[Federal Register Volume 70, Number 207 (Thursday, October 27, 2005)]
[Proposed Rules]
[Pages 61924-61927]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21428]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-143-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-203, -204, and -222 
Airplanes, and Model A310-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 61925]]

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A310-203, -204, and -222 airplanes, and Model 
A310-300 series airplanes. This proposed AD would require a one-time 
rototest inspection for cracking of the frame foot and adjacent frames 
and skin in the area surrounding the frame foot run-outs from fuselage 
frames (FR) 43 through FR 46, and repair if necessary. The proposed AD 
also requires modification of certain fastener holes. This proposed AD 
results from a structural evaluation of Model A310 airplanes for 
widespread fatigue damage of the frame foot run-outs from FR 43 through 
FR 46. The evaluation revealed that, on in-service airplanes, 
undetected cracking in this area can lead to the rupture of the frame 
foot and subsequent cracking of the adjacent frames and fuselage skin. 
We are proposing this AD to prevent fatigue cracking of the frame foot 
run-outs, which could lead to rupture of the frame foot and cracking in 
adjacent frames and skin, and result in reduced structural integrity of 
the fuselage.

DATES: We must receive comments on this proposed AD by November 28, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
22810; Directorate Identifier 2005-NM-143-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 received 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 
that 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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may 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 located 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 Docket Management System 
receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A310-203, -204, and 
-222 airplanes, and Model A310-300 series airplanes. The DGAC advises 
that a structural evaluation for widespread fatigue damage of the frame 
foot run-outs from fuselage frame (FR) 43 through FR 46 was done on the 
subject airplanes. The evaluation revealed that, on in-service 
airplanes, undetected cracking in this area can lead to the rupture of 
the frame foot and subsequent cracking of the adjacent frames and 
fuselage skin. Such cracking would require an extensive repair and 
could have an impact on pressure loading strength capacity of the 
structure. These conditions, if not corrected, could result in reduced 
structural integrity of the fuselage.

Relevant Service Information

    Airbus has issued Service Bulletin A310-53-2124, dated April 4, 
2005. The service bulletin describes procedures for performing a one-
time rototest inspection to find cracking of the frame foot and 
adjacent frames and skin in the area surrounding the frame foot run-
outs from FR 43 through FR 46, and repair of cracking within certain 
limits. If the cracking is outside the limits specified in the service 
bulletin, the service bulletin procedures recommend contacting the 
manufacturer for repair instructions. The service bulletin also 
describes procedures for modification of certain fastener holes. The 
modification includes cold expanding the fastener holes most 
susceptible to fatigue, which are located between FR 43 and FR 46 on 
the center box and on the upper fuselage bent sections, and installing 
new fasteners. 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 F-2005-078, dated May 11, 2005, to ensure the continued 
airworthiness of these airplanes in France.
    Section 1.E., Compliance, of the service bulletin specifies 
compliance times for the actions in the service bulletin. The 
thresholds for the one-time inspection and modification range from 
between 22,200 flight cycles or 51,700 flight hours, whichever is 
first, to 26,800 flight cycles or 77,700 flight hours, whichever is 
first, depending on the configuration of the airplane. The service 
bulletin also includes a grace period of 3,000 flight cycles for 
airplanes that have exceeded certain flight-hour or flight-cycle 
thresholds, depending on the configuration of the airplane.

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 we need to 
issue an AD for airplanes of this

[[Page 61926]]

type design that are certificated for operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Among 
Proposed AD, French Airworthiness Directive, and Service Bulletin.''

Differences Among Proposed AD, French Airworthiness Directive, and 
Service Bulletin

    The applicability of the French Airworthiness Directive excludes 
airplanes on which Airbus Service Bulletin A310-53-2124 has been 
accomplished in service. However, we have not excluded those airplanes 
in the applicability of this proposed AD; rather, this proposed AD 
would include a requirement to accomplish the actions specified in that 
service bulletin. This proposed AD would ensure that the actions 
specified in the service bulletin and required by this proposed AD are 
accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this proposed AD 
unless an alternative method of compliance is approved.
    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing 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.

Costs of Compliance

    This proposed AD would affect about 59 airplanes of U.S. registry. 
The proposed actions would take about 31 work hours per airplane, at an 
average labor rate of $65 per work hour. Required parts would cost 
about $1,730 per kit (two kits per airplane). Based on these figures, 
the estimated cost of the proposed AD for U.S. operators is $323,025, 
or $5,475 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-
143-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, and -222 
airplanes, and Model A310-304, -322, -324, and -325 airplanes; 
certificated in any category; except those airplanes on which Airbus 
Modification 13023 has been accomplished in production.

Unsafe Condition

    (d) This AD results from a structural evaluation of Model A310 
airplanes for widespread fatigue damage of the frame foot run-outs 
from frame (FR) 43 through FR 46. We are issuing this AD to prevent 
fatigue cracking of the frame foot run-outs, which could lead to 
rupture of the frame foot and cracking in adjacent frames and skin, 
and result in reduced structural integrity of the fuselage.

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.

Inspection/Repair/Modification

    (f) At the later of the times specified in paragraphs (f)(1) and 
(f)(2) of this AD, perform a one-time rototest inspection for 
cracking of the frame foot and adjacent frames and skin in the area 
surrounding the frame foot run-outs from fuselage frame FR 43 
through FR46 by doing all the applicable actions specified in the 
Accomplishment Instructions of the service bulletin. Except as 
required by paragraph (g) of this AD, repair any cracking before 
further flight in accordance with the Accomplishment Instructions of 
the service bulletin. Before further flight after performing the 
inspection, modify the fastener holes located between FR 43 and FR 
46 on the center box and on the upper fuselage bent sections in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (1) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in the Accomplishment 
Timescale table in paragraph 1.E.(2), ``Compliance'' of the service 
bulletin.
    (2) At the earlier of the times specified in paragraphs 
(f)(2)(i) and (f)(2)(ii) of this AD.
    (i) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in Notes 01, 02, and 
03 in paragraph 1.E.(2), ``Compliance'' of the service bulletin, 
after the effective date of this AD.
    (ii) Within 3,000 flight cycles after the effective date of this 
AD.

Repair Per FAA or Direction G[eacute]n[eacute]rale de l'Aviation Civile 
(DGAC)

    (g) For any cracking found during any inspection required by 
this AD for which the

[[Page 61927]]

service bulletin specifies to contact the manufacturer for an 
appropriate repair: Before further flight, repair in accordance with 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the DGAC (or its delegated 
agent).

Alternative Methods of Compliance (AMOCs)

    (h)(1) 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.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (i) French airworthiness directive F-2005-078, dated May 11, 
2005, also addresses the subject of this AD.


    Issued in Renton, Washington, on October 20, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-21428 Filed 10-26-05; 8:45 am]
BILLING CODE 4910-13-P