Airworthiness Directive · Amendment 39-17089 · Horizontal stabilizer structure
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 reports of cracks found on the center section ribs of the horizontal stabilizers. This AD requires repetitive inspections for cracking of the aft face of the left and right rib hinge bearing lugs of the center section of the horizontal stabilizer; and crack measurement, repairs, post-repair repetitive inspections, and installation of a new center section rib if necessary. We are issuing this AD to detect and correct cracking in the left and right bearing lugs of the rib hinge spreading at the same time, which could result in failure of both hinge bearing lugs. Failure of the hinge bearing lugs could result in the inability of the horizontal stabilizer to sustain flight loads and thereby reduce the controllability of the airplane.
Before the accumulation of 35,000 total flight cycles, or within 8,275 flight cycles after the effective date of this AD, whichever occurs later: Do an ETHF inspection for cracks of the aft face on the left and right rib hinge bearing lugs of the center section of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011. If no crack is found, repeat the inspection thereafter at intervals not to exceed 10,500 flight cycles.
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, measure the length of the crack, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011.
For any crack that meets “Condition 2A” of Table 1 of 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011: Do the actions in paragraphs (i)(1) and (i)(2) of this AD.
(1) Before further flight, do a blend out repair, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011.
(2) Within 14,200 flight cycles after accomplishing the blend out repair required by paragraph (i)(1) of this AD: Do an ETHF inspection of the blend out repair area for cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,400 flight cycles.
(i) If any crack is found during the ETHF inspection required by paragraph (i)(2) of this AD: Before further flight, remove the cracked center section rib of the horizontal stabilizer and install a new center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011.
(ii) Within 35,000 flight cycles after the installation of the new center section rib, do the actions in paragraph (g) of this AD.
For any crack that meets “Condition 2D” of Table 1 of 1.E., “Compliance,” of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011: Before further flight, remove the cracked center section rib of the horizontal stabilizer and install a new center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011. Within 35,000 flight cycles after the installation of the new rib, do the actions in paragraph (g) of this AD.
Although Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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
