Source: https://www.federalregister.gov/documents/2013/08/13/2013-19528/airworthiness-directives-airbus-airplanes
Timestamp: 2017-08-20 09:04:54
Document Index: 134695587

Matched Legal Cases: ['art 1', 'art 1', 'art 1', 'art 1', 'art 4', 'art 1', 'art 4', 'art 1', 'art 4', '§\u200939', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 4', 'art 1', 'art 4', 'art 1', 'art 1', 'art 4']

78 FR 49213
49213-49217 (5 pages)
2013-19528
(h) Retained Grace Period for New or More Restrictive Actions
(i) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs With Revised Compliance Times
(j) Retained Special Compliance Times for Certain Tasks
(k) Retained Limitation: No Alternative Life Limits, Inspections, or Inspection Intervals After Accomplishment of the Actions Specified in Paragraph (g) of This AD
(l) Retained Limitation: No Alternative Life Limits, Inspections, or Inspection Intervals After Accomplishment of the Actions Specified in Paragraph (j) of This AD
(m) New Maintenance Program Revision
(n) New Limitation: No Alternative Actions or Intervals
https://www.federalregister.gov/d/2013-19528 https://www.federalregister.gov/d/2013-19528
We propose to supersede airworthiness directive (AD) 2011-14-06 that applies to all Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires revising the maintenance program. Since we issued that AD, we have determined that more restrictive limitations are necessary. This proposed AD would require revising the maintenance program to incorporate new limitations. We are proposing 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.
On June 24, 2011, we issued AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). That AD required actions intended to address an unsafe condition on the products listed above.
Since we issued AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), we have determined that more restrictive limitations are necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012-0008, dated January 16, 2012 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:
The airworthiness limitations for Airbus aeroplanes are currently published in Airworthiness Limitations Section (ALS) documents. The airworthiness limitations applicable to the Safe Life Airworthiness Limitation Items (SL ALI) are specified in Airbus A318/A319/A320/A321 ALS Part 1, which is approved by the European Aviation Safety Agency (EASA).
EASA AD 2006-0162 [which corresponds to FAA AD 2007-20-05, Amendment 39-15215 (72 FR 56262, October 3, 2007) which was superseded by FAA AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)] was issued to require the implementation of the instructions and airworthiness limitations as specified in Airbus A318/A319/A320/A321 ALS Part 1 original issue. Failure to comply with the instructions of ALS Part 1 could result in an unsafe condition.
This [EASA] AD retains the requirements of EASA AD 2006-0162, which is superseded, extends the applicability by adding the Models A318-121, A318-122, A320-215 and A320-216, and requires the implementation of the instructions and airworthiness limitations as specified in Airbus A318/A319/A320/A321 ALS part 1 revision 02, approved on 13 May 2011.
The unsafe condition is 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. The required actions also include revising the maintenance program to include Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. You may obtain further information by examining the MCAI in the AD docket.
Airbus has issued A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011; and A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
This product has been approved by the aviation authority of another country, and is approved for operation Start Printed Page 49214in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.
This proposed AD requires revisions to certain operator maintenance documents to include new actions. Compliance with these actions is required by section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, an operator might not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval of an alternative method of compliance (AMOC) in accordance with the provisions of paragraph (o) of this proposed AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure and the continued operational safety of the airplane.
Although the MCAI requires revising the maintenance program to include the incorporation of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011, this AD also requires revising the maintenance program to include the incorporation of Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. This difference has been coordinated with EASA.
Based on the service information, we estimate that this proposed AD would affect about 851 products of U.S. registry.
The actions that are required by AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $85 per product.
We estimate that it would take about 1 work-hour per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $72,335, or $85 per product.
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2011-14-06, Amendment 39-16741 (
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 Start Printed Page 49215ALS Part 1—Safe Life Airworthiness Limitation Items, 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, 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 (h) of this AD. Doing the actions required by paragraph (m) of this AD 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, 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, 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.
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 (j) of this AD. Doing the actions required by paragraph (m) 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 (j) 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 (j) of this AD: The initial compliance time for doing the tasks is specified in table 1 to paragraph (j) of this AD.
Table 1 to Paragraph (j) of This AD—Compliance Times for Tasks
Note 1 to table 1 to paragraph (j) 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 paragraph (g) of this AD have been accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as provided by paragraph (h) of this AD, and except as required by paragraph (m) 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 (i) of this AD have been accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as required by paragraph (m) of this AD.
Within 30 days after the effective date of this AD, revise the maintenance program to incorporate Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011; and Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. The initial compliance time for the accomplishing the actions is at the applicable time specified in Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011, and Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Start Printed Page 49217Maintenance, dated January 8, 2008; or within 4 months after the effective date of this AD; whichever occurs later.
After accomplishing the revision required by paragraph (m) of this AD, no alternative actions (e.g., inspections) or intervals, may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (o) of this AD.
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), are approved as AMOCs for the corresponding actions specified in this AD.
(1) Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency (EASA) Airworthiness Directive 2012-0008, dated January 16, 2012, and the service information specified in paragraphs (p)(1)(i) through (p)(1)(viii) of this AD, for related information.
(i) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(ii) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, dated February 28, 2006.
(iii) Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008.
(iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005.
(v) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006.
(vi) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006.
(vii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009.
(viii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 11, dated September 2010.
[FR Doc. 2013-19528 Filed 8-12-13; 8:45 am]