AD 2005-07-07

[Federal Register Volume 70, Number 58 (Monday, March 28, 2005)]
[Rules and Regulations]
[Pages 15577-15580]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 05-6106]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20748; Directorate Identifier 2005-NM-063-AD; 
Amendment 39-14031; AD 2005-07-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 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), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A310 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). This AD requires one-time 
general visual, detailed, and tap test inspections for discrepancies in 
the structural integrity of the rudder and its attachments, and 
corrective actions if necessary. This AD is prompted by a report that, 
during cruise, a Model A310 series airplane lost most of its rudder, 
which was made from composite-fiber-reinforced plastic. Investigation 
revealed that most of the rudder, including the front spar portion 
above the three servo control actuators was missing. We are issuing 
this AD to prevent detachment of the rudder from the airplane, which 
could degrade airplane handling qualities and result in reduced 
controllability of the airplane.

DATES: Effective March 28, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of March 
28, 2005.
    We must receive comments on this AD by May 27, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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> 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 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 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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. This 
docket number is FAA-2005-20748; the directorate identifier for this 
docket is 2005-NM-063-AD.

Examining the Docket

    You can examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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 DMS receives them.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 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 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, during cruise, a 
Model A310 series airplane lost most of its rudder, which was made from 
composite-fiber-reinforced plastic (CFRP). Investigation revealed that 
most of the rudder, including the front spar portion above the three 
servo control actuators was missing. The cause of this rudder loss is 
under investigation. This condition, if not corrected, could result in 
detachment of the rudder from the airplane, which could degrade 
airplane handling qualities and result in reduced controllability of 
the airplane.

Similar Airplane Models

    A rudder having the same part number as that installed on Model 
A310 series airplanes also is installed on Model A300-600 series 
airplanes. Therefore, the latter airplanes are also subject to the 
identified unsafe condition and are included in the applicability of 
the U.S. AD.
    Further, a rudder having the same part number is installed on early 
versions of Model A330 and A340 series airplanes. However, we have 
confirmed that the affected rudder is not installed on any Model A330 
series airplanes of U.S. registry. Additionally, there are no Model 
A340 series airplanes on the U.S. Register.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A310A55-2035 (for A310 
series airplanes) and AOT A300-600 55A6035 (for A300-600 series 
airplanes), both dated March 16, 2005. The AOTs describe procedures for 
one-time general visual, detailed visual, and tap test inspections for 
damage in the structural integrity of the rudder and its attachments. 
The inspection procedures include a general visual inspection for 
damage of the rear spar aft face of the vertical stabilizer, including 
the trailing edge structure; a detailed visual inspection of the rudder 
hinge arms and support fittings, the actuator support fittings and the 
rudder hinge fittings; and a tap test inspection for damage of the 
rudder side panels of the leading edge from the bottom to top and the 
forward trailing edge connection from the bottom up to hinge No. 5 
around the hoisting points and certain additional areas. The AOTs also 
specify contacting the manufacturer for certain repair conditions and 
reporting of inspection results. The DGAC mandated the service 
information and issued French airworthiness directive UF-2005-048, 
dated March 18, 2005, to ensure the continued airworthiness of these 
airplanes in France.

[[Page 15578]]

FAA's Determination and Requirements of This 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 products of this type design that are certificated for 
operation in the United States.
    Therefore, we are issuing this AD to prevent detachment of the 
rudder from the airplane, which could degrade airplane handling 
qualities and result in reduced controllability of the airplane. This 
AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the AD and the Service Information.'' The AD also 
requires sending the inspection results to Airbus, regardless of the 
findings.

Differences Among the AD, French Airworthiness Directive and Service 
Information

    Although the French airworthiness directive and the AOTs specify 
that operators may contact the manufacturer for certain repair 
conditions, this AD requires operators to repair those conditions 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 
unsafe condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this AD, a repair approved by 
either the FAA or the DGAC (or its delegated agent) would be acceptable 
for compliance with this AD.
    The French airworthiness directive and AOTs specify inspecting the 
rudder attachments and the rudder side panels for damage and reporting 
findings to the manufacturer, but there is no definition of the type of 
damage to inspect for or findings to report. This AD requires 
inspecting for discrepancies in the structural integrity of the rudder 
and its attachments. For the general visual and detailed inspections, 
the discrepancies to inspect for and report include corrosion, cracks, 
abrasion, scratches, and dents. For the tap test, the discrepancies to 
inspect for and report include delamination in the outer CFRP layers 
and debonding between the outer CFRP layers and the honeycomb core.

Clarification of Certain Sections in Airbus A310 and A300-600 
Structural Repair Manuals

    Although the French airworthiness directive and AOTs do not 
identify the sections in the SRMs that specify damage limits for the 
rudder attachments and the rudder side panels, those sections are 
specified in Note 3 of this AD.

Clarification of Inspection Terminology/AOT Number

    In this AD, the ``detailed visual inspection'' specified in the 
AOTs is referred to as a ``detailed inspection.'' We have included the 
definition for a detailed inspection in a note in the AD.
    The French airworthiness directive identifies the AOT number for 
A310 series airplanes as A310 55A2035; however, the number is 
transposed in the AOT and identified as A310A55-2035. This AD will 
identify the AOT number as A310A55-2035 to adhere to the Office of the 
Federal Register guidelines for materials incorporated by reference.

Interim Action

    This is considered to be interim action. The inspection report that 
is required by this AD will enable the FAA, DGAC, and the manufacturer 
to obtain better insight into the potential unsafe condition, and 
eventually to develop final action to address it, if necessary. If 
final action is identified, the FAA may consider further rulemaking.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective upon publication in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed under ADDRESSES. Include ``Docket No. FAA-2005-20748; 
Directorate Identifier 2005-NM-063-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this 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 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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

[[Page 15579]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-07-07 Airbus: Amendment 39-14031. Docket No. FAA-2005-20748; 
Directorate Identifier 2005-NM-063-AD.

Effective Date

    (a) This AD becomes effective March 28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310 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; equipped with any composite-fiber-
reinforced plastic (CFRP) rudder with part number (P/N) A55471500 
series installed.

Unsafe Condition

    (d) This AD was prompted by a report that, during cruise, a 
Model A310 series airplane lost most of its rudder, which was made 
from CFRP. The FAA is issuing this AD to prevent detachment of the 
rudder from the airplane, which could degrade airplane handling 
qualities and result in reduced controllability of the airplane.

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.

One-Time Inspections

    (f) Within 550 flight hours or 3 months after the effective date 
of this AD, whichever is first: Perform one-time general visual, 
detailed, and tap test inspections for discrepancies in the 
structural integrity of the rudder and its attachments, in 
accordance with Airbus All Operators Telex (AOT) A310A55-2035 (for 
A310 series airplanes) and Airbus AOT A300-600 55A6035 (for A300-600 
series airplanes), both dated March 16, 2005. For the one-time 
general visual and detailed inspections, discrepancies include 
corrosion, cracks, abrasion, scratches, and dents. For the tap test, 
discrepancies include delamination in the outer CFRP layers and 
debonding between the outer CFRP layers and the honeycomb core.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''


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

Actions Accomplished Previously

    (g) Inspections accomplished within the last 18 months before 
the effective date of this AD in accordance with section 4.2.2 of 
Airbus AOTs A310A55-2035 and A300-600 55A6035, both dated March 16, 
2005; are considered acceptable for compliance with the 
corresponding actions specified in paragraph (f) of this AD, after 
the inspection results are reported to Airbus as required in 
paragraph (i) of this AD.

Corrective Actions

    (h) If any discrepancy of the rudder attachments that exceeds 
the limits specified in the Airbus A310 or A300-600 Structural 
Repair Manual (SRM), or any discrepancy of the rudder side panels is 
found during any inspection required by paragraph (f) of this AD: 
Before further flight, repair or otherwise disposition, in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate; or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its 
delegated agent).

    Note 3: Limits for allowable damage and rework for the rudder 
attachment fittings are specified in Sections 55-40-00, 55-36-42, 
55-30-00, and 55-46-11 of the Airbus A310 and A300-600 SRM.

Reporting Requirement

    (i) Within 10 days after accomplishing all the inspections 
required by paragraph (f) of this AD: Submit Airbus Technical 
Disposition 943.0267/05, Issue A, ``CFRP Rudder--Inspection 
Reporting Sheets'' with the inspection results (both positive and 
negative findings) to Airbus Customer Service Engineering, Mr. X. 
Jolivet, SEE83, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex 
France; fax (+33) 5 61 93 36 14. Under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office 
of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD and has assigned OMB 
Control Number 2120-0056.

    Note 4: The reporting sheets referenced in paragraph (j) of this 
AD will be provided by Airbus, as specified in Section 2., of Airbus 
AOTs A310A55-2035 and A300-600 55A6035, both dated March 16, 2005.

Parts Installation

    (j) As of the effective date of this AD, no person may install 
on any airplane a CFRP rudder, P/N A55471500 series, unless the 
requirements specified in paragraphs (f), (h) and (i) of this AD 
have been accomplished.

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 UF-2005-048, dated March 18, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use Airbus All Operators Telex A310A55-2035, dated 
March 16, 2005; and Airbus All Operators Telex A300-600 55A6035, 
dated March 16, 2005; as applicable; to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approves the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. For copies of the service information, contact Airbus, 1 Rond 
Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD 
docket go to the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.


[[Page 15580]]


    Issued in Renton, Washington, on March 23, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-6106 Filed 3-25-05; 8:45 am]
BILLING CODE 4910-13-P