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, 41118-41121 [E6-11414]
Download as PDF
<![CDATA[
41118
Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
Actions
Compliance
Procedures
Incorporate the following information into the
Limitations Section of the FAA-approved Airplane Flight Manual (AFM):
(1) For airplanes listed in Type Certificate No.
A2PC insert pages 3 and 4 from Mitsubishi
Heavy Industries, Ltd. (MHI) MU–2 Service
Bulletin No. 229, dated February 20, 1996.
(2) For airplanes listed in Type Certificate No.
A10SW insert page 3 of 3 from MHI MU–2
Service Bulletin No. 090/76–003, dated January 22, 1997.
(3) For all of the above airplanes the logbook
entry required after each pilot check on page
3 of MHI MU–2 Service Bulletin No. 090/76–
003, dated January 22, 1997, and page 4 of
MHI MU–2 Service Bulletin No. 229, dated
February 20, 1996, is not required.
Within 100 hours time-in-service after August
24, 2006 (the effective date of this AD).
The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations
(14 CFR 43.7) may insert the information
into the AFM as specified in paragraph (e)
of this AD. Make an entry into the aircraft
records showing compliance with this portion of the AD in accordance with section
43.9 of the Federal Aviation Regulations
(14 CFR 43.9).
Note: The language in the service
information states the procedure is an
‘‘inspection,’’ but the procedure is a ‘‘pilot
check.’’
(f) The Manager, Fort Worth Aircraft
Certification Office (ACO), FAA, ATTN: Rao
Edupuganti, Aerospace Engineer, ASW–150,
Fort Worth ACO, 2601 Meacham Blvd., Fort
Worth, Texas 76193; telephone: (817) 222–
5284; facsimile: (817) 222–5960, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
Related Information
(g) Japan Civil Aviation Bureau
Airworthiness Directive No. TCD 4379–96,
dated February 20, 1996, addresses the
subject of this AD.
(h) For service information related to this
AD, contact Mitsubishi Heavy Industries
America, Inc., 4951 Airport Parkway, Suite
800, Addison, Texas 75001; telephone: (972)
934–5480; facsimile: (972) 934–5488. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–23645; Directorate Identifier 2006–CE–
04–AD.
Issued in Kansas City, Missouri, on July 11,
2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11419 Filed 7–19–06; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
Alternative Methods of Compliance
(AMOCs)
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2006–23675; Directorate
Identifier 2001–NM–320–AD; Amendment
39–14686; AD 2006–15–06]
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to 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 new AD requires
replacing the flight augmentation
computers (FACs) with new improved
FACs. This AD also revises the
applicability of the existing AD. This
AD results from the development of a
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.
DATES: This AD becomes effective
August 24, 2006.
PO 00000
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Fmt 4700
Sfmt 4700
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of August 24, 2006.
On December 20, 2000 (65 FR 68876,
November 15, 2000), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications listed in the AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2797; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2000–23–07, amendment
39–11977 (65 FR 68876, November 15,
2000). The existing AD applies to
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
certain Airbus Model A300 series
airplanes and all Model A300–600 and
A310 series airplanes. That NPRM was
published in the Federal Register on
January 25, 2006 (71 FR 4062). That
NPRM proposed to require repetitive
inspections of the pitch trim system to
detect continuity defects in the autotrim
function, and follow-on corrective
actions if necessary. That NPRM also
proposed to require replacing the flight
augmentation computers (FACs) with
new improved FACs on certain
airplanes.
airplanes are restated from AD 2000–
23–07, so no new requirements for those
airplanes are introduced in this AD.
We agree that this AD adds no new
requirements for those airplanes. In the
revised applicability for those airplanes,
the forward-facing-cockpit restriction is
removed because it is included in the
service bulletin effectivity. We have not
revised the applicability specified in the
NPRM.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
The same commenter found a
typographical error in the NPRM.
Paragraph (c)(3), which identifies
affected A310–200 and –300 series
airplanes by their associated
modification number, should have
referred to Modification 12931 instead
of Modification 12932.
We acknowledge this error and have
revised this final rule accordingly.
Request To Revise Applicability:
Paragraph (c)(1)
The commenter, Airbus, requests that
we revise paragraph (c)(1) of the NPRM
to retain the applicability of the existing
AD for A300 B2–203 and A300 B4–203
airplanes. The applicability of AD 2000–
23–07 for those airplanes is:
Model A300 B2–203 and A300 B4–203
airplanes in a forward facing cockpit version,
as listed in Airbus Service Bulletin A300–
22A0115, Revision 02, dated March 7, 2000.
The applicability specified in paragraph
(c)(1) of the NPRM omitted the
restriction ‘‘in a forward facing cockpit
version.’’ The commenter asserts that
the mandatory actions for those
Request To Revise Applicability:
Paragraph (c)(3)
41119
We have revised this description to
clarify the affected airplanes. Once an
AD is superseded, no airplane is subject
to its requirements, and it may not be
possible for operators to obtain a copy
to identify the affected airplanes and
requirements. Because AD compliance
records must be maintained
permanently and transferred with
airplanes, operators must always be able
to determine whether a particular AD
has been accomplished, even after it has
been superseded. Therefore, we have
revised paragraph (f) in this final rule to
more precisely describe the airplanes
affected by that requirement.
We have also clarified paragraph (g)
in this final rule by introducing the
paragraph with the airplanes affected by
this new requirement. Those airplanes
are also identified in Table 1 of the AD.
Conclusion
Additional Changes to NPRM
The requirements of paragraph (f) of
the NPRM would apply to ‘‘airplanes
subject to the requirements of AD 2000–
23–07,’’ which include:
• Model A300 B2–203 and A300 B4–
203 airplanes in a forward-facing
cockpit configuration;
• All Model A310–200 and –300
series airplanes; and
• Model A300–600 series airplanes,
except those with Modification 12277
installed in production.
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
This AD affects about 86 airplanes of
U.S. registry. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
COST ESTIMATES
Work
hours
Action
Service bulletins
Inspection, per inspection cycle ..........
A300–22A6042,
A300–22A0115,
A310–22A2053.
A300–22–6050, A310–22–2058 .........
FAC replacement ................................
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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
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16:42 Jul 19, 2006
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Hourly
labor rate
$65
None ....
$65, per inspection cycle.
9
65
$2,677 ..
$3,262.
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 this AD:
Frm 00025
Fmt 4700
Sfmt 4700
Total per airplane
1
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.
PO 00000
Parts
cost
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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41120
Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–11977 (65
FR 68876, November 15, 2000) and by
adding the following new airworthiness
directive (AD):
I
2006–15–06 Airbus: Amendment 39–14686.
Docket No. FAA–2006–23675;
Directorate Identifier 2001–NM–320–AD.
Effective Date
(a) This AD becomes effective August 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 12931.
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-oftrim 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 Model A300 B2–203 and A300 B4–
203 airplanes in a forward-facing cockpit
configuration; all Model A310–200 and –300
series airplanes; and Model A300–600 series
airplanes, except those with Modification
12277 installed in production: 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) For airplanes identified in paragraphs
(c)(2) and (c)(3) of this AD: 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
Required
compliance
time after the
effective date
of this AD
Airplane
model/series
Configuration
A300–600 ......
Without accomplishment 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 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.
Without accomplishment 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 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.
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A310 ..............
Part Installation
(h) On or after the effective date of this AD,
no person may install, on any airplane, any
FAC having part number (P/N) B471AAM7
(for Model A300–600 series airplanes) or
FAC P/N B471ABM4 (for Model A310 series
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16:42 Jul 19, 2006
Jkt 208001
airplanes), unless the FAC is in compliance
with this AD.
PO 00000
24 months.
36 months.
24 months.
36 months.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
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20JYR1
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
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.
Material Incorporated by Reference
(k) You must use the documents identified
in Table 2 of this AD, as applicable, to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
TABLE 2.—DOCUMENTS INCORPORATED BY REFERENCE
Airbus Service Bulletin
A300–22–6050
A300–22A0115
A300–22A6042
A310–22–2058
A310–22A2053
...............
...............
...............
...............
...............
Revision
Date
Original .......................................................................................................................................
02, including Appendix 01 ..........................................................................................................
01, including Appendix 01 ..........................................................................................................
Original .......................................................................................................................................
01, including Appendix 01 ..........................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents identified in Table 3 of this
October 8, 2004.
March 7, 2000.
March 7, 2000.
April 6, 2005.
March 7, 2000.
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
TABLE 3.—NEW DOCUMENTS INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision
A300–22–6050 ...............
A310–22–2058 ...............
Original .......................................................................................................................................
Original .......................................................................................................................................
(2) On December 20, 2000 (65 FR 68876,
November 15, 2000), the Director of the
Federal Register approved the incorporation
Date
October 8, 2004.
April 6, 2005.
by reference of the documents identified in
Table 4 of this AD.
TABLE 4.—DOCUMENTS PREVIOUSLY INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision
A300–22A0115 ...............
A300–22A6042 ...............
A310–22A2053 ...............
02, including Appendix 01 ..........................................................................................................
01, including Appendix 01 ..........................................................................................................
01, including Appendix 01 ..........................................................................................................
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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Issued in Renton, Washington, on July 7,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11414 Filed 7–19–06; 8:45 am]
BILLING CODE 4910–13–P
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16:42 Jul 19, 2006
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Date
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23706; Directorate
Identifier 2006–NE–03–AD; Amendment 39–
14688; AD 2006–15–08]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. TPE331 Series
Turboprop Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Honeywell International Inc. TPE331
series turboprop engines with certain
part numbers of Woodward fuel control
unit (FCU) assemblies installed. This
AD requires initial and repetitive
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
March 7, 2000.
March 7, 2000.
March 7, 2000.
dimensional inspections of the fuel
control drive, for wear or damage. This
AD results from reports of loss of the
fuel control drive, leading to engine
overspeed, overtorque, overtemperature,
uncontained rotor failure, and
asymmetric thrust in multi-engine
airplanes. We are issuing this AD to
prevent destructive overspeed that
could result in uncontained rotor
failure, and damage to the airplane.
This AD becomes effective
August 24, 2006.
DATES:
You can get the service
information identified in this AD from
Honeywell Engines, Systems & Services,
Technical Data Distribution, M/S 2101–
201, P.O. Box 52170, Phoenix, AZ
85072–2170; telephone: (602) 365–2493
(General Aviation); (602) 365–5535
(Commercial); fax: (602) 365–5577
(General Aviation and Commercial).
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
ADDRESSES:
E:\FR\FM\20JYR1.SGM
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]]>Agencies
[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41118-41121]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11414]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23675; Directorate Identifier 2001-NM-320-AD;
Amendment 39-14686; AD 2006-15-06]
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), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to 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 new AD requires
replacing the flight augmentation computers (FACs) with new improved
FACs. This AD also revises the applicability of the existing AD. This
AD results from the development of a 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.
DATES: This AD becomes effective August 24, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 24,
2006.
On December 20, 2000 (65 FR 68876, November 15, 2000), the Director
of the Federal Register approved the incorporation by reference of
certain other publications listed in the AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2000-23-07, amendment
39-11977 (65 FR 68876, November 15, 2000). The existing AD applies to
[[Page 41119]]
certain Airbus Model A300 series airplanes and all Model A300-600 and
A310 series airplanes. That NPRM was published in the Federal Register
on January 25, 2006 (71 FR 4062). That NPRM proposed to require
repetitive inspections of the pitch trim system to detect continuity
defects in the autotrim function, and follow-on corrective actions if
necessary. That NPRM also proposed to require replacing the flight
augmentation computers (FACs) with new improved FACs on certain
airplanes.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Revise Applicability: Paragraph (c)(1)
The commenter, Airbus, requests that we revise paragraph (c)(1) of
the NPRM to retain the applicability of the existing AD for A300 B2-203
and A300 B4-203 airplanes. The applicability of AD 2000-23-07 for those
airplanes is:
Model A300 B2-203 and A300 B4-203 airplanes in a forward facing
cockpit version, as listed in Airbus Service Bulletin A300-22A0115,
Revision 02, dated March 7, 2000.
The applicability specified in paragraph (c)(1) of the NPRM omitted the
restriction ``in a forward facing cockpit version.'' The commenter
asserts that the mandatory actions for those airplanes are restated
from AD 2000-23-07, so no new requirements for those airplanes are
introduced in this AD.
We agree that this AD adds no new requirements for those airplanes.
In the revised applicability for those airplanes, the forward-facing-
cockpit restriction is removed because it is included in the service
bulletin effectivity. We have not revised the applicability specified
in the NPRM.
Request To Revise Applicability: Paragraph (c)(3)
The same commenter found a typographical error in the NPRM.
Paragraph (c)(3), which identifies affected A310-200 and -300 series
airplanes by their associated modification number, should have referred
to Modification 12931 instead of Modification 12932.
We acknowledge this error and have revised this final rule
accordingly.
Additional Changes to NPRM
The requirements of paragraph (f) of the NPRM would apply to
``airplanes subject to the requirements of AD 2000-23-07,'' which
include:
Model A300 B2-203 and A300 B4-203 airplanes in a forward-
facing cockpit configuration;
All Model A310-200 and -300 series airplanes; and
Model A300-600 series airplanes, except those with
Modification 12277 installed in production.
We have revised this description to clarify the affected airplanes.
Once an AD is superseded, no airplane is subject to its requirements,
and it may not be possible for operators to obtain a copy to identify
the affected airplanes and requirements. Because AD compliance records
must be maintained permanently and transferred with airplanes,
operators must always be able to determine whether a particular AD has
been accomplished, even after it has been superseded. Therefore, we
have revised paragraph (f) in this final rule to more precisely
describe the airplanes affected by that requirement.
We have also clarified paragraph (g) in this final rule by
introducing the paragraph with the airplanes affected by this new
requirement. Those airplanes are also identified in Table 1 of the AD.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 86 airplanes of U.S. registry. The following
table provides the estimated costs for U.S. operators to comply with
this AD.
Cost Estimates
--------------------------------------------------------------------------------------------------------------------------------------------------------
Hourly
Action Service bulletins Work labor Parts cost Total per airplane
hours rate
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle..... A300-22A6042, A300-22A0115, 1 $65 None.............. $65, per inspection cycle.
A310-22A2053.
FAC replacement...................... A300-22-6050, A310-22-2058.. 9 65 $2,677............ $3,262.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
[[Page 41120]]
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-11977 (65 FR 68876, November 15, 2000) and by
adding the following new airworthiness directive (AD):
2006-15-06 Airbus: Amendment 39-14686. Docket No. FAA-2006-23675;
Directorate Identifier 2001-NM-320-AD.
Effective Date
(a) This AD becomes effective August 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 12931.
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 Model A300 B2-203 and A300 B4-203 airplanes in a
forward-facing cockpit configuration; all Model A310-200 and -300
series airplanes; and Model A300-600 series airplanes, except those
with Modification 12277 installed in production: 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) For airplanes identified in paragraphs (c)(2) and (c)(3) of
this AD: 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
------------------------------------------------------------------------
Required
compliance time
Airplane model/ Configuration after the
series effective date of
this AD
------------------------------------------------------------------------
A300-600.......... Without accomplishment of 24 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.
With accomplishment of Airbus 36 months.
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 of 24 months.
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 Airbus 36 months.
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.
------------------------------------------------------------------------
Part Installation
(h) On or after the effective date of this AD, no person may
install, on any airplane, any FAC having part number (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
[[Page 41121]]
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.
Material Incorporated by Reference
(k) You must use the documents identified in Table 2 of this AD,
as applicable, to perform the actions that are required by this AD,
unless the AD specifies otherwise.
Table 2.--Documents Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A300-22-6050............................. Original....................... October 8, 2004.
A300-22A0115............................. 02, including Appendix 01...... March 7, 2000.
A300-22A6042............................. 01, including Appendix 01...... March 7, 2000.
A310-22-2058............................. Original....................... April 6, 2005.
A310-22A2053............................. 01, including Appendix 01...... March 7, 2000.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the documents identified in Table 3 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 3.--New Documents Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A300-22-6050............................. Original....................... October 8, 2004.
A310-22-2058............................. Original....................... April 6, 2005.
----------------------------------------------------------------------------------------------------------------
(2) On December 20, 2000 (65 FR 68876, November 15, 2000), the
Director of the Federal Register approved the incorporation by
reference of the documents identified in Table 4 of this AD.
Table 4.--Documents Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A300-22A0115............................. 02, including Appendix 01...... March 7, 2000.
A300-22A6042............................. 01, including Appendix 01...... March 7, 2000.
A310-22A2053............................. 01, including Appendix 01...... March 7, 2000.
----------------------------------------------------------------------------------------------------------------
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on July 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11414 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P
