Airworthiness Directive · Amendment 39-17427 · Wings
Kelowna Flightcraft R & D Ltd. Airplanes
This AD applies to Tracor (Convair) Model 340 and 440 airplanes, including airplanes modified by Supplemental Type Certificates (STC) SA1096WE http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BAB5BE3241FF1FD085256CC10080DDDC?OpenDocument&Highlight=sa1096we (commonly referred to as Model 640 airplanes), STC SA6088NM http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BEFFE27E85EAFF9186257714007C8B4B?OpenDocument&Highlight=sa6088nm (commonly referred to as Model 5800 airplanes), and STC SA4-1100 http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/AFD81364EE6A3EAC85256CC2000C5CC2?OpenDocument&Highlight=sa4-1100 (commonly referred to as Model 580 airplanes) and Military Model C-131B, C-131D, C-131E, and C131F/R4Y-1 airplanes; certificated in any category.
We are adopting a new airworthiness directive (AD) for certain Tracor (Convair) Model 340 and 440 airplanes and certain Military Model C-131B, C-131D, C-131E, and C131F/R4Y-1 airplanes. This AD requires repetitive inspections of the lower skin of the wings for cracking around the inboard side of the wing station (WS) 6 and 7 access panel doubler fingers and between stringers 5 and 11; repetitive inspections of the lower skin of the wings for cracking around stringers 6, 8, and 10, and around the WS 6 and WS 7 access panel doubler fingers; and repair if necessary. This AD was prompted by a report of a crack found on the lower skin of the right-hand wing between WS 5 and WS 6. We are issuing this AD to detect and correct fatigue cracking of the lower skin of the wings, which could result in reduced structural integrity of the wings.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 20 flight hours after the effective date of this AD: Do a one-time detailed inspection for cracking of the lower skin of the left-hand (LH) and RH wings around the inboard side of the WS 6 and WS 7 access panel doubler fingers and between stringers 5 and 11, in accordance with the Accomplishment Instructions of Kelowna Flightcraft Service Bulletin 340-57-001, dated February 12, 2013. Repeat the inspection thereafter at intervals not to exceed 1,000 flight hours.
Within 100 flight hours after the effective date of this AD: Do an eddy current inspection for cracking of the lower skin of the LH and RH wings for cracking around stringers 6, 8, and 10, and around the WS 6 and WS 7 access panel doubler fingers, in accordance with the Accomplishment Instructions of Kelowna Flightcraft Service Bulletin 340-57-001, dated February 12, 2013. Repeat the inspection thereafter at intervals not to exceed 1,000 flight hours.
If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, repair using a method approved by either the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
The inspections required by this AD are approved as a method of compliance to the structurally significant detail (SSD) 57-1-4 inspection required by AD 92-06-06, Amendment 39-8186 (57 FR 9382, March 18, 1992), for only the locations addressed by the detailed and eddy current inspections specified in paragraphs (g) and (h) of this AD. Inspections at all other locations addressed by SSD 57-1-4 remain applicable.
Submit a report of the findings (both positive and negative) of each inspection required by paragraphs (g) and (h) of this AD to Kelowna Flightcraft Convair Division, 5655 Airport Way, Kelowna, Canada BC, V1V 1S1; telephone (250) 807-5416; fax (250) 765-7140; email matt_palmberg@flghtcraft.ca; at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
