Source: https://www.federalregister.gov/documents/2012/05/31/2012-13191/airworthiness-directives-airbus-airplanes
Timestamp: 2018-04-25 19:03:33
Document Index: 530587882

Matched Legal Cases: ['art 5', '§\u200939', 'art 5', 'art 5', 'art 5', 'art 5']

77 FR 32060
32060-32064 (5 pages)
Docket No. FAA-2012-0493
Directorate Identifier 2011-NM-180-AD
2012-13191
FAA-2012-0493
Airbus Model A318-111 and -112 airplanes; and all Model A319, A320, and A321 series airplanes
Explanation of Changes Made to This NPRM
(g) Retained Revision of the Airworthiness Limitations Section (ALS) To Incorporate Fuel Maintenance and Inspection Tasks
(h) Retained Revision of the ALS To Incorporate CDCCLs
(i) Retained No Alternative Inspections, Inspection Intervals, or CDCCLs
(j) Revise Maintenance Program
(k) No Alternative Actions Intervals, and/or CDCCLs
https://www.federalregister.gov/d/2012-13191 https://www.federalregister.gov/d/2012-13191
We propose to supersede an existing airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; and all Model A319, A320, and A321 series airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. Since we issued that AD, Airbus has issued more restrictive maintenance requirements and/or airworthiness limitations. This proposed AD would revise the maintenance program to incorporate revised fuel maintenance and inspection tasks, and add airplanes to the applicability. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2012-0493; Directorate Identifier 2011-NM-180-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.
On November 16, 2009, we issued AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). That AD required actions intended to address an unsafe condition on the products listed above.
Since we issued AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009), Airbus has issued A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011-0155, dated August 25, 2011 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:
The airworthiness limitations are currently published in the Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS).
The Fuel Airworthiness Limitations (FAL) are specified in Airbus A318/A319/A320/A321 FAL Document reference 95A.1931/05, which is approved by the European Aviation Safety Agency (EASA) and referenced in the Airbus A318/A319/A320/A321 ALS Part 5.
The issue 4 of Airbus A318/A319/A320/A321 FAL Document introduces more restrictive maintenance requirements and/or airworthiness limitations. Failure to comply with these more restrictive maintenance requirements and airworthiness limitations contained in this document constitutes an unsafe condition.
This [EASA] AD retains the requirement of EASA AD 2006-0203, which is superseded, and requires the implementation of the new or more restrictive maintenance requirements and/or airworthiness limitations as specified in Airbus A318/A319/A320/A321 FAL Document issue 4.
We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. You may obtain further information by examining the MCAI in the AD docket.
Airbus has issued A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
We have changed Note 1 and Note 2 of the restated requirements of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009), to lettered paragraphs (i) and (j), respectively, in this NPRM. These changes do not add any additional burden upon the public than was required in the existing AD.
Based on the service information, we estimate that this proposed AD would affect about 745 products of U.S. registry.
The actions that are required by AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009), and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the currently required actions is $170 per product.
We estimate that it would take about 2 work-hours 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 $126,650, or $170 per product.
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009), and adding the following new AD:
Airbus: Docket No. FAA-2012-0493; Directorate Identifier 2011-NM-180-AD.
This AD supersedes AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009).
(1) This AD applies to 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; Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all serial numbers.
(2) This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections and/or Critical Design Configuration Control Limitations (CDCCLs). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) according to paragraph (l)(1) of this AD. The request should include a description of changes to the required actions that will ensure the continued operational safety of the airplane.
This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). For Model A318-111 and -112 airplanes, and Model A319, A320, and A321 airplanes: Within 3 months after August 28, 2007 (the effective date of AD 2007-15-06), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 ALS Part 5—Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005 (approved by the European Aviation Safety Agency (EASA) on March 14, 2006), Section 1, “Maintenance/Inspection Tasks;” or Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008 (approved by the EASA on December 19, 2008), Section 1, ”Maintenance/Inspection Tasks.” For all tasks identified in Section 1 of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008; the initial compliance times start from August 28, 2007, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1, ”Maintenance/Inspection Tasks,” of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008.
Airbus Operator Information Telex (OIT) SE 999.0076/06, dated June 20, 2006, provides guidance on identifying the applicable sections of the Airbus A318/A319/A320/A321 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 ”Maintenance/Inspection Tasks,” of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008.
This paragraph restates the requirements of paragraph (g) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). For Airbus Model A318-111 and -112 airplanes, and Model A319, A320, and A321 airplanes: Within 12 months after August 28, 2007 (the effective date of AD 2007-15-06), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005 (approved by the EASA on March 14, 2006), Section 2, “Critical Design Configuration Control Limitations;” or Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008 (approved by EASA on December 19, 2008), Section 2, ”Critical Design Configuration Control Limitations.”
(1) This paragraph restates the requirements of paragraph (h) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). Except as provided by paragraph (l) of this AD: After accomplishing the actions specified in paragraphs (g) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.
(2) Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraphs (g) and (h) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.
Within 6 months after the effective date of this AD: Revise the maintenance program to incorporate the new or revised tasks, life limits, and CDCCLs specified in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, except as required in paragraph (j)(4) of this AD. The initial compliance times and intervals are stated in these documents, except as required in paragraphs (j)(1) through (j)(4) of this AD, or within 6 months after the effective date of this AD, whichever occurs later. For certain tasks, the compliance times depend on the pre-modification and post-modification status of the airplane. Incorporating the requirements of this paragraph terminates the corresponding requirements of paragraphs (g) and (h) of this AD.
(1) For airplanes whose first flight occurred before August 28, 2007 (the effective date of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009)), the first accomplishment of tasks 281800-01-1, Functional Check of Tank Vapour Seal and Vent Drain System; and 281800-02-1, Detailed Inspection of Vapour Seal; must be performed no later than 11 months after the effective date of this AD.
(2) The first accomplishment of Tasks 470000-01-1, Operational Check of DFSOV, Dual Flapper Check Valves and NEA Line for Leaks; 470000-02-1, Operational Check of both Dual Flapper Check Valves for Leaks; 470000-03-1, Operational Check of Dual Flapper Check Valves for Reverse Flow and NEA Line for Leaks; 470000-04-1, Operational Check of Dual Flapper Check Valves for Reverse Flow; and 470000-05-1, Remove Air Separation Module (ASM) and Return to Vendor for Workshop Check; must be calculated, in accordance with paragraphs (j)(2)(i) or (j)(2)(ii) of this AD.
(i) From the airplane first flight for airplanes on which Airbus modification 38062 or 38195 has been embodied in production, or
(ii) From the in-service installation of the fuel tank inerting system specified in Airbus Service Bulletin A320-47-1001, Airbus Service Bulletin A320-47-1002, Airbus Service Bulletin A320-47-1003, Airbus Service Bulletin A320-47-1004, Airbus Service Bulletin A320-47-1006, or Airbus Service Bulletin A320-47-1007.
(3) Although Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, does not refer to Airbus Service Bulletin A320-47-1006 and Airbus Service Bulletin A320-47-1007, the tasks apply as follows:
(i) Tasks 470000-01-1, Operational Check of DFSOV, Dual Flapper Check Valves and NEA Line for Leaks; and 470000-02-1, Operational Check of both Dual Flapper Check Valves for leaks; apply to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(ii) Task 470000-03-1, Operational Check of Dual Flapper Check Valves for Reverse Flow and NEA Line for Leaks; applies to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1006, and that have not accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(iii) Task 470000-04-1, Operational Check of Dual Flapper Check Valves for Reverse Flow; applies to airplanes in post-modification 38195 configuration and that have not accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(iv) Task 470000-05-1, Remove ASM and return to Vendor for workshop check; applies to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1007, and are in pre-modification 151529 configuration.
(4) Replace each ASM identified in table 1 of this AD in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). The compliance time for the replacement is before the accumulation of 27,000 flight hours (component time)—i.e., the life limitation.
Note 2 to paragraph (g)(4) of this AD:
Airbus A318/A319/A320/A321 Maintenance Manual Task 47-10-43-920-001-A, Air Separation Module Replacement, is an additional source of guidance for accomplishment of the removal and replacement of the ASM.
Table 1—ASM Replacement
ASM Part No.
Affected airplane configuration
2060017-101 Post-modification 38062, or
Post-Airbus Service Bulletin A320-47-1002, or
Post-Airbus Service Bulletin A320-47-1004, or
Post-Airbus Service Bulletin A320-47-1007
2060017-102 Post-modification 152033, or
Post-Airbus Service Bulletin A320-47-1011
After accomplishing the revisions required by paragraph (j) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used other than those specified in Airbus A318/A319/A320/A321 ALS Part 5—Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, unless the actions, intervals, and/or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (l)(1) of this AD.
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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, Washington 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.
(1) Refer to MCAI EASA Airworthiness Directive 2011-0155, dated August 25, 2011, and the following service information, for related information.
(i) Airbus A318/A319/A320/A321 ALS Part 5—Fuel Airworthiness Limitations, dated February 28, 2006.
(ii) Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005.
(iii) A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008.
(iv) Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010.
[FR Doc. 2012-13191 Filed 5-30-12; 8:45 am]