Airworthiness Directives: Airbus Model A318-111 and -112 Series Airplanes, and Model A319, A320, and A321 Series Airplanes
Federal Register: November 27, 2009 (Volume 74, Number 227)
Rules and Regulations
Page 62219-62222
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr27no09-7
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2009-1073; Directorate Identifier 2009-NM-174-AD;
Amendment 39-16097; AD 2007-15-06 R1
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318-111 and -112 Series
Airplanes, and Model A319, A320, and A321 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
SUMMARY: The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A318-111 and -112 series airplanes, and all Model A319, A320, and A321 series airplanes. That AD currently requires revising the Airworthiness Limitations section of the
Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. 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.
DATES: This AD is effective December 14, 2009.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 14, 2009.
On August 28, 2007 (72 FR 40222, July 24, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
We must receive any comments on this AD by January 11, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http:// www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus,
Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e- mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com.
Examining the AD Docket
You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
Page 62220
International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On July 13, 2007, we issued AD 2007-15-06, Amendment 39-15135 (72
FR 40222, July 24, 2007). That AD applied to all Airbus Model A318-111 and -112 series airplanes, and all A319, A320, and A321 series airplanes. That AD required revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems.
Critical design configuration control limitations (CDCCLs) are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection.
Actions Since AD was Issued
Since we issued that AD, we have determined that it is necessary to clarify the AD's intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness.
Section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)) specifies the following:
No person may operate an aircraft for which a manufacturer's maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory * * * procedures * * * have been complied with.
Some operators have questioned whether existing components affected by the new CDCCLs must be reworked. We did not intend for the AD to retroactively require rework of components that had been maintained using acceptable methods before the effective date of the AD. Owners and operators of the affected airplanes therefore are not required to rework affected components identified as airworthy or installed on the affected airplanes before the required revisions of the ALS. But once the CDCCLs are incorporated into the ALS, future maintenance actions on components must be done in accordance with those CDCCLs.
Relevant Service Information
AD 2007-15-06 cites Airbus A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; and Airbus A318/A319/A320/A321 ALS Part 5--Fuel Airworthiness
Limitations, dated February 28, 2006. Since we issued that AD, Airbus has revised the referenced service information and issued Airbus A318/
A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05,
Issue 2, dated July 8, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This AD
The affected product(s) have been approved by the aviation authority of another country, and are approved for operation in the
United States. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.
This new AD retains the requirements of the existing AD, and adds a new note to clarify the intended effect of the AD on spare and on-airplane fuel tank system components.
Costs of Compliance
Based on the service information, we estimate that this AD would affect about 720 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of the AD on U.S. operators to be $115,200, or $160 per product.
FAA's Justification and Determination of the Effective Date
This revision merely clarifies the intended effect on spare and on- airplane fuel tank system components, and makes no substantive change to the AD's requirements. For this reason, it is found that notice and opportunity for prior public comment for this action are unnecessary, and good cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2009-1073; Directorate Identifier 2009-NM-174-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may amend this AD because of those comments.
We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.
Page 62221
See the ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment 0
Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing amendment 39-15135 (72 FR 40222, July 24, 2007) and adding the following new AD: 2007-15-06 R1 Airbus: Amendment 39-16097. Docket No. FAA-2009-1073;
Directorate Identifier 2009-NM-174-AD.
Effective Date
(a) This airworthiness directive (AD) is effective December 14, 2009.
Affected ADs
(b) This AD revises AD 2007-15-06, Amendment 39-15135.
Applicability
(c) This AD applies to all Airbus 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; certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents 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 and CDCCLs, the operator may not be able to accomplish inspections and CDCCLs 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 according to paragraph (i) of this AD. The request should include a description of changes to the required inspections and
CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the manufacturer. 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.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the actions have already been done.
Restatement of AD 2007-15-06, With Revised Service Information
Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel
Maintenance and Inspection Tasks
(f) 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 Document 95A.1931/05, the initial compliance times start from August 28, 2007, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1931/05.
Note 2: Airbus Operator Information Telex (OIT) SE 999.0076/06, dated June 20, 2006, identifies the applicable sections of the
Airbus A318/A319/A320/A321 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1931/ 05.
Revise ALS To Incorporate CDCCLs
(g) Within 12 months after August 28, 2007, 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.''
No Alternative Inspections, Inspection Intervals, or CDCCLs
(h) Except as provided by paragraph (i) of this AD: After accomplishing the actions specified in paragraphs (f) and (g) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.
New Information
Explanation of CDCCL Requirements
Note 3: 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 (f) and (g) 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.
Other FAA AD Provisions
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(j) EASA Airworthiness Directive 2006-0203, dated July 11, 2006, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Airbus A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005;
Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008; and Airbus A319/A319/A320/
A321 ALS Part 5--Fuel Airworthiness Limitations, dated February 28, 2006; as applicable; to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of Airbus A318/A319/A320/A321 Fuel
Page 62222
Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the incorporation by reference of Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated
December 19, 2005; and Airbus A319/A319/A320/A321 ALS Part 5--Fuel
Airworthiness Limitations, dated February 28, 2006; on August 28, 2007 (72 FR 40222, July 24, 2007).
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.
(5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.
Issued in Renton, Washington, on November 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
FR Doc. E9-28159 Filed 11-25-09; 8:45 am
BILLING CODE 4910-13-P
