Airworthiness Directive · Amendment 39-18081 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2025-10-07. Comply with the one in force.
This AD applies to the Airbus airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers (MSNs).
(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, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) 2009-20-05 for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2009-20-05 required one-time inspections for cracking, damage, correct installation, and correct adjustment of the main landing gear (MLG) door hinge and actuator fittings on the keel beam, and corrective actions if necessary. This new AD expands the applicability, reduces the compliance time, and requires repetitive inspections instead of the one-time inspection. This AD also requires revising the maintenance or inspection program. This AD was prompted by reports of cracks on fittings that had successfully passed certain required inspections. We are issuing this AD to detect and correct cracking on the MLG door hinge fitting and actuator fitting on the keel beam, which could lead to in-flight detachment of an MLG door, possibly resulting in injury to persons on the ground and/or damage to the airplane.
This paragraph restates the requirements of paragraphs (f)(1) and (f)(2) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009), with specific delegation approval language. For airplanes having serial numbers up to MSN 2850 inclusive, except MSNs 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD.
(1) At the latest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Perform detailed visual, high frequency eddy current (HFEC), and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the left-hand (LH) and right-hand (RH) MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, including Appendix 01, dated April 5, 2007; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(i) Within 6,000 flight cycles since first flight.
(ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)).
(iii) Within 6,000 flight cycles from the latest MLG door actuator fitting replacement.
(2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Perform detailed visual and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, including Appendix 01, dated November 29, 2006; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(i) Within 4,500 flight cycles since first flight.
(ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)).
This paragraph restates the exception specified in paragraph (f)(4) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009). Where the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, including Appendix 01, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, including Appendix 01, dated November 29, 2006; as applicable; specify to submit a report where no damage or crack is found during the inspection required by paragraph (g)(1) or (g)(2) of this AD: Send the report to Airbus using the applicable reporting sheet in Appendix 01 of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, dated November 29, 2006. Send the report at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after the inspection.
(2) If the inspection was done before November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after November 3, 2009.
(1) At the latest of the times specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD: Perform detailed, HFEC, and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Repeat the inspections thereafter at intervals not to exceed 2,250 flight cycles.
(i) Before the accumulation of 3,000 flight cycles since first flight.
(ii) Within 2,250 flight cycles after the most recent inspection done as described in Airbus Service Bulletin A320-53-1195, or Task 533154-02-1 of the Airbus A318/A319/A320/A321 Airworthiness Limitations Section Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), as applicable.
(iii) Within 1,500 flight cycles after the effective date of this AD.
(2) At the latest of the times specified in paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD: Perform detailed and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles.
(i) Before the accumulation of 3,000 flight cycles since first flight.
(ii) Within 3,000 flight cycles after the most recent inspection done as described in Airbus Service Bulletin A320-53-1196, or Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitation Items (DT ALI), as applicable.
(iii) Within 1,500 flight cycles after the effective date of this AD.
The accomplishment of a corrective action on an airplane, as required by paragraph (i) of this AD, does not constitute terminating action for the repetitive inspection requirements of this AD for that airplane.
After the effective date of this AD and before further flight after doing the inspection required by paragraph (i) of this AD: Revise the maintenance or inspection program, as applicable, to remove Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated September 2010. The actions required by this AD take precedence over Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitation Items (DT ALI), Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; and Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated September 2010.
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.
