Airworthiness directives › 2016-02-01
AD 2016-02-01 Airworthiness Directives; Airbus Airplanes
Models named: A320-211, -212, -231. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers 0002 through 0104 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (a) of AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), with revised service information for Airbus Model A320-211 and -231 airplanes. Prior to the accumulation of 16,000 total landings, or within 6 months after October 10, 1996 (the effective date of AD 96-18-06), whichever occurs later, perform a visual inspection to detect cracks of the 6 fittings of the pressurized floor at frame 36 under the lower surface panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Accomplishment of the initial inspection required by paragraph (i) of this AD terminates the actions required by this paragraph. (1) If no cracking is found, prior to further flight, renew the zone protective finish, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Repeat the visual inspection thereafter at intervals not to exceed 12,000 landings. (2) If only 1 of the 6 fittings is found to be cracked and that crack is less than or equal to 0.59 inch (15 mm) in length, prior to further flight, replace the cracked fitting with a new fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Thereafter, prior to the accumulation of 500 landings following accomplishment of this replacement, replace the remaining 5 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. (3) If only 1 of the 6 fittings is found to be cracked, and that crack is greater than 0.59 inch (15 mm) in length, prior to further flight, replace all six fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. (4) If 2 or more fittings are found to be cracked, prior to further flight, replace all 6 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph.
Unsafe condition
This AD was prompted by an extended service goal analysis by the manufacturer, which revealed that the compliance times and repetitive inspection intervals should be reduced to meet the design service goal. We are issuing this AD to detect and correct fatigue cracking in the pressurized floor fittings at frame 36, which could result in failure of a floor fitting and subsequent depressurization of the fuselage.
Affected ADs
This AD replaces AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1