Airworthiness Directive · Amendment 39-15662 · McDonnell Douglas Model 717-200 Airplanes
McDonnell Douglas Model 717-200 Airplanes
This AD applies to McDonnell Douglas Model 717-200 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 717-27A0039, dated December 6, 2007.
We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires inspecting the drive assembly of the aft elevator standby loop of the elevator standby cable system for interference between the clevis and bolt of the bellcrank assembly, correct orientation of the pull-pull cable clevis bolt, and excessive freeplay of the bellcrank assembly bearing, and corrective actions if necessary. This AD also requires modifying the pull-pull cable clevis in the drive assembly of the aft elevator standby loop for certain airplanes. This AD results from a report of an aborted takeoff due to a control column disconnect. We are issuing this AD to prevent binding of the bolt that connects the cable 264A clevis to the bellcrank assembly against the adjacent (upper) clevis of the pull-pull cable assembly. This binding condition could result in slow airplane rotation or a control column disconnect during takeoff and a runway excursion if takeoff must be aborted.
Comply with this AD within the compliance times specified, unless already done.
Do the applicable actions specified in paragraphs (f)(1) and (f)(2) of this AD at the time specified, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-27A0039, dated December 6, 2007.
(1) For all airplanes: Do a general visual inspection of the drive assembly of the aft elevator standby loop of the elevator standby cable system for interference between the clevis and bolt of the bellcrank assembly, correct orientation of the pull-pull cable clevis bolt, and excessive freeplay of the bellcrank assembly bearing. Do the inspection within 3,000 flight hours or 27 months after the effective date of this AD, whichever occurs later. Do all applicable corrective actions before further flight.
(2) For airplanes identified in the service bulletin as Group 1, Configuration 1: Modify the pull-pull cable clevis in the drive assembly of the aft elevator standby loop of the elevator standby cable system. Do the modification at the applicable time specified in paragraph 1.E., “Compliance,” of the service bulletin; except, where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.
