Airworthiness Directive · Amendment 39-18503 · Stabilizers
The Boeing Company Airplanes
Superseded. A later AD replaced this one: AD 2018-10-08. Comply with the one in force.
This AD applies to The Boeing Company Model 717-200 airplanes, certificated in any category, as specified in Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 717-200 airplanes. This AD was prompted by multiple reports of the vertical stabilizer leading edge showing signs of fastener distress. This AD requires a detailed inspection for any distress of the vertical stabilizer leading edge skin, and related investigative and corrective actions if necessary. This AD also requires, for certain airplanes, repetitive detailed inspections of the spar cap for any loose and missing fasteners, repetitive eddy current testing high frequency (ETHF) and radiographic testing (RT) inspections of the spar cap for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct any crack in the vertical stabilizer leading edge and front spar cap, which may result in the structure becoming unable to support limit load, and may lead to the loss of the vertical stabilizer.
Except as required by paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015: Do a detailed inspection for any distress of the vertical stabilizer leading edge skin and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight.
For all airplanes on which no cracking was found during any related investigative action required by paragraph (g) of this AD: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection thereafter at the intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015.
(1) Do detailed inspections for any loose and missing fasteners of the vertical stabilizer leading edge as specified in “Part 4” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015.
(2) Do eddy current testing high frequency (ETHF) and radiographic testing (RT) inspections for any crack of the vertical stabilizer spar cap as specified in “Part 2” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015; or do ETHF inspections for any crack of the vertical stabilizer spar cap as specified in “Part 3” of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015.
(1) Where Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015 specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
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
