[Federal Register Volume 72, Number 205 (Wednesday, October 24, 2007)]
[Rules and Regulations]
[Pages 60236-60238]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-20815]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28853; Directorate Identifier 2006-NM-218-AD; 
Amendment 39-15241; AD 2007-22-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 28, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 28, 
2007.
    The Director of the Federal Register approved the incorporation by 
reference of Airbus A300-600 Airworthiness Limitations Items Document 
AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, as of October 31, 
2007 (72 FR 54536, September 26, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue, SE., Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 3, 2007 (72 
FR 43199). A correction of that NPRM was published in the Federal 
Register on August 15, 2007 (72 FR 45866). That NPRM proposed 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 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. You may obtain further 
information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Clarification of Compliance Times

    We added ``total'' to the flight hour compliance times in 
paragraphs (f)(1)(i)(A), (f)(2)(i)(A), and (f)(3)(i)(A) of the AD. The 
flight cycle compliance times already specify total flight cycles.

Change of Service Bulletin Appendix Reference

    We changed ``including'' to ``excluding'' when referring to 
Appendix 01 of Airbus Service Bulletin A300-53-6154, dated June 20, 
2006, in paragraph (h) and in the subparagraphs of paragraph (f) of the 
AD. Appendix 01 is a reporting form, and this AD does not require 
reporting.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 7 products of U.S. registry. 
We also estimate that it will take about 79 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 
this AD to the 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.

[[Page 60237]]

Regulatory Findings

    We 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 this AD:
    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.

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 the NPRM, 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.

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 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 adding the following new AD:

2007-22-05 Airbus: Amendment 39-15241. Docket No. FAA-2007-28853; 
Directorate Identifier 2006-NM-218-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
28, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300-600 series airplanes, 
manufacturing serial numbers (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) of this AD: 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, excluding 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 total 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, excluding 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) of this AD: 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, excluding 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 total 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, excluding 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) of this AD: 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, excluding 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 total 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, excluding 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 (XRAY) 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 571022-02-2 of Airbus A300-600 
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.


[[Page 60238]]



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, 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: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 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 requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2006-0257, dated 
August 24, 2006; Airbus Service Bulletin A300-53-6154, excluding 
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.

Material Incorporated by Reference

    (i) You must use the service information specified in Table 1 of 
this AD 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 Service Bulletin A300-53-6154, 
excluding Appendix 01, dated June 20, 2006, 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 A300-600 Airworthiness 
Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated 
April 2006, on October 31, 2007 (72 FR 54536, September 26, 2007).
    (3) For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (4) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html.

              Table 1.--Material Incorporated by Reference
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     Service information         Revision level             Date
------------------------------------------------------------------------
Airbus Service Bulletin A300- Original............  June 20, 2006.
 53-6154, excluding Appendix
 01.
Airbus A300-600               Issue 11............  April 2006.
 Airworthiness Limitations
 Items Document AI/SE-M2/
 95A.0502/06.
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    Issued in Renton, Washington, on October 12, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E7-20815 Filed 10-23-07; 8:45 am]
BILLING CODE 4910-13-P