[Federal Register Volume 67, Number 112 (Tuesday, June 11, 2002)]
[Proposed Rules]
[Pages 39900-39904]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-14585]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-378-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and A300 B4-600, B4-600R, and 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

[[Page 39901]]

directive (AD), applicable to all Airbus Model A300 B4-600, B4-600R, 
and F4-600R (collectively called A300-600) series airplanes, that 
currently requires repetitive inspections to detect cracking of the 
upper radius of the forward fitting of frame 47, and repair if 
necessary. This action would continue to require those actions but 
would shorten the compliance time and repetitive inspection intervals. 
This action also would expand the applicability to include additional 
airplanes. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a civil airworthiness 
authority. The actions specified by the proposed AD are intended to 
detect and correct such fatigue cracking, which could result in 
propagation of the cracking to the rear fitting and reduced structural 
integrity of fuselage frame 47.

DATES: Comments must be received by July 11, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-378-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. 2001-NM-378-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 for Windows 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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, 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 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 2001-NM-378-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 2001-NM-378-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056.

Discussion

    On August 29, 1996, the FAA issued AD 96-18-18, amendment 39-9744 
(61 FR 47808, September 11, 1996), applicable to all Airbus Model A300-
600 series airplanes, to require repetitive inspections to detect 
cracking of the upper radius of the forward fitting of frame 47, and 
repair if necessary. That action was prompted by results of full-scale 
fatigue testing, which revealed cracking in the upper radius of frame 
47. The requirements of that AD are intended to prevent such fatigue 
cracking, which could result in reduced structural integrity of frame 
47 of the fuselage.

Actions Since Issuance of Previous Rule

    Based on investigations and analyses and reports by the 
manufacturer, and in concert with the determination by the Direction 
Gnrale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, the FAA has determined that the inspection 
thresholds and intervals required by AD 96-18-18 must be shortened. 
This proposed AD follows from these findings.

Related Rulemaking

    The FAA issued a related AD that applies to Model A300 B2 and B4 
series airplanes. AD 96-13-11, amendment 39-9679 (61 FR 35122, July 5, 
1996), mandates the incorporation of Airbus Industrie A300 Supplemental 
Structural Inspection Document (SSID). That SSID includes a requirement 
to inspect in accordance with Airbus Service Bulletin A300-53-0246, 
which would be required by paragraph (d) of this proposed AD.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A300-53-6029, Revision 05, dated 
April 11, 2001 (for Model A300-600 series airplanes). AD 96-18-18 cited 
Revision 02 of this service bulletin as the appropriate source of 
service information for accomplishment of the required repetitive eddy 
current inspections to detect cracking of the upper radius of the 
forward fitting of frame 47. Subsequent service bulletin revisions 
provide improved inspection methods. Flight cycles were incorporated 
into the compliance times and the corresponding values were adjusted in 
flight hours.
    Airbus has also issued Service Bulletin A300-53-0246, Revision 03, 
dated April 11, 2001, which describes the same procedures as those in 
Service Bulletin A300-53-6029 for inspecting the same area on Model 
A300 B2 and B4 series airplanes.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive 2001-355(B), dated August 8, 2001, 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

[[Page 39902]]

applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has 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 Proposed Requirements

    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 96-18-18 to 
continue to require repetitive eddy current inspections to detect 
cracking of the upper radius of the forward fitting of frame 47, and 
repair if necessary. The actions would be required to be accomplished 
in accordance with the service bulletins described previously, except 
as discussed below. The proposed AD also would require that operators 
report results of inspection findings to Airbus. These inspection 
reports will enable the DGAC, the FAA, and the manufacturer to develop 
a better understanding of the nature and extent of the problem. This 
understanding will aid in developing a more permanent resolution to the 
cracking problem. The results of these reports may warrant further 
rulemaking.

Differences Between Proposed AD and Service Bulletins

    Although the service bulletins specify that the manufacturer may be 
contacted for disposition of certain repair conditions, this proposal 
would require the repair of those conditions to be accomplished per 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, the FAA has determined that, for this 
proposed AD, a repair approved by either the FAA or the DGAC would be 
acceptable for compliance with this proposed AD.
    Unlike the procedures described in the service bulletins, this 
proposed AD would prohibit further flight if cracks are detected in the 
upper radius of the forward fitting of frame 47. However, the FAA may 
consider allowing continued flight with cracks on a case-by-case basis. 
Paragraph (f)(1) of this proposed AD would allow operators to request 
an alternative method of compliance that would allow continued flight 
with cracks, provided data are presented to justify the use of such an 
alternative method. The manufacturer has advised that it may propose an 
alternative method of compliance with the requirements of this AD to 
include a repetitive inspection interval that is based on crack size. 
Once this method is developed, approved, and available, the FAA may 
consider additional rulemaking.
    In addition, the FAA finds that the thresholds specified in the 
service bulletin for Model A300-600 series airplanes (11,500 total 
flight cycles/29,600 total flight hours) are inadequate to ensure the 
safety of affected airplanes. Cracking has recently been found on an 
airplane at a lower threshold, so the FAA has determined that those 
thresholds must be reduced to 10,000 total flight cycles/26,000 total 
flight hours.

Explanation of Proposed Change to Paragraph (c)

    Due to organizational restructuring within the Transport Airplane 
Directorate since AD 96-18-18 was issued, this proposed AD specifies 
that operators direct their requests for repair method approvals to the 
Manager of the FAA's International Branch, ANM-116 (not the 
Standardization Branch).

Clarification of Model Designation

    The applicability of AD 96-18-18 and this proposed AD includes 
Model A300-600 series airplanes. However, the model designation of 
these airplanes has been revised in this proposed AD to conform to the 
type certificate data sheet listing.

Explanation of Change in Terminology

    AD 96-18-18 specifies the compliance times in terms of 
``landings.'' This proposed AD refers instead to ``flight cycles'' to 
more closely correspond to the terminology of the French airworthiness 
directive and the revised service bulletins described previously.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing repair procedures that will 
address the unsafe condition identified in this AD and terminate the 
repetitive inspections. Once these procedures are developed, approved, 
and available, the FAA may consider additional rulemaking.

Cost Impact

    There are approximately 127 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The inspection that is currently required by AD 96-18-18, and 
retained in this proposed AD, takes approximately 4 work hours per 
airplane, per inspection cycle, to accomplish, at an average labor rate 
of $60 per work hour. Based on these figures, the cost impact of the 
currently required actions is estimated to be $240 per airplane, per 
inspection cycle.
    The new proposed actions would take approximately 5 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the proposed requirements of 
this AD on U.S. operators is estimated to be $38,100, or $300 per 
airplane, per inspection cycle.
    The cost impact figures discussed above are 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, 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.

[[Page 39903]]

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 39-9744 (61 FR 
47808, September 11, 1996), and by adding a new airworthiness directive 
(AD), to read as follows:

AIRBUS: Docket 2001-NM-378-AD. Supersedes AD 96-18-18, Amendment 39-
9744.

    Applicability: All Model A300 B2 and B4 series airplanes; and 
all Model A300 B4-600, B4-600R, and F4-600R (collectively called 
A300-600) series airplanes; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking of the upper radius of 
the forward fitting of fuselage frame 47, which could result in 
propagation of the cracking to the rear fitting and reduced 
structural integrity of frame 47, accomplish the following:

Model A300-600: Inspection

    (a) For Model A300-600 series airplanes: At the earlier of the 
times specified by paragraphs (a)(1) and (a)(2) of this AD, perform 
an eddy current inspection to detect cracking of the upper radius of 
the left and right forward fitting of frame 47, in accordance with 
Airbus Service Bulletin A300-53-6029, Revision 2, dated November 7, 
1994; or Revision 05, dated April 11, 2001. After the effective date 
of this AD, only Revision 05 of the service bulletin may be used.

    Note 2: Accomplishment of an inspection before the effective 
date of this AD in accordance with Airbus Service Bulletin A300-53-
6029, Revision 03, dated October 7, 1997, or Revision 04, dated 
October 25, 1999, is acceptable for compliance with the initial 
inspection requirements of paragraph (a) of this AD.

    (1) Before the accumulation of 17,300 total flight cycles, or 
within one year after October 16, 1996 (the effective date of AD 96-
18-18, amendment 39-9744), whichever occurs later.
    (2) At the later of the times specified by paragraphs (a)(2)(i) 
and (a)(2)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight cycles or 
26,000 total flight hours, whichever occurs first.
    (ii) Within 60 days after the effective date of this AD.

A300-600: Follow-on Inspections

    (b) For Model A300-600 series airplanes on which no cracking is 
found during any inspection required by paragraph (a) of this AD:
    (1) If the initial inspection WAS accomplished before the 
effective date of this AD, repeat the inspection within 6,600 flight 
cycles after that inspection or within 60 days after the effective 
date of this AD, whichever occurs first. Thereafter, repeat the 
inspection at least every 6,100 flight cycles or 15,600 flight 
hours, whichever occurs first.
    (2) If the initial inspection was NOT accomplished before the 
effective date of this AD, repeat the inspection thereafter at least 
every 6,100 flight cycles or 15,600 flight hours, whichever occurs 
first.

Model A300-600: Corrective Action

    (c) For Model A300-600 series airplanes on which any cracking is 
found during any inspection required by this AD: Before further 
flight, repair and/or reinspect the airplane in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate or the Direction Gnrale de 
l'Aviation Civile (DGAC) (or its delegated representative).

    Note 3: Repair and/or reinspection accomplished before the 
effective date of this AD in accordance with a method approved by 
the Manager of the Standardization Branch is acceptable for 
compliance with the requirements of paragraph (c) of this AD.

Model A300 B2 and B4: Inspection and Follow-On Actions

    (d) For Model A300 B2 and B4 series airplanes: At the applicable 
time specified in paragraph (d)(1), (d)(2), or (d)(3) of this AD, 
perform repetitive eddy current inspections to detect cracking of 
the upper radius of the forward fitting of frame 47, left and right 
sides, per Airbus Service Bulletin A300-53-0246, Revision 03, dated 
April 11, 2001. If any cracking is found: Before further flight, 
repair and/or reinspect the airplane in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the DGAC 
(or its delegated agent). This requirement terminates the 
corresponding inspection requirement of the A300 Supplemental 
Structural Inspection Document (SSID) for Model A300 B2 and B4 
series airplanes. That SSID is mandated by AD 96-13-11, amendment 
39-9679.
    (1) For Model A300 B2 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(d)(1)(i) and (d)(1)(ii) of this AD. Repeat the inspection 
thereafter at least every 10,400 flight cycles or 13,300 flight 
hours, whichever occurs first.
    (i) Before the accumulation of 16,500 total flight cycles or 
21,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 1,300 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For Model A300 B4-100 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(d)(2)(i) and (d)(2)(ii) of this AD. Repeat the inspection 
thereafter at least every 8,500 flight cycles or 16,400 flight 
hours, whichever occurs first.
    (i) Before the accumulation of 10,300 total flight cycles or 
19,800 total flight hours, whichever occurs first.
    (ii) Within 750 flight cycles or 1,500 flight hours after the 
effective date of this AD, whichever occurs first.
    (3) For Model A300 B4-200 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(d)(3)(i) and (d)(3)(ii) of this AD. Repeat the inspection 
thereafter at least every 7,000 flight cycles or 13,600 flight 
hours, whichever occurs first.
    (i) Before the accumulation of 11,000 total flight cycles or 
21,200 total flight hours, whichever occurs first.
    (ii) Within 750 flight cycles or 1,500 flight hours after the 
effective date of this AD, whichever occurs first.

Reporting Requirement

    (e) At the applicable time specified in paragraph (e)(1) or 
(e)(2) of this AD: Submit a report of all results of each inspection 
required by paragraphs (a) and (d) of this AD to Airbus Industrie, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, Attention 
Jacques Leborgne, fax 33-5-61-93-36-14. The report must include the 
inspection results, a description of any discrepancies found, the 
airplane serial number, and the number of landings and flight hours 
on the airplane. Information collection requirements contained in 
this AD have been approved by the Office of Management and Budget 
(OMB) under the provisions of the Paperwork Reduction Act of 1980 
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 
2120-0056.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 10 days 
after performing the inspection required by paragraph (a) of this 
AD.
    (2) For airplanes on which the inspection has been accomplished 
before the effective date of this AD: Submit the report within 10 
days after the effective date of this AD.

Alternative Methods of Compliance

    (f)(1) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then

[[Page 39904]]

send it to the Manager, International Branch, ANM-116.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 96-18-18, amendment 39-9744, and AD 96-13-11, 
amendment 39-9679, are approved as alternative methods of compliance 
with the requirements of paragraphs (c) and (d) of this AD.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 2001-355(B), dated August 8, 2001.


    Issued in Renton, Washington, on June 4, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-14585 Filed 6-10-02; 8:45 am]
BILLING CODE 4910-13-P