Airworthiness Directive · Amendment 39-17604 · Fuselage
The Boeing Company Airplanes
This AD applies to all The Boeing Company Model 717-200 airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by multiple reports of cracks of overwing frames. This AD requires repetitive inspections for cracking of the overwing frames, and corrective actions if necessary. We are issuing this AD to detect and correct such cracking that could sever a frame, which may increase the loading of adjacent frames, and result in damage to the adjacent structure and consequent loss of structural integrity of the airplane.
At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a general visual inspection and a high frequency eddy current (HFEC) inspection for cracking of the left-side and right-side overwing frames at stations 674, 696, and 715; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-53A0034, Revision 1, dated November 7, 2012. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-53A0034, Revision 1, dated November 7, 2012, except as provided by paragraph (h) of this AD.
(1) Before the accumulation of 12,000 total flight cycles.
(2) Within 24 months or 8,275 flight cycles after the effective date of this AD, whichever occurs first.
Modification of left-side and right-side overwing frames at stations 674, 696, and 715, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 717-53-0035, dated June 8, 2012, terminates the inspections required by paragraph (g) of this AD, and extends the compliance time of the modified area for the next repetitive HFEC inspection to 45,000 flight cycles after the modification, provided that the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD are accomplished, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 717-53-0035, dated June 8, 2012. Do the inspections specified in paragraph (g) of this AD prior to, or concurrently with, the modification specified in paragraph (h) of this AD.
(1) The overwing frame improvement modification of left-side and right-side overwing frames at stations 674, 696, and 715 is installed and HFEC inspection is done within 45,000 flight cycles from the time the modification is installed, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 717-53-0035, dated June 8, 2012.
(2) If no crack is found during any inspection specified by paragraph (h)(1) of this AD, the HFEC inspections at the modified area are repeated thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 717-53-0035, dated June 8, 2012.
(3) If any crack is found during any inspection specified by paragraph (h)(1) of this AD, the frame is repaired or replaced using a method approved in accordance with the procedures specified in paragraph (j) of this AD, before further flight.
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.
Aircraft
