[Federal Register Volume 71, Number 176 (Tuesday, September 12, 2006)]
[Rules and Regulations]
[Pages 53559-53562]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-14942]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25047; Directorate Identifier 2006-NM-028-AD; 
Amendment 39-14759; AD 2006-19-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes)

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300-600 series airplanes. 
That AD currently requires repetitive eddy current inspections to 
detect cracks of the outer skin of the fuselage at certain frames, and 
repair or reinforcement of the structure at the frames, if necessary. 
That AD also requires eventual reinforcement of the structure at 
certain frames, which, when accomplished, terminates the repetitive 
inspections. This new AD requires, for airplanes that were previously 
reinforced but not repaired in accordance with the existing AD, a one-
time inspection for cracking of the fuselage outer skin at frames 28A 
and 30A above stringer 30, and repair if necessary. This AD results 
from a report that the previously required actions were not sufficient 
to correct cracking before the structural reinforcement was installed. 
We are issuing this AD to prevent such fatigue cracking, which could 
result in reduced structural integrity, and consequent rapid 
decompression of the airplane.

DATES: This AD becomes effective October 17, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of October 17, 
2006.
    On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the 
Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A300-53-6045, dated March 21, 1995, as revised by 
Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin 
A300-53-6037, dated March 21, 1995.

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: 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:

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 97-14-02, amendment 39-
10059 (62 FR 35072, June 30, 1997). The existing AD applies to certain 
Airbus Model A300-600 series airplanes. That NPRM was published in the 
Federal Register on June 15, 2006 (71 FR 34563). That NPRM proposed to 
continue to require repetitive eddy current inspections to detect 
cracks of the outer skin of the fuselage at certain frames, and repair 
or reinforcement of the structure at the frames, if necessary. That 
NPRM also proposed to continue to require eventual reinforcement of the 
structure at certain frames, which, when accomplished, terminates the 
repetitive inspections. That NPRM also proposed

[[Page 53560]]

to require, for airplanes that were previously reinforced but not 
repaired in accordance with the existing AD, a one-time inspection for 
cracking of the fuselage outer skin at frames 28A and 30A above 
stringer 30, and repair if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    This AD will affect about 53 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this AD. The average labor rate is $80 per work hour.

                                                                     Estimated Costs
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                                       Work
              Action                  hours      Parts                   Cost per airplane                                  Fleet cost
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Inspection (required by AD 97-14-           1       None  $80, per inspection cycle.....................  $4,240, per inspection cycle.
 02).
Reinforcement (required by AD 97-          93     $7,200  $14,640.......................................  $775,920.
 14-02).
Inspection (new required action)..          1       None  $80...........................................  $4,240.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 39-10059 (62 FR 35072, June 30, 1997) and by adding 
the following new airworthiness directive (AD):

2006-19-02 Airbus: Amendment 39-14759. Docket No. FAA-2006-25047; 
Directorate Identifier 2006-NM-028-AD.

Effective Date

    (a) This AD becomes effective October 17, 2006.

Affected ADs

    (b) This AD supersedes AD 97-14-02.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes, certificated in any category, except those on which 
Airbus Modification 8683 has been done.

Unsafe Condition

    (d) This AD results from a report that the previously required 
actions were not sufficient to correct cracking before the 
structural reinforcement was installed. We are issuing this AD to 
prevent fatigue cracking of the outer skin of the fuselage at 
certain frames, which could result in reduced structural integrity, 
and consequent rapid decompression 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 the Requirements of AD 97-14-02

    (f) Prior to the accumulation of 14,100 total flight cycles, or 
within 12 months after August 4, 1997 (the effective date of AD 97-
14-02), whichever occurs later, conduct an eddy current inspection 
to detect cracking of the fuselage outer skin at frames 28A and 30A 
above stringer 30, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6045, dated March 
21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; 
or Airbus Service Bulletin A300-53-6045, Revision 03, dated October 
28, 2004. After the effective date of this AD, only Revision 03 may 
be used. After the effective date of this AD, the initial eddy 
current inspection and all applicable repairs required by this 
paragraph must be done before doing the reinforcement specified in 
paragraph (g) of this AD.
    (1) If no cracking is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 4,500 flight cycles.
    (2) If any cracking is found that is within the limits specified 
in the service bulletin: Prior to further flight do the actions in 
paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective 
date of this AD, only Airbus Service Bulletin A300-53-6045, Revision 
03, dated October 28, 2004, may be used for the repair specified in 
paragraph (f)(2)(i) of this AD; and the reinforcement option 
specified in paragraph (f)(2)(ii) of this AD is not allowed in 
accordance with this paragraph.

[[Page 53561]]

    (i) Repair in accordance with paragraph 2.D. of the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, 
dated March 21, 1995, as revised by Change Notice No. O.A., dated 
June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6045, Revision 03, dated October 
28, 2004. After the repair, repeat the eddy current inspection 
thereafter at intervals not to exceed 4,500 flight cycles.
    (ii) Reinforce the structure at frames 28 and 29, and at frames 
30 and 31, between stringers 29 and 30, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, 
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, 
Revision 02, dated October 28, 2004. Such reinforcement constitutes 
terminating action for the repetitive inspections required by this 
AD.
    (3) If any cracking is found that is outside the limits 
specified in the service bulletin: Prior to further flight, 
reinforce the structure at frames 28 and 29, and at frames 30 and 
31, between stringers 29 and 30, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, 
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, 
Revision 02, dated October 28, 2004. After the effective date of 
this AD, only Revision 02 may be used. Such reinforcement 
constitutes terminating action for the repetitive inspections 
required by this AD.
    (g) Within 5 years after August 4, 1997: Reinforce the structure 
at frames 28 and 29, and at frames 30 and 31, between stringers 29 
and 30, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus 
Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. 
After the effective date of this AD, only Revision 02 may be used. 
Such reinforcement constitutes terminating action for the repetitive 
inspections required by this AD. After the effective date of this 
AD, the initial eddy current inspection and all applicable repairs 
required by paragraph (f) of this AD must be done before doing the 
reinforcement.

New Requirements of This AD

Inspection and Corrective Action

    (h) For airplanes that meet the conditions of both paragraphs 
(h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18 
months after the effective date of this AD, whichever occurs first, 
conduct an eddy current inspection to detect cracking of the 
fuselage outer skin at frames 28A and 30A above stringer 30, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6045, Revision 03, dated October 28, 2004. If no 
cracking is found: No further action is required by this paragraph. 
If any cracking is found: Before further flight, repair the cracking 
using 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).
    (1) Airplanes that were reinforced before the effective date of 
this AD in accordance with any service bulletin specified in Table 1 
of this AD.

                                    Table 1.--Reinforcement Service Bulletins
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          Airbus service bulletin                  Revision level                          Date
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A300-53-6037..............................  Original...................  March 21, 1995.
                                            1..........................  February 3, 1999.
                                            02.........................  October 28, 2004.
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    (2) Airplanes that were not inspected and repaired in accordance 
with any service bulletin specified in Table 2 of this AD.

                                Table 2.--Inspection and Repair Service Bulletins
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          Airbus service bulletin                  Revision level                          Date
----------------------------------------------------------------------------------------------------------------
A300-53-6045..............................  Original...................  March 21, 1995.
                                            01.........................  August 25, 1997.
                                            02.........................  May 2, 1999.
                                            03.........................  October 28, 2004.
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Alternative Methods of Compliance (AMOCs)

    (i)(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 Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (j) French airworthiness directive F-2005-002, dated January 5, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use the service information identified in Table 3 
of this AD to perform the actions that are required by this AD, 
unless the AD specifies otherwise.

                                  Table 3.--Material Incorporated by Reference
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          Airbus service bulletin                  Revision level                          Date
----------------------------------------------------------------------------------------------------------------
A300-53-6037..............................  Original...................  March 21, 1995.
A300-53-6037..............................  02.........................  October 28, 2004.
A300-53-6045..............................  03.........................  October 28, 2004.
A300-53-6045, as revised by Change Notice   Original...................  March 21, 1995.
 No. O.A., dated June 1, 1995.
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[[Page 53562]]

    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Service Bulletin A300-53-6037, 
Revision 02, dated October 28, 2004; and Airbus Service Bulletin 
A300-53-6045, Revision 03, dated October 28, 2004; in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director 
of the Federal Register approved the incorporation by reference of 
Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as 
revised by Change Notice No. O.A., dated June 1, 1995; and Airbus 
Service Bulletin A300-53-6037, dated March 21, 1995.
    (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.

    Issued in Renton, Washington, on September 1, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-14942 Filed 9-11-06; 8:45 am]
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