# Cessna Service Bulletin F406-104: No revision named - Rights: © Textron Aviation Inc. Filed by the FAA in regulations.gov docket FAA-2015-3398, the docket of AD 2015-16-07, 2015-16-07 R1. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Cessna Service Bulletin F406-104](https://openairdocs.org/service-documents/cessna/f406-104.md) - Title as filed: SB F406-104 Rev 00 - Pages: 7 - PDF: https://openairdocs.org/files/sha256/8d/33/8d33322f9adbd792a45dbe13b9510eda1646ee6bc8e0cee173e5fb4e2a7cfd28 - Page: https://openairdocs.org/service-documents/cessna/f406-104/file/8d33322f9adb ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 1/7 28th July 2015 SERVICE BULLETIN N° F406-104 MANUFACTURER REFERENCE: N°F406-104 N° ATA: 27 Date: 28th July 2015 TITLE: Inspection of rudder control pedal torque tube EFFECTIVITY Model Serial Number F406 0001 to 0098 PURPOSE A pilot rudder pedal became detached in fligh t. No change in aircraft attitude occurred and the flight continued back. Rudder was control normally by copilot rudder pedal until a safe landing. This service bulletin describes the procedure for detection of potential cracks on rudder control pedal torque tube. COMPLIANCE: MANDATORY APPLICATION : VISUAL AND PENETRANT INSPECTION MUST BE CARRIED OUT PRIOR TO NEXT FLIGHT. REFER TO PART A MAGNETIC PARTICLE INSPECTION MUST BE CARRIED OUT DURING NEXT SCHEDULED 100 FLIGHT HOURS MAINTENANCE CHECKS. REFER TO PART B APPROBATION This service bulletin has been approved under the privileges of the design organization approval EASA 21J.064. This ASI Aviation servi ce bulletin is attached to the AD EASA approval number: 2015- 0159-E. REFERENCE None ### Page 2 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 2/7 28th July 2015 MAN-HOURS Approximately 20 man-hours. MATERIAL Not applicable CREDIT Not applicable OVERVIEW ### Page 3 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 3/7 28th July 2015 ACCOMPLISHMENT INSTRUCTIONS WARNING: WHENEVER MAINTENANCE IS CONDUCTED ON ANY FLIGHT CONTROL SYSTEM REQUIRING REMOVAL/INSTALLATION OF CONTROL CABLES, ENSURE CONTROL CABLES ARE NOT CROSSED DURING CONTROL CABLES REINSTALLATION. PART A : VISUAL AND PENETRANT INSPECTION Instruction VISA INSPECTION A.1 Remove flight compartment carpet and scuff plate following AMM Chapter 25-22-01 page 201 to get access to rudder pedals. A.2 Clean parts with alkaline solvent as per AMM-Chapter 20-30- 04. Torque tubes shall be free from grease or other contaminates which could decrease contrast between a discontinuity and its background. A.3 Inspect visually both torque tube for cracks in welded joint areas. Carry out a penetrant inspection by a qualified personnel on rudder pedal torque tube (both side: pilot and copilot). ### Page 4 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 4/7 28th July 2015 A.4 If any defect is detected, please fill attached form and contact ASI Aviation customer support for further information. If no defect is detected, apply following steps. A.5 Clean parts with alkaline solvent as per AMM-Chapter 20-30- 04 to remove all penetrant substance. A.6 Install flight compartment carpet and scuff plate following AMM Chapter 25-22-01 page 201 to get access to rudder pedals. A.7 Perform adjustement/test of rudder control system following AMM Chapter 27-20-00 page 501 ### Page 5 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 5/7 28th July 2015 PART B : MAGNETIC PARTICLE INSPECTION Instruction VISA INSPECTION B.1 Remove Rudder pedal assembly following AMM Chapter 27- 20-01 page 206. B.2 Clean parts with alkaline solvent as per AMM-Chapter 20-30- 04. Torque tubes shall be free from grease or other contaminates which could restrict particle movement. B.3 Carry out a magnetic particle inspection by a qualified personnel on rudder pedal torque tube (both side: pilot and copilot). Magnetic particle inspection can be performed using the fluorescent, wet continuous or direct current technique whichever possibilities. Cracks can occur at welded joint between torque tube and pedals. B.4 If any defect is detected, please fill attached form and contact ASI Aviation customer support for further information. ### Page 6 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 6/7 28th July 2015 If no defect is detected, apply following steps. B.5 Demagnetize parts after final inspection. B.6 Clean parts with alkaline solvent as per AMM-Chapter 20-30- 04 to remove all magnetic substance. B.7 Install Rudder pedal assembly following AMM Chapter 27-20- 01 page 206. B.8 Perform adjustement/test of rudder control system following AMM Chapter 27-20-00 page 501 OWNER NOTIFICATION The Service Bulletin F406-104 dated 28th July 2015 will be addressed to the owners of the F406 airplanes. It is recommended to the customers to contact ASI AVIATION for any further information relating to the application of this Service Bulletin on your airplane. ASI AVIATION Aérodrome de Reims-Prunay 51360 Prunay France Tel : (33) 3.26.48.46.65 Customer Support Website: http://asi-aviation.fr/asi-aviation-support/1.html ### Page 7 ASI AVIATION 51360 PRUNAY - FRANCE Service Bulletin N° F406-104 Page 7/7 28th July 2015 INSPECTION FORM SB-F406-104 Company : ................................ ................................ ................................ ................................ ...... Adress : ................................ ................................ ................................ ................................ .......... ................................ ................................ ................................ ................................ ....................... ................................ ................................ ................................ ................................ ....................... Name : ................................ ........................ Occupation : ................................ ........................ Email : ................................ ........................ Telephone : ................................ ................ Actual configuration: Serial Number: F406- ................. Defect is detected on LH rudder pedal torque tube: □ Yes (Visual / Penetrant / Magnetic particle inspection) □ No Defect is detected on LH rudder pedal torque tube: □ Yes (Visual / Penetrant / Magnetic particle inspection) □ No (Surround applied inspection) Maintenance Phase : ................................ ......... Date : .......................... Total flight hours : ....................... Total landings : ........................... Commentary : ................................ ................................ ................................ ................................ . ................................ ................................ ................................ ................................ ....................... ................................ ................................ ................................ ................................ ....................... ................................ ................................ ................................ ................................ ....................... To send at : http://asi-aviation.fr/asi-aviation-support/1.html Or by letter at : ASI Aviation Support Client Aérodrome de Reims-Prunay 51360 Prunay, France --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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