixth of a turn of each screw equals approximately 3.5% change in N1.
c. Tighten FCU lever clamp screw.
3. With N1 set at 62% - 65%, N2 should be 1,050 +50/-0 RPM. Adjust Ground Idle Solenoid as
necessary to set N2 to 1,050 +50/-0 RPM.
a. Loosen bolts on Ground Idle Solenoid Bracket securing solenoid. Do not loosen bolts
securing bracket to the Reversing Cable.
To increase N2, move Ground Idle Solenoid aft. This will increase pull on Beta Valve when
solenoid is energized, flattening the blade angle.
To decrease N2, move Ground Idle Solenoid forward. This will decrease pull on Beta Valve when
solenoid is energized, resulting in a coarser blade angle.
4. Adjust taxi speed characteristics as follows:
a. Observing N1 and N2 limitations, adjust Beta Valve Ground Fine Solenoid pull and N1 Low Idle
in concert to tailor taxi characteristics.
Decreasing pull on the Beta Valve and increasing N1 will result in a faster taxi speed.
Increasing pull on the Beta Valve and decreasing N1 will result in a slower taxi speed.
Dead Band Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
High Idle Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Maximum Reverse Check

1. Position Power Lever to the full REVERSE position. N1 should be 84 - 86%.
2. Adjust N1 by turning Reverse Stop Screw in to increase RPM or out to decrease RPM. One half
turn equals approximately 2.7% N1.
3. When moving Power Lever through ground fine, observe that N2 rises. If there is a slight
decrease in N2 just before going into the reverse detent, it indicates that the propellers are going
into reverse too soon. Adjust as necessary.
a. Measure and record Beta Valve Depth.
b. Remove aft Beta Clevis from Reversing Cam and reinstall it one hole lower than its original
position.
c. Adjust the Rear Clevis to obtain the Beta Valve Depth recorded in Step a. The Torque
Adjusting Screw may be used for fine adjustment of Beta Valve depth.
d. Repeat Steps b and c as necessary to eliminate drop in N2 when the Power Levers pass
through ground fine.

NOTE: If necessary to make this adjustment, repeat Power Symetry and Low Pitch
Torque Check and Low Idle Check.

Power Lever Mismatch Check

Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Governing RPM Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Solenoid Release Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Ground Solenoid Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Beta Valve Adjustment Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Low Pitch Warning Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.
Maximum Power Check
Accomplished in accordance with applicable Beechcraft Super King Air Model 300/300LW or
B300/B300C Maintenance Manual.

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Propeller Synchrophaser Functional Check

1. Start engines and place propeller levers in the HIGH IDLE position. Increase N2 to 1,700 RPM on
both propellers.
2. Retard the propellers levers to reduce N2 to 1,500 RPM on both propellers.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

3. Turn synchrophaser to the ON position.
4. Using the propeller lever, increase N2 of the left propeller slightly and verify that the
synchrophaser system increased N2 of the right propeller to match.
If this check is not satisfactory, turn the synchrophaser off and repeat Steps 1 thru 4 to confirm result.
Continue to Step 5 if result is satisfactory.
5. Continue increasing N2 with the propeller lever until synchronization is lost and record that RPM.
6. Using the propeller lever, slowly decrease N2 on the left engine below that of the right engine until
synchronization is lost and record that RPM.
The difference between the RPM recorded in Steps 5 and 6, where synchronization was lost should
be at least 23 to 27 RPM. Satisfactory results indicate the right propeller governor is responding to
commands from the control box and the control box is functioning properly. If the Synchrophaser
Functional Check was not satisfactory, perform the Continuity Check.
Continuity Check
1. Turn the Battery Master Switch OFF and open the Synchrophaser Circuit Breaker.
2. Remove the connector from the Control Box.
3. Reference FIGURE 1 and verify connector plug configuration.
4. Perform continuity checks indicated in TABLE 1 thru 3.

NOTE: Readings in TABLES may be as much as 20% higher during heat soak, after
engine shut-down.
5. After continuity checks, close the Synchrophaser Circuit Breaker and turn the Battery Master
Switch ON. Check for voltage between pins A and B. Turn Battery Master Switch OFF and open
Synchrophaser Circuit Breaker.

CAUTION: DO NOT CONNECT THE CONNECTOR PLUG TO THE CONTROL BOX

BEFORE TURNING BATTERY MASTER SWITCH OFF AND OPENING
SYNCHROPHASER CIRCUIT BREAKER.
6. Correct and wiring discrepancies revealed in Steps 1 thru 5. Replace any component that failed
the resistance checks as specified in TABLE 1 thru 3 and repeat Steps 1 thru 5 to verify no
discrepancies remain.
7. If no faults were found, restore the Synchronization System and perform the Governor
Operational Check.

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Raisbeck Systems as Installed on King Air and Super King Air aircraft

Governor Operational Check

1. Connect Breakout Box between plug P151 of the aircraft wiring harness and Synchrophaser
Control Box (P/N 2136696 or 213765).

NOTE: Breakout Box may be fabricated referencing FIGURE 2.

2. Start engines and set the propeller levers in HIGH. Increase N2 to 1,700 RPM.
3. Using the propeller levers, reduce N2 to 1,500 RPM to verify the propellers are being controlled
by the governors.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

4. Install a jumper between pins R and A. Close the control switch. N2 of the right propeller should
increase.
5. Open the control switch and remove the jumper.
6. Install a jumper between pins L and A. Close the control switch. N2 of the left propeller should
increase.
7. Open the control switch and remove the jumper.
Failure of either governor indicates:
a. No voltage from the control box (pins K and J).
b. Fault in the governor.
8. If there is no N2 increase in Step 4 or 6, check resistance between pins B and J or B and K of the
Control Box. There should be approximately 800 ohm of resistance. This indicates that the 3.9
ohm resistor is functional. Some Control Boxes have an automatic resetting resistor that will
reset when power is removed from the Control Box.
9. If no faults were found, perform the Pick-Up Output Check.

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Pick-Up Output Check

In order to check the Pick-Up voltage output, an oscilloscope is needed to display the output
waveform and measure peak to peak voltages.
1. Turn the Battery Master Switch OFF and open the Synchrophaser Circuit Breaker.
2. Disconnect the connector plug from the Control Box.
3. Connect the oscilloscope:
a. Between pins D and E, left Pick-Up.
b. Between pins C and G, right Pick-Up.
4. Start the engines and adjust N2 to 1,700 RPM.

CAUTION: DO NOT EXCEED TORQUE LIMITATIONS.

5. Observe the wave form generated by the Pick-Ups. The wave forms should depart and rise
smoothly from the baseline to positive peak, drop off to negative peak, and return smoothly to
baseline. The ascending and descending sides of the peaks should be symmetrical, with no
secondary peaks. Reference FIGURE 3 for waveform and fault diagnostics.
6. Record peak to peak voltage of the left and right Pick-Ups. The output voltage should be
between 2 and 4 volts.
7. Adjust the gap between the Targets and Pick-Ups to obtain matching output voltage between the
left and right Pick-Ups. The output voltage should match to within .5 volt, necessary to maintain
the 1 volt variation from left to right for proper Control Box function.
Moving the Pick-Up away from the Target will decrease output voltage.
Moving the Pick-Up towards the Target will increase the output voltage.
.007 inch adjustment equals approximately .5 volt.
8. After final adjustment, torque the Pick-Up locknuts to a maximum of 25 lb-in and secure with
lockwire.
9. Ensure the Battery Master Switch is OFF and the Synchrophaser Circuit Breaker is open before
reconnecting the connector plug to the Control Box.

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61-00-52-10 FIGURE 1

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61-00-52-10 FIGURE 2

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61-00-52-10 FIGURE 3

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61-00-52-20 Five-Blade Swept Turbofan Propellers Maintenance

Practices
Propeller Removal and Installation
Reference the applicable Beechcraft Super King Air 300/300LW or B300/B300C Maintenance Manual
and Hartzell Propeller Owner’s Manual and Logbook (Manual No. 147) for propeller removal and
installation. Reference FIGURE 4 for External Beta System Decompression Tool (85-1500-0002T)
general arrangement.

Propeller De-Ice and Synchrophaser System Bracketry Installation

300/300LW Serial Number FA-2 thru FA-218, Serial Number FF-1 and After
B300 Serial Number FL-1 thru FL-35
Reference FIGURE 1
Assemble Brush Block Brackets (P/N 15BC-72-201-1), Propeller Synchrophaser Pick-Up Brackets
(P/N 18BC-61-300-1), Angle Brackets (P/N AN743-13), Metal Oxide Varistor (MOV) Mounting
Brackets (P/N 105070), and MOV Module Assemblies (P/N 106343) as shown in as shown.
300/300LW Serial Number FA-219 and After
B300 Serial Number FL-36 and After
B300C Serial Number FM-1 and After
Reference FIGURE 1
Assemble Brush Block Brackets (P/N 1BC-72-201-1), Propeller Synchrophaser Pick-Up Brackets
(P/N 18BC-61-300-1), Angle Bracket (P/N AN743-13), Metal Oxide Varistor (MOV) Mounting
Brackets (P/N 105070), and MOV Module Assemblies (P/N 106343) as shown in FIGURE 3.

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Synchrophaser Target Installation

300/300LW Serial Number FA-2 thru FA-218, Serial Number FF-1 and After
B300 Serial Number FL-1 thru FL-35
Reference FIGURE 2
1. Weigh each Target (P/N 14BC-61-400-1) and attaching hardware (Bolts, P/N 130909B15;
Washers, P/N NAS1149CN616R; and Nuts, P/N MS21043-3). Record result for counterweight
installation.
Optional installation – Magnetic Target (P/N 3360-078) may be installed on Bracket
(P/N 14BC-61-400-1) with Washer (P/N NAS1149CN616R) and Nut (P/N MS21043-06).
2. Temporarily assemble Counterweights (P/N 90-960028-5) and Bolts (P/N130909B15) to equal
the corresponding Target installation weight recorded in Step 1. Reference the Static and
Dynamic Balance Chapter of Hartzell Standard Practices Manual 202A for alternate
counterweights and attaching hardware.
3. Install Targets with Bolts (P/N 130909B15), Washers (P/N NAS1149F0332P), and Nuts (P/N
MS21043-3) as shown.
a. LH propeller – Install Target centered 2.5 degrees counterclockwise from blade centerline, as
viewed from rear.
b. RH propeller – Install Target centered 22.5 degrees counterclockwise from blade centerline,
as viewed from rear.
4. Install corresponding Counterweights 180 degrees opposite of Targets as shown.

NOTE: If using salvaged attaching hardware, ensure locking feature of Nuts

(P/N MS21043) fully engage. Replace as necessary.

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300/300LW Serial Number FA-219 and After

B300 Serial Number FL-36 and After
B300C Serial Number FM-1 and After
Reference FIGURE 2
1. Install Magnetic Targets (P/N 3360-078, salvaged) on Brackets (P/N 14BC-61-400-1) with
Washers (P/N NAS1149CN616R) and Nuts (P/N MS21043-06) as shown.
2. Weigh each Target Assembly and attaching hardware (Bolts, P/N 130909B15; Washers, P/N
NAS1149F0332P; and Nuts, P/N MS21043-3). Record results for Counterweight installation.
3. Temporarily assemble Counterweights (P/N 90-960028-5) and Bolts (P/N 130909B15) to equal
the corresponding Target Assembly installation weight recorded in Step 1. Reference the Static
and Dynamic Balance Chapter of Hartzell Standard Practices Manual 202A for alternate
counterweights and attaching hardware.
4. Install Target assemblies with Bolts (P/N 130909B15), Washers (P/N NAS1149F0332P), and
Nuts (P/N MS21043-3) as shown.
a. LH propeller – Install Target Assembly centered 2.5 degrees counterclockwise from blade
centerline, as viewed from rear.
b. RH propeller – Install Target Assembly centered 22.5 degrees counterclockwise from blade
centerline, as viewed from rear.
5. Install corresponding Counterweights 180 degrees opposite of Target Assemblies as shown.

NOTE: If using salvaged attaching hardware, ensure locking feature of Nuts

(P/N MS21043-3 and MS21043-06) fully engage. Replace as necessary.

Synchrophaser Pick-Up Installation

Single or Dual Pick-Up Installation
Reference FIGURE 1
1. Adjust Pick-Up to provide an initial clearance between the Target and Pick-Up. The Target should
pass across the center of the Pick-Up, with the face of the Target and Pick-Up parallel.
Aircraft with Magnetic Target - .10 inch.
Aircraft with Ferrous Target - .04 inch.

NOTE: This is an initial setting only. Additional adjustments may be necessary.

Reference 61-00-52-10 Five-Blade Swept Turbofan Propellers Checks and
Fault Isolation for further adjustment as necessary.
2. Torque Lock Nut to a maximum of 25 lb-in and lockwire after final adjustments.

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Propeller Controls Nominal Setting

Reference FIGURE 3 and set the Propeller Controls to their nominal position. This will establish a
base line condition for proper rigging.

NOTE: The following steps are initial settings only. Addition adjustments may be
necessary.

Beta Arm Clevis Nominal Setting

Install the Beta Arm with the new Carbon Block.
Set the distance from the end of the Clevis to the Beta Arm to .55 inch as shown.
Beta Valve Nominal Setting
Set Beta Valve depth so chamfer is evenly divided by forward face of cap nut as shown. 
Nf Link Nominal Setting
Set the gap between the bottom of the Nf Link and the jam nut to .090 to .110 inch as shown.
Ground Fine Solenoid Nominal Setting
Set Ground Fine Solenoid Bracket to affixed position of 2.5 inches as shown. Set Ground Fine
Solenoid “Pull” dimension to .30 to .36 inch as shown.

Propeller Balancing
Dynamically balancing the propellers is recommended to reduce vibrations that may be caused by a
rotating system (propeller and engine). Reference Hartzell Propeller Owner’s Manual and Logbook
(Manual No.147).

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61-00-52-20 FIGURE 1

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61-00-52-20 FIGURE 2

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61-00-52-20 FIGURE 3

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61-00-52-20 FIGURE 4

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61-30-52-20 Five-Blade Swept Turbofan Propellers Maintenance De-Ice

Practices
Reference 61-00-52-20, FIGURE 1 for De-Ice Brush Block Assembly installation.
1. Install Brush Block Assembly (P/N 3E2090-1) as shown.
2. Adjust Brush Block Assembly in accordance with the Beechcraft Super King Air 300/300LW or
B300/B300C Maintenance Manual.

Five-Blade Swept Turbofan Propellers Indicating

61-31-52-00 Description and Operation
Changes to the airspeed and engine and propeller indicating instruments are defined in this section.

61-31-52-05 Inspections
Verify that all instruments are properly rangemarked as indicated in Chapter 61-31-52-20 of this
manual.

61-31-52-20 Airspeed Indicator Rangemarking

The Airspeed Indicators are rangemarked in accordance with STC SA02559SE as described below.
Reference Chapter 11 for Placard placement.
300/300LW Equipped with Rockwell Collins’ Pro Line 2
Red radial (VMCA) at 95 knots. Install Re-rangemarked Placard (18BC-11-401-1) on indicators.
300/300LW Equipped with Rockwell Collins’ Pro Line 21
Install VMCA Placard (18BC-11-300-1) centered above each pilot’s primary display.
300/300LW Equipped with Rockwell Collins’ Fusion
Install VMCA Placard (17BC-11-300-1) Centered above each pilot’s primary display.
300/300LW Equipped with Garmin’s G1000
Install VMCA Placard (18BC-11-300-1) centered above each pilot’s primary display.
B300/B300C Equipped with Rockwell Collins’ Pro Line 2
Red radial (VMCA) at 97 knots. Install Re-rangemarked Placard (17BC-11-401-1) on indicators.
B300/B300C Equipped with Rockwell Collins’ Pro Line 21
Install a VMCA Placard (17BC-11-001) centered above each pilot’s primary display.
B300/B300C Equipped with Rockwell Collins’ Fusion
Install a VMCA Placard (17BC-11-001) centered above each pilot’s primary display.
B300/B300C Equipped with Gamin’s G1000
Install a VMCA Placard (17BC-11-001) centered above each pilot’s primary display.

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