Airworthiness Directive · Amendment 39-16640 · Flight controls
Reims Aviation S.A. Model F406 Airplanes
This AD applies to REIMS AVIATION S.A. Model F406 airplanes, serial numbers (SNs) 0002, 0003, 0004, 0006, 0008, 0009, 0010, 0012, 0013, 0017, 0024, 0025, 0039, 0042, 0044, 0045, 0066, 0070, 0073, 0074, 0075, 0077, 0080 through 0092, certificated in any category.
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:
Unless already done, do the following actions:
(1) For all affected SNs except F406-0091:
(i) Within the next 10 hours time-in-service (TIS) after February 13, 2007 (the effective date retained from AD 2007-02-12), perform the initial inspection as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010.
(ii) If no cracking is found following the initial inspection required in paragraph (f)(1)(i) of this AD, repetitively thereafter inspect every 50 hours TIS or 1 month, whichever occurs first, until the installation of the modified pulley bracket specified in paragraphs (f)(1)(iii) or (f)(1)(iv) of this AD is done.
(iii) If any cracking is found during the inspections required in paragraphs (f)(1)(i) or (f)(1)(ii) of this AD, before further flight, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(1)(ii) of this AD.
(iv) Within the next 100 hours TIS or 2 months after February 13, 2007 (the effective date retained from AD 2007-02-12), whichever occurs first, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(1)(ii) of this AD.
(v) The modified pulley bracket specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010, may be installed at any time after the inspection required in paragraph (f)(1)(i) of this AD, as long as no cracking is found, but no later than the compliance time specified in paragraph (f)(1)(iv) of this AD. If cracking is found, it must be replaced before further flight as required in paragraph (f)(1)(iii) of this AD.
(2) For serial number F406-0091:
(i) Within the next 10 hours TIS after April 26, 2011 (the effective of this AD), perform the initial inspection as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010.
(ii) If no cracking is found following the initial inspection required in paragraph (f)(2)(i) of this AD, repetitively thereafter inspect every 50 hours TIS or 1 month, whichever occurs first, until the installation of the modified pulley bracket specified in paragraphs (f)(2)(iii) or (f)(2)(iv) of this AD is done.
(iii) If any cracking is found during the inspections required in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, before further flight, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(2)(ii) of this AD.
(iv) Within the next 100 hours TIS or 2 months after April 26, 2011 (the effective date of this AD), whichever occurs first, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(2)(ii) of this AD.
(v) The modified pulley bracket specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, REV 2, dated July 27, 2010, may be installed at any time after the inspection required in paragraph (f)(2)(i) of this AD as long as no cracking is found, but no later than the compliance time specified in paragraph (f)(2)(iv) of this AD. If cracking is found, it must be replaced before further flight as required in paragraph (f)(2)(iii) of this AD.
Note: This AD differs from the MCAI and/or service information as follows: No differences.
