[Federal Register: January 25, 2006 (Volume 71, Number 16)]
[Proposed Rules]
[Page 4062-4065]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25ja06-20]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23675; Directorate Identifier 2001-NM-320-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2-203 and A300 B4-
203 Airplanes; 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 A310-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that affects certain Airbus Model A300 series airplanes
and all Model A300-600 and A310 series airplanes. That AD currently
requires repetitive inspections of the pitch trim system to detect
continuity defects in the autotrim function, and follow-on corrective
actions if necessary. For certain airplanes, this proposed AD would
also require replacing the flight augmentation computers (FACs) with
new improved FACs. This proposed AD also revises the applicability of
the existing AD. This proposed AD results from the development of a
final action intended to address the unsafe condition. We are proposing
this AD to prevent a sudden change in pitch due to an out-of-trim
condition combined with an autopilot disconnect, which could result in
reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by February 24,
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.
For service information identified in this proposed AD, contact
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France.
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.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-23675;
Directorate Identifier 2001-NM-320-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 our
docket web site, anyone can find and read the comments in any of our
dockets, including the name of the individual
[[Page 4063]]
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 may 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 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
On November 6, 2000, we issued AD 2000-23-07, amendment 39-11977
(65 FR 68876, November 15, 2000), for certain Airbus Model A300 series
airplanes and all Model A300-600 and A310 series airplanes. That AD
requires repetitive inspections of the pitch trim system to detect any
continuity defect in the autotrim function, and follow-on corrective
actions if necessary. That AD was prompted by issuance of mandatory
continuing airworthiness information by the Direction Generale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France. We issued that AD to prevent a sudden change in pitch due to an
out-of-trim condition combined with an autopilot disconnect, which
could result in reduced controllability of the airplane.
Actions Since Existing AD Was Issued
One operator reported an undetected slow pitch trim movement in the
nose-down direction leading to an out-of-trim situation and airplane
nose-down attitude during climb phase after autopilot engagement.
Investigation revealed an open circuit in the existing flight
augmentation computer (FAC) software design did not allow the FAC pitch
trim monitoring function to provide automatic disengagement of pitch
trim.
Since AD 2000-23-07 was issued, as a result of these new findings
and the incidents that prompted AD 2000-23-07, a new FAC was developed
for Model A300-600 and A310-200 and -300 series airplanes to restore
full capability of the FAC autotrim monitoring function.
In AD 2000-23-07, we explain that we consider the requirements
``interim action'' and were considering further rulemaking. We now have
determined that further rulemaking is indeed necessary, and this
proposed AD follows from that determination.
Relevant Service Information
Airbus has issued Service Bulletins A300-22-6050, dated October 8,
2004, and A310-22-2058, dated April 6, 2005. The service bulletins
describe procedures for replacing the FACs with new improved FACs. To
ensure the continued airworthiness of these airplanes in France, the
DGAC mandated the service information by issuing French airworthiness
directive F-2005-111 R1, dated December 21, 2005. (The DGAC also
mandated Airbus Service Bulletin A300-22-6041, described in AD 2000-23-
07, for Model A300 B2-203 and A300 B4-203 airplanes, in French
airworthiness directive F-2000-115-304 R5, dated July 6, 2005.)
Accomplishing the actions specified in the service bulletins is
intended to adequately address the unsafe condition.
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.
We are proposing to supersede AD 2000-23-07. This proposed AD would
retain the requirements of the existing AD. This action would also
require accomplishing the actions specified in the service information
described in this proposed AD.
Explanation of Changes to Existing AD
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
AD 2000-23-07 requires operators to report their inspection
findings. We no longer need this information and have removed this
requirement from this proposed AD.
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
This AD would affect about 86 airplanes of U.S. registry. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Cost Estimates
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Hourly labor
Action Service bulletins Work hours rate Parts cost Total per airplane
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Inspection required by AD 2000-03- A300-22A6042, A300- 1 $65 None $65, per inspection cycle.
07, per inspection cycle. 22A0115, A310-22A2053.
Proposed FAC replacement............ A300-22-6050, A310-22- 9 $65 $2,677 $3,262.
2058.
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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
[[Page 4064]]
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 FAA amends Sec. 39.13 by removing amendment 39-11977 (65 FR
68876, November 15, 2000) and adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2006-23675; Directorate Identifier 2001-NM-
320-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by February 24, 2006.
Affected ADs
(b) This AD supersedes AD 2000-23-07.
Applicability
(c) This AD applies to the following Airbus airplanes,
certificated in any category.
(1) Model A300 B2-203 and A300 B4-203 airplanes, as identified
in Airbus Service Bulletin A300-22A0115, Revision 02, dated March 7,
2000.
(2) Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-
622R, A300 F4-605R, F4-622R, and A300 C4-605R Variant F airplanes,
except those modified in production by Airbus Modification 12932.
(3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes, except those modified in production by Airbus
Modification 12932.
Unsafe Condition
(d) This AD results from the development of final action
intended to address the unsafe condition. We are issuing this AD to
prevent a sudden change in pitch due to an out-of-trim condition
combined with an autopilot disconnect, which could 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.
Restatement of Requirements of AD 2000-23-07
Repetitive Inspections
(f) For airplanes subject to the requirements of AD 2000-23-07:
At the applicable time specified by paragraph (f)(1) or (f)(2) of
this AD, perform an inspection of the autotrim function by testing
the flight control computer (FCC)/flight augmentation computer (FAC)
integrity in logic activation of the autotrim, in accordance with
Airbus Service Bulletin A300-22A6042, Revision 01 (for Model A300-
600 series airplanes); A300-22A0115, Revision 02 (for Model A300
series airplanes); or A310-22A2053, Revision 01 (for Model A310
series airplanes); all dated March 7, 2000; as applicable. If any
discrepancy is found, prior to further flight, perform all
applicable corrective actions (including trouble-shooting; replacing
the FCC and/or FAC, as applicable; retesting; checking the wires
between certain FCC and FAC pins; and repairing damaged wires) in
accordance with the applicable service bulletin. Repeat the
inspection thereafter at intervals not to exceed 500 flight hours.
Replacement of both FACs in accordance with paragraph (g) of this AD
terminates the inspection requirements of this paragraph.
(1) For airplanes on which the pitch trim system test has been
performed in accordance with the requirements of AD 2000-02-04,
amendment 39-11522: Inspect within 500 flight hours after
accomplishment of the test required by that AD, or within 20 days
after December 20, 2000 (the effective date of AD 2000-23-07,
whichever occurs later.
(2) For all other airplanes: Inspect within 20 days after
December 20, 2000.
New Requirements of This AD
FAC Replacement
(g) At the time specified in Table 1 of this AD, replace the two
FACs with new FACs in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-22-6050, dated October
8, 2004, or A310-22-2058, dated April 6, 2005; as applicable.
Table 1.--Compliance Times To Replace FACs
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Required compliance
time after the
Airplane model/series Configuration effective date of this
AD
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A300-600............... Without accomplishment 24 months.
of Airbus Service
Bulletin A300-22-6041,
Revision 01, dated
February 21, 2001, or
previous version, or
Modification 12277.
And without
accomplishment of
Airbus Service
Bulletin A300-22-6050,
dated October 8, 2004,
or Modification 12932.
With accomplishment of 36 months.
Airbus Service
Bulletin A300-22-6041,
Revision 01, dated
February 21, 2001, or
previous version, or
Modification 12277.
And without
accomplishment of
Airbus Service
Bulletin A300-22-6050,
dated October 8, 2004,
or Modification 12932.
A310................... Without accomplishment 24 months.
of Airbus Service
Bulletin A310-22-2052,
Revision 01, dated
November 8, 2001, or
previous version, or
Modification 12277.
And without
accomplishment of
Airbus Service
Bulletin A310-22-2058,
dated April 6, 2005,
or Modification 12931.
With accomplishment of 36 months.
Airbus Service
Bulletin A310-22-2052,
Revision 01, dated
November 8, 2001, or
previous version, or
Modification 12277.
[[Page 4065]]
And without
accomplishment of
Airbus Service
Bulletin A310-22-2058,
dated April 6, 2005,
or Modification 12931.
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Part Installation
(h) On or after the effective date of this AD, no person may
install, on any airplane, any FAC having P/N B471AAM7 (for Model
A300-600 series airplanes) or FAC P/N B471ABM4 (for Model A310
series airplanes), unless the FAC is in compliance with this AD.
Alternative Methods of Compliance (AMOCs)
(i)(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 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
(j) The subject of this AD is addressed in French airworthiness
directives F-2005-111 R1, dated December 21, 2005, and F-2000-115-
304 R5, dated July 6, 2005.
Issued in Renton, Washington, on January 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-897 Filed 1-24-06; 8:45 am]
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