Airworthiness Directives; Airbus Model A300 Airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Airplanes, 29112-29116 [E9-13146]
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<![CDATA[
29112
Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations
consulting with employing agencies and
determining that this would give
agencies sufficient time to modify their
personnel and payroll systems to
provide for immediate agency
contributions. That is, in order to
efficiently administer the Thrift Savings
Plan and to carry out his responsibilities
as Executive Director, he determined it
necessary to give employing agencies
sufficient time to modify their computer
systems to carry out the requirements of
this regulation and the law that was
passed by the House less than eighteen
hours after it was passed by the Senate.
This flexibility will also benefit those
participants whose employing agencies
are capable of implementing sooner.
That is, their employing agencies may
begin making contributions on behalf of
these employees as soon as practicable.
Providing implementing flexibility is
consistent with the grant of authority
given to the Executive Director by the
Thrift Savings Plan Enhancement Act of
2009. Section 102 of the Act provides
for ‘‘Automatic Enrollments and
Immediate Employing Agency
Contributions.’’ Immediate Employing
Agency Contributions was meant as an
enhancement to automatic enrollment.
For example, it envisions a 3 percent
default contribution rate in order to
provide participants with a dollar for
dollar match on their contributions. It
specifies that the default contribution
rate may not exceed 5 percent, which
would provide participants with the
greatest matching contributions allowed
by law. Section 102 gives the Executive
Director the authority to promulgate
regulations pertaining to automatic
enrollment. The Executive Director
relies on this authority as well as the
authorities specified above in
promulgating this regulation.
Regulatory Flexibility Act
I certify that these regulations will not
have a significant economic impact on
a substantial number of small entities.
They will affect only employees of the
Federal government and members of the
uniformed services.
cprice-sewell on PRODPC61 with RULES
Paperwork Reduction Act
I certify that these regulations do not
require additional reporting under the
criteria of the Paperwork Reduction Act.
Unfunded Mandates Reform Act of
1995
Pursuant to the Unfunded Mandates
Reform Act of 1995, 2 U.S.C. 602, 632,
653, 1501–1571, the effects of this
regulation on State, local, and Tribal
governments and the private sector have
been assessed. This regulation will not
compel the expenditure in any one year
VerDate Nov<24>2008
14:33 Jun 18, 2009
Jkt 217001
of $100 million or more by State, local,
and Tribal governments, in the
aggregate, or by the private sector.
Therefore, a statement under section
1532 is not required.
DEPARTMENT OF TRANSPORTATION
Submission to Congress and the
General Accounting Office
[Docket No. FAA–2008–1082; Directorate
Identifier 2007–NM–337–AD; Amendment
39–15925; AD 2009–12–02]
Pursuant to 5 U.S.C. 810(a)(1)(A), the
Agency submitted a report containing
this rule and other required information
to the U.S. Senate, the U.S. House of
Representatives, and the Comptroller
General of the United States before
publication of this rule in the Federal
Register. This rule is not a major rule as
defined at 5 U.S.C. 814(2).
RIN 2120–AA64
List of Subjects in 5 CFR Part 1600
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
Government employees, Pensions,
Retirement.
Gregory T. Long,
Executive Director, Federal Retirement Thrift
Investment Board.
For the reasons stated in the preamble,
the Federal Retirement Thrift
Investment Board amends part 1600 of
title 5 of the Code of Federal
Regulations as follows:
■
PART 1600—EMPLOYEE
CONTRIBUTION ELECTIONS AND
CONTRIBUTION ALLOCATIONS
1. The authority citation for part 1600
is revised to read as follows:
■
Authority: 5 U.S.C. 8351, 8432(a), 8432(b),
8432(c), 8432(j), 8474(b)(5) and (c)(1), Thrift
Savings Plan Enhancement Act of 2009,
section 102.
■
2. Revise § 1600.13 to read as follows:
§ 1600.13
Timing of agency contributions.
An employee appointed or
reappointed to a position covered by
FERS is immediately eligible to receive
agency contributions. In order to enable
agencies to modify their personnel and
payroll systems, agencies must
implement this regulation as soon as
practicable, but in no case later than the
first full pay period in August 2009.
Effective with the first full pay period of
August 2009, all eligible employees
must receive immediate agency
contributions.
[FR Doc. E9–14478 Filed 6–18–09; 8:45 am]
BILLING CODE 6760–01–P
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Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Airbus Model
A300 Airplanes; Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes);
and Model A310 Airplanes
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to the airplanes identified
above. That AD currently requires
revising the FAA-approved maintenance
program to include a new airplane
maintenance manual task that specifies
a detailed inspection after each ram air
turbine (RAT) retraction. That existing
AD also currently requires, for certain
airplanes, a one-time inspection to
detect breaks in the bottom flange fitting
of the RAT and corrective actions, if
necessary; for certain airplanes, an
adjustment of the ejection jack; and, for
certain other airplanes, replacement of
the aluminum part with an improved
steel part. This AD also continues to
require certain actions for additional
airplanes and revising the FAAapproved maintenance program to
include procedures for replacing the
RAT swivel coupling fork fitting with a
new steel part only. This AD results
from a report that an additional swivel
coupling of the RAT yoke fitting was
found cracked during the
accomplishment of the requirements of
the existing AD. We are issuing this AD
to prevent misrigging of the ejection jack
of the RAT and to ensure removal of any
RAT yoke fitting made from aluminum
material. Such conditions could result
in a broken or cracked swivel coupling
and consequent failure of the RAT yoke
fitting, which could result in the loss of
RAT function and possible loss of
critical flight control systems in the
event of certain emergency situations.
DATES: This AD becomes effective July
24, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 24, 2009.
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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations
For service information
identified in this AD, contact: Airbus
SAS—EAW (Airworthiness Office), 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51;
e-mail account.airwortheas@airbus.com; Internet https://
www.airbus.com.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
cprice-sewell on PRODPC61 with RULES
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2007–03–09, amendment
39–14920 (72 FR 5157, February 5,
2007). The existing AD applies to all
Model A300 airplanes; Model A300 B4–
601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–
605R Variant F airplanes; and Model
A310 airplanes. That NPRM was
published in the Federal Register on
October 10, 2008 (73 FR 60203). That
NPRM proposed to continue to require
revising the FAA-approved maintenance
program to include a new airplane
maintenance manual task that specifies
a detailed inspection after each ram air
turbine (RAT) retraction and, for certain
airplanes, to continue to require
replacing the aluminum yoke fitting of
the swivel coupling of the RAT with a
new steel yoke fitting. That NPRM also
proposed to require replacing the RAT
swivel coupling fork fitting for
additional airplanes and revising the
FAA-approved maintenance program to
include procedures for replacing the
RAT swivel coupling fork fitting with a
new steel part only.
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Actions Since NPRM Was Issued
The NPRM cited Airbus Mandatory
Service Bulletin A300–57–0244, dated
March 4, 2005, as the appropriate source
of service information for procedures to
replace the RAT swivel coupling fork
fitting with a new steel fitting. Airbus
has since revised that service bulletin.
Revision 01, dated September 3, 2007,
of that service bulletin includes revised
installation procedures. The procedures
in Revision 02, dated November 19,
2007, of that service bulletin are
essentially the same as those in Revision
01, dated September 3, 2007.
We have revised paragraphs (f) and
(h) of this AD to refer to Revision 02 of
Airbus Mandatory Service Bulletin
A300–57–0244. We have also added a
new paragraph (k) to this AD to give
credit for actions done in accordance
with Revision 01 of Airbus Mandatory
Service Bulletin A300–57–0244.
We have also revised paragraph (f) to
refer to Airbus Mandatory Service
Bulletins A310–57–2086, Revision 01,
dated September 3, 2007; and A300–57–
6099, Revision 01, dated September 3,
2007. We referred to the original issue
of Airbus Mandatory Service Bulletin
A310–57–2086, dated March 1, 2005;
and Airbus Mandatory Service Bulletin
A300–57–6099, dated February 23,
2005; for the replacement in paragraph
(f) of the NPRM. The replacement
procedures specified in Revision 01 of
these service bulletins are identical to
those in the original issue of these
service bulletins.
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 the Applicability
Airbus requests that modification
19578 be removed from Table 1 in the
NPRM because this modification applies
to the A300F4–608ST model only. This
model is not included on any U.S.-type
certificate and is not referenced in
paragraph (c) of the NPRM.
We agree. Airbus Model A300F4–
608ST is not included on any U.S.-type
certificate; therefore, we have removed
the reference to the modification for this
model from Table 1 of this AD.
Request for Revising Requirements
The Air Transport Association (ATA),
on behalf of its member American
Airlines (AA), requests that paragraph
(g) of the NPRM be revised to coincide
with the requirements of paragraph (k)
of the NPRM. AA finds that paragraphs
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29113
(g) and (k) of the NPRM require similar
actions.
AA states that paragraph (g) of the
NPRM would require changes to the
FAA-approved maintenance program;
specifically, changes to select AMM
chapters are required, with a mandate to
replace broken yoke fittings with new
steel or aluminum parts. AA states that
these AMM chapters are cited by both
page block and date. AA states that
paragraph (k) of the NPRM would
similarly require changes to the
maintenance program, and also would
mandate changes to AMM sections;
however, in paragraph (k) of the NPRM,
specific revision dates of the AMM
sections in question are not discussed.
AA states that furthermore, paragraph
(k) of the NPRM would require that a
broken yoke be replaced with only a
new steel part; paragraph (g) of the
NPRM would authorize the use of an
aluminum part. AA states that the
requirements of paragraph (k) of the
NPRM include the updated requirement
to use only the steel yoke as a
replacement. AA also states that
paragraph (k) of the NPRM, unlike
paragraph (g) of the NPRM, does not cite
specific revision dates, allowing
operators necessary latitude for
incorporating future AMM revisions.
We find that clarification is necessary.
Paragraph (g) of this final rule restates
the requirements from superseded AD
2007–03–09, and paragraph (l) of this
final rule (referred to as paragraph (k) in
the NPRM) provides the new
requirements. Performing the actions in
paragraph (l) of this AD terminates the
requirements of paragraph (g) of this
AD. However, the requirements of
paragraph (g) of this AD must be
retained to ensure that applicable
requirements of this AD are done.
Paragraph (g) of this final rule states that
the actions must be accomplished in
accordance with the service
information; therefore that service
information contains specific revision
numbers and dates. Paragraph (k)
provides additional information;
therefore, that information does not
contain specific dates.
We have clarified paragraphs (g) and
(l) of this AD to specify the actions are
to be done in accordance with a method
approved by the FAA or Direction
´ ´
Generale de l’Aviation Civile (DGAC) or
European Aviation Safety Agency
(EASA). Also, we have added Notes 2
and 4 of this final rule to specify where
the information pertaining to the
replacement and inspection procedures
can be found.
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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations
Request for Alternative Replacement
Procedures
The ATA, on behalf of its member
AA, requests that the yoke replacement
not be limited to the accomplishment
procedures contained in Airbus
Mandatory Service Bulletin A300–57–
6099. AA requests that alternative
replacement procedures be incorporated
into the final rule.
We disagree. We find that the
procedures included Airbus Mandatory
Service Bulletin A300–57–6099 provide
an adequate level of safety. However, we
have no evidence that any alternative
procedures not included in that service
bulletin would provide an adequate
level of safety. An operator may apply
for approval of an alternative method of
compliance (AMOC) in accordance with
the procedures outlined in paragraph
(m) of this AD. We have not changed the
final rule regarding this issue.
moved Note 1 to the applicability
section.
Explanation of Changes to Paragraphs
(g) and (l) of This AD and Additions of
Note 2 and Note 4 in This AD
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.
We have revised paragraphs (g) and (l)
of this AD and have added Note 2 and
Note 4 to this AD to clarify the
requirements of those paragraphs. The
revised paragraphs (g) and (l) specify the
actions are to be done in accordance
with a method approved by the FAA.
However, we have added Notes 2 and 4
to specify where information pertaining
to the replacement and inspection
procedures can be found. We have also
Conclusion
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Average labor
rate per hour
Work hours
Replacement ......................
Revision of FAA-approved
maintenance program.
14
1
In consideration of the compliance
time and effective date for
accomplishing the replacement and
revision of the FAA-approved
maintenance program required by AD
2007–03–09 (retained in paragraphs (f)
and (g) of this AD), we assume that
operators of the affected airplanes have
already initiated the required actions.
The AD adds no new costs associated
with those airplanes.
cprice-sewell on PRODPC61 with RULES
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.
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$80
80
$470 ....................................
None ....................................
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.
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:
■
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Number of
U.S.-registered
airplanes
Cost per
airplane
Parts
$1,590
80
205
205
Fleet cost
$325,950
16,400
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14920 (72
FR 5157, February 5, 2007) and by
adding the following new airworthiness
directive (AD):
■
2009–12–02 Airbus: Amendment 39–15925.
Docket No. FAA–2008–1082; Directorate
Identifier 2007–NM–337–AD.
Effective Date
(a) This AD becomes effective July 24,
2009.
Affected ADs
(b) This AD supersedes AD 2007–03–09.
Applicability
(c) This AD applies to all Model A300
airplanes; Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes;
and Model A310 airplanes, certificated in
any category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (m) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529–1.
Unsafe Condition
(d) This AD results from a report that an
additional swivel coupling of the ram air
turbine (RAT) yoke fitting was found cracked
while accomplishing the requirements of the
existing AD. We are issuing this AD to
prevent misrigging of the ejection jack of the
RAT and to ensure removal of any RAT yoke
fitting made from aluminum material. Such
conditions could result in a broken or
cracked swivel coupling and consequent
failure of the RAT yoke fitting, which could
result in the loss of RAT function and
possible loss of critical flight control systems
in the event of certain emergency situations.
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.
Certain Requirements of AD 2007–03–09
Replacement
(f) For Model A300 airplanes, Model
A300–600 series airplanes, and Model A310
airplanes equipped with Dowty Rotol RATs,
except airplanes on which Airbus
Modification 12986 has been done: Within 12
months after March 12, 2007 (the effective
date of AD 2007–03–09), replace the RAT
swivel coupling fork fitting with a new steel
fitting, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0244, dated March
4, 2005, or Airbus Mandatory Service
Bulletin A300–57–0244, Revision 02, dated
November 19, 2007 (for Model A300
airplanes); Airbus Service Bulletin A300–57–
6099, dated February 23, 2005, or Airbus
Mandatory Service Bulletin A300–57–6099,
Revision 01, dated September 3, 2007 (for
Model A300–600 series airplanes); or Airbus
Service Bulletin A310–57–2086, dated March
1, 2005, or Airbus Mandatory Service
Bulletin A310–57–2086, Revision 01, dated
September 3, 2007 (for Model A310
airplanes); except as provided by paragraph
(h) of this AD.
Revisions of FAA-Approved Maintenance
Program
(g) For all airplanes: Within 3 months after
March 12, 2007, incorporate information into
the FAA-approved maintenance program to
specify an inspection for breaks of the bottom
flange of the RAT swivel coupling yoke
fitting after each RAT retraction; and
replacement of the RAT swivel coupling yoke
fitting with a new aluminum or steel part as
applicable; in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
´ ´
Directorate, FAA; or the Direction Generale
de l’Aviation Civile (or its delegated agent);
or the European Aviation Safety Agency (or
its delegated agent). Thereafter, except as
provided by paragraphs (l) and (m) of this
AD, no alternative inspection intervals may
be approved for the bottom flange of the RAT
swivel coupling yoke fitting.
Note 2: Guidance on the inspection and
replacement procedures specified in
paragraph (g) of this AD can be found in
these documents as applicable:
• Airbus A300–600 Aircraft Maintenance
Manual (AMM), Chapter 29–25–00, Page
Block 301, dated June 1, 2005.
29115
• Airbus A310 AMM, Chapter 29–25–00,
Page Block 301, dated June 1, 2005.
• Airbus A300 AMM Chapter 29–25–00,
Page Block 301, dated March 1, 2006.
Note 3: After revising the maintenance
program to include the required periodic
inspections according to paragraph (g) or (l)
of this AD, operators do not need to make a
maintenance log entry to show compliance
with this AD every time those inspections are
accomplished thereafter.
New Requirements of This AD
Revised Service Bulletins
(h) As of the effective date of this AD, use
only the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310–57–
2086, Revision 01, dated September 3, 2007
(for Model A310 series airplanes); Airbus
Mandatory Service Bulletin A300–57–6099,
Revision 01, dated September 3, 2007 (for
Model A300–600 series airplanes); or Airbus
Mandatory Service Bulletin A300–57–0244,
Revision 02, dated November 19, 2007 (for
Model A300 airplanes), to do the
replacement required by paragraph (f) of this
AD.
Replacement
(i) For airplanes identified in Table 1 of
this AD: Before 102 months since first flight,
or within 12 months after the effective date
of this AD, whichever occurs later, replace
the aluminum yoke fitting of the swivel
coupling of the RAT with a new steel yoke
fitting, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–57–2086,
Revision 01, dated September 3, 2007 (for
Model A310 series airplanes); or Airbus
Mandatory Service Bulletin A300–57–6099,
Revision 01, dated September 3, 2007 (for
Model A300–600 series airplanes).
TABLE 1—AIRPLANES AFFECTED BY THE REQUIREMENTS OF PARAGRAPH (I) OF THIS AD
Except for those airplanes on which—
Or on which—
(1) A310 series airplanes equipped with Hamilton Sundstrand RAT.
Airbus Modification 12986 has been done in
production.
(2) A300–600 series airplanes equipped with
Hamilton Sundstrand RAT.
cprice-sewell on PRODPC61 with RULES
Model—
Airbus Modification 12986 has been done in
production.
Airbus Service Bulletin A310-57-2086, dated
March 1, 2005; or Airbus Mandatory Service Bulletin A310-57-2086, Revision 01,
dated September 3, 2007; has been done
in service.
Airbus Service Bulletin A300-57-6099, dated
February 23, 2005; or Airbus Mandatory
Service Bulletin A300-57-6099, Revision 01,
dated September 3, 2007; has been done
in service.
Credit for Actions Performed According to
Previous Service Bulletins
(j) Replacements done before the effective
date of this AD in accordance with Airbus
Service Bulletin A310–57–2086, dated March
1, 2005 (for Model A310 series airplanes); or
Airbus Service Bulletin A300–57–6099,
dated February 23, 2005 (for Model A300–
600 series airplanes); are acceptable for
compliance with the requirements of
paragraph (i) of this AD.
(k) Replacements done before the effective
date of this AD in accordance with Airbus
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14:33 Jun 18, 2009
Jkt 217001
Service Bulletin A300–57–0244, Revision 01,
dated September 3, 2007 (for Model A300
airplanes), are acceptable for compliance
with the requirements of paragraph (f) of this
AD for the affected airplanes.
Revision of FAA-Approved Maintenance
Program
(l) For all airplanes: Within 3 months after
the effective date of this AD, incorporate
information into the FAA-approved
maintenance program to specify an
inspection for breaks of the bottom flange of
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the RAT swivel coupling yoke fitting after
each RAT retraction; and replacement of the
RAT swivel coupling yoke fitting with a new
steel part; in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or European Aviation
Safety Agency (or its delegated agent).
Thereafter, except as provided by paragraph
(m) of this AD, no alternative inspection
intervals may be approved for the bottom
flange of the RAT swivel coupling yoke
fitting. Accomplishing this incorporation
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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations
terminates the requirements of paragraph (g)
of this AD.
Note 4: Guidance on the inspection and
replacement procedures specified in
paragraph (l) of this AD can be found in these
documents as applicable:
• Airbus A300–600 AMM, Chapter 29–25–
00, Page Block 301.
• Airbus A310 AMM, Chapter 29–25–00,
Page Block 301.
• Airbus A300 AMM Chapter 29–25–00,
Page Block 301.
Alternative Methods of Compliance
(AMOCs)
(m) The Manager, International Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1138; fax
(425) 227–1149. Before using any approved
AMOC on any airplane to which the AMOC
applies, notify your principal maintenance
inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight
Standards District Office. The AMOC
approval letter must specifically reference
this AD.
Related Information
(n) European Aviation Safety Agency
(EASA) airworthiness directive 2007–0273,
dated October 23, 2007, and French
airworthiness directive F–2005–089, dated
June 8, 2005, also address the subject of this
AD.
Material Incorporated by Reference
(o) You must use the service information
contained in Table 2 of this AD to do the
actions required by this AD, as applicable,
unless the AD specifies otherwise.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Airbus Mandatory Service Bulletin A300–57–0244 ...................................................................................
Airbus Mandatory Service Bulletin A300–57–6099 ...................................................................................
Airbus Mandatory Service Bulletin A310–57–2086 ...................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at 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 May 20,
2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–13146 Filed 6–18–09; 8:45 am]
cprice-sewell on PRODPC61 with RULES
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0261 Directorate
Identifier 2009–CE–017–AD; Amendment
39–15943; AD 2009–13–04]
RIN 2120–AA64
Airworthiness Directives; Dornier
Luftfahrt GmbH Models Dornier 228–
100, Dornier 228–101, Dornier 228–200,
Dornier 228–201, Dornier 228–202, and
Dornier 228–212 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
14:33 Jun 18, 2009
Jkt 217001
02
01
01
November 19, 2007.
September 3, 2007.
September 3, 2007.
On July 24, 2009, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Greg
Davison, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; fax: (816)
329–4090.
SUPPLEMENTARY INFORMATION:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Discussion
Excessive wear on a guide pin of a power
lever has been detected during inspections.
The total loss of the pin could cause loss of
the flight idle stop and lead to inadvertent
activation of the beta mode in flight. The
inadvertent activation of beta mode in flight
can result in loss of control of the airplane.
Excessive wear on a guide pin of a power
lever has been detected during inspections.
The total loss of the pin could cause loss of
the flight idle stop and lead to inadvertent
activation of the beta mode in flight. The
inadvertent activation of beta mode in flight
can result in loss of control of the airplane.
For the reasons described above, this new
EASA Airworthiness Directive (AD)
introduces a repetitive detailed inspection of
the guide pins of the power and condition
levers and requires the replacement of the
pins that exceed the allowable wear-limits.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
24, 2009.
VerDate Nov<24>2008
Date
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
We issued a supplemental notice of
proposed rulemaking (NPRM) to amend
14 CFR part 39 to include an AD that
would apply to the specified products.
That NPRM was published in the
Federal Register on April 23, 2009 (74
FR 18477). That NPRM proposed to
correct an unsafe condition for the
specified products. The MCAI states:
E:\FR\FM\19JNR1.SGM
19JNR1
]]>Agencies
[Federal Register Volume 74, Number 117 (Friday, June 19, 2009)]
[Rules and Regulations]
[Pages 29112-29116]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-13146]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-337-AD;
Amendment 39-15925; AD 2009-12-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Airplanes; Model A300
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R Variant F Airplanes (Collectively Called A300-600 Series
Airplanes); and Model A310 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 the airplanes identified above. That AD
currently requires revising the FAA-approved maintenance program to
include a new airplane maintenance manual task that specifies a
detailed inspection after each ram air turbine (RAT) retraction. That
existing AD also currently requires, for certain airplanes, a one-time
inspection to detect breaks in the bottom flange fitting of the RAT and
corrective actions, if necessary; for certain airplanes, an adjustment
of the ejection jack; and, for certain other airplanes, replacement of
the aluminum part with an improved steel part. This AD also continues
to require certain actions for additional airplanes and revising the
FAA-approved maintenance program to include procedures for replacing
the RAT swivel coupling fork fitting with a new steel part only. This
AD results from a report that an additional swivel coupling of the RAT
yoke fitting was found cracked during the accomplishment of the
requirements of the existing AD. We are issuing this AD to prevent
misrigging of the ejection jack of the RAT and to ensure removal of any
RAT yoke fitting made from aluminum material. Such conditions could
result in a broken or cracked swivel coupling and consequent failure of
the RAT yoke fitting, which could result in the loss of RAT function
and possible loss of critical flight control systems in the event of
certain emergency situations.
DATES: This AD becomes effective July 24, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 24, 2009.
[[Page 29113]]
ADDRESSES: For service information identified in this AD, contact:
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail account.airworth-eas@airbus.com; Internet https://www.airbus.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2007-03-09, amendment
39-14920 (72 FR 5157, February 5, 2007). The existing AD applies to all
Model A300 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and
Model A310 airplanes. That NPRM was published in the Federal Register
on October 10, 2008 (73 FR 60203). That NPRM proposed to continue to
require revising the FAA-approved maintenance program to include a new
airplane maintenance manual task that specifies a detailed inspection
after each ram air turbine (RAT) retraction and, for certain airplanes,
to continue to require replacing the aluminum yoke fitting of the
swivel coupling of the RAT with a new steel yoke fitting. That NPRM
also proposed to require replacing the RAT swivel coupling fork fitting
for additional airplanes and revising the FAA-approved maintenance
program to include procedures for replacing the RAT swivel coupling
fork fitting with a new steel part only.
Actions Since NPRM Was Issued
The NPRM cited Airbus Mandatory Service Bulletin A300-57-0244,
dated March 4, 2005, as the appropriate source of service information
for procedures to replace the RAT swivel coupling fork fitting with a
new steel fitting. Airbus has since revised that service bulletin.
Revision 01, dated September 3, 2007, of that service bulletin includes
revised installation procedures. The procedures in Revision 02, dated
November 19, 2007, of that service bulletin are essentially the same as
those in Revision 01, dated September 3, 2007.
We have revised paragraphs (f) and (h) of this AD to refer to
Revision 02 of Airbus Mandatory Service Bulletin A300-57-0244. We have
also added a new paragraph (k) to this AD to give credit for actions
done in accordance with Revision 01 of Airbus Mandatory Service
Bulletin A300-57-0244.
We have also revised paragraph (f) to refer to Airbus Mandatory
Service Bulletins A310-57-2086, Revision 01, dated September 3, 2007;
and A300-57-6099, Revision 01, dated September 3, 2007. We referred to
the original issue of Airbus Mandatory Service Bulletin A310-57-2086,
dated March 1, 2005; and Airbus Mandatory Service Bulletin A300-57-
6099, dated February 23, 2005; for the replacement in paragraph (f) of
the NPRM. The replacement procedures specified in Revision 01 of these
service bulletins are identical to those in the original issue of these
service bulletins.
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 the Applicability
Airbus requests that modification 19578 be removed from Table 1 in
the NPRM because this modification applies to the A300F4-608ST model
only. This model is not included on any U.S.-type certificate and is
not referenced in paragraph (c) of the NPRM.
We agree. Airbus Model A300F4-608ST is not included on any U.S.-
type certificate; therefore, we have removed the reference to the
modification for this model from Table 1 of this AD.
Request for Revising Requirements
The Air Transport Association (ATA), on behalf of its member
American Airlines (AA), requests that paragraph (g) of the NPRM be
revised to coincide with the requirements of paragraph (k) of the NPRM.
AA finds that paragraphs (g) and (k) of the NPRM require similar
actions.
AA states that paragraph (g) of the NPRM would require changes to
the FAA-approved maintenance program; specifically, changes to select
AMM chapters are required, with a mandate to replace broken yoke
fittings with new steel or aluminum parts. AA states that these AMM
chapters are cited by both page block and date. AA states that
paragraph (k) of the NPRM would similarly require changes to the
maintenance program, and also would mandate changes to AMM sections;
however, in paragraph (k) of the NPRM, specific revision dates of the
AMM sections in question are not discussed. AA states that furthermore,
paragraph (k) of the NPRM would require that a broken yoke be replaced
with only a new steel part; paragraph (g) of the NPRM would authorize
the use of an aluminum part. AA states that the requirements of
paragraph (k) of the NPRM include the updated requirement to use only
the steel yoke as a replacement. AA also states that paragraph (k) of
the NPRM, unlike paragraph (g) of the NPRM, does not cite specific
revision dates, allowing operators necessary latitude for incorporating
future AMM revisions.
We find that clarification is necessary. Paragraph (g) of this
final rule restates the requirements from superseded AD 2007-03-09, and
paragraph (l) of this final rule (referred to as paragraph (k) in the
NPRM) provides the new requirements. Performing the actions in
paragraph (l) of this AD terminates the requirements of paragraph (g)
of this AD. However, the requirements of paragraph (g) of this AD must
be retained to ensure that applicable requirements of this AD are done.
Paragraph (g) of this final rule states that the actions must be
accomplished in accordance with the service information; therefore that
service information contains specific revision numbers and dates.
Paragraph (k) provides additional information; therefore, that
information does not contain specific dates.
We have clarified paragraphs (g) and (l) of this AD to specify the
actions are to be done in accordance with a method approved by the FAA
or Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) or
European Aviation Safety Agency (EASA). Also, we have added Notes 2 and
4 of this final rule to specify where the information pertaining to the
replacement and inspection procedures can be found.
[[Page 29114]]
Request for Alternative Replacement Procedures
The ATA, on behalf of its member AA, requests that the yoke
replacement not be limited to the accomplishment procedures contained
in Airbus Mandatory Service Bulletin A300-57-6099. AA requests that
alternative replacement procedures be incorporated into the final rule.
We disagree. We find that the procedures included Airbus Mandatory
Service Bulletin A300-57-6099 provide an adequate level of safety.
However, we have no evidence that any alternative procedures not
included in that service bulletin would provide an adequate level of
safety. An operator may apply for approval of an alternative method of
compliance (AMOC) in accordance with the procedures outlined in
paragraph (m) of this AD. We have not changed the final rule regarding
this issue.
Explanation of Changes to Paragraphs (g) and (l) of This AD and
Additions of Note 2 and Note 4 in This AD
We have revised paragraphs (g) and (l) of this AD and have added
Note 2 and Note 4 to this AD to clarify the requirements of those
paragraphs. The revised paragraphs (g) and (l) specify the actions are
to be done in accordance with a method approved by the FAA. However, we
have added Notes 2 and 4 to specify where information pertaining to the
replacement and inspection procedures can be found. We have also moved
Note 1 to the applicability section.
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
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement............................... 14 $80 $470........................ $1,590 205 $325,950
Revision of FAA-approved maintenance 1 80 None........................ 80 205 16,400
program.
--------------------------------------------------------------------------------------------------------------------------------------------------------
In consideration of the compliance time and effective date for
accomplishing the replacement and revision of the FAA-approved
maintenance program required by AD 2007-03-09 (retained in paragraphs
(f) and (g) of this AD), we assume that operators of the affected
airplanes have already initiated the required actions. The AD adds no
new costs associated with those airplanes.
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.
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 39-14920 (72 FR 5157, February 5, 2007) and by
adding the following new airworthiness directive (AD):
2009-12-02 Airbus: Amendment 39-15925. Docket No. FAA-2008-1082;
Directorate Identifier 2007-NM-337-AD.
Effective Date
(a) This AD becomes effective July 24, 2009.
Affected ADs
(b) This AD supersedes AD 2007-03-09.
Applicability
(c) This AD applies to all Model A300 airplanes; Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R Variant F airplanes; and Model A310 airplanes, certificated
in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the
[[Page 29115]]
inspections described in the revisions. In this situation, to comply
with 14 CFR 91.403(c), the operator must request approval for an
alternative method of compliance according to paragraph (m) of this
AD. The request should include a description of changes to the
required inspections that will ensure the continued damage tolerance
of the affected structure. The FAA has provided guidance for this
determination in Advisory Circular (AC) 25-1529-1.
Unsafe Condition
(d) This AD results from a report that an additional swivel
coupling of the ram air turbine (RAT) yoke fitting was found cracked
while accomplishing the requirements of the existing AD. We are
issuing this AD to prevent misrigging of the ejection jack of the
RAT and to ensure removal of any RAT yoke fitting made from aluminum
material. Such conditions could result in a broken or cracked swivel
coupling and consequent failure of the RAT yoke fitting, which could
result in the loss of RAT function and possible loss of critical
flight control systems in the event of certain emergency situations.
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.
Certain Requirements of AD 2007-03-09
Replacement
(f) For Model A300 airplanes, Model A300-600 series airplanes,
and Model A310 airplanes equipped with Dowty Rotol RATs, except
airplanes on which Airbus Modification 12986 has been done: Within
12 months after March 12, 2007 (the effective date of AD 2007-03-
09), replace the RAT swivel coupling fork fitting with a new steel
fitting, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-0244, dated March 4, 2005, or Airbus
Mandatory Service Bulletin A300-57-0244, Revision 02, dated November
19, 2007 (for Model A300 airplanes); Airbus Service Bulletin A300-
57-6099, dated February 23, 2005, or Airbus Mandatory Service
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for
Model A300-600 series airplanes); or Airbus Service Bulletin A310-
57-2086, dated March 1, 2005, or Airbus Mandatory Service Bulletin
A310-57-2086, Revision 01, dated September 3, 2007 (for Model A310
airplanes); except as provided by paragraph (h) of this AD.
Revisions of FAA-Approved Maintenance Program
(g) For all airplanes: Within 3 months after March 12, 2007,
incorporate information into the FAA-approved maintenance program to
specify an inspection for breaks of the bottom flange of the RAT
swivel coupling yoke fitting after each RAT retraction; and
replacement of the RAT swivel coupling yoke fitting with a new
aluminum or steel part as applicable; in accordance with a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (or its delegated agent); or the European
Aviation Safety Agency (or its delegated agent). Thereafter, except
as provided by paragraphs (l) and (m) of this AD, no alternative
inspection intervals may be approved for the bottom flange of the
RAT swivel coupling yoke fitting.
Note 2: Guidance on the inspection and replacement procedures
specified in paragraph (g) of this AD can be found in these
documents as applicable:
Airbus A300-600 Aircraft Maintenance Manual (AMM),
Chapter 29-25-00, Page Block 301, dated June 1, 2005.
Airbus A310 AMM, Chapter 29-25-00, Page Block 301,
dated June 1, 2005.
Airbus A300 AMM Chapter 29-25-00, Page Block 301, dated
March 1, 2006.
Note 3: After revising the maintenance program to include the
required periodic inspections according to paragraph (g) or (l) of
this AD, operators do not need to make a maintenance log entry to
show compliance with this AD every time those inspections are
accomplished thereafter.
New Requirements of This AD
Revised Service Bulletins
(h) As of the effective date of this AD, use only the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-57-2086, Revision 01, dated September 3, 2007 (for Model A310
series airplanes); Airbus Mandatory Service Bulletin A300-57-6099,
Revision 01, dated September 3, 2007 (for Model A300-600 series
airplanes); or Airbus Mandatory Service Bulletin A300-57-0244,
Revision 02, dated November 19, 2007 (for Model A300 airplanes), to
do the replacement required by paragraph (f) of this AD.
Replacement
(i) For airplanes identified in Table 1 of this AD: Before 102
months since first flight, or within 12 months after the effective
date of this AD, whichever occurs later, replace the aluminum yoke
fitting of the swivel coupling of the RAT with a new steel yoke
fitting, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-57-2086, Revision 01, dated
September 3, 2007 (for Model A310 series airplanes); or Airbus
Mandatory Service Bulletin A300-57-6099, Revision 01, dated
September 3, 2007 (for Model A300-600 series airplanes).
Table 1--Airplanes Affected by the Requirements of Paragraph (i) of This
AD
------------------------------------------------------------------------
Except for those
Model-- airplanes on which-- Or on which--
------------------------------------------------------------------------
(1) A310 series airplanes Airbus Modification Airbus Service
equipped with Hamilton 12986 has been done Bulletin
Sundstrand RAT. in production. A310[dash]57[dash]2
086, dated March 1,
2005; or Airbus
Mandatory Service
Bulletin
A310[dash]57[dash]2
086, Revision 01,
dated September 3,
2007; has been done
in service.
(2) A300-600 series Airbus Modification Airbus Service
airplanes equipped with 12986 has been done Bulletin
Hamilton Sundstrand RAT. in production. A300[dash]57[dash]6
099, dated February
23, 2005; or Airbus
Mandatory Service
Bulletin
A300[dash]57[dash]6
099, Revision 01,
dated September 3,
2007; has been done
in service.
------------------------------------------------------------------------
Credit for Actions Performed According to Previous Service Bulletins
(j) Replacements done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2086, dated March 1,
2005 (for Model A310 series airplanes); or Airbus Service Bulletin
A300-57-6099, dated February 23, 2005 (for Model A300-600 series
airplanes); are acceptable for compliance with the requirements of
paragraph (i) of this AD.
(k) Replacements done before the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-0244, Revision 01,
dated September 3, 2007 (for Model A300 airplanes), are acceptable
for compliance with the requirements of paragraph (f) of this AD for
the affected airplanes.
Revision of FAA-Approved Maintenance Program
(l) For all airplanes: Within 3 months after the effective date
of this AD, incorporate information into the FAA-approved
maintenance program to specify an inspection for breaks of the
bottom flange of the RAT swivel coupling yoke fitting after each RAT
retraction; and replacement of the RAT swivel coupling yoke fitting
with a new steel part; in accordance with a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or European Aviation Safety Agency (or its
delegated agent). Thereafter, except as provided by paragraph (m) of
this AD, no alternative inspection intervals may be approved for the
bottom flange of the RAT swivel coupling yoke fitting. Accomplishing
this incorporation
[[Page 29116]]
terminates the requirements of paragraph (g) of this AD.
Note 4: Guidance on the inspection and replacement procedures
specified in paragraph (l) of this AD can be found in these
documents as applicable:
Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301.
Airbus A310 AMM, Chapter 29-25-00, Page Block 301.
Airbus A300 AMM Chapter 29-25-00, Page Block 301.
Alternative Methods of Compliance (AMOCs)
(m) The Manager, International Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-1138; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
Related Information
(n) European Aviation Safety Agency (EASA) airworthiness
directive 2007-0273, dated October 23, 2007, and French
airworthiness directive F-2005-089, dated June 8, 2005, also address
the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information contained in Table 2 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 2--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300-57-0244. 02 November 19, 2007.
Airbus Mandatory Service Bulletin A300-57-6099. 01 September 3, 2007.
Airbus Mandatory Service Bulletin A310-57-2086. 01 September 3, 2007.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information at the
National Archives and Records Administration (NARA). For information
on the availability of this material at 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 May 20, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-13146 Filed 6-18-09; 8:45 am]
BILLING CODE 4910-13-P
