[Federal Register Volume 72, Number 149 (Friday, August 3, 2007)]
[Proposed Rules]
[Pages 43199-43202]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 07-3774]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28853; Directorate Identifier 2006-NM-218-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    At some locations, the new calculated fatigue life [for the wing 
to center box assembly] falls below the aircraft Design Service 
Goal.
    The aim of this Airworthiness Directive (AD) is * * * to ensure 
detection of cracks on the panels and stiffeners at rib No. 1. This 
situation, if left uncorrected, could affect the structural 
integrity of the area.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by September 4, 
2007.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

[[Page 43200]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Operations 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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This proposed AD references the MCAI and related service 
information that we considered in forming the engineering basis to 
correct the unsafe condition. The proposed AD contains text copied from 
the MCAI and for this reason might not follow our plain language 
principles.

Comments Invited

    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-2007-
28853; Directorate Identifier 2006-NM-218-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.
    We will post all comments we receive, without change, to http://dms.dot.gov. including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2006-0257, dated August 24, 2006 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During installation of the wing to the centre box junction on 
the Final Assembly Line, some ``taperlocks'' fasteners were found 
non compliant with the specification.
    Fatigue tests on samples and calculation performed on non-
conform fasteners demonstrated that this defect could lead to 
decrease the fatigue lift of the wing to centre wing box assembly.
    At some locations, the new calculated fatigue life falls below 
the aircraft Design Service Goal.
    The aim of this Airworthiness Directive (AD) is to mandate 
repetitive inspections to ensure detection of cracks on the panels 
and stiffeners at rib No. 1. This situation, if left uncorrected, 
could affect the structural integrity of the area.

The corrective action includes contacting Airbus for repair 
instructions in the event of crack finding. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A300-53-6154, including Appendix 
01, dated June 20, 2006, and A300-600 Airworthiness Limitations Items 
Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. 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 Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the Unitejd 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.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 7 products of U.S. registry. We also estimate that 
it would take about 79 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $44,240, or $6,320 per product.

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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 43201]]

    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 the4 estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2007-28853; Directorate Identifier 2006-NM-
218-AD.

Comments Due Date

    (a) We must receive comments by September 4, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300-600 series airplanes, 
manufacturing serial number (MSN) 0815 up to MSN 0821 inclusive, 
certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During installation of the wing to the centre box junction on 
the Final Assembly Line, some ``taperlocks'' fasteners were found 
non compliant with the specification.
    Fatigue tests on samples and calculation performed on non-
conform fasteners demonstrated that this defect could lead to 
decrease the fatigue life of the wing to centre wing box assembly.
    At some locations, the new calculated fatigue life falls below 
the aircraft Design Service Goal.
    The aim of this Airworthiness Directive (AD) is to mandate 
repetitive inspections to ensure detection of cracks on the panels 
and stiffeners at rib No. 1 This situation, if left uncorrected, 
could affect the structural integrity of the area.
    The corrective action includes contacting Airbus for repair 
instructions in the event of crack finding.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Action No. 1, for the center wing box:
    (i) At the later of the times in paragraphs (f)(1)(i)(A) and 
(f)(1)(i)(B): Do an external ultrasonic inspection for cracking of 
the taperlocks fasteners of the center wing box, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6154, including appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 19,800 total flight cycles or 
41,200 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
3,300 flight cycles or 6,900 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(1)(ii) 
of this AD is valid until the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571006-02-1 is reached. 
After reaching this threshold, the ultrasonic inspection is to be 
done according to Task 571006-02-1, ``Special detailed inspection 
(Ultrasonic) of wing junction at rib 1 horizontal flange of lower T 
section, between FR40 and FR47 inboard side, LH/RH,'' of Airbus 
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006.
    (2) Action No. 2, for the outer wing box:
    (i) At the later of the times in paragraphs (f)(2)(i)(A) and 
(f)(2)(i)(B): Do an external ultrasonic inspection for cracking of 
the taperlocks fasteners of the outer wing box, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6154, including Appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 15,200 total flight cycles or 
31,700 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
3,700 flight cycles or 7,700 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(2)(ii) 
of this AD is valid until reaching the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571022-01-2, ``Special 
detailed inspection (Ultrasonic) of wing-fuselage lower skin splice 
at rib 1 (wing side).'' After reaching this threshold, the 
ultrasonic inspection is to be done according to Task 571022-01-2 of 
Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/
95A.0502/06, Issue 11, dated April 2006.
    (3) Action No. 3, for the outer wing box:
    (i) At the later of the times in paragraphs (f)(3)(i)(A) and 
(f)(3)(i)(B): Do an internal x-ray inspection for cracking of the 
taperlocks fasteners of the outer wing box, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, 
including Appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 20,900 total flight cycles or 
43,400 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
1,800 flight cycles or 3,700 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(3)(ii) 
of this AD is valid until reaching the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571022-02-2, ``Special 
detailed inspection (x-ray) of wing-fuselage lower skin splice at 
rib 1 (wing side).'' After reaching this threshold, the x-ray 
inspection is to be done according to Task 5710022-02-2 of Airbus 
A300-60 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to 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. Send information to ATTN: Tom Stafford, Aerospace Engineer, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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, the 
Office of Management and Budget (OMB) has approved the information 
collection

[[Page 43202]]

requirements and has assigned OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAIEASA Airworthiness Directive 2006-0257, dated 
August 24, 2006; Airbus Service Bulletin A300-53-6154, including 
Appendix 01, dated June 20, 2006; and Airbus A300-600 Airworthiness 
Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated 
April 2006; for related information.

    Issued in Renton, Washington, on July 25, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 07-3774 Filed 8-2-07; 8:45 am]
BILLING CODE 4910-13-M