[Federal Register Volume 69, Number 149 (Wednesday, August 4, 2004)]
[Proposed Rules]
[Pages 47035-47037]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17762]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-211-AD]
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: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to all Airbus Model A300 B4 series airplanes 
and all Airbus Model A300-600 series airplanes, that would have 
superseded an existing AD that currently requires a one-time high 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. The original NPRM proposed to require 
new repetitive inspections of an expanded area, and would have added 
airplanes to the applicability in the existing AD. This new action 
revises the original NPRM by adding airplanes to the applicability. The 
actions specified by this new proposed 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: Comments must be received by August 30, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-211-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-211-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall

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identify the Rules Docket number and be submitted in triplicate to the 
address specified above. All communications received on or before the 
closing date for comments, specified above, will be considered before 
taking action on the proposed rule. The proposals contained in this 
action may be changed in light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-211-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2002-NM-211-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to all 
Airbus Model A300 B4 series airplanes and all Airbus Model A300-600 
series airplanes, was published as a notice of proposed rulemaking 
(NPRM) in the Federal Register on December 17, 2003 (68 FR 70206). That 
NPRM proposed to supersede AD 2001-03-14, amendment 39-12118 (66 FR 
10957, February 21, 2001), which is applicable to certain Airbus Model 
A300 series airplanes and all Airbus Model A300-600 series airplanes. 
That NPRM would have added new repetitive inspections of an expanded 
area of the splice fitting at fuselage frame (FR) 47, and would have 
added airplanes to the applicability of the existing AD. That NPRM was 
prompted by cracks found on airplanes on which the modification 
required by the existing AD had been done. That condition, if not 
corrected, could result in reduced structural integrity of the 
airplane.

Comments

    Due consideration has been given to the comments received in 
response to the original NPRM. One commenter has no technical 
objection.

Request To Reference Latest Revisions of Service Information

    One commenter asks that Airbus Service Bulletin A300-53-6123, 
Revision 02, dated November 12, 2002, be added to the original NPRM. 
(Revision 01 of that service bulletin was referenced in the original 
NPRM for accomplishment of certain actions.) The commenter states that 
Revision 02 adds improvements after the service bulletin kits specified 
in Revision 01 were validated on an airplane, and notes that adding 
Revision 02 will eliminate requests for approval of alternative methods 
of compliance. The commenter also notes that Revision 02 adds nine 
airplanes to the effectivity of the service bulletin.
    Another commenter asks that Airbus Service Bulletin A300-53-0350, 
Revision 02, dated November 12, 2002, be added to the original NPRM. 
(Revision 01 of that service bulletin was referenced in the original 
NPRM for accomplishment of certain actions.)
    The FAA agrees with the commenters' requests. The procedures in 
Revision 02 of both service bulletins are essentially the same as those 
in Revision 01 of the referenced service bulletins. However, Revision 
02 of the service bulletins adds nine U.S. airplanes to the effectivity 
of the service bulletins. Accordingly, the Cost Impact section of this 
supplemental NPRM has been changed to include the additional airplanes. 
We also have revised paragraphs (a), (b), and (c) of this supplemental 
NPRM to refer to Revision 02 of the Airbus service bulletins as the 
appropriate sources of service information for accomplishment of the 
required actions. We have added a new paragraph (d) (and reidentified 
subsequent paragraphs accordingly) to state that inspections and 
repairs accomplished before the effective date of this AD per Revision 
01 of the service bulletins are acceptable for compliance with the 
requirements of this supplemental NPRM.

Request To Remove Interim Action

    One commenter, the manufacturer, states that the repetitive 
inspections should not be considered as an interim action. The 
commenter adds that, ``Due to the fact that, in this specific location, 
the splice is considered as a ``fuse part'' (to be replaced when found 
cracked, the residual strength analysis has shown that the structure is 
able to sustain ultimate loads with the complete failure of splices--
both sides--and able to sustain limit loads with the complete failure 
of frame and splices) * * *'' The commenter states that the Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, agrees that the repetitive inspections required 
by French airworthiness directive 2002-184(B), dated April 3, 2002 
(referenced in the original NPRM), are the final fix.
    We agree. In light of the data provided by the commenter, and 
consistent with the findings of the DGAC, we will not retain the 
Interim Action section in this supplemental NPRM. In making this 
determination, we consider that long-term continued operational safety 
in this case will be adequately ensured by repetitive inspections to 
detect cracking before it represents a hazard to the airplane, and by 
repair within the specified time limits. Accordingly, the Interim 
Action section has been removed from this supplemental NPRM.

Conclusion

    Since the addition of airplanes to the applicability of this 
supplemental NPRM expands the scope of the originally proposed rule, we 
have determined that it is necessary to reopen the comment period to 
provide additional opportunity for public comment.

Cost Impact

    This supplemental NPRM would affect about 92 airplanes of U.S. 
registry.
    The inspection of an expanded area that is proposed in this AD 
action would 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 proposed 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 proposed 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

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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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation: (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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    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), to read as follows:

Airbus: 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 01, dated December 18, 2001: 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 Generale 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.

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


    Issued in Renton, Washington, on July 27, 2004.
Kyle L. Olsen,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-17762 Filed 8-3-04; 8:45 am]
BILLING CODE 4910-13-P