Airworthiness Directive · Amendment 39-14898 · EXTRA Flugzeugproduktions-und Vertriebs-GmbH Models EA-300, EA-300S, EA-300L, and EA-300/200 Airplanes
EXTRA Flugzeugproduktions-und Vertriebs-GmbH Models EA-300, EA-300S, EA-300L, and EA-300/200 Airplanes
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. |
We are adopting a new airworthiness directive (AD) to supersede AD 2002-21-11, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. AD 2002-21-11 currently requires you to inspect, using a fluorescent dye check penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, repair any cracks found, and modify the horizontal stabilizer. That AD also requires a limit on operation to the Normal category until the initial inspection and modification on airplanes with less than 200 hours time-in-service is done. Since we issued AD 2002-21-11, cracks have been found on Models EA-300L and EA-300/200 airplanes. Consequently, this AD adds airplanes to the Applicability section and requires you to inspect and modify the upper longeron at the horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD 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.
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. |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
