Airworthiness Directive · Amendment 39-17972 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A320-111, -211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers.
We are superseding Airworthiness Directive (AD) 2004-03-19, which applies to certain Airbus Model A320-111, -211 and -231 series airplanes. AD 2004-03-19 required repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. AD 2004-03-19 also provided for an optional terminating modification for the repetitive inspection requirements. This new AD requires accomplishing the modification by installing washers between the transition pick-up angle and the pin nuts, and doing related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability of AD 2004-03-19. This AD was prompted by a determination that the optional terminating modification must be required in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
This paragraph restates the requirements of paragraph (b) of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For Model A320-111, -211, and -231 airplanes on which the modification specified in AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), has not been done: Do the applicable inspections specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections required by AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have been done: Within 12,000 flight cycles after accomplishment of the last inspection required by AD 98-12-18, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking.
(2) For airplanes on which the inspections required by AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have not been done: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or 24,600 total flight hours, whichever is first.
(ii) Before the accumulation of 16,000 total flight cycles, or within 3,500 flight cycles after March 15, 2004 (the effective date of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), whichever is first.
This paragraph restates the requirements of paragraph (c) of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For Model A320-111, -211, and -231 airplanes: Repeat the detailed and rotating probe inspections specified in paragraphs (g)(1) and (g)(2) of this AD at intervals not to exceed 10,400 flight cycles or 24,600 flight hours, whichever is first, until the modification specified in paragraph (m) of this AD has been done.
This paragraph restates the requirements of paragraph (d) of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), with specific delegation approval language. For Model A320-111, -211, and -231 airplanes: If any cracking is found during any inspection required by paragraph (g) or (h) of this AD, prior to further flight, either repair the cracking per the Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002; or do the modification specified in paragraph (m) of this AD. Where Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002, specifies to contact the manufacturer for repair instructions, prior to further flight, repair the cracking in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); or the Direction Générale de l'Aviation Civile (or its delegated agent). If the cracking is repaired, repeat the inspections as required by paragraph (h) of this AD.
For Model A320-212 airplanes on which the modification specified in Airbus Service Bulletin A320-53-1027 has not been done as of the effective date of this AD: Do the applicable inspections specified in paragraph (j)(1) or (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections specified in Airbus Service Bulletin A320-53-1028 have been done as of the effective date of this AD: At the later of the times specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking.
(i) Within 10,400 flight cycles or 24,600 flight hours, whichever occurs first after accomplishing the most recent inspection specified in Airbus Service Bulletin A320-53-1028.
(ii) Within 90 days after the effective date of this AD.
(2) For airplanes on which the inspections specified in Airbus Service Bulletin A320-53-1028 have not been done as of the effective date of this AD: At the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or 24,600 total flight hours, whichever occurs first.
(ii) Within 90 days after the effective date of this AD.
For Model A320-212 airplanes: Repeat the detailed and rotating probe inspections specified in paragraphs (j)(1) and (j)(2) of this AD at intervals not to exceed 10,400 flight cycles or 24,600 flight hours, whichever occurs first, until the modification specified in paragraph (m) of this AD has been done.
For Model A320-212 airplanes: If any cracking is found during any inspection required by paragraph (j) or (k) of this AD, before further flight, do the actions specified in either paragraph (l)(1) or (l)(2) of this AD.
(1) Repair the crack in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002, except where Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002, specifies to contact the manufacturer, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). After the cracking is repaired, repeat the inspections required by paragraph (k) of this AD.
(2) Do the modification specified in paragraph (m) of this AD.
For all airplanes: Before the accumulation of 40,000 flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, but not exceeding 48,000 flight cycles since first flight, modify by doing rotating probe inspections for cracking of certain fastener holes, replacing transition angles if any cracking is found in the transition angles, repairing if any pick-up angles cracking is found, and installing washers between the transition pick-up angle and the pin nuts; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1027, Revision 03, dated February 12, 2002, except where Airbus Service Bulletin A320-53-1027, Revision 03, dated February 12, 2001, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Accomplishment of this modification terminates the repetitive inspections required by paragraphs (h) and (k) of this AD.
For airplanes on which Airbus Modification 21202 has been embodied in production: No actions are required by this AD.
