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

[Federal Register Volume 70, Number 218 (Monday, November 14, 2005)]
[Rules and Regulations]
[Pages 69056-69059]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22216]



[[Page 69056]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22110; Directorate Identifier 2004-NM-205-AD; 
Amendment 39-14366; AD 2005-23-08]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A300 B4-600 and A300 B4-600R 
series airplanes, and all Model A300 F4-605R airplanes. That AD 
currently requires repetitive inspections to detect cracks of certain 
attachment holes, installation of new fasteners, follow-on inspections 
or repair if necessary, and modification of the angle fittings of 
fuselage frame FR47. This new AD revises certain inspection thresholds 
and intervals. This new AD also adds inspections to detect cracks of 
additional attachment holes. This AD results from reports of cracks 
found before the inspection thresholds in the existing AD and cracks 
found in nearby areas not inspected by the existing AD. We are issuing 
this AD to prevent fatigue cracking of the forward fitting of fuselage 
frame FR47, which could result in reduced structural integrity of the 
frame.

DATES: This AD becomes effective December 19, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 19, 
2005.
    On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of the 
Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A300-57-6086, dated June 6, 2000.

ADDRESSES: You may examine the 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., Nassif Building, 
room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2002-11-04, amendment 
39-12765 (67 FR 38193, June 3, 2002). The existing AD applies to all 
Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all 
Model A300 F4-605R airplanes. That NPRM was published in the Federal 
Register on August 16, 2005 (70 FR 48085). That NPRM proposed to 
continue to require repetitive inspections to detect cracks of certain 
attachment holes, installation of new fasteners, follow-on inspections 
or repair if necessary, and modification of the angle fittings of 
fuselage frame FR47. That NPRM also proposed to revise certain 
inspection thresholds and intervals and add inspections to detect 
cracks of additional attachment holes.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
received on the NPRM.

Request To Clarify Inspection in Paragraph (k)

    One commenter, the manufacturer, requests that we clarify the 
inspection specified in paragraph (k) of the NPRM. The commenter states 
that the inspection of hole T is not required if ``any cracking is 
found'' but is required only if cracking is found at hole G.
    We agree with the commenter that the inspection of hole T is 
required only if cracking is found at hole G. As specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, 
Revision 01, dated April 2, 2002 (which is referenced as the 
appropriate source of service information for accomplishing the 
required actions for certain airplanes), the inspection of hole T is 
applicable only if cracking is found at hole G. For clarity, we have 
revised paragraph (k) of the final rule.

Clarification of Service Bulletin References

    We have revised certain references to the service bulletins for 
clarity. We have clarified that the actions specified in paragraphs (j) 
and (k) of the final rule are done in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, 
Revision 01, dated April 2, 2002. We have also clarified that the 
modifications specified in paragraph (l) of the final rule are done in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6050, Revision 03, dated May 31, 2001.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, 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. This AD will affect about 74 airplanes of U.S. 
registry.

[[Page 69057]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                Average
             Action               Work hours   labor rate       Parts       Cost per airplane      Fleet cost
                                                per hour
----------------------------------------------------------------------------------------------------------------
Inspection per Airbus Service             13          $65               $0  $845.............  $62,530, per
 Bulletin A300-57-6049.                                                                         inspection
                                                                                                cycle.
Inspection per Airbus Service             30           65     6,637-19,091  $8,587-$21,041,    $635,438-$1,557,0
 Bulletin A300-57-6086.                                                      per inspection     34, per
                                                                             cycle.             inspection
                                                                                                cycle.
Modification per Airbus Service       65-365           65            3,370  $7,595-$27,095...  $562,030-$2,005,0
 Bulletin A300-57-6050.                                                                         30.
----------------------------------------------------------------------------------------------------------------

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 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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12765 (67 FR 38193, June 3, 2002) and by adding 
the following new airworthiness directive (AD):

2005-23-08 Airbus: Amendment 39-14366. Docket No. FAA-2005-22110; 
Directorate Identifier 2004-NM-205-AD.

Effective Date

    (a) This AD becomes effective December 19, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-11-04.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; 
Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F 
airplanes; certificated in any category; except airplanes on which 
Airbus Modification 12171 or 12249 has been accomplished or on which 
Airbus Service Bulletin A300-57-6069 has been accomplished.

Unsafe Condition

    (d) This AD was prompted by reports of cracks found before the 
inspection thresholds in the existing AD and cracks found in nearby 
areas not inspected by the existing AD. We are issuing this AD to 
prevent fatigue cracking of the forward fitting of fuselage frame 
FR47, which could result in reduced structural integrity of the 
frame.

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.

Inspections for Attachment Holes on the Internal Angles of the Wing 
Center Box, and Corrective Action

    (f) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes on the left and right internal 
angles of the wing center box in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, 
dated July 15, 2004. Do the inspection at the applicable time 
specified by paragraph 1.E.(2), Accomplishment Timescale, of 
Revision 06 of the service bulletin, except as required by paragraph 
(m) of this AD. Repeat the rotating probe inspection specified in 
this paragraph thereafter at intervals not to exceed the applicable 
interval specified in Revision 06 of the service bulletin, except 
that all touch-and-go landings must be counted in determining the 
total number of flight cycles between consecutive inspections.
    (g) If no cracking is found during any inspection required by 
paragraph (f) of this AD: Prior to further flight, install new 
fasteners in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 
2004.
    (h) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Prior to further flight, perform 
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and 
installing new or oversize fasteners) in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, 
Revision 06, dated July 15, 2004, except as required by paragraph 
(n) of this AD.

Inspections for Attachment Holes in the Horizontal Flange of the 
Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective 
Action

    (i) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes in the horizontal flange of the 
internal corner angle fitting of fuselage frame FR47, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6086, Revision 01, dated April 2, 2002. Do the inspection at 
the applicable time specified in paragraph 1.E., Compliance, of 
Airbus Service Bulletin A300-57-6086,

[[Page 69058]]

Revision 01, dated April 2, 2002, except as provided by paragraph 
(m) of this AD; or within 1,500 flight cycles after July 8, 2002 
(the effective date of AD 2002-11-04, amendment 39-12765); whichever 
occurs later. Repeat the rotating probe inspection specified in this 
paragraph thereafter at intervals not to exceed the applicable 
interval specified in Airbus Service Bulletin A300-57-6086, dated 
June 6, 2000, except that all touch-and-go landings must be counted 
in determining the total number of flight cycles between consecutive 
inspections.
    (j) If no cracking is found during any inspection required by 
paragraph (i) of this AD: Prior to further flight, install new 
fasteners in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 
2002.
    (k) If any cracking is found during any inspection required by 
paragraph (i) of this AD: Prior to further flight, perform 
applicable corrective actions (including inspecting hole T if any 
cracking is found at hole G, reaming the holes, and installing 
oversize fasteners) in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002, except as required by paragraph (n) of this AD.

Modification of Angle Fittings of the Wing Center Box

    (l) Modify the left and right internal angle fittings of the 
wing center box. The modification includes performing a rotating 
probe inspection to detect cracking, repairing cracks, cold 
expanding holes, and installing medium interference fitting bolts. 
Perform the modification in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6050, Revision 03, 
dated May 31, 2001; and at the applicable time specified by 
paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service 
Bulletin A300-57-6050, Revision 03, dated May 31, 2001; except as 
required by paragraphs (m) and (n) of this AD.

Exceptions to Specifications in Service Bulletins

    (m) Where the service bulletins specified in paragraphs (f), 
(i), and (l) of this AD specify a grace period relative to receipt 
of the service bulletin, this AD requires compliance within the 
applicable grace period following the effective date of this AD, if 
the threshold has been exceeded.
    (n) If any crack is detected during any inspection required by 
this AD, and the applicable service bulletin specifies to contact 
the manufacturer for disposition of certain corrective actions: 
Prior to further flight, repair in accordance with a method approved 
by either the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC) (or its delegated agent).

Actions Accomplished According to Previous Issue of Service Bulletins

    (o) Actions accomplished prior to the effective date of this AD 
in accordance with Airbus Service Bulletin A300-57-6086, dated June 
6, 2000, are acceptable for compliance with the requirements of 
paragraph (i) of this AD.
    (p) Modifications accomplished prior to the effective date of 
this AD in accordance with Airbus Service Bulletin A300-57-6050, 
Revision 02, dated February 10, 2000; are acceptable for compliance 
with the requirements of paragraph (l) of this AD.

No Reporting Requirement

    (q) Although Airbus Service Bulletin A300-57-6049, Revision 06, 
dated July 15, 2004; and Airbus Service Bulletin A300-57-6086, 
Revision 01, dated April 2, 2002; specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Alternative Methods of Compliance (AMOCs)

    (r)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously according to AD 2002-11-04, are 
not approved as AMOCs with this AD.

Related Information

    (s) French airworthiness directive F-2004-159, dated September 
29, 2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (t) You must use the service bulletins listed in Table 1 of this 
AD to perform the actions that are required by this AD, unless the 
AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of the service bulletins listed in Table 
2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of 
the Federal Register approved the incorporation by reference of 
Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

            Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
     Airbus service bulletin       Revision level           Date
------------------------------------------------------------------------
A300-57-6049, excluding Appendix  06..............  July 15, 2004.
 01.
A300-57-6050....................  03..............  May 31, 2001.
A300-57-6086....................  Original........  June 6, 2000.
A300-57-6086....................  01..............  April 2, 2002.
------------------------------------------------------------------------


            Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
     Airbus service bulletin       Revision level           Date
------------------------------------------------------------------------
A300-57-6049, excluding Appendix  06..............  July 15, 2004.
 01.
A300-57-6050....................  03..............  May 31, 2001.
A300-57-6086....................  01..............  April 2, 2002.
------------------------------------------------------------------------

    Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 
2001, contains the following effective pages:

------------------------------------------------------------------------
                               Revision level
         Page number            shown on page      Date shown on page
------------------------------------------------------------------------
1, 4, 10A-11, 75-76..........  03............  May 31, 2001.
2, 8-9, 17-32, 41-42, 57-58,   02............  February 10, 2000.
 61-63, 77.
3, 5-7, 10, 12, 33-34, 37-38,  01............  May 31, 1999.
 47, 59-60.
13-16, 35-36, 39-40, 43-46,    Original......  September 9, 1994.
 48-56, 64-74.
------------------------------------------------------------------------



[[Page 69059]]

    Issued in Renton, Washington, on October 31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22216 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P

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