[Federal Register Volume 69, Number 227 (Friday, November 26, 2004)]
[Rules and Regulations]
[Pages 68779-68782]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-25785]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18593; Directorate Identifier 2004-NM-21-AD; 
Amendment 39-13875; AD 2004-23-20]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-
600, and A300 B4-600R Series Airplanes; and Model A300 C4-605R Variant 
F and A300 F4-605R Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Airbus Model A300 B4-601, A300 B4-603, A300 
B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. That AD 
currently requires repetitive inspections for cracking in the area 
surrounding certain fuselage attachment holes, installation of new 
fasteners for certain airplanes, and certain follow-on corrective 
actions if necessary. This new AD requires modifying certain fuselage 
frames, which would terminate certain repetitive inspections. This AD 
also adds airplanes to the applicability. This AD is prompted by the 
development of a modification intended to prevent cracking of the 
center section of the fuselage, which could result in a ruptured frame 
foot and reduced structural integrity of the airplane.

DATES: This AD becomes effective January 3, 2005.
    The incorporation by reference of Airbus Service Bulletin A300-53-
0271, Revision 03, dated June 13, 2003; and Airbus Service Bulletin 
A300-53-6125, Revision 01, dated June 13, 2003; as listed in the AD, is 
approved by the Director of the Federal Register as of January 3, 2005.
    On May 7, 2001 (66 FR 17490, April 2, 2001), the Director of the 
Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A300-53-6122, dated February 9, 2000.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You 
can examine this information 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/code_of_federal_regulations/ibr_locations.html.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:
    Technical information: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2125; fax (425) 227-1149.
    Plain language information: Marcia Walters, <a href="/cdn-cgi/l/email-protection#adc0ccdfcec4cc83daccc1d9c8dfdeedcbcccc83cac2db"><span class="__cf_email__" data-cfemail="c5a8a4b7a6aca4ebb2a4a9b1a0b7b685a3a4a4eba2aab3">[email protected]</span></a>.

Examining the Docket

    The AD docket contains the proposed AD, comments, and any final 
disposition. You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede 
AD 2001-06-10, amendment 39-12157 (66 FR 17490, April 2, 2001). The 
existing AD applies to all Airbus Model A300 B4-601, A300 B4-603, A300 
B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. The 
proposed AD, published in the Federal Register on July 16, 2004 (69 FR 
42612), would require modifying certain fuselage frames, which would 
terminate certain repetitive inspections, and add airplanes to the 
applicability.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Request To Clarify Grace Period

    One commenter requests that we clarify the grace period specified 
in paragraph (i) of the proposed AD, specifically regarding the 
following sentence:

For airplanes that have exceeded the specified threshold, this AD 
requires compliance within the earlier of the flight-cycle and flight-
hour grace periods specified in the service bulletin.

    The commenter states that this language could be confusing. In Note 
(01), paragraph 1.E.(2)(b) (``COMPLIANCE''), of Airbus Service 
Bulletins A300-53-0271 and A300-53-6125, the grace period is described 
in terms of flight hours and flight cycles only for airplanes that have 
exceeded their ``design service goal'' (DSG). For airplanes that have 
exceeded the ``threshold'' but not their DSG, the service bulletins (in 
Note (02)) describe the grace period as the earlier of accomplishment 
of two service bulletins required by related AD 96-13-11, amendment 39-
9679 (61 FR 35122, July 5, 1996).
    We partially agree. For airplanes above their DSG, NOTE (01) 
specifies the imprecise grace period ``3,300FC/3700FH for B2, 2900FC/
3900FH for B4-100 and 2,200FC/4500FH for B4-200.'' We added the 
sentence quoted by the commenter only to specify that the grace period 
must be determined by the earlier of the flight-hour and flight-cycle 
values. While ``design service goal'' might have been more precise than 
``threshold'' in this context, we referred to these two terms 
collectively as ``the specified threshold'' to clarify the compliance-
time conditions of the service bulletins. We have revised

[[Page 68780]]

paragraph (i) of this final rule to clarify the method for determining 
the appropriate grace period.

Request To Add Service Bulletin Reference

    One commenter requests that we revise Table 1 of the proposed AD to 
add Airbus Service Bulletin A300-53-6122. The commenter provides no 
further explanation.
    We find that clarification of Table 1 is necessary. Table 1 
identifies the service bulletin references for the requirements of 
paragraph (i) of this AD. Service Bulletin A300-53-6122 is the 
reference for the requirements of paragraphs (f) and (g) of this AD. 
That service bulletin does not provide information relevant to Table 1. 
We have not changed the final rule regarding this issue.

Request To Approve Future Service Information

    One commenter requests that we revise the proposed AD to indicate 
that any approved revisions of the identified service bulletins are 
acceptable, as stated in the parallel French airworthiness directives 
F-224-001 and F-224-002, both dated January 7, 2004.
    We cannot accept as-yet unpublished service documents for 
compliance with the requirements of an AD. Referring to an unavailable 
service bulletin in an AD violates Office of the Federal Register 
regulations for approving materials that are incorporated by reference. 
We have not changed the final rule regarding this issue. However, under 
the provisions of paragraph (k)(1) of this final rule, affected 
operators may request approval to use a later revision of the 
referenced service bulletin as an alternative method of compliance 
(AMOC).

Request To Clarify Repair Approval

    One commenter requests that we revise paragraphs (j) and (k) of the 
proposed AD to clarify the acceptability of DGAC-or Airbus-approved 
repairs. The commenter points out that such explicit approval would 
eliminate the processing time and work duplication for requests for 
AMOCs if an approval by DGAC or its agent is available. We infer that 
the commenter is requesting that paragraph (k) of this AD provide 
explicit approval of repairs done in accordance with a method approved 
by the DGAC, as specified in paragraph (j) of this AD.
    We do not agree. We cannot allow operators to contact the 
manufacturer for repair instructions; to do so would be delegating our 
rulemaking authority to the manufacturer. Furthermore, we do not agree 
that clarification is necessary regarding approvals for repairs 
specified in paragraph (j) of this AD, which specifically allows repair 
approval by the DGAC or its delegated agent. Concerning paragraph (k) 
of this AD, AMOCs must be approved by the FAA.

Request To Approve Alternative Materials

    One commenter reports that the oversize fasteners (specified in 
Airbus Service Bulletins A300-53-0271 and A300-53-6125) may be 
difficult to obtain. The commenter therefore requests that we revise 
the proposed AD to approve use of the alternative substitute fasteners 
listed in the Airbus Structural Repair Manual (SRM) or the Airbus 
Process and Materials Specification Manual.
    We do not find it necessary to revise the AD regarding this issue. 
Because the service bulletins refer to the appropriate sections of the 
applicable Airbus SRM, the specific substitute parts listed in the SRM 
are considered acceptable for any repair or modification required by 
this AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                         Labor                                                          Number of U.S.-
            Action                 Model       Work     rate per       Parts cost              Cost per airplane          registered       Fleet cost
                                              hours       hour                                                             airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection....................    A300-600          6        $65  None required.......  $390, per inspection..........             106  $41,340, per
                                                                                                                                         inspection.
Modification..................        A300         90         65  2,000...............  7,850.........................              24  188,400.
Modification..................    A300-600         56         65  4,000...............  7,640.........................             106  809,840.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Regulatory Findings

    We have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

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 airworthiness 
directive (AD):


[[Page 68781]]


2004-23-20 Airbus: Amendment 39-13875. Docket No. FAA-2004-18593; 
Directorate Identifier 2004-NM-21-AD.

Effective Date

    (a) This AD becomes effective January 3, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-06-10, amendment 39-12157. 
Paragraph (i) of this AD terminates certain requirements of AD 96-
13-11, amendment 39-9679.

Applicability

    (c) This AD applies to all Airbus Model A300 B2, A300 B4, A300 
B4-600, and A300 B4-600R series airplanes; and all Airbus Model A300 
C4-605R Variant F and A300 F4-605R airplanes; certificated in any 
category; except those airplanes modified by Airbus Modification 
12168.

Unsafe Condition

    (d) This AD was prompted by the development of a modification 
intended to prevent cracking of the center section of the fuselage, 
which could result in a ruptured frame foot and reduced structural 
integrity of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 2001-06-10

Inspections

    (f) For Model A300 B4-600 and A300 B4-600R series airplanes, and 
Model A300 C4-605R Variant F and A300 F4-605R airplanes: Perform a 
high-frequency eddy-current or rototest inspection to detect 
cracking in the area surrounding the frame feet attachment holes 
between fuselage frames (FR) 41 and FR46 from stringers 24 to 28, 
left- and right-hand sides, in accordance with Airbus Service 
Bulletin A300-53-6122, dated February 9, 2000, at the time specified 
in paragraph (f)(1) or (f)(2), as applicable.
    (1) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has not been 
accomplished as of May 7, 2001 (the effective date of AD 2001-06-
10): Perform the inspection at the later of the times specified in 
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
    (i) Prior to the accumulation of the total flight-cycle or 
flight-hour threshold, whichever occurs first, specified in 
paragraph 1.E. (``Compliance'') of the service bulletin; or
    (ii) Within the applicable grace period specified in paragraph 
1.E. (``Compliance'') of the service bulletin.
    (2) For airplanes on which Task 53-15-54 in the MRBD, Revision 
3, dated April 1998, has been accomplished as of May 7, 2001: 
Perform the next repetitive inspection at the later of the times 
specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
    (i) Within the flight-cycle or flight-hour interval, whichever 
occurs first, specified in paragraph 1.E. (``Compliance'') of the 
service bulletin, following the latest inspection accomplished in 
accordance with the MRBD; or
    (ii) Within the grace period specified in paragraph 1.E. 
(``Compliance'') of the service bulletin.
    (g) For airplanes on which no cracking is detected during the 
inspection required by paragraph (f) of this AD, prior to further 
flight, install new fasteners as applicable, in accordance with 
Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and 
repeat the inspection required by paragraph (f) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin, until the actions required by paragraph (i) of this AD 
have been done.

Corrective Actions

    (h) For airplanes on which cracking is detected during any 
inspection required by paragraph (f) of this AD: Prior to further 
flight, except as required by paragraph (j) of this AD, accomplish 
corrective actions (e.g., performing rotating probe inspections, 
reaming out cracks, cold working fastener holes, and installing 
oversized fasteners) in accordance with Airbus Service Bulletin 
A300-53-6122, dated February 9, 2000. Repeat the inspection required 
by paragraph (f) of this AD thereafter at intervals not to exceed 
the applicable intervals specified in paragraph 1.E. 
(``Compliance'') of the service bulletin, until the actions required 
by paragraph (i) of this AD have been done.

New Requirements of This AD

Modification: All Airplanes

    (i) For all airplanes: Within the compliance times specified in 
paragraph 1.E. of the applicable service bulletin listed in Table 1 
of this AD, modify the fuselage frames in accordance with the 
Accomplishment Instructions of the applicable service bulletin. For 
airplanes that have exceeded their design service goal, as specified 
in NOTE (01) of paragraph 1.E. of the service bulletin, this AD 
requires compliance within the earlier of the flight-cycle and 
flight-hour grace periods specified in the service bulletin.

                                          Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
                                                                                         Revision level(s) also
                                           Airbus service                              acceptable for compliance
             Airplane model                   bulletin       Required revision level       if done before the
                                                                                       effective date of this AD
----------------------------------------------------------------------------------------------------------------
A300 B2 and A300 B4 series airplanes...       A300-53-0271  Revision 03, dated June    Original, dated September
                                                             13, 2003.                  10, 1991.
                                                                                       Revision 01, dated
                                                                                        February 16, 1993.
                                                                                       Revision 02, dated July
                                                                                        13, 2000.
A300 B4-600 and A300 B4-600R series           A300-53-6125  Revision 01, dated June    Original, dated November
 airplanes, and A300 C4-605 Variant F                        13, 2003.                  8, 2000.
 and A300 F4-605R airplanes.
----------------------------------------------------------------------------------------------------------------

    (1) For the affected Model A300 B4-600 series airplanes: 
Accomplishment of the modification terminates the requirements of 
this AD.
    (2) For Model A300 B2 and A300 B4 series airplanes: 
Accomplishment of the modification terminates certain repetitive 
inspections required by AD 96-13-11, i.e., inspections of the frame 
feet holes for frames 41 to 46 (as specified in Airbus Service 
Bulletin A300-53-0345) and frames 48 to 54 (as specified in Airbus 
Service Bulletin A300-53-238). However, the repetitive inspections 
of the frame foot angle radius (as specified in Service Bulletin 
A300-53-238), which are required by AD 96-13-11, must continue.

Exceptions to Service Bulletin Procedures

    (j) During any inspection required by this AD, if the applicable 
service bulletin specifies to contact the manufacturer for 
appropriate instructions: Before further flight, perform applicable 
corrective action in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the Direction Generale de l'Aviation Civile 
(DGAC) (or its delegated agent).

Alternative Methods of Compliance

    (k)(1) The Manager, International Branch, ANM-116, has the 
authority to approve alternative methods of compliance (AMOCs) for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) AMOCs approved previously in accordance with AD 2001-06-10, 
amendment 39-12157, are approved as AMOCs with the corresponding 
requirements of this AD.

Related Information

    (l) French airworthiness directives F-2004-001 and F-2004-002, 
both dated January 7, 2004, also address the subject of this AD.

Material Incorporated by Reference

    (m) Unless the AD specifies otherwise, you must use the service 
information that is

[[Page 68782]]

specified in Table 2 of this AD to perform the actions that are 
required by this AD, as applicable.

                                  Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
          Service bulletin                       Revision level                             Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-53-     03...................................  June 13, 2003.
 0271.
Airbus Service Bulletin A300-53-     Original.............................  February 9, 2000.
 6122.
Airbus Service Bulletin A300-53-     01...................................  June 13, 2003.
 6125.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of Airbus Service Bulletin 
A300-53-0271, Revision 03, dated June 13, 2003; and Airbus Service 
Bulletin A300-53-6125, Revision 01, dated June 13, 2003; is approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) On May 7, 2001 (66 FR 17490, April 2, 2001), the Director of 
the Federal Register approved the incorporation by reference of 
Airbus Service Bulletin A300-53-6122, dated February 9, 2000.
    (3) For copies of the service information, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may 
be inspected 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 10, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-25785 Filed 11-24-04; 8:45 am]
BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>