[Federal Register: October 12, 2006 (Volume 71, Number 197)]
[Proposed Rules]
[Page 60087-60089]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12oc06-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26045; Directorate Identifier 2006-NM-145-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 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 supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model A300 B2 and B4
series airplanes. The existing AD currently requires modifying the
wiring of the autopilot pitch torque limiter switch. This proposed AD
would add repetitive operational tests of the autopilot disconnection
upon pitch override, and related investigative/corrective actions if
necessary. This proposed AD results from the determination that such
operational tests are necessary following the modification. 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 November 13,
2006.
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: Thomas Stafford, Aerospace Engineer,
[[Page 60088]]
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; 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 ``Docket No.
FAA-2006-26045; Directorate Identifier 2006-NM-145-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
On June 14, 2005, we issued AD 2005-13-33, amendment 39-14170 (70
FR 36833, June 27, 2005), for certain Airbus Model A300 B2 and B4
series airplanes. That AD requires modifying the wiring of the
autopilot (AP) pitch torque limiter switch. That AD resulted from
several reports of pitch trim disconnect caused by insufficient length
in the wiring to the pitch torque limiter lever. We issued that 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.
Actions Since Existing AD Was Issued
Since we issued AD 2005-13-33, it has been determined that
repetitive operational tests of the autopilot disconnection upon pitch
override are necessary following the modification to ensure the
reliability of AP disconnection by stick force.
Relevant Service Information
AD 2005-13-33 cites Airbus Service Bulletin A300-22-0117, dated
September 7, 2004, as the appropriate source of service information for
the modification. Airbus has since revised the service bulletin.
Revision 01, dated April 20, 2005, and Revision 02, dated September 14,
2005, provide minor changes only.
Airbus has also issued Service Bulletin A300-22-0118, including
Appendix 01, dated May 18, 2005. The service bulletin describes
procedures for repetitive operational tests of the autopilot
disconnection upon pitch override. Related investigative and corrective
actions for discrepant results include inspecting for discrepancies
(including chafing) of the wiring between the relay and the autopilot
flight director logic monitor (AP/FD L/M) computer, replacing the relay
with a new relay having the same part number, repairing the torque
limiter lever or replacing it with a new one having the same part
number, and repairing or replacing the wiring.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, mandated the service information
and issued French airworthiness directive F-2005-107, dated July 6,
2005, 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 airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2005-13-33 and retain the
requirements of that AD. This proposed AD would add repetitive
operational tests of the AP disconnection upon pitch override, and
related investigative/corrective actions if necessary.
Costs of Compliance
This proposed AD would affect about 29 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Estimated Costs
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Average
Action Work hours labor rate Parts Cost per airplane Fleet cost
per hour
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Modification............................ 8-11 $80 $1,700-$4,280 $2,340-$5,160............. $67,860-$149,640.
Operational test........................ 4 80 0 $320, per test cycle...... $9,280, per test cycle.
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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
[[Page 60089]]
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
removing amendment 39-14170 (70 FR 36833, June 27, 2005) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-26045; Directorate Identifier 2006-NM-
145-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
13, 2006.
Affected ADs
(b) This AD supersedes AD 2005-13-33.
Applicability
(c) This AD applies to Airbus A300 aircraft, all certified
models and all serial numbers, certificated in any category, except
for:
(1) 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, and A300 C4-605R Variant F airplanes.
(2) Models A300B4-220, A300B4-203, and A300B2-203 in forward
facing crew cockpit certified configuration.
Unsafe Condition
(d) This AD results from the determination that repetitive
operational tests are necessary following incorporation of the
wiring modification required by AD 2005-13-33. 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.
Restatement of Requirements of AD 2005-13-33
Modification
(f) Within 20 months after August 1, 2005 (the effective date of
AD 2005-13-33), 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; Revision 01, dated April 20, 2005; or
Revision 02, dated September 14, 2005. After the effective date of
this AD, only Revision 02 may be used.
New Requirements of This AD
Repetitive Operational Tests
(g) At the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD: Do an operational test of the autopilot
disconnection upon pitch override, and do all applicable related
investigative and corrective actions. Do the actions in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-22-0118, excluding Appendix 01, dated May 18, 2005; except that
this AD does not require a report of the inspection results. Do all
applicable related investigative and corrective actions before
further flight. Repeat the test thereafter at intervals not to
exceed 2,000 flight hours.
(1) For airplanes modified before the effective date of this AD
in accordance with Airbus Service Bulletin A300-22-0117, dated
September 7, 2004: Do the initial test within 2,000 flight hours
after the effective date of this AD.
(2) For airplanes modified in accordance with Airbus Service
Bulletin A300-22-0117, Revision 01, dated April 20, 2005; or
Revision 02, dated September 14, 2005: Do the initial test within
2,000 flight hours after the modification required by paragraph (f)
of this AD, or within 2,000 flight hours after the effective date of
this AD, whichever occurs later.
Alternative Methods of Compliance (AMOCs)
(h)(1) 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.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 2005-13-33
are not approved as AMOCs with this AD.
Related Information
(i) French airworthiness directive F-2005-107, dated July 6,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on October 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-16880 Filed 10-11-06; 8:45 am]
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