
[Federal Register: March 19, 2008 (Volume 73, Number 54)]
[Rules and Regulations]               
[Page 14670-14673]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19mr08-6]                         

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28944; Directorate Identifier 2006-NM-239-AD; 
Amendment 39-15430; AD 2008-06-18]
RIN 2120-AA64

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

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

ACTION: Final rule.

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

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:

    [T]he detection of cracks on multiple aircraft in lower skin 
panel No. 2 forward of access panel 575FB/675FB held on the rear 
dummy spar, inboard of rib 9, fuselage side, aft of the rear spar.
    This area of structure has been subjected to several repairs and 
modifications in previous years.
    The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and 
A300-57-6029 at Revision 4 define the various configurations for the 
mandatory inspections to be conducted 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 April 23, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 23, 
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: 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 16, 2007 (72 
FR 45978). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    This Airworthiness Directive (AD) is published subsequent to the 
detection of cracks on multiple aircraft in lower skin panel No. 2 
forward of access panel 575FB/675FB held on the rear dummy spar, 
inboard of rib 9, fuselage side, aft of the rear spar.
    This area of structure has been subjected to several repairs and 
modifications in previous years.
    The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and 
A300-57-6029 at Revision 4 define the various configurations for the 
mandatory inspections to be conducted in order to control or correct 
the development of cracks which could affect the structural 
integrity of the aircraft.

    The MCAI requires various repetitive inspections (detailed visual, 
high frequency eddy current, X-ray) of the wing lower skin panel and 
associated internal support structure for cracking and, if necessary, 
corrective measures (modifying the lower panel inboard of rib 9 aft of 
the rear spar and repairing cracks). 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 comments received.

Request To Revise Applicability of NPRM

    FedEx requests that we revise the applicability of the NPRM to 
exclude

[[Page 14671]]

certain airplanes which have already been modified. FedEx states that 
airplanes having post-production modification 11178 (identified as 
Config. 14 in Airbus Service Bulletin A300-57-6029, Revision 06, dated 
March 23, 2007) installed should not be included in the service 
bulletin, as the Limit of Validity (LOV) for the airframe is close 
enough to the inspection thresholds for post-production modification 
11178 to consider the modification as sufficient without specific 
follow-up maintenance requirements. FedEx therefore requests that we 
consider revising the applicability of the NPRM to exclude airplanes 
that have production modification 11178 installed, and asserts that if 
the LOV is extended, an airworthiness limitations instruction (ALI) 
could be added for the post mod inspection requirements.
    We don't agree. These airplanes must be inspected before they reach 
their current LOV as it could not be demonstrated that extending the 
thresholds up to the revised LOV would provide an acceptable level of 
safety. Operators are provided some relief as the inspection is 
estimated to be 2 work-hours, which will not have significant impact on 
airplane maintenance. We have not changed the AD in this regard.

Request To Simplify Compliance Intervals

    FedEx states it has 69 A300-600 aircraft affected by the NPRM and, 
so far, has had no problems with the wing skin at the intersection of 
the rear spar to the dummy spar inboard of Rib 9. FedEx states it finds 
Airbus Service Bulletin A300-57-6029, Revision 06, to be overly 
complex, constituting an undue burden to implement into its records 
system. We infer that FedEx is requesting that we reduce or streamline 
the inspection thresholds and intervals in the NPRM.
    We do not agree with this request. The fatigue load spectrum 
differs from one airplane model to another. To reduce the number of 
inspection programs specified in the service bulletin, it would be 
necessary to require the more conservative compliance times which would 
place an excessive burden on some operators. However, operators are 
always permitted to accomplish the requirements of an AD before the 
required compliance time. Therefore, an operator with several Model 
A300-600 airplanes may choose to streamline the process by inspecting 
all those models using the most stringent compliance time specified in 
the AD. If an operator decides that more compliance time is needed, the 
operator may request an AMOC in accordance with paragraph (g)(1) of the 
AD. We have not changed the AD in this regard.

Request To Add Optional Terminating Action

    FedEx requests that we add an optional terminating action to the 
NPRM. FedEx states that, for airplanes not found to be cracked that 
have not been previously repaired, an equivalent level of safety could 
be obtained by modifying the airplane in accordance with Airbus Service 
Bulletin A300-57-6064 (which describes procedures for installing 
internal and external reinforcing plates on bottom skin panel No. 2, a 
stiffener for the support structure, and a new cleat) prior to 
accumulating 10,000 total flight cycles or within 380 flight cycles 
after the effective date of the AD, whichever is later. FedEx states 
that some of its airplanes already have this modification installed, 
and asserts, therefore, that credit should be given for installing this 
modification using Revision 0 through 4 of Airbus Service Bulletin 
A300-57-6064. FedEx asserts that providing this terminating action 
would place the airplane beyond the LOV and make further follow-up 
inspections unnecessary, thereby enhancing safety and greatly 
simplifying compliance tracking.
    We do not agree with this request. Fatigue and damage tolerance 
analysis has shown that, after installing modification 11178 as 
described in Airbus Service Bulletin A300-57-6064, this area must still 
be inspected to control or correct the development of cracks. 
Therefore, we have not changed the AD in this regard. However, 
operators may request an AMOC for adjustments to compliance times in 
accordance with paragraph (g)(1) of the AD.

Clarification of Typographical Error in Service Information

    Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 
2007, specifies repetitive inspections for cracking if Airbus Service 
Bulletin A300-57-022 has not been embodied. Service Bulletin A300-57-
022 does not exist. This AD correctly requires doing repetitive 
inspections for cracking if Airbus Service Bulletin A300-57-0222 
(modification 11178H5410) has not been embodied.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Differences Between This AD and the MCAI or Service Information 
Conclusion

    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 162 products of U.S. registry. 
We also estimate that it will 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 
this AD to the U.S. operators to be $25,920, or $160 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.

[[Page 14672]]

    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:

2008-06-18 Airbus: Amendment 39-15430. Docket No. FAA-2007-28944; 
Directorate Identifier 2006-NM-239-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
23, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 series airplanes and 
Model A300-600 series airplanes; certificated in any category; all 
certified models, all serial numbers.

Subject

    (d) Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    This Airworthiness Directive (AD) is published subsequent to the 
detection of cracks on multiple aircraft in lower skin panel No. 2 
forward of access panel 575FB/675FB held on the rear dummy spar, 
inboard of rib 9, fuselage side, aft of the rear spar.
    This area of structure has been subjected to several repairs and 
modifications in previous years.
    The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and 
A300-57-6029 at Revision 4 define the various configurations for the 
mandatory inspections to be conducted in order to control or correct 
the development of cracks which could affect the structural 
integrity of the aircraft.

The MCAI requires doing repetitive inspections (detailed visual, 
high frequency eddy current, x-ray) of the wing lower skin panel and 
associated internal support structure for cracking and, if 
necessary, doing corrective measures (modifying the lower panel 
inboard of rib 9 aft of the rear spar and repairing cracks).

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 specified 
in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-0177, 
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, 
dated March 23, 2007; as applicable; perform the inspection of the 
wing lower skin panel and associated internal support structure aft 
of the rear spar and inboard of rib 9 and apply applicable 
corrective measures in accordance with Airbus Service Bulletin A300-
57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, 
Revision 06, dated March 23, 2007; as applicable. All applicable 
corrective measures must be done at the applicable times specified 
in paragraph 1.E.(2) and the Accomplishment Instructions of the 
applicable service bulletin.
    (i) Where the tables in paragraph 1.E.(2), ``Accomplishment 
Timescale,'' of the service bulletins specify a grace period for 
doing the actions, this AD requires that the actions be done within 
the specified grace period relative to the effective date of this 
AD.
    (ii) Where the tables in paragraph 1.E.(2)(e), ``Config 04,'' of 
Airbus Service Bulletin A300-57-0177, Revision 05, specify an 
inspection interval but not an initial threshold, this AD requires 
that the actions be done within the specified interval after 
inspecting in accordance with Table 1A or 1B, as applicable, for 
Configuration 01 airplanes described in the service bulletin and 
thereafter at the inspection interval specified in the tables in 
paragraph 1.E.(2)(e), ``Config 04,'' of Airbus Service Bulletin 
A300-57-0177, Revision 05.
    (iii) Where the tables in paragraph 1.E.(2)(f), ``Config 05,'' 
of Airbus Service Bulletin A300-57-6029, Revision 06, specify an 
inspection interval but not an initial threshold, this AD requires 
that the actions be done within the specified interval after 
inspecting in accordance with Table 1A or 1B, as applicable, for 
configuration 01 of the service bulletin and thereafter at the 
inspection interval specified in the tables in paragraph 1.E.(2)(f), 
``Config 05,'' of A300-57-6029, Revision 06.
    (iv) All crack lengths specified in Airbus Service Bulletin 
A300-57-0177, Revision 05, and A300-57-6029, Revision 06, are 
considered ``not to exceed'' lengths.
    (2) Repeat the inspection at the intervals in, and according to 
the instructions defined in, Airbus Service Bulletin A300-57-0177, 
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, 
dated March 23, 2007; as applicable; except where Service Bulletin 
A300-57-0177, Revision 05, specifies repetitive inspections for 
cracking if Airbus Service Bulletin A300-57-022 has not been 
embodied, this AD requires doing repetitive inspections for cracking 
if Airbus Service Bulletin A300-57-0222 (modification 11178H5410) 
has not been embodied.
    (3) Report to Airbus the first inspection results, whatever they 
may be, at the applicable time specified in paragraph (f)(3)(i) or 
(e)(f)(ii) of this AD.
    (i) If the inspection was done after the effective date of this 
AD, submit the report within 30 days after the inspection.
    (ii) If the inspection was accomplished prior to the effective 
date of this AD, submit the report within 30 days after the 
effective date of this AD.
    (4) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-57-0177, Revision 03, 
dated May 29, 2006; Airbus Service Bulletin A300-57-0177, Revision 
04, dated January 5, 2007; Airbus Service Bulletin A300-57-6029, 
Revision 04, dated May 29, 2006; or Airbus Service Bulletin A300-57-
6029, Revision 05, dated October 23, 2006; are considered acceptable 
for compliance with the corresponding action specified in this AD.

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, 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, FAA, 
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

[[Page 14673]]

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 Airworthiness 
Directive 2006-0282, dated September 12, 2006; and the service 
information in Table 1 of this AD; for related information.

                                          Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
             Airbus Service Bulletin               Revision level                       Date
----------------------------------------------------------------------------------------------------------------
A300-57-0177....................................                05  March 23, 2007.
A300-57-0222....................................                01  March 13, 2006.
A300-57-6029....................................                06  March 23, 2007.
A300-57-6064....................................                04  March 9, 2006.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information specified in Table 2 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 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
             Airbus Service Bulletin               Revision level                       Date
----------------------------------------------------------------------------------------------------------------
A300-57-0177....................................                05  March 23, 2007.
A300-57-6029....................................                06  March 23, 2007.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on March 7, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-5149 Filed 3-18-08; 8:45 am]

BILLING CODE 4910-13-P
