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

[Federal Register Volume 69, Number 197 (Wednesday, October 13, 2004)]
[Rules and Regulations]
[Pages 60809-60811]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22564]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-211-AD; Amendment 39-13819; AD 2004-20-14]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Airbus Model A300 B4 series airplanes and all 
Airbus Model A300-600 series airplanes. That AD currently requires a 
one-time high frequency eddy current inspection to detect cracking of 
the splice fitting at fuselage frame (FR) 47 between stringers 24 and 
25; and corrective actions if necessary. This amendment requires new 
repetitive inspections of an expanded area and adds airplanes to the 
applicability in the existing AD. The actions specified by this AD are 
intended to detect and correct cracking of the splice fitting at 
fuselage FR 47, which could result in reduced structural integrity of 
the airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective November 17, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 17, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
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.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2001-03-14, 
amendment 39-12118 (66 FR 10957, February 21, 2001), was published as a 
supplemental notice of proposed rulemaking (NPRM) in the Federal 
Register on August 4, 2004 (69 FR 47035). The proposal is applicable to 
all Airbus Model A300 series airplanes and all Airbus Model A300-600 
series airplanes. The action proposed to require new repetitive high 
frequency eddy current inspections to detect cracking of an expanded 
area, and corrective actions, if necessary; and to add airplanes to the 
applicability in the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Clarification of Service Information Requirements for Paragraph (b) of 
This AD

    In our response to comments in the Preamble of the supplemental 
NPRM, we stated our intent to revise paragraphs (a), (b), and (c) of 
the supplemental NPRM to refer to Revision 02 of the referenced Airbus 
service bulletins as the appropriate sources of service information for 
accomplishment of the required actions. (Revision 01 of those service 
bulletins was referenced in the original NPRM for accomplishment of the 
required actions.) However, while we revised paragraphs (a) and (c) of 
the supplemental NPRM, we inadvertently omitted the revision to 
paragraph (b). Therefore, we have revised paragraph (b) of this final 
rule to reference Revision 02 of Airbus Service Bulletin A300-53-6123 
as the appropriate source of service information for the required 
actions in that paragraph.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the change

[[Page 60810]]

described previously. The FAA has determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Cost Impact

    There are approximately 92 airplanes of U.S. registry that will be 
affected by this AD.
    The inspection of an expanded area that is required in this AD will 
take approximately 29 work hours per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the required inspection on U.S. operators is estimated 
to be $173,420, or $1,885 per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-12118 (66 FR 
10957, February 21, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-13819, to read as follows:

2004-20-14 Airbus: Amendment 39-13819. Docket 2002-NM-211-AD. 
Supersedes AD 2001-03-14, Amendment 39-12118.

    Applicability: All Model A300 B4-600, B4-600R, and F4-600R 
(collectively called A300-600) series airplanes; and all Model A300 
B4 series airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking of the splice fitting at fuselage 
frame (FR) 47, which could result in reduced structural integrity of 
the airplane, accomplish the following:

Repetitive Inspections

    (a) For airplanes defined in Airbus Service Bulletin A300-53-
0350, Revision 02, dated November 12, 2002: Do a high frequency eddy 
current (HFEC) inspection to detect cracking of the splice fitting 
at fuselage FR 47 between stringers 24 and 26 (left- and right-hand 
sides), at the applicable times specified in paragraph (a)(1) or 
(a)(2) of this AD. Repeat the inspection thereafter at the earlier 
of the flight-cycle/flight-hour intervals specified in the 
applicable column in Table 2 of Figure 1 and Sheet 1 of the 
Accomplishment Instructions of the service bulletin. Do the 
inspections in accordance with the service bulletin, excluding 
Appendix 01.
    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of the effective date of this AD: Do the initial 
inspection at the later of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD:
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after the effective date of this AD, as specified in the applicable 
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment 
Instructions of the service bulletin.
    (ii) Within 750 flight cycles or 1,500 flight hours after the 
effective date of this AD, whichever is first.
    (2) For airplanes that have accumulated fewer than 20,000 total 
flight cycles as of the effective date of this AD: Do the initial 
inspection at the later of the times specified in paragraphs 
(a)(2)(i) and (a)(2)(ii) of this AD.
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after the effective date of this AD, as specified in the applicable 
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment 
Instructions of the service bulletin.
    (ii) Within 1,800 flight cycles or 3,000 flight hours after the 
effective date of this AD, whichever is first.
    (b) For airplanes defined in Airbus Service Bulletin A300-53-
6123, Revision 02, dated November 12, 2002: Do the HFEC inspection 
required by paragraph (a) of this AD at the applicable times 
specified in paragraph (b)(1) or (b)(2) of this AD. Repeat the 
inspection thereafter at the earlier of the flight-cycle/flight-hour 
intervals specified in the applicable column in Table 2 of Figure 1 
and Sheet 1 of the Accomplishment Instructions of the service 
bulletin. Do the inspections in accordance with the service 
bulletin, excluding Appendix 01.
    (1) For airplanes that have accumulated 10,000 or more total 
flight cycles as of the effective date of this AD: Do the initial 
inspection within 750 flight cycles or 1,900 flight hours after the 
effective date of this AD, whichever is first.
    (2) For airplanes that have accumulated fewer than 10,000 total 
flight cycles as of the effective date of this AD: Do the initial 
inspection at the later of the times specified in paragraphs 
(b)(2)(i) and (b)(2)(ii) of this AD.
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after the effective date of this AD, as specified in the applicable 
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment 
Instructions of the service bulletin.
    (ii) Within 1,500 flight cycles or 3,800 flight hours after the 
effective date of this AD, whichever is first.

Repair

    (c) Repair any cracking found during any inspection required by 
this AD before further flight, in accordance with Airbus Service 
Bulletin A300-53-0350 or A300-53-6123, both Revision 02, both 
excluding Appendix 01, both dated November 12, 2002; as applicable. 
Where the service bulletins specify to contact Airbus in case of 
certain crack findings, this AD requires that a repair be 
accomplished before further flight in accordance with a method 
approved by either the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).

Credit for Previous Issues of Airbus Service Bulletin

    (d) Accomplishment of the actions before the effective date of 
this AD in accordance with Airbus Service Bulletin A300-53-0350 or 
A300-53-6123, Revision 01, dated December 18, 2001; is considered 
acceptable for compliance with the corresponding actions specified 
in this AD.

Alternative Methods of Compliance

    (e) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

[[Page 60811]]

Incorporation by Reference

    (f) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Airbus Service Bulletin A300-53-0350, 
Revision 02, excluding Appendix 01, dated November 12, 2002; and 
Airbus Service Bulletin A300-53-6123, Revision 02, excluding 
Appendix 01, dated November 12, 2002; as applicable. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from 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.

    Note 1: The subject of this AD is addressed in French 
airworthiness directive 2002-184(B), dated April 3, 2002.

Effective Date

    (g) This amendment becomes effective on November 17, 2004.

    Issued in Renton, Washington, on September 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-22564 Filed 10-12-04; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:01:35.324506+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

b2e54fdc4f2984e05d2d3031623d14f5b78f7b5003d7a559721424c740171011

Text SHA-256

988b3391c8bb103f6cfa251c1f8bece5678021cf4e0b0a38b748f93661451d90