[Federal Register Volume 76, Number 97 (Thursday, May 19, 2011)]
[Proposed Rules]
[Pages 28914-28915]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-12309]
[[Page 28914]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0518; Directorate Identifier 2010-NM-150-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes); and Model A310 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD was prompted by events of
excessive rudder pedal inputs and consequent high loads on the vertical
stabilizer on several airplanes. High loads on the vertical stabilizer
that exceed ultimate design loads could cause failure of the vertical
stabilizer and consequent reduced controllability of the airplane. The
proposed AD would require actions that are intended to address this
unsafe condition.
DATES: We must receive comments on this proposed AD by July 5, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 425-
227-2125; fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0518;
Directorate Identifier 2010-NM-150-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of events of excessive rudder pedal inputs
that resulted in high vertical stabilizer loads on Airbus Model A300-
600 and A310 series airplanes. In one case, the in-flight separation of
the vertical stabilizer resulted from loads beyond ultimate design that
were created by the pilot making excessive rudder pedal reversals. In
another incident, during stall recovery, the airplane accelerations
were so high that the rudder travel limiter was not capable of
appropriately limiting rudder travel. Rudder pedal inputs in this case
also resulted in high vertical stabilizer loads. Contributing to these
rudder pedal inputs were characteristics of the rudder system design.
Rudder pedal sensitivity on Model A300-600 and A310 series airplanes is
greater than that of other transport category airplane designs. Such
rudder control sensitivity could result in rudder over-control and
contribute to hazardous rudder pedal inputs such as rudder reversals.
Hazardous rudder pedal inputs could result in loads that exceed
ultimate design loads, potentially causing failure of the vertical
stabilizer and consequent reduced controllability of the airplane.
Currently, there are no service instructions to address this unsafe
condition. However, one option under consideration consists of a
modification to the rudder control system that is called the pedal
travel limiter unit (PTLU). The PTLU limits rudder pedal stroke and
allows the yaw damper to decrease the rudder deflection. The PTLU also
provides limiting rates that ensure that rudder travel is appropriately
limited during high acceleration maneuvers. Other potential design
changes are also under review. We anticipate that one of these design
changes will be approved within three years and will meet the
requirements of this proposed AD.
FAA's Determination and Requirements of This Proposed AD
These airplanes 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.
We are proposing this AD because we evaluated all relevant
information and determined that the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
The proposed AD would require actions to address this unsafe
condition.
Costs of Compliance
We estimate that this proposed AD would affect 215 airplanes of
U.S. registry.
One way, but not the only way, to modify the rudder control system
is to install a PTLU. The following table provides the estimated costs
for U.S. operators to comply with this proposed AD if a PTLU is
installed based on preliminary information provided by the
manufacturer.
[[Page 28915]]
Estimated Costs for PTLU Installation
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Average labor Cost per
Work hours rate per hour Parts product Fleet cost
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100............................................. $85 $190,000 $198,500 $42,677,500
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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 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 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. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 AD:
Airbus: Docket No. FAA-2011-0518; Directorate Identifier 2010-NM-
150-AD.
Comments Due Date
(a) We must receive comments by July 5, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A300 B4-601, B4-603, B4-
620, and B4-622 airplanes; A300 B4-605R and B4-622R airplanes; A300
F4-605R and F4-622R airplanes; A300 C4-605R Variant F airplanes; and
A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Unsafe Condition
(e) This AD was prompted by events of excessive rudder pedal
inputs and consequent loads on the vertical stabilizer that exceed
ultimate design loads. Such events could lead to failure of the
vertical stabilizer and consequent reduced controllability of the
airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Modification
(g) Within 48 months after the effective date of this AD,
incorporate a design change to the rudder control system and/or
other systems to address the unsafe condition identified in
paragraph (e) of this AD, in accordance with a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(i) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone 425-227-2125; fax 425-227-1149.
Issued in Renton, Washington, on April 26, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-12309 Filed 5-18-11; 8:45 am]
BILLING CODE 4910-13-P