[Federal Register Volume 69, Number 217 (Wednesday, November 10, 2004)]
[Proposed Rules]
[Pages 65097-65099]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-25030]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19566; Directorate Identifier 2004-NM-72-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series 
Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called 
A300-600)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus airplanes as listed above. This proposed AD would 
require repetitively inspecting for cracking in the web of nose rib 7 
of the inner flap on the wings, and related investigative/corrective 
actions if necessary. This proposed AD is prompted by reports of 
cracking in the web of nose rib 7 of the inner flap. We are proposing 
this AD to detect and correct cracking in the web of nose rib 7, which 
could result in rupture of the attachment fitting between the inner 
flap and flap track no. 2, and consequent reduced structural integrity 
of the flap.

DATES: We must receive comments on this proposed AD by December 10, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> By fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:
    Technical information: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.
    Plain language information: Marcia Walters, <a href="/cdn-cgi/l/email-protection#5835392a3b3139762f39342c3d2a2b183e3939763f372e"><span class="__cf_email__" data-cfemail="523f3320313b337c25333e26372021123433337c353d24">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-19566; 
Directorate Identifier 2004-NM-72-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is on the plaza level of the Nassif Building at the DOT street 
address stated in the ADDRESSES section. Comments will be available in 
the AD docket shortly after the DMS receives them.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the

[[Page 65098]]

airworthiness authority for France, notified us that an unsafe 
condition may exist on all Airbus Model A300 B2 and A300 B4 series 
airplanes; and Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively called 
A300-600). The DGAC advises that two operators have found cracking in 
the web of nose rib 7 at flap track no. 2 of the inner flap. Cracking 
in this area, if not corrected, could result in rupture of the 
attachment fitting between the inner flap and flap track no. 2, and 
consequent reduced structural integrity of the flap.

Relevant Service Information

    Airbus has issued Service Bulletins A300-57-0240 (for Model A300 B2 
and B4 series airplanes) and A300-57-6095 (for Model A300 B4-600, B4-
600R, and F4-600R series airplanes, and Model C4-605R Variant F 
airplanes (collectively called A300-600)), both including Appendix 01, 
and both dated April 7, 2003. These service bulletins describe 
procedures for performing an inspection using a borescope or endoscope 
to detect cracking of the vertical stiffeners of nose rib 7 of the 
inner flap of the left- and right-hand wings, and related 
investigative/corrective actions if necessary. The related 
investigative/corrective actions apply if any cracking is found and 
involve performing high-frequency eddy current inspections for cracking 
of the fastener holes of nose rib 7, performing a detailed visual 
inspection for cracking in the upper radii of the upper and lower skin 
flanges of the ribs and front spar of the wing, and replacing nose rib 
7 with a new, improved nose rib. If any cracking is found during the 
related investigative actions, the service bulletin specifies to 
contact Airbus. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition. The 
DGAC mandated the service information and issued French airworthiness 
directive 2003-410(B), dated October 29, 2003, to ensure the continued 
airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    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. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require you to do 
the actions specified in the service information described previously, 
except as discussed under ``Differences Among the Proposed AD, Service 
Information, and French Airworthiness Directive.''

Differences Among the Proposed AD, Service Information, and French 
Airworthiness Directive

    The service information specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair those conditions using a 
method that we or the DGAC (or its delegated agent) approve. In light 
of the type of repair that would be required to address the unsafe 
condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this proposed AD, a repair we 
or the DGAC approve would be acceptable for compliance with this 
proposed AD.
    Unlike the procedures described in the service information, this 
proposed AD would not permit further flight if any crack is detected in 
nose rib 7 of the inner flap. We have determined that, because of the 
safety implications and consequences associated with that cracking, all 
applicable related investigative/corrective actions must be done before 
further flight after the crack finding.
    The service information and the French airworthiness directive 
specify reporting inspection findings to Airbus. This proposed AD would 
not require that action.

Costs of Compliance

    This proposed AD would affect about 143 airplanes of U.S. registry. 
The proposed actions would take about 2 work hours per airplane, at an 
average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $18,590, or 
$130 per airplane, per inspection cycle.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

    Airbus: Docket No. FAA-2004-19566; Directorate Identifier 2004-
NM-72-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by December 10, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 B2 and A300 B4 
series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively 
called A300-600); certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports of cracking in the web of 
nose rib 7 of the inner flap. We are issuing this AD to detect and 
correct cracking in the web of nose rib 7, which could result in 
rupture of the attachment fitting between the inner flap and flap 
track no. 2, and consequent reduced structural integrity of the 
flap.

[[Page 65099]]

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the service bulletin in paragraph 
(f)(1) or (f)(2) of this AD, as applicable. These service bulletins 
specify to submit certain information to the manufacturer, but this 
AD does not include that requirement.
    (1) For Model A300 B2 and B4 series airplanes: Airbus Service 
Bulletin A300-57-0240, including Appendix 01, dated April 7, 2003.
    (2) For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively 
called A300-600): Airbus Service Bulletin A300-57-6095, including 
Appendix 01, dated April 7, 2003.

Inspections

    (g) Do an inspection, using a borescope or endoscope, for 
cracking of the vertical stiffeners of nose rib 7 of the inner flap 
of the left- and right-hand wings in accordance with the 
Accomplishment Instructions of the service bulletin. Do the initial 
inspection at the applicable compliance time specified in paragraph 
(g)(1) or (g)(2) of this AD.
    (1) For airplanes with 18,599 or fewer total flight cycles as of 
the effective date of this AD: Prior to the accumulation of 5,000 
total flight cycles, or within 1,000 flight cycles after the 
effective date of this AD, whichever is later.
    (2) For airplanes with 18,600 or more total flight cycles as of 
the effective date of this AD: Within 500 flight cycles after the 
effective date of this AD.

Repetitive Inspections

    (h) If no cracking is found during the inspection required by 
paragraph (g) of this AD: Repeat the inspection at intervals not to 
exceed 1,000 flight cycles.

Related Investigative/Corrective Actions

    (i) If any cracking is found during any inspection required by 
paragraph (g) or (h) of this AD: Before further flight, accomplish 
all related investigative and corrective actions specified in the 
Accomplishment Instructions of the service bulletin, except as 
provided by paragraph (j) of this AD. Within 5,000 flight cycles 
after doing the repair specified in the service bulletin, do the 
inspection in paragraph (g) of this AD, and thereafter, repeat the 
inspection, as applicable, at intervals not to exceed 1,000 flight 
cycles.
    (j) If any cracking is found for which the service bulletin 
specifies to contact Airbus: Before further flight, repair per a 
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction Generale 
de l'Aviation Civile (or its delegated agent).

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (l) French airworthiness directive 2003-410(B), dated October 
29, 2003, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 1, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-25030 Filed 11-9-04; 8:45 am]
BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>