[Federal Register: April 6, 2005 (Volume 70, Number 65)]
[Proposed Rules]
[Page 17347-17349]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06ap05-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20861; Directorate Identifier 2005-NM-020-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A300 B2 and B4 series airplanes. This proposed
AD would require modifying the wiring of the autopilot pitch torque
limiter switch. This proposed AD is prompted by several reports of
pitch trim disconnect caused by insufficient length in the wiring to
the pitch torque limiter lever. We are proposing this AD to prevent
possible trim loss when the flightcrew tries to override the autopilot
pitch control, which could result in uncontrolled flight of the
airplane.
DATES: We must receive comments on this proposed AD by May 6, 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.
By 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.
For service information identified in this proposed AD, contact
Jacques Leborgne, Airbus Customer Service Directorate, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex, France; fax (+33) 5 61 93 36 14.
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. This docket
number is FAA-2005-20861; the directorate identifier for this docket is
2005-NM-020-AD.
FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2139; 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 under ADDRESSES. Include ``Docket No. FAA-2005-20861;
Directorate Identifier 2005-NM-020-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 website, 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.
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 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.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France,
[[Page 17348]]
notified us that an unsafe condition may exist on certain Airbus Model
A300 B2 and B4 series airplanes. The DGAC advises of several reports of
pitch trim disconnect caused by insufficient length in the wiring to
the pitch torque limiter lever. The DGAC also advises of possible trim
loss when the flightcrew tries to override the autopilot pitch control.
Possible trim loss, if not corrected, could result in uncontrolled
flight of the airplane.
Relevant Service Information
Airbus has issued Service Bulletin A300-22-0117, dated September 7,
2004. The service bulletin describes procedures for modifying the
wiring of the autopilot pitch torque limiter switch. For certain
airplanes, modification includes installing new clamps and harnesses.
For certain other airplanes, modification includes the following:
Modifying the equipment and wiring in the left-hand
electronics rack 80VU.
Modifying the equipment and wiring in relay box 103VU.
Modifying the wiring between the left-hand rack 80VU and
relay box 103VU.
Modifying the wiring between the rudder and the upper half
of the fuselage.
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-
2004-186, dated November 24, 2004, 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
Sec. 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 proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Costs of Compliance
This proposed AD would affect about 20 airplanes of U.S. registry.
The proposed actions would take about between 8 and 11 work hours per
airplane, depending on airplane configuration, at an average labor rate
of $65 per work hour. Required parts would cost about $1,840 and $4,280
per airplane, depending on airplane configuration. Based on these
figures, the estimated cost of the proposed AD for U.S. operators is
between $47,200 and $99,900, or between $2,360 and $4,995 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. 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-2005-20861; Directorate Identifier 2005-NM-
020-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by May 6, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B2 and B4 series
airplanes, certificated in any category; as identified in Airbus
Service Bulletin A300-22-0117, dated September 7, 2004.
Unsafe Condition
(d) This AD was prompted by several reports of pitch trim
disconnect caused by insufficient length in the wiring to the pitch
torque limiter lever. We are issuing this AD to prevent possible
trim loss when the flightcrew tries to override the autopilot pitch
control, which could result in uncontrolled flight 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.
Modification
(f) Within 20 months after the effective date of this AD, modify
the wiring of the autopilot pitch torque limiter switch, by doing
all of the applicable actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A300-22-0117, dated
September 7, 2004.
Alternative Methods of Compliance (AMOCs)
(g) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
[[Page 17349]]
Related Information
(h) French airworthiness directive F-2004-186, dated November
24, 2004, also addresses the subject of this AD.
Issued in Renton, Washington, on March 30, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6768 Filed 4-5-05; 8:45 am]
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