AD 2007-02-11 Airworthiness Directives; EXTRA Flugzeugproduktions-und Vertriebs-GmbH Models EA-300, EA-300S, EA-300L, and EA-300/200 Airplanes

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

This AD applies to the following airplanes that are certificated in any category:   Models Serial Nos. EA-300 01 through 62. EA-300L 01 through 71, 73 through 77, 79 through 83, 85 through 89, 91, and 92. EA-300S 01 through 29. EA-300/200 01 through 31 and 1032 through 1039.

To address this problem, you must do the following, unless already done:   Actions Compliance Procedures (1) Inspect, using a fluorescent dye penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, as applicable. You may take “unless already done” credit for the inspections if you previously used Extra Service Bulletin No. 300-2-95 (pages 2-6 at Issue: C, dated July 15, 1998; and pages 1 and 7 through 11 at Issue: D, dated January 30, 2001) (i) For Models EA-300S airplanes: Upon accumulating 250 hours time-in-service (TIS) after December 17, 2002 (the effective date of AD 2002-21-11) or within the next 50 hours TIS after February 28, 2007 (the effective date of this AD), whichever occurs first. (ii) For Models EA-300, EA-300L, and EA-300/200 airplanes: Within the next 50 hours TIS after February 28, 2007 (the effective date of this AD). (iii) For all affected airplanes: If the modifications specified in Part II and Part III of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006, have already been incorporated, no further action is required Follow Part I of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. (2) If cracks are found during the inspection required in paragraph (e)(1) of this AD in areas A, B, and C (as shown in Figure 1 of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006), weld the crack and modify the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts) For all affected airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD in which cracks are found, unless already done Follow Part II of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. (3) If no cracks are found during the inspection required in paragraph (e)(1) of this AD, modify the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts) For all affected airplanes: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done Follow Part II of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. (4) For Models EA-300S and EA-300L airplanes only: Reinforce the fuselage frame underneath the horizontal stabilizer main spar attachment bracket by installing the applicable modification kit (or FAA-approved equivalent parts) (i) For Model EA-300S: Within the next 200 hours TIS after December 17, 2002 (the effective date of AD 2002-21-11) or within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), whichever occurs first, unless already done. (ii) For Model EA-300L: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done Follow Part III of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2002-21-11 are approved for this AD. Related Information (h) The European Aviation Safety Agency (EASA) AD No. 2006-0281, dated September 14, 2006, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006 to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact EXTRA Flugzeugproduktions- und Vertriebs- GmbH, Schwarze Heide 21, D-46569 Huenxe, Germany; fax: (+49)-2858-9137-42. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-775 Filed 1-23-07; 8:45 am] BILLING CODE 4910-13-P

This AD is the result from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified in this AD are intended to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control.