CONTROL QUADRANT MODIFICATION

CESSNA CARAVAN 208 · Service Bulletins

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Overview

This document is a service bulletin for the Cessna Caravan 208 and 208B models, detailing a modification to the control quadrant. The modification aims to enhance the operation of the Emergency Power Lever and Condition Lever by adding stop tabs to prevent inadvertent movements that could lead to engine damage.

Modification improves Emergency Power Lever and Condition Lever operation.
Stop tabs reduce risk of inadvertent lever movement.
Compliance recommended within 200 hours or 12 months.
FAA approval obtained for the modification.
Non-compliance may result in engine damage.
Approximately 5.4 man-hours required for installation.
Parts available from Cessna Parts Distribution.
Applicable to specific serial numbers of models 208 and 208B.

Document

Source

Originally published by mcfarlaneaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Service Bulletins
Year: 2006
File size: 386 KB
Publisher: mcfarlaneaviation.com
Language: en

About this document

What is the CONTROL QUADRANT MODIFICATION?

The CONTROL QUADRANT MODIFICATION is a service bulletins for the CESSNA CARAVAN 208, dated 2006.

Where does the CONTROL QUADRANT MODIFICATION come from?

This copy of the CONTROL QUADRANT MODIFICATION was originally published by mcfarlaneaviation.com and is hosted on Sprinkle as a free, searchable reference copy.

What year was the CONTROL QUADRANT MODIFICATION published?

The CONTROL QUADRANT MODIFICATION — the CESSNA CARAVAN 208 service bulletins on file — is dated 2006.

Documentation completeness

2/7

Most owners only have the POH. Here's the essential set for the CESSNA CARAVAN 208.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins on file
Type Certificate (TCDS)

More CESSNA CARAVAN 208manuals & documents

Cessna Model 208 Series Pilot's Operating HandbookPilot's Operating Handbook

In this document

Purpose

To announce a modification to the control quadrant that assists in optimizing the operation of the Emergency Power Lever and Condition Lever.

Compliance

Recommended compliance should be accomplished within the next 200 hours of operation or 12 months, whichever occurs first.

Material Information

Lists parts and quantities required for the control quadrant modification installation.

Accomplishment Instructions

Step-by-step instructions for preparing the airplane and installing the new control quadrant components.

Owner Notification

Notification to owners regarding the service bulletin and its implications for their aircraft.

Change in Weight and Balance

Negligible change in weight and balance due to the modification.

Safety notes

Non-compliance with this Service Bulletin could result in engine damage.
Improper movements of the Emergency Power Lever and/or Condition Lever may lead to issues.
Ensure all switches are in the OFF/NORM position before maintenance.
Disconnect electrical power from the airplane during maintenance.
Use maintenance warning tags to prevent accidental power connection.

Full document text

Caravan CessnaA Textron Comoanv Service Bulletin March 20, 2006 TITLE CONTROL QUADRANT MODIFICATION EFFECTIVITY Model 208 208B CAB06-3 Serial Numbers 20800001 thru 20800395 208B0001 thru 208B1170 PURPOSE To announce a modification to the control quadrant that is designed to assist in optimizing the operation of the Emergency Power Lever and the Condition Lever by providing stop tabs in the quadrant cover. The stop tab for the Emergency Power Lever is designed to assist in reducing the potential of inadvertent movement of the Emergency Power Lever past the idle position from the stowed position. The lever design has also been changed so the geometry of the lever and system linkage operate to assist in reducing the sensitivity of the lever movement and to make the lever movement more linear relative to its position in the quadrant and resultant engine power. The stop tab for the Condition Lever is designed to assist in reducing the potential of inadvertent movement of the Condition Lever into the cutoff position. Non-compliance with this Service Bulletin could result in engine damage if improper movements are made with the Emergency Power Lever and/or the Condition Lever. COMPLIANCE Recommended: should be accomplished within the next 200 hours of operation or 12 months, whichever occurs first. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. Page 1 of 3 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. Cessna Aircraft Company, Product Support, PO. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800, Facsimile (316) 942-9006 COPYRIGHT © 2006 MAN-HOURS Approximately 5.4 man-hours MATERIAL The parts listed below are available from Cessna Parts Distribution Station for the suggested list price shown. through an appropriate Cessna Service Part Number SK208-166 SL6004-11 SL6004-8 SL6004-9 2613048-22 SL6004-10 2601455-18 2601455-13 C489003 MS21042L08 U074093 Description Control Quadrant Modification Kit Lever (See Note 1) Lever (See Note 2) Lever (See Note 3) Cover Assembly (See Note 3) Lever (See Note 4) Cover Assembly (See Note 4) Guard Assembly (See Note 4) Lock Wire (See Note 5) Nut (See Note 5) Alodine 1132 Marker Qty/Airplane 1 1 1 1 1 1 1 1 12 inches 1 (as required) Price $ 69.90 (A) ea $ 755.00 (PD) ea $ 363.00 (PS) ea $ 302.00 (PS) ea $ 450.00 (S) ea $ 302.00 (PS) ea $ 866.00 (D) ea $ 252.00 (S) ea $ 662.50 (VR) lb $ 0.21 (PS) ea MQ 100 $ 146.00 (VA) ea ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE Applicable to airplanes equipped with a 600 SHP engine. Applicable to airplanes equipped with a 675 SHP engine. Applicable to airplanes equipped with a standard control quadrant cover. Applicable to British Certified airplanes. Applicable to airplanes that are not equipped with an Engine Trend Monitoring (ETM) system. ACCOMPLISHMENT INSTRUCTIONS Service Kit SK208-166: Control Quadrant Modification instructions are attached. CAB06-3 March 20, 2006 NOTE 1: NOTE 2: NOTE 3: NOTE 4: NOTE 5: Page 2 CREDIT Not Applicable OWNER NOTIFICATION On April 3, 2006 the following Owner Advisory message will be sent to applicable owners of record in CAB06-3A. Dear Caravan Owner: This Owner Advisory is to inform you that Cessna Service Bulletin CAB06-3 has been issued to announce a modification to the control quadrant that is designed to assist in optimizing the operation of the Emergency Power Lever and the Condition Lever by providing stop tabs in the quadrant cover. The stop tab for the Emergency Power Lever is designed to assist in reducing the potential of inadvertent movement of the Emergency Power Lever past the idle position from the stowed position. The lever design has also been changed so the geometry of the lever and system linkage operate to assist in reducing the sensitivity of the lever movement and to make the lever movement more linear relative to its position in the quadrant and resultant engine power. The stop tab for the Condition Lever is designed to assist in reducing the potential of inadvertent movement of the Condition Lever into the cutoff position. Non-compliance with CAB06-3 could result in engine damage if improper movements are made with the Emergency Power Lever and/or the Condition Lever. Compliance is recommended: should be accomplished within the next 200 hours of operation or 12 months, whichever occurs first. The information contained in the referenced Cessna Service Bulletin shall be considered an amendment to the Cessna Manufacturer's Service/Maintenance Manual and should be accomplished within the specified time requirement. Please contact a Cessna Caravan or Propjet Service Station for detailed information and arrange to have Cessna Service Bulletin CAB06-3 accomplished on your airplane. CAB06-3 March 20, 2006 Page 3 * * CessnaA Textron Company SK208-166 TITLE CONTROL QUADRANT MODIFICATION EFFECTIVITY Serial Numbers 20800001 thru 20800395 208B0001 thru 208B1170 DESCRIPTION This service kit gives parts and instructions to install a new control quadrant cover, fuel condition lever (FCL), emergency power lever (EPL) and emergency power control cable bracket. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE CAB06-3 CHANGE IN WEIGHT AND BALANCE Negligible March 20, 2006 Page 1 of 8 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication.

Show full text

Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800, Facsimile (316) 942-9006 COPYRIGHT © 2006 Caravan SERVICE KIT Model 208 208B SERVICE KIT SK208-166 MATERIAL INFORMATION The parts below cover installation for one airplane. NEW P/N QUANTITY DESCRIPTION SK208-166 1 Kit, consisting of the following parts: AN3-4A 1 Bolt AN3-5A 2 Bolt AN23-15 MS21045-3 MS24665-86 NAS1149F0332P NAS1149F0363P 1250025-1 2650112-8 1 3 2 1 2 1 1 1 Bolt Nut Cotter Pin Washer Washer Retainer Mount Instructions OLD P/N DISPOSITION None None None Same None None None 2650112-2 and 2650112-6 Discard In addition to the SK208-166 kit, airplanes with a 600 SHP engine installed, NEW P/N QUANTITY DESCRIPTION OLD P/N SL6004-11 1 Lever SL6004-1 order the following part. DISPOSITION Discard In addition to the SK208-166 kit, airplanes with a 675 SHP engine installed, order the following part. NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION SL6004-8 1 Lever SL6004-1 Discard In addition to the SK208-166 kit, airplanes with a standard control quadrant cover installed, order the following parts. NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION SL6004-9 1 Lever SL6004-3 Discard 2613048-22 1 Cover Assembly 2613048 Discard In addition to the SK208-166 kit, British Certified airplanes, order the following parts. NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION SL6004-10 1 Lever SL6004-5 Discard SK208-166 Page 2 SERVICE KIT SK208-166 2601455-18 1 Cover Assembly 2601455 Discard 2601455-13 1 Guard Assembly 2601455 Discard In addition to the SK208-166 kit, airplanes without Engine Trend Monitoring (ETM) installed, order the following parts. NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION C489003 12 inches Wire Same Discard MS21042L08 1 Nut Same Discard Airplanes without ETM installed, the following materials, or equivalent, are necessary. NAME NUMBER MANUFACTURER USE Alodine 1132 U074093 Cessna Aircraft Company To apply to bare metal. Marker Cessna Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS 67218 ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. (2) Disconnect external electrical power. C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them. 2. (Refer to Figure 1, Detail A.) Remove the control quadrant cover and keep the screws that attach it. A. Remove and keep the emergency power lever, the propeller speed control lever, and fuel condition lever knobs and hardware. B. (Airplanes with Engine Trend Monitoring (ETM) installed) Discard the control column cover. C. (Airplanes without ETM installed) Temporarily keep the control column cover to match drill the shear-wire hole in the new control column cover that will be installed in a later step. 3. Replace the emergency power lever and fuel condition lever. A. Disconnect the elevator trim cable assembly from the elevator trim wheel as necessary. (Refer to the Maintenance Manual, Chapter 27, Elevator Trim - Maintenance Manual.) B. Remove the elevator trim wheel from the control quadrant shaft. Keep the hardware. C. Remove the quadrant assembly. (Refer to the Maintenance Manual, Chapter 76, Quadrant Assembly and Controls - Maintenance Practices.) D. (Refer to Figure 1, Detail B.) Remove the shaft and quadrant axle while you hold the stack-up of spacers and other hardware together. E. Remove and discard the fuel condition lever and emergency power lever. SK208-166 Page 3 SERVICE KIT SK208-166 F. Install the SL6004-8 Emergency Power Lever (675 SHP engine) or SL6004-11 Emergency Power Lever (600 SHP engine) and the SL6004-9 Fuel Condition Lever (Standard) or the SL6004-10 Fuel Condition Lever (British certified airplanes) with the kept shaft and spacers. G. Assemble the quadrant. H. Install the quadrant assembly. (Refer to the Maintenance Manual, Chapter 76, Quadrant Assembly and Controls - Maintenance Practices.) I. Rig the emergency power lever annunciator light switch. J. Install the elevator trim wheel with the kept hardware. K. Connect the elevator trim cable assembly to the elevator trim wheel. L. Rig the elevator trim. (Refer to the Maintenance Manual, Chapter 27, Elevator Trim - Maintenance Manual.) 4. (Refer to Figure 1, Detail C.) Replace the emergency power control cable bracket. A. Get access to the bracket for the emergency power control cable by opening the right engine cowling. B. Disconnect the starter-generator cooling hose from the starter-generator to get access to the emergency power control cable bracket. C. Remove the emergency power control cable from the manual override arm. Keep the hardware that attaches it. D. Remove the emergency power control cable bracket from the fuel control unit and from the control cable. Keep the 2650064-2 Bracket, 2650064-3 Bracket, 2650065-1 Bolt and two NAS509-3 Nuts. Discard all other control cable retaining brackets, spacers and hardware. E. Assemble the 2650064-2 Bracket, the 2650064-3 Bracket and the 2650112-8 Mount with two each AN3-5A Bolts, NAS1149F0363P Washers and MS21045-3 Nuts. F. Install the brackets on the fuel control unit with the kept 2650065-1 Bolt and two NAS509-3 Nuts. Safety wire the nuts. (Refer to the Maintenance Manual, Chapter 20, Safetying - Maintenance Practices.) G. Install the control cable on the mount with one each 1250025-1 Retainer, AN3-4A Bolt, NAS1149F0332P Washer and MS21045-3 Nut. H. Connect the starter-generator cooling hose to the starter-generator. 5. (Refer to Figure 1, Detail C.) Do an initial rig of the emergency power control. A. Loosen the nut that attaches the manual override arm of the fuel control unit on its shaft enough to allow the arm to rotate. B. Change the position of the manual override arm so that its centerline is aligned with the stop on the manual override shaft, +7 or - 7 degrees. C. Tighten the nut that holds the manual override arm in place. Attach the nut with one MS24665-86 Cotter Pin. D. Attach the emergency power control cable to the manual override arm with the kept hardware and one MS24665-86 Cotter Pin. E. Make sure that the head of the bolt does not interfere with surrounding structure. If interference is noted, replace the bolt with an AN23-15 Bolt. 6. Connect the airplane battery. 7. Rig the emergency power control. (Refer to the Maintenance Manual, Chapter 76, Engine Control Rigging - Maintenance Practices.) 8. Disconnect the airplane battery. 9. Close the right engine cowling. SK208-166 Page 4 SERVICE KIT SK208-166 10. (Refer to Figure 1, Detail A.) Install the new quadrant cover assembly. (Refer to the Maintenance Manual, Chapter 76, Quadrant Assembly and Controls - Maintenance Practices.) A. (Airplanes without ETM installed) Install shear wire and quadrant cover. (1) Use the kept control column cover as a guide and mark the shear-wire hole location on the new 2613048-22 Cover Assembly (standard) or 2601455-13 Guard and 2601455-18 Cover Assembly (British). (2) Match drill a 0.172-inch diameter hole through the cover. British Certified airplanes, enlarge the hole in the 2601455-18 Cover Assembly only to 0.438 inch diameter. Deburr the hole. (3) Apply Alodine to the hole. (4) Reinstall the kept screw, washer and one new MS21042L08 Nut in the new hole. (5) Install the 2613048-22 Cover Assembly (standard) or 2601455-18 Cover Assembly (British) with the 2601455-13 Guard Assembly and the kept screws. (6) Install one C489003 Wire, cut to length, with the double-twist method around the emergency power lever. (Refer to the Maintenance Manual, Chapter 20, Safetying - Maintenance Practices.) B. (Airplanes with ETM installed) Install the 2613048-22 Cover Assembly (standard) or 2601455-18 Cover Assembly (British) with the 2601455-13 Guard and the kept screws. C. Install the kept knobs on the new levers with the kept hardware. 11. Remove maintenance warning tags and connect the airplane battery. 12. Make an entry in the airplane logbook stating this Service Kit has been installed. SK208-166 Page 5 SERVICE KIT SK208-166 A43182 DETAIL A Cover Assembly-Standard 2601455-18 Cover Assembly 2601455-13 Guard Assembly (1 Each Required) DETAIL A Cover Assembly-British Certified Airplanes 2615R1006 A-C299T514 A-C299T514 Figure 1. Control Quadrant Modification (Sheet 1) SK208-166 Page 6 C -22 sembly ed) B SERVICE KIT SK208-166 A43183 SL6004-8 Lever-Emergency Power SL6004-11 Lever-Emergency Power (600 SHP) (1 Required) SL6004-9 Lever- Fuel Condition (1 Required) Shaft (Reference) L SL6004-8 Lever-Emergency Power (675 SHP) or SL6004-11 Lever-Emergency Power (600 SHP) (1 Required) Shaft (Reference) \r Quadrant Axle (Reference) DETAIL B Control QL SL6004-10 Lever- Fuel Condition (1 Required) iadrant-Standard Quadrant Axle (Reference) DETAIL B Control Quadrant-British Certified Airplanes Figure 1. Control Quadrant Modification (Sheet 2) SK208-166 B-C299T514 B-C299T514 Page 7 - SERVICE KIT SK208-166 AN3-5A Bolt NAS1149F0363P Washer MS21045-3 Nut (2 Each Required) .. 2650112-8 Mount (1 Required) 1250025-1 Retainer (1 Required) AN3-4A Bolt MS21045-3 Nut Control (1 Each Required) Cable (Reference) DETAIL C AN3-10 Bolt (NOTE 1) NAS1149F0332P Washer - (2 Places) 2650071-2 Bushing S1450-3-10-032 Washer AN310-3 Nut (Reference) MS24665-86 Cotter Pin (1 Required) Manual Overide Arm 2650064-3 E (I (Reference) ,rence) within +7 or -7 Degrees VIEW B-B VIEW A-A NOTE 1: If the AN3-10 Bolt interferes with structure, use an AN23-15 Bolt. NOTE 2: Install the cotter pin after you position the manual overide arm. C2650T071 Figure 1. Control Quadrant Modification (Sheet 3) SK208-166 Page 8 A43184 NAS509-3 Nut 2650065-1 Bolt (Reference) Nut (Re Wa (Re MS Col (1 F (NC A B

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