Document ID: FAA-2008-0222-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes
Posted Date: 2008-07-10T04:00Z

[Federal Register: July 10, 2008 (Volume 73, Number 133)]
[Rules and Regulations]               
[Page 39580-39583]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10jy08-7]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0222; Directorate Identifier 2007-NM-300-AD; 
Amendment 39-15604; AD 2008-14-09]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300 and 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

[[Page 39581]]

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:

    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins rendered 
mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published * * * in order to control or correct the 
development of cracks, which could affect the structural integrity 
of the aircraft.

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

DATES: This AD becomes effective August 14, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 14, 
2008.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; 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 February 29, 2008 
(73 FR 11067). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins [SBs] 
rendered mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published in order to render mandatory an inspection 
subsequent to accomplishment of repair SB A300-53-0282 or A300[-53]-
0291 or A300-57-6069 in the affected area. The SB A300-53-0381, 
A300-53-0383 and A300-57-6102 define the various configurations for 
the mandatory [repetitive] inspections to be conducted in order to 
control or correct the development of cracks [in the center wing box 
at FR47], which could affect the structural integrity of the 
aircraft.

    The inspections include x-ray, high frequency eddy current, visual, 
and ultrasonic inspections. Corrective actions include contacting 
Airbus if any cracking is found, repairing if any cracking is found, 
and doing other specified actions. The other specified actions include 
contacting Airbus for oversizing fastener holes, oversizing fastener 
holes, installing new fasteners, and installing new plugs. 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 considered the comment received.

Request To Revise Cost

    Air Transport Association (ATA), on behalf of its member, American 
Airlines, states that the cost estimate of $1,760 specified in the NPRM 
is far too low. ATA states that Airbus Service Bulletin A300-57-6102, 
dated January 12, 2007 (which is referred to as an appropriate source 
of service information for doing certain actions specified in the 
NPRM), specifies that an accomplishment kit costs $1,650 for one wing 
and that the labor requirement for inspecting one wing is 19 hours. ATA 
notes that costs will double for airplanes on which Airbus A300-57-6102 
is accomplished on both wings.
    We agree that the cost estimate is too low. We have revised the 
labor hours in the Costs of Compliance section of this AD to reflect 
the 38 hours necessary to inspect both wings.
    However, we do not agree to add the cost of the kits necessary to 
do applicable corrective actions. The information in the Costs of 
Compliance section is limited to the cost of actions actually required 
by the AD. It does not consider the costs of ``on-condition'' actions 
(e.g., ``repair, as applicable'') because, regardless of AD direction, 
those actions would be required to correct an unsafe condition 
identified in an airplane and ensure operation of that airplane in an 
airworthy condition, as required by the Federal Aviation Regulations.

New Service Information

    Airbus has issued Service Bulletins A300-53-0381, A300-53-0383, and 
A300-57-6102, all including Appendix 1, all Revision 01, all dated May 
27, 2008 (we referred to the original issues of the service bulletins 
as the appropriate source of service information for accomplishing the 
actions specified in the NPRM). Revision 01 of the service bulletins 
specify that no more action is needed on airplanes on which actions 
specified in the original issues have been done. Revision 01 of the 
service bulletins updates the Effectivity section and clarifies the 
unit of measurement for the values of certain tables in the Compliance 
section of the service bulletins.
    We have revised this final rule to refer to Revision 01 of the 
service bulletins. We have not restated paragraph (f)(1)(ii) of the 
NPRM in this AD because Revision 01 of the service bulletins addresses 
the unit of measurement for the specified tables. We have also added 
paragraph (f)(5) of this AD to give credit for actions done in 
accordance with the original issues of the service bulletins.

Revision to Airplane Model Reference

    For clarity, we have revised the airplane model references in 
paragraphs (c)(1), (c)(2), (c)(3) of this AD by adding the word 
``airplanes'' to the model designations as published in the most recent 
type certificate data sheet for the affected models.

Conclusion

    We reviewed the available data, including the comment received, 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.

[[Page 39582]]

Costs of Compliance

    We estimate that this AD will affect 107 products of U.S. registry. 
We also estimate that it will take about 38 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 $325,280, or $3,040 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 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://
www.regulations.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:

2008-14-09 Airbus: Amendment 39-15604. Docket No. FAA-2008-0222; 
Directorate Identifier 2007-NM-300-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
14, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 and A300-600 series 
airplanes, certificated in any category, as listed in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD.
    (1) Airbus Model A300 B2-1C, B2-203 and B2K-3C airplanes, all 
serial numbers that have been repaired in accordance with Airbus 
Service Bulletin A300-53-0282.
    (2) Airbus Model A300 B4-103, B4-203, and B4-2C airplanes, all 
serial numbers that have been repaired in accordance with Airbus 
Service Bulletin A300-53-0291.
    (3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, C4-605R Variant F, and F4-605R airplanes, all serial 
numbers that have been repaired in accordance with Airbus Service 
Bulletin A300-57-6069.

Subject

    (d) Air Transport Association (ATA) of America Codes 53 and 57: 
Fuselage and Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins [SBs] 
rendered mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published in order to render mandatory an inspection 
subsequent to accomplishment of repair SB A300-53-0282 or A300[-53]-
0291 or A300-57-6069 in the affected area. The SB A300-53-0381, 
A300-53-0383 and A300-57-6102 define the various configurations for 
the mandatory [repetitive] inspections to be conducted in order to 
control or correct the development of cracks [in the center wing box 
at FR47], which could affect the structural integrity of the 
aircraft.
    The inspections include x-ray, high frequency eddy current, 
visual, and ultrasonic inspections. Corrective actions include 
contacting Airbus if any cracking is found, repairing if any 
cracking is found, and doing other specified actions. The other 
specified actions include contacting Airbus for oversizing fastener 
holes, oversizing fastener holes, installing new fasteners, and 
installing new plugs.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii), 
(f)(1)(iii), and (f)(1)(iv) of this AD, at the threshold defined in 
paragraph 1.E., ``Compliance,'' of the applicable service bulletin 
listed in Table 1 of this AD and according to the Accomplishment 
Instructions of the applicable service bulletin, perform all 
applicable inspections and, before further flight, perform all 
applicable other specified actions, of FR47 forward fitting vertical 
splice (including crack stop hole), crack stop hole (depending on 
crack's length and position), center wing box lower panel, and 
reinforced parts (internal angle, lower external splice and external 
fitting).

                   Table 1.--Airbus Service Bulletins
------------------------------------------------------------------------
          Service Bulletin            Revision            Date
------------------------------------------------------------------------
A300-53-0381.......................         01  May 27, 2008.
A300-53-0383.......................         01  May 27, 2008.
A300-57-6102.......................         01  May 27, 2008.
------------------------------------------------------------------------

    (i) Where the tables in paragraph 1.E., ``Compliance,'' of the 
service bulletins listed in Table 1 of this AD contain compliance 
times in both flight cycles and flight hours, this AD requires that 
the corresponding actions be done at the earlier of the flight cycle 
and flight hour compliance times.
    (ii) Where any table in paragraph 1.E., ``Compliance,'' of the 
service bulletins listed in Table 1 of this AD specifies exact 
measurements in the rows of the table for LA, use the ranges 
specified in Table 2 of this AD.

                         Table 2.--Ranges for LA
------------------------------------------------------------------------
    Where row of the table specifies--                  Use--
------------------------------------------------------------------------
LA = 0....................................  LA = 0.
LA = 10...................................  0 < LA <= 10 mm.

[[Page 39583]]

LA = 15...................................  10 mm < LA <= 15 mm.
LA = 20...................................  15 mm < LA <= 20 mm.
------------------------------------------------------------------------

    (iii) Where in paragraph 1.E., ``Compliance,'' of the service 
bulletins listed in Table 1 of this AD the service bulletins specify 
a compliance time after receipt of the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD.
    (iv) Where any table in paragraph 1.E., ``Compliance,'' of the 
service bulletins listed in Table 1 of this AD specifies 
measurements of LA > 40 mm, this AD requires that the corresponding 
action be done if LA >= 40 mm.
    (2) If any crack is detected during any inspection required by 
paragraph (f)(1) of this AD, before further flight, contact Airbus 
and repair.
    (3) Repeat the actions specified in paragraph (f)(1) of this AD 
at the intervals defined in paragraph 1.E., ``Compliance,'' of the 
applicable service bulletin listed in Table 1 of this AD and 
according to the Accomplishment Instructions of the applicable 
service bulletin, except as provided by paragraphs (f)(1)(i), 
(f)(1)(ii), and (f)(1)(iv) of this AD.
    (4) Within 30 days after doing the inspection required by 
paragraph (f)(1) of this AD or within 30 days after the effective 
date of this AD, whichever occurs later, report the first inspection 
results, whatever they may be, to Airbus as specified in the 
applicable service bulletin listed in Table 1 of this AD.
    (5) Actions accomplished before the effective date of this AD 
according to the applicable service bulletin specified in Table 3 of 
this AD are considered acceptable for compliance with the 
corresponding action specified in this AD.

                   Table 3.--Credit Service Bulletins
------------------------------------------------------------------------
         Airbus Service Bulletin                       Date
------------------------------------------------------------------------
A300-53-0381............................  Jan. 15, 2007.
A300-53-0383............................  Jan. 11, 2007.
A300-57-6102............................  Jan. 12, 2007.
------------------------------------------------------------------------

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: The MCAI and service bulletin did not provide adequate 
descriptions for certain compliance requirements. We have clarified 
the compliance requirements in paragraphs (f)(1)(i), (f)(1)(ii), 
(f)(1)(iii), and (f)(1)(iv) of this AD.

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: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; 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 European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0150, dated May 22, 2007 [corrected May 
23, 2007], and the Airbus service bulletins listed in Table 1 of 
this AD, for related information.

Material Incorporated by Reference

    (i) You must use the applicable service information specified in 
Table 4 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 this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) 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 4.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Airbus Service Bulletin                Revision                            Date
----------------------------------------------------------------------------------------------------------------
A300-53-0381, including Appendix 1...........              01  May 27, 2008.
A300-53-0383, including Appendix 1...........              01  May 27, 2008.
A300-57-6102, including Appendix 1...........              01  May 27, 2008.
----------------------------------------------------------------------------------------------------------------

    Issued in Renton, Washington, on June 26, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-15265 Filed 7-9-08; 8:45 am]

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