[Federal Register Volume 73, Number 41 (Friday, February 29, 2008)]
[Proposed Rules]
[Pages 11067-11069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-3823]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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:

    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.

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 March 31, 2008.

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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

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 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, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

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-2008-0222; 
Directorate Identifier 2007-NM-300-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.

[[Page 11068]]

    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 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 2007-0150, dated May 22, 2007 [corrected May 
23, 2007] (referred to after this as ``the MCAI''), 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 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.

    The initial compliance times range from 10,800 flight hours or 
23,300 flight cycles, whichever occurs first, to 30,200 flight hours or 
33,500 flight cycles, whichever occurs first, after doing the repair, 
depending on the airplane configuration and inspection area. The 
repetitive intervals range from 500 flight cycles or 1,100 flight 
cycles, whichever occurs first, to 45,500 flight cycles or 61,500 
flight hours, whichever occurs first, depending on the airplane 
configuration and inspection area. You may obtain further information 
by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0381, dated January 15, 
2007; A300-53-0383, dated January 11, 2007; and A300-57-6102, dated 
January 12, 2007. 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 United 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 107 products of U.S. registry. We also estimate that 
it would take about 22 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 $188,320, or $1,760 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;
    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 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-2008-0222; Directorate Identifier 2007-NM-
300-AD.

Comments Due Date

    (a) We must receive comments by March 31, 2008.

Affected ADs

    (b) None.

[[Page 11069]]

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 models, 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, 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 models, 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), (f)(1)(iv), and (f)(1)(v) 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 cracks length and position), center wing box lower 
panel, and reinforced parts (internal angle, lower external splice 
and external fitting).

                   Table 1.--Airbus Service Bulletins
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           Service Bulletin                           Date
------------------------------------------------------------------------
A300-53-0381.........................  January 15, 2007.
A300-53-0383.........................  January 11, 2007.
A300-57-6102.........................  January 12, 2007.
------------------------------------------------------------------------

    (i) Where the tables in 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 1.E. Compliance of the service bulletins 
listed in Table 1 of this AD specifies measurements for LA and LB 
and the table does not list the unit of measurements, the unit of 
measurement is millimeters (mm).
    (iii) Where any table in 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 40mm, 
this AD requires that the corresponding action be done if LA >= to 
40mm.
    (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), (f)(1)(iii), and (f)(1)(v) 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.

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 times. We have clarified the 
compliance times in paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), 
(f)(1)(iv), and (f)(1)(v) 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: 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 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.

    Issued in Renton, Washington, on February 21, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-3823 Filed 2-28-08; 8:45 am]
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