[Federal Register Volume 68, Number 242 (Wednesday, December 17, 2003)]
[Proposed Rules]
[Pages 70206-70208]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31067]


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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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain 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 action would require new repetitive inspections of an 
expanded area, and would add airplanes to the applicability in the 
existing AD. The actions specified by the 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 January 16, 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 Industrie, 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
1137; 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 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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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

    On February 9, 2001, the FAA issued AD 2001-03-14, amendment 39-
12118 (66 FR 10957, February 21, 2001), applicable to certain Airbus 
Model A300 series airplanes and all Airbus Model A300-600 series 
airplanes. That AD requires a one-time high frequency eddy current 
(HFEC) inspection to detect cracking of the splice fitting at fuselage 
frame (FR) 47 between stringers 24 and 25; and corrective actions if 
necessary. That action was prompted by issuance of mandatory continuing 
airworthiness information by a foreign

[[Page 70207]]

civil airworthiness authority. The requirements of that 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.

Actions Since Issuance of Previous AD

    Since the issuance of AD 2001-03-14, the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, notified the FAA that an unsafe condition may exist on certain 
Airbus Model A300 B4 and all A300-600 series airplanes. The DGAC 
advises that cracks have been found on airplanes on which the 
modification specified in the existing AD has been done, and HFEC 
inspections of the modification performed. A laboratory investigation 
was done on a cracked splice fitting, and the analysis of crack growth 
rate shows that an inspection program is necessary for all airplanes 
affected by the existing AD. This program involves expanding the 
inspection area to fuselage frame (FR) 47 between stringers 24 and 26 
(the existing AD specified stringers 24 and 25), and adding new 
repetitive inspections. Cracking of the splice fitting at fuselage FR 
47 could result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0350 (for Model A300 
series airplanes) and A300-53-6123 (for Model A300-600 series 
airplanes), both Revision 01, both dated December 18, 2001. The 
procedures specified in Revision 01 of the service bulletins are 
similar to those specified in the original issue of the service 
bulletins referenced in the existing AD for accomplishment of the 
inspections and corrective actions. However, Revision 01 defines a new 
inspection program for pre-mod and post-mod airplanes which expands the 
inspection area to fuselage frame (FR) 47 between stringers 24 and 26, 
and adds an HFEC rotating probe inspection after bolt removals. 
Revision 01 also adds airplanes to the applicability specified in the 
original issue. Revision 01 of the service bulletins also describes 
certain repair procedures. The DGAC classified the service bulletins as 
mandatory and issued French airworthiness directive 2002-184(B), dated 
April 3, 2002, to ensure the continued airworthiness of these airplanes 
in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept us informed of the 
situation described above. We have examined the findings of the DGAC, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 2001-03-14 to 
require new repetitive inspections of an expanded area and to add 
airplanes to the applicability in the existing AD. The actions would be 
required to be accomplished in accordance with the service bulletins 
described previously, except as discussed below.

Clarification of Compliance Times

    The compliance times specified in the service bulletins for doing 
the high frequency eddy current inspections do not specify whether the 
inspections should be done at the earlier or later of the recommended 
flight cycles/flight hours. This proposed AD adds ``whichever is 
first'' to those compliance times. In addition, the compliance times 
specified do not give an effective date for when the inspections are to 
be accomplished; this proposed AD requires accomplishment of the 
inspections ``after the effective date of this AD.''

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently developing a modification that would address the unsafe 
condition identified in this proposed AD. Once this modification is 
developed, approved, and available, we may consider additional 
rulemaking.

Differences Between Proposed AD and Service Information

    Although the service bulletins specify that the manufacturer may be 
contacted for disposition of certain repair conditions, this proposed 
AD would require the repair of those conditions to be accomplished in 
accordance with a method approved by either the FAA or the DGAC (or its 
delegated agent). In light of the type of repair that would be required 
to address the identified unsafe condition, and in consonance with 
existing bilateral airworthiness agreements, we have determined that, 
for the proposed AD, a repair approved by either us or the DGAC would 
be acceptable for compliance with this proposed AD.
    Service Bulletin A300-53-0350 specifies doing the initial 
inspection at the next C-check, but not exceeding a certain number of 
flight cycles or flight hours, as the recommended compliance time. 
Because ``C-check'' schedules vary among operators, such a nonspecific 
interval would provide no assurance that operators would do the 
inspection within the prescribed schedule. This proposed AD would 
exclude the C-check and specify only flight cycles or flight hours. We 
find that such a compliance time is appropriate for affected airplanes 
to continue to operate without compromising safety.
    The service bulletins referenced in this proposed AD specify to 
submit certain inspection findings to the manufacturer; however, this 
AD does not include such a requirement.

Cost Impact

    There are approximately 83 airplanes of U.S. registry that would be 
affected by this proposed AD.
    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 $156,455, 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 current or 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 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,

[[Page 70208]]

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 01, dated December 18, 2001: 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 per 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 per 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, per Airbus Service Bulletin A300-53-
0350 or A300-53-6123, both Revision 01, both excluding Appendix 01, 
both dated December 18, 2001; 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[egrave]n[egrave]rale de l'Aviation 
Civile (DGAC) (or its delegated agent).

Alternative Methods of Compliance

    (d) 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 December 5, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31067 Filed 12-16-03; 8:45 am]
BILLING CODE 4910-13-P