AD/B737/314 Cracking Around Heads of Fasteners (Cth)
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 737 Series Aeroplanes
| AD/B737/314 | Cracking Around Heads of Fasteners | 2/2008 |
Applicability: | Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, as identified in Boeing Special Attention Service Bulletin 737-53-1267, dated |
Requirement: | 1. Perform detailed and high-frequency eddy current inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the STA 259.5 circumferential butt splice, by doing all of the actions specified in Part 1 of the Accomplishment Instructions of the Boeing Special Attention Service Bulletin 737-53-1267. The following exception is provided: 2. If any crack is found during any inspection required by this AD, repair in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1267, dated November 28, 2006. 3. Perform the preventive modification in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1267, dated Note 1: FAA AD 2007-26-04 refers. Note 2: Accomplishing repairs and modifications described in paragraphs (1) and (2) of this AD is considered acceptable for compliance with repair requirements of paragraphs (f) and (g) FAA AD 92-25-09 as referenced by AD/B737/313, for the areas of the station (STA) 259.5 circumferential butt splice only. Note 3: Inspection described in paragraph 1 of this AD are not required for areas of the STA 259.5 circumferential butt splice that have been modified in accordance with Boeing Service Bulletin 737-53-1076. Boeing Service Bulletin 737-53-1076, |
Compliance: | 1. At the applicable initial compliance time specified in paragraph 1.E. ''Compliance'' of Boeing Special Attention Service Bulletin 737-53-1267, dated 28 November 2006, except where the Service Bulletin specifies compliance times relative to the release date of the service bulletin, this AD requires compliance at compliance times relative to the effective date of this AD. 2. Subsequent to requirement 1, if required, before further flight. 3. At the applicable compliance time specified in paragraph 1.E. ''Compliance'' of Boeing Special Attention Service Bulletin 737-53-1267, dated 28 November 2006, except where the Service Bulletin specifies compliance times relative to the release date of the service bulletin, this AD requires compliance at compliance times relative to the effective date of this AD. |
| This Airworthiness Directive becomes effective on 14 February 2008. | |
Background: | This AD results from a report that an operator found multiple cracks in the fuselage skin of a Model 737-200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers 19 and 24. We are issuing this AD to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. |
David Punshon
Delegate of the Civil Aviation Safety Authority
4 January 2008
0
0
0