Document ID: chunk:federal_register_of_legislation:F2008L03974:body:0:p1
Version: federal_register_of_legislation:F2008L03974
Segment Type: other
Provision Reference: 
Character Range: 0–3079

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Boeing 717 Series Aeroplanes
AD/B717/31  Elevator Standby Cable  12/2008

Applicability:  McDonnell Douglas Model 717-200 aeroplanes, as identified in Boeing Alert Service Bulletin 717-27A0039, dated 6 December 2007.
Requirement:       1. For all aeroplanes:  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 all applicable corrective actions before further flight.

                   2. For aeroplanes 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 applicable actions specified in Requirements 1 and 2 of this AD in accordance with Boeing Alert Service Bulletin (ASB) 717-27A0039 dated 6 December 2007.

                Later revisions of the above ASB, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2008-18-05 are considered acceptable for compliance with the equivalent Requirements of this AD.

                Note:  FAA AD 2008-18-05 Amdt 39-15662 dated 18 August 2008 refers.
Compliance:     For Requirement 1 - Within 3,000 flight hours or 27 months after the effective date of this AD, whichever occurs later.

                For Requirement 2 - 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.
                This Airworthiness Directive becomes effective on 20 November 2008.

Background:  This AD results from a report of an aborted takeoff due to a control column disconnect.  The issuing of this AD is intended 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