Airworthiness Directive · Amendment 39-18031 · Periodic inspections
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2015-05-02. Comply with the one in force.
This AD applies to all Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) AD 2011-14-06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-14-06 required revising the maintenance program. This new AD requires revising the maintenance program to incorporate new, more restrictive limitations. This AD was prompted by the determination that more restrictive limitations are necessary. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes: Within 3 months after November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72 FR 56262, October 3, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Sub-part 1-2, “Life Limits,” and Sub-part 1-3, “Demonstrated Fatigue Lives,” of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006. Accomplish the actions in Sub-part 1-2, “Life Limits,” and Sub-part 1-3, “Demonstrated Fatigue Lives,” of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, at the times specified in Sub-part 1-2, “Life Limits,” and Sub-part 1-3, “Demonstrated Fatigue Lives,” of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, dated February 28, 2006, except as provided by paragraph (i) of this AD. Accomplishing the actions required by paragraph (j) of this AD terminates the requirements of this paragraph.
This paragraph restates certain provisions of paragraph (h) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; except Model A319 airplanes on which Airbus Modifications 28238, 28162, and 28342 have been incorporated in production: Within 14 days after November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72 FR 56262, October 3, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005 (approved by the European Aviation Safety Agency (EASA) on February 7, 2006); Issue 08, dated March 2006 (approved by the EASA on January 4, 2007); or Issue 09, dated November 2006 (approved by the EASA on May 21, 2007). Accomplish the actions in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006; at the times specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006; as applicable; except as provided by paragraph (i) of this AD. Accomplishing the actions required by paragraph (j) or (n) of this AD, as applicable, terminates the requirements of this paragraph.
This paragraph restates certain provisions of paragraph (i) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes: For any new or more restrictive life-limit introduced with Sub-part 1-2, “Life Limits,” and Sub-part 1-3, “Demonstrated Fatigue Lives,” of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, replace the part at the time specified in Sub-part 1-2, “Life Limits,” and Sub-part 1-3, “Demonstrated Fatigue Lives,” of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, or within 6 months after November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72 FR 56262, October 3, 2007)), whichever is later. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph.
This paragraph restates the requirements of paragraph (j) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with revised compliance times. Within 9 months after August 22, 2011 (the effective date of AD 2011-14-06): Revise the maintenance program by incorporating all maintenance requirements and associated airworthiness limitations specified in the Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. Comply with all applicable maintenance requirements and associated airworthiness limitations included in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010; except as provided by paragraph (k) of this AD. Accomplishing the actions required by this paragraph terminates the requirements of paragraph (h) of this AD. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph.
This paragraph restates the requirements of paragraph (k) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with changes to table 1 to paragraph (k) of this AD. For new and more restrictive tasks introduced with Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010; as specified in table 1 to paragraph (k) of this AD: The initial compliance time for doing the tasks is specified in table 1 to paragraph (k) of this AD. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph.
| Task | Applicability (as specified in the applicability column of the task) | Compliance time, whichever occurs later | |
| 545102-01-6 | Group 19-1A CFM, Group 19-1B CFM, and Model A320-200 airplanes with CFM Industrial (CFM)/International Aero Engine (IAE) engines | The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010 | Within 2,000 flight cycles or 5,500 flight hours, after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)), whichever occurs first. |
| 545102-01-7 | Model A320-100 series airplanes | The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010 | Within 2,000 flight cycles or 2,000 flight hours, after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)), whichever occurs first. |
| 572050-01-1 or alternative task 572050-02-1 | Group 19-1A and Group 19-1B airplanes | At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006 | Within 6 months after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)). |
| 572050-01-4 or alternative task 572050-02-4 | Model A320-200 series airplanes | At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006 | Within 6 months after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)). |
| 572050-01-5 or alternative task 572050-02-5 | Group 21-1A airplanes | At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006 | Within 6 months after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)). |
| 572050-01-7 or alternative task 572050-02-7 | Model A320-100 series airplanes | At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006 | Within 6 months after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)). |
| 534132-01-1 | Model A320 PRE 30748 airplanes | The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010 | Within 100 days after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. |
| 531118-01-1 | Model A318 (except (A318-121 and -122), Group 19-1A, Group 19-1B, and Model A320 and A321 series airplanes | The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010 | Within 100 days after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. |
| 531118-01-1 | Model A318-121 and -122 airplanes | The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010 | Within 100 days after August 22, 2011 (the effective date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)). |
Note 1 to table 1 to paragraph (k) of this AD: ALI Task 572050 refers to the outer wing dry bay and is comprised of extracts from three ALI Tasks 572004, 572020, and 572053. The threshold of ALI Task 572050 for the whole dry bay area is that of the lowest threshold of the source ALI tasks, i.e., that of ALI Task 572053.
This paragraph restates the requirements of paragraph (l) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After the actions specified in paragraphs (g) and (h) of this AD have been accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as provided by paragraphs (i) and (m) of this AD, and except as required by paragraphs (j) and (n) of this AD.
This paragraph restates the requirements of paragraph (m) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After the actions specified in paragraph (j) of this AD have been accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as required by paragraph (n) of this AD.
Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD. The initial compliance time for accomplishing the actions is at the applicable time specified in the ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD; or within 4 months after the effective date of this AD; whichever occurs later. Accomplishing these actions terminates the requirements of paragraphs (g), (h), (i), (j), and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013.
(3) Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008.
After accomplishing the revision required by paragraph (n) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (p)(1) of this AD.
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.
Aircraft
