AD 2015-16-07 Airworthiness Directives; REIMS AVIATION S.A. Airplanes

Models named: F406. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Reims Aviation S.A. Model F406 airplanes, serial numbers 0001 through 0098, certificated in any category.

Unless already done, do the actions in paragraphs (f)(1) through (f)(4) of this AD. (1) Before further flight after August 18, 2015 (the effective date retained from AD 2015-16-07), do a visual inspection and a dye or fluorescent penetrant inspection of the rudder control pedal torque tubes, LH (Part Number (P/N) 5115260-1) and RH (P/N 5115260-2), following the instructions of PART A of ASI AVIATION Service Bulletin No.: F406-104, dated July 28, 2015. (2) If no crack is detected during the inspection required by paragraph (f)(1) of this AD, within 100 hours time-in-service (TIS) after August 18, 2015 (the effective date retained from AD 2015-16-07), do a magnetic particle inspection of the rudder control pedal torque tubes, LH (P/N 5115260-1) and RH (P/N 5115260-2), following the instructions of PART B of ASI AVIATION Service Bulletin No.: F406-104, dated July 28, 2015. (3) If any crack is detected on a rudder control pedal torque tube during the inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the affected part with a serviceable part following the instructions of ASI AVIATION Service Bulletin No.: F406-104, dated July 28, 2015. (4) For the purpose of this AD, a serviceable part is: (i) A rudder control pedal torque tube (LH P/N 5115260-1 or RH P/N 5115260-2) that has had a magnetic particle inspection following the instructions of PART B of ASI AVIATION Service Bulletin No.: F406-104, dated July 28, 2015, and no cracks were found; or (ii) A new rudder control pedal torque tube (LH P/N 5115260-1 or RH P/N 5115260-2) that has never been installed on an airplane. (5) You may install a rudder control pedal torque tube P/N 5115260-1 (LH) or P/N 5115260-2 (RH) on an airplane, provided it is a serviceable part.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as detachment of the pilot's rudder control pedal in flight. We are issuing this AD to detect and correct cracking of the pilot rudder control pedal which, if not corrected, could result in detachment of the pedal with possible loss of airplane directional control.

This AD replaces AD 2015-16-07, Amendment 39-18232 (80 FR 49127, August 17, 2015) (“AD 2015-16-07”).