AD 2014-10-01 Airworthiness Directives; Vulcanair S.p.A. Airplanes

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

This AD applies to Vulcanair S.p.A. Models P 68, P 68B, P 68C, P 68C-TC, P 68 “OBSERVER,” P68TC “OBSERVER,” and P68 “OBSERVER 2” airplanes, serial numbers (S/N) 01 through 429, S/Ns 431 through 452, and S/N 454, certificated in any category.

Unless already done, do the following actions specified in paragraphs (f)(1) through (f)(8) of this AD, to include all subparagraphs. (1) Within 10 days after June 18, 2014] (the effective date of this AD), incorporate Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010, into the FAA-approved maintenance program (maintenance manual) following Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010. (2) Within 10 days after June 18, 2014 (the effective date of this AD), determine the safe life limit of the wing structure as follows: (i) For all rows except rows (c) and (e) in table 1, of paragraph 1.3, of Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010, use the safe life limit specified in the appropriate row of the table; and (ii) For rows (c) and (e) in table 1, of paragraph 1.3, of Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010, before further flight, you must modify the wing structure following Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010. After modification, use the safe life limit specified in the appropriate row of the table. (3) Before reaching the life limit as determined in paragraph (f)(2) of this AD, before further flight, you must replace the wing structure and wing fuselage attachments and bolts with new ones. Do the replacement following Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010, as specified in the instructions in WORK PROCEDURE, paragraph 2 of Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010. (4) Do an initial inspection of the wing structure as specified in the instructions in paragraph 2.1 of Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010, at the applicable times as specified in paragraphs (f)(4)(i) and (f)(4)(ii). Repetitively thereafter inspect and replace the wing structure following the limitations in Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010. (i) For aircraft that have not exceeded the safe life limit hours time-in-service (TIS) on the wing structure as determined in paragraph (f)(2) of this AD: Before accumulating 6,000 hours TIS on the wing structure or within 100 hours TIS after June 18, 2014 (the effective date of this AD), whichever occurs later, follow Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010. You may take “unless already done” credit for this inspection if inspected in compliance with AD 2008-24-11, Amendment 39-15751 (73 FR 72314; November 28, 2008); or (ii) For aircraft that have exceeded the safe life limit hours TIS on the wing structure as determined in paragraph (f)(2) of this AD: Within 100 hours TIS after June 18, 2014 (the effective date of this AD), follow Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010. (5) Before accumulating 8,500 hours TIS since new on the stabilator, within 500 hours TIS after January 2, 2009 (the effective date of AD 2008-24-11, Amendment 39-15751 (73 FR 72314; November 28, 2008)), or within 500 hours TIS from the last inspection done in compliance with AD 2008-24-11, whichever occurs later, do the initial inspection of the stabilator following paragraph 2.2 of Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010, or Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 120, Revision 1, dated June 7, 2006. Repetitively thereafter inspect the stabilator following the limitations in Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010. (6) If any cracks are found during the inspections required in paragraphs (f)(4) and/or (f)(5) of this AD, before further flight, modify the wing structure following Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010. (7) For certain Model P 68 airplanes, AD 2009-24-03, Amendment 39-16090 (74 FR 62211, November 27, 2009) requires repetitive inspections of the front and rear wing spars for cracks and modification if cracks are found. The modification terminates the repetitive inspections required in AD 2009-24-03 and may be done regardless if cracks are found. The actions of AD 2009-24-03 are independent of this AD action and remain in effect. (8) EASA AD No.: 2010-0051, dated March 25, 2010; Vulcanair Aircraft, P68 Variants, Maintenance Manual Supplement NOR10.771-52, 1st Issue, dated March 1, 2010; Vulcanair Aircraft, P68 Variants, Mandatory Service Bulletin No. 162, dated March 1, 2010; Vulcanair S.p.A. Service Instruction No. 88, dated March 1, 2010; and Vulcanair S.p.A. Service Instruction No. 89, dated March 1, 2010, base the required preventive and corrective actions on allowing flight with known cracks in critical structure. The FAA's Small Airplane Directorate does not allow further flight with known cracks in critical structure without additional substantiating data. Advisory Circular (AC) 23-13A, Chapter 6, dated September 29, 2005, describes what additional data is required to allow flight with known cracks (found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf ).

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: Mike Kiesov, Aerospace Safety Engineer, FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: mike.kiesov@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.

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 cracking and/or corrosion of the wing spar. We are issuing this AD to detect and correct cracking and corrosion of the wing spars, which, if not corrected, could result in structural failure of the wing.

This AD supersedes AD 2008-24-11, Amendment 39-15751 (73 FR 72314; November 28, 2008).