Airworthiness Directive · Amendment 39-18279 · Wings
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188A and 188C airplanes, certificated in any category, serial numbers 1001 and subsequent.
We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating the left and right lower surface panels of the wings are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking at these panels, and repair if necessary. The AD also requires a one-time bolt- hole eddy current inspection of all open holes for cracking, repair if necessary, and modification. We are issuing this AD to prevent fatigue cracking of the left and right lower surface panels of the wings, which could result in reduced structural integrity of the airplane.
At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Inspect for cracking of the inboard and outboard sides of the lower splice joint at BL 65, using X-ray, ultrasonic, and bolt-hole eddy current inspection techniques, as applicable, and repair any cracking found, in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-707C, Revision C, dated April 30, 2014. All applicable repairs must be done before further flight. Repeat the inspections at intervals not to exceed 2,000 flight hours, until the modification required by paragraph (h) of this AD has been done. Accomplishing the inspections required by this paragraph terminates the inspections required by paragraphs A. and B. of AD 81-03-53R1, Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347, January 25, 1982).
(1) Before the accumulation of 19,000 total flight hours.
(2) Within 600 flight hours or 365 days after the effective date of this AD, whichever occurs first.
At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD: Do a bolt-hole eddy current inspection of all open holes for cracking, repair any cracking found before further flight, and modify the BL 65 wing root lower joint, in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-707C, Revision C, dated April 30, 2014. Accomplishing this modification terminates the inspections required by paragraph (g) of this AD.
(1) Before the accumulation of 29,000 total flight hours.
(2) Within 600 flight hours or 365 days after the effective date of this AD, whichever occurs first.
Although Lockheed Martin Electra Service Bulletin 88/SB-707C, Revision C, dated April 30, 2014, specifies to submit a report of crack findings, this AD does not include that requirement.
