Airworthiness Directive · Amendment 39-19628 · Fuselage
Airbus SAS Airplanes
This AD applies to the Airbus SAS airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) 2014-20-04, which applied to all Airbus SAS Model A318 and A319 series airplanes; Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-20-04 required repetitive inspections of the titanium angles between the belly fairing and the keel beam side panel, an inspection of the open holes of cracked titanium angles, and corrective action if necessary. This AD continues to require those actions, adds Model A320-216 airplanes, and requires a detailed inspection for, and replacement of, certain rivets, and corrective actions if necessary. This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2014-20-04, with no changes. For Model A320-211 and -231 series airplanes, manufacturer serial numbers 003 through 092 inclusive: Prior to the accumulation of 12,000 total landings on the airplane, or within 300 days after January 10, 1994 (the effective date of AD 93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), whichever occurs later, modify the belly fairing structure, in accordance with the Accomplishment Instructions of an Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. As of November 7, 2014 (the effective date of AD 2014-20-04), use only the Airbus service bulletin specified in paragraph (g)(3) of this AD.
(1) Airbus Industrie Service Bulletin A320-53-1014, dated June 25, 1992.
(2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, dated May 26, 1993.
(3) Airbus Service Bulletin A320-53-1014, Revision 2, dated September 1, 1994.
This paragraph restates the requirements of paragraph (h) of AD 2014-20-04, with updated service information. At the latest of the compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD: Do a detailed inspection for cracking of the four titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
(1) Before the accumulation of 30,000 total flight cycles or 60,000 total flight hours, whichever occurs first after first flight of the airplane.
(2) Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after modification of the airplane as required by paragraph (g) of this AD, or after installation of new titanium angles, provided that, prior to installation, a rototest for cracking on the open holes has been accomplished with no crack findings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
(3) Within 3,000 flight cycles or 6,000 flight hours, whichever occurs first after November 7, 2014 (the effective date of AD 2014-20-04).
This paragraph restates the requirements of paragraph (i) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is no crack finding: Accomplish the actions specified in either paragraph (i)(1) or (i)(2) of this AD.
(1) Repeat the inspection required by paragraph (h) of this AD at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first.
(2) Before further flight after the inspection required by paragraph (h) of this AD, remove all inspected titanium angles, accomplish a rototest for cracking on the open holes and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
This paragraph restates the requirements of paragraph (j) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is any crack finding: Before further flight, remove the affected titanium angle(s), accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
This paragraph restates the requirements of paragraph (k) of AD 2014-20-04, with updated service information and revised compliance language. For airplanes on which new titanium angles were installed as specified in paragraph (i)(2) or (j) of this AD: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after the installation, accomplish a detailed inspection for cracking of the replaced titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
This paragraph restates the requirements of paragraph (l) of AD 2014-20-04, with updated service information. If, during any inspection as required by paragraph (k) of this AD, there is any crack finding: Before further flight, remove the affected titanium angles, accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
This paragraph restates the requirements of paragraph (m) of AD 2014-20-04, with updated contact information. If, during any rototest as required by paragraph (i), (j), or (l) of this AD, any crack is found: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
This paragraph restates the requirements of paragraph (n) of AD 2014-20-04, with no changes. Repair or replacement of parts as specified in this AD does not terminate the repetitive inspections required by this AD.
For airplanes previously modified (replacement of affected titanium angles) using the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259: At the earlier of the times specified in paragraphs (o)(1) and (o)(2) of this AD, do a detailed inspection of the rivet installation in the belly fairing shear walls and the titanium angles for part number EN6081D4 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. A review of the airplane maintenance records is acceptable to comply with the requirements of this paragraph for that airplane, provided it can be determined that no titanium angles have been installed on that airplane in accordance with the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259, or if only rivets having part number EN6081D5 have been used to install the titanium angles on that airplane in accordance with the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
(1) Within 2,000 flight cycles or 4,000 flight hours, whichever occurs first after the effective date of this AD.
(2) Before exceeding 5,000 flight cycles or 10,000 flight hours, whichever occurs first after accomplishment of the last inspection specified in paragraph (h) of this AD.
If any part number EN6081D4 series rivet is found during any inspection required by paragraph (o) of this AD, before further flight, do the actions specified in paragraphs (p)(1) and (p)(2) of this AD.
(1) Remove the part number EN6081D4 series rivets and do a rotating probe test of the open holes for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. If any crack is found during any inspection required by this paragraph, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature.
(2) Replace part number EN6081D4 series rivets with part number EN6081D5 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA—Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018.
Where the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specify to install titanium angle part numbers D5337060121200 and D5337060121400, this AD allows the installation of titanium angle part numbers D5337060121295 and D5337060121495, respectively.
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.
