[Federal Register Volume 66, Number 6 (Tuesday, January 9, 2001)]
[Proposed Rules]
[Pages 1610-1612]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-510]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-223-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-620, A310-203, 
A310-221, and A310-222 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A300 B4-620, 
A310-203, A310-221, and A310-222 series airplanes. This proposal would 
require repetitive inspections of fuselage frame 07 in the upper frame 
section assemblies of the lateral cockpit windows, and corrective 
action, if necessary. Accomplishment of certain corrective actions 
would extend the repetitive inspection interval. This action is 
necessary to detect and correct fatigue cracking in that area, 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 February 8, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-223-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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: 
<a href="/cdn-cgi/l/email-protection#4c75612d222161223c3e212f2321212922380c2a2d2d622b233a"><span class="__cf_email__" data-cfemail="c6ffeba7a8abeba8b6b4aba5a9ababa3a8b286a0a7a7e8a1a9b0">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-223-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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2125; 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:

    <bullet> 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.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> 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 No. 2000-NM-223-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. 2000-NM-223-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 certain Airbus Model A300 B4-620, A310-203, 
A310-221, and A310-222 series airplanes. The DGAC has advised that, 
during a scheduled corrosion inspection in accordance with the Model 
A300 Corrosion Prevention and Control Programme (A300 CPCP), a crack of 
100 millimeters in length was discovered forward of fuselage frame 07, 
in the upper frame section assembly of the lateral cockpit windows. 
When the crack was discovered, the airplane had accumulated 36,077 
total flight hours and 30,733 total flight cycles. During the Model 
A300 full-scale fatigue test program, similar cracking was found at 
approximately 84,000 simulated flight cycles. The test results 
indicated that the onset of cracking could occur sooner than calculated 
from the original test results, suggesting the inspection threshold for 
this area of the airplane should be reduced from the threshold 
specified by the A300 CPCP. The cracking has been attributed to the 
effect of cabin pressure on the junction points, where thickness 
variations can lead to local bending and subsequent fatigue damage. If 
not corrected, the cracking could result in reduced structural 
integrity of the airplane.

Similar Model

    The frame section is similar on all airplanes affected by this AD. 
Therefore, Model A310-203, A310-221, and A310-222 series airplanes are 
also subject to the identified unsafe condition.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-53-6120 (for Model A300-
600 series airplanes) and A310-53-2109 (for Model A310 series 
airplanes), both dated May 5, 2000. These service bulletins describe 
procedures for repetitive detailed visual inspections of the upper 
frame section assemblies of the left and right forward lateral cockpit 
windows. The service bulletins describe temporary and permanent repairs 
for cracking. The temporary repair, which is acceptable if cracking is 
found only in a certain area, involves replacing a

[[Page 1611]]

pick-up fitting and bracket with new parts, and installing a doubler. 
The permanent repair, which is recommended if any cracking is found in 
any other specified area, involves replacing the upper frame section 
assembly with a new assembly, which would reset the inspection 
threshold. The DGAC classified these service bulletins as mandatory and 
issued French airworthiness directive 2000-263-314(B), dated June 28, 
2000, in order 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 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 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 bulletins described previously, 
except as described below.

Difference Between Proposed AD and Service Bulletins

    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for certain repair or inspection 
instructions, this proposal would require the repair or inspection 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 or 
inspection 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 
or inspection approved by either the FAA or the DGAC would be 
acceptable for compliance with this proposed AD.

Cost Impact

    The FAA estimates that 27 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed inspection, 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 
$1,620, or $60 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 proposed 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.

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-223-AD.

    Applicability: Model A300 B4-620, A310-203, A310-221, and A310-
222 series airplanes; certificated in any category; as listed in 
Airbus Service Bulletin A300-53-6120 or A310-53-2109, both dated May 
5, 2000; excluding airplanes on which Airbus Modification 3632 has 
been accomplished.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (c) 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 fuselage frame 07 in 
the upper frame section assembly of the lateral cockpit windows, 
which could result in reduced structural integrity of the airplane, 
accomplish the following:

Inspection and Corrective Actions

    (a) Before the accumulation of 25,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a detailed visual inspection to 
detect cracking of fuselage frame 07 in the left and right upper 
frame section assemblies of the lateral cockpit windows, in 
accordance with Airbus Service Bulletin A300-53-6120 (for Model 
A300-600 series airplanes) or A310-53-2109 (for Model A310 series 
airplanes), both dated May 5, 2000; as applicable.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (1) If no cracking is found: Repeat the inspection thereafter at 
least every 7,000 flight cycles.
    (2) If any cracking is found and the cracking is only in ``area 
A,'' as depicted in

[[Page 1612]]

view B of Figure 4 of the service bulletin: Before further flight, 
do the actions specified by either paragraph (a)(2)(i) or (a)(2)(ii) 
of this AD.
    (i) Do a temporary repair per the applicable service bulletin. 
Within 3,000 flight cycles thereafter, do a permanent repair per the 
applicable service bulletin. Within 32,000 flight cycles thereafter, 
except as required by paragraph (b) of this AD, repeat the 
inspection specified by paragraph (a) of this AD.
    (ii) Do a permanent repair per the applicable service bulletin. 
Within 32,000 flight cycles thereafter, except as required by 
paragraph (b) of this AD, repeat the inspection specified by 
paragraph (a) of this AD.
    (3) If any cracking is in ``area B,'' or in both ``area A'' and 
``area B''; as depicted in view B of Figure 4 of the service 
bulletin: Before further flight, do a permanent repair per the 
applicable service bulletin. Within 32,000 flight cycles thereafter, 
except as required by paragraph (b) of this AD, repeat the 
inspection specified by paragraph (a) of this AD.
    (b) If the service bulletin specifies to contact Airbus for 
further instructions for a repair or inspection: Prior to further 
flight, perform a repair or inspection per a method approved by the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate. For a repair or inspection method to be approved by the 
Manager, International Branch, ANM-116, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD.

Alternative Methods of Compliance

    (c) 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 3: 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

    (d) Special flight permits may be issued in accordance with 
Secs. 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 4: The subject of this AD is addressed in French 
airworthiness directive 2000-263-314(B), dated June 28, 2000.


    Issued in Renton, Washington, on January 3, 2001.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-510 Filed 1-8-01; 8:45 am]
BILLING CODE 4910-13-U


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