[Federal Register Volume 66, Number 167 (Tuesday, August 28, 2001)]
[Proposed Rules]
[Pages 45192-45194]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21632]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-247-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Airbus Model A300 B2 and B4 
series airplanes. This proposal would require identifying the types and 
areas of repairs on the airplane between frame 10 and frame 80, and 
follow-on actions for certain repairs. This action is necessary to 
detect and correct fatigue cracking of certain repairs of the fuselage 
between frame 10 and frame 80, 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 September 27, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-247-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. 2000-NM-247-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 Number 2000-NM-247-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 2000-NM-247-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056.

Discussion

    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 all Airbus Model A300 B2 and B4 series 
airplanes. The DGAC advises that certain repairs and areas of repairs 
of the skin between frame 10 and frame 80 require inspection. These 
repairs, which had been done in accordance with a version of Structural 
Repair Manual (SRM) 53-10-10 earlier than Revision 55, may not meet the 
specifications of Revisions 55 and subsequent of that SRM. An 
inspection program has been developed in order to meet the structural 
fatigue and damage tolerance requirements of Amendment 45 of part 25 of 
the Federal Aviation Regulations.
    Fatigue cracking of certain repairs of the fuselage between frame 
10 and frame 80, if not detected and corrected, could result in reduced 
structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A300-53-0313, Revision 01, dated 
April 27, 1999. The service bulletin describes procedures for 
identifying the types and areas of repairs on the airplane between 
frame 10 and frame 80, and follow-on actions for certain repairs. The 
follow-on actions include repetitive inspections of specified areas to 
detect cracking, or replacement of the repair, if necessary. Such 
replacement would eliminate the need for the repetitive inspections. 
These actions are intended to adequately address the unsafe condition. 
The DGAC classified this service bulletin as mandatory and issued 
French airworthiness directive 2000-261-312(B), dated June 28, 2000, 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

[[Page 45193]]

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 Rule

    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 require accomplishment of 
the actions specified in the service bulletin described previously, 
except as discussed below.

Differences Between the Proposed AD and the Service Bulletin

    Operators should note that, unlike the procedures described in 
Airbus Service Bulletin A300-53-0313, this proposed AD would not permit 
further flight if cracks are detected in specific areas identified in 
the service bulletin. The FAA has determined that, because of the 
safety implications and consequences associated with such cracking, any 
area specified in the service bulletin that is found to be cracked must 
be repaired prior to further flight.
    Operators also should note that, although the service bulletin 
specifies that the manufacturer may be contacted for disposition of 
certain repair conditions, this proposal 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, 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.

Explanation of Compliance Times

    On April 19, 2000, the FAA issued amendments 91-264, 121-275, 125-
33, and 129-28, which add new sections 91.410, 121.370, 125.248, and 
129.32 (``Repair Assessment for Pressurized Fuselages'') to 14 CFR part 
25 of the Federal Aviation Regulations. The final rule, which was 
published in the Federal Register on April 25, 2000 (65 FR 24108), 
requires operators of certain transport category airplanes to 
incorporate repair assessment guidelines for the fuselage pressure 
boundary into their FAA-approved maintenance or inspection program.
    The final rule specifies that certain airplanes cannot be operated 
beyond a certain flight-cycle implementation time unless operator 
specifications are issued to reference repair assessment guidelines for 
the fuselage pressure boundary (fuselage skin, door skin, and bulkhead 
webs) and those guidelines are incorporated into the operator's 
maintenance program. The final rule also specifies that these repair 
assessment guidelines must be approved by the FAA's Aircraft 
Certification Office or the office of the Transport Airplane 
Directorate having cognizance over the type certificate for the 
affected airplane.
    For Airbus Model A300 B2 and B4 series airplanes, the 
implementation times specified in the final rule are as follows:

------------------------------------------------------------------------
              Airplane model                    Implementation times
------------------------------------------------------------------------
A300 B2...................................  36,000 total flight cycles.
A300 B4-100 and B4-2C.....................  30,000 total flight cycles
                                             (above the window line);
                                            36,000 total flight cycles
                                             (below the window line).
A300 B2-200...............................  25,500 total flight cycles
                                             (above the window line);
                                            36,000 total flight cycles
                                             (below the window line).
------------------------------------------------------------------------

    The service bulletin described previously recommends that certain 
repairs must be inspected for fatigue damage before the implementation 
times specified in the regulation described above. The initial 
implementation time recommended in the service bulletin and specified 
in French airworthiness directive 2000-261-312(B) is before 
accumulating 10,000 total flights or within 2,500 flights, whichever 
occurs later. An interval of 2,500 flights is specified for repetitive 
inspections of specified areas and corrective actions. The service 
bulletin was issued in response to a finding of a specific repair for 
which fatigue and damage tolerance is a concern. This specific repair 
involves a skin doubler with an average rivet spacing greater than or 
equal to 30 mm in the outer rivet row. The repair is located in the 
upper part of the fuselage in the pressurized shell.
    Since the compliance time described above, as specified in the 
French airworthiness directive, for identification of this particular 
repair is earlier than the implementation times specified in the repair 
assessment guidelines, the FAA finds that issuance of this proposed AD 
is necessary to require the specified actions at the earlier time.

Cost Impact

    The FAA estimates that 13 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$1,560, or $120 per airplane.
    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 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 45194]]

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 adding the following new 
airworthiness directive:

Airbus Industrie: Docket 2000-NM-247-AD.

    Applicability: All Model B2 and B4 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 (d) 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 certain repairs of the 
fuselage between frame 10 and frame 80, which could result in 
reduced structural integrity of the airplane, accomplish the 
following:

Identification of Repairs

    (a) Before 10,000 total landings, or before 2,500 landings after 
the effective date of this AD, whichever occurs later: Identify the 
types and areas of repairs on the airplane between frame 10 and 
frame 80, as specified in Airbus Service Bulletin A300-53-0313, 
Revision 01, dated April 27, 1999. Do the actions per the 
Accomplishment Instructions of the service bulletin. If none of the 
repairs specified in the service bulletin are found, no additional 
action is needed under this AD.

Follow-On Actions

    (b) If, during the inspection, any repair is found that meets 
the criteria specified in Airbus Service Bulletin A300-53-0313, 
Revision 01, dated April 27, 1999: Do either an eddy current or 
ultrasonic inspection, depending on the type of repair found, to 
detect cracking of the applicable area identified in Flow Chart 1, 
Figure 1, Sheet 1, of the service bulletin. Do the inspection at the 
time and in the manner specified in the service bulletin. Based on 
the results of the inspection, take the actions shown in the 
following table:

                       Table 1.--Follow-On Actions
------------------------------------------------------------------------
 If the following is found:          Then--          Per this schedule:
------------------------------------------------------------------------
(1) No cracking.............  Repeat the            At least every 2,500
                               inspection.           landings.
(2) Any cracking............  Replace the repair    Before further
                               per a method          flight.
                               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).
------------------------------------------------------------------------

Terminating Action

    (c) Replacement of a repair that is specified in Airbus Service 
Bulletin A300-53-0313, Revision 01, dated April 27, 1999, per a 
method approved by either the Manager, International Branch, ANM-
116, or the DGAC (or its delegated agent), terminates the 
requirements of this AD.

Alternative Methods of Compliance

    (d) 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 send 
it to the Manager, International Branch, ANM-116.

    Note 2: 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

    (e) 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 3: The subject of this AD is addressed in French 
airworthiness directive 2000-261-312(B), dated June 28, 2000.


    Issued in Renton, Washington, on August 21, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21632 Filed 8-27-01; 8:45 am]
BILLING CODE 4910-13-U