Airworthiness Directives; Airbus Model A340-211, -212, -311, and -312 Airplanes, 31171-31174 [E7-10754]
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31171
Rules and Regulations
Federal Register
Vol. 72, No. 108
Wednesday, June 6, 2007
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
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new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28354; Directorate
Identifier 2006–NM–245–AD; Amendment
39–15086; AD 2007–12–08]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A340–211, –212, –311, and –312
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A340–211, –212, –311, and –312
airplanes. The existing AD currently
requires an initial rotating probe
inspection and initial and repetitive
ultrasonic inspections for discrepancies
of the first fastener hole of the
horizontal flange of the keel beam on
previously modified airplanes,
installation of new fasteners, and
corrective action if necessary. This AD
retains the actions required by the
existing AD and adds new rotating
probe inspections and a terminating
action for the repetitive inspections of
the existing AD. This AD results from a
report that certain inspections, done
before accomplishing the modification
of the lower keel beam fitting and
forward lower shell connection,
revealed cracking that was outside the
modification limits specified in the
service bulletin; the cracking was
repaired by installing a titanium
doubler. We are issuing this AD to
prevent discrepancies of the fastener
holes of the horizontal flange of the keel
beam, which could result in reduced
structural integrity of the fuselage.
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This AD becomes effective June
21, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 21, 2007.
On October 27, 2005 (70 FR 59233,
October 12, 2005), the Director of the
Federal Register approved the
incorporation by reference of Airbus
Service Bulletin A340–57–4087,
including Appendix 01, dated
November 21, 2003.
We must receive comments on this
AD by August 6, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
On September 28, 2005, the FAA
issued AD 2005–20–27, amendment 39–
14324 (70 FR 59233, October 12, 2005).
That AD applies to certain Airbus
Model A340–211, –212, –311, and –312
airplanes. That AD requires an initial
rotating probe inspection and initial and
repetitive ultrasonic inspections for
discrepancies of the first fastener hole of
the horizontal flange of the keel beam
on previously modified airplanes,
installation of new fasteners, and
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corrective action if necessary. That AD
resulted from a report that certain
inspections done before accomplishing
the modification of the lower keel beam
fitting and forward lower shell
connection revealed cracking that was
outside the modification limits specified
in the service bulletin; the cracking was
repaired by installing a titanium
doubler. The actions specified in that
AD are intended to find and fix
discrepancies of the fastener holes of the
horizontal flange of the keel beam,
which could result in reduced structural
integrity of the fuselage.
Actions Since AD Was Issued
Since we issued that AD, further
manufacturer analysis of the keel beam/
center wing box (CWB) interface
determined that cold working of
additional fastener holes and
modifications of the CWB lower panel/
keel beam interface was needed to
adequately ensure structural integrity of
the airplane. These modifications would
provide terminating action for the
repetitive inspections required by the
existing AD.
Relevant Service Information
Airbus has issued Service Bulletin
A340–57–4099, dated March 27, 2006.
The service bulletin describes
procedures for disconnecting one
fastener from the keel beam/bottom skin
panel junction by reaming a hole in the
keel beam and oversizing fastener 5 of
the CWB lower panel, and for coldworking two adjacent fastener holes of
the CWB lower panel to install
interference fit fasteners. These
modifications include rotating probe
inspections, if applicable.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
We have also reviewed Airbus Service
Bulletin A340–57–4087, Revision 01,
including Appendix 01, dated February
15, 2005. (Service Bulletin A340–57–
4087, including Appendix 01, dated
November 21, 2003, was cited as the
appropriate source of service
information in AD 2005–20–27.)
Revision 01 is technically the same as
the original issue; revisions were made
only to the effectivity and certain
descriptive paragraphs.
The European Aviation Safety Agency
(EASA), which is the airworthiness
authority for the European Union,
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mandated the service information and
issued airworthiness directive 2006–
0314, dated October 13, 2006, to ensure
the continued airworthiness of these
airplanes in the European Union.
Therefore, we have revised paragraph
(h) of this AD to specify making repairs
using a method approved by either the
FAA, the DGAC (or its delegated agent),
or the EASA (or its delegated agent).
FAA’s Determination and Requirements
of This AD
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. As described in FAA Order
8100.14A, ‘‘Interim Procedures for
Working with the European Community
on Airworthiness Certification and
Continued Airworthiness,’’ dated
August 12, 2005, the EASA has kept the
FAA informed of the situation described
above. We have examined the EASA’s
findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
supersede AD 2005–20–27. This new
AD retains the requirements of the
existing AD. This AD also requires
accomplishing the actions specified in
Service Bulletin A340–57–4099,
described previously, except as
discussed under ‘‘Difference Between
AD and Service Bulletin A340–57–
4099.’’
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
For any affected airplane imported and
placed on the U.S. Register in the future,
the estimated costs to accomplish the
specified actions, at an average labor
rate of $80 per work hour, are as
follows:
For the actions required by AD 2005–
20–27 and retained by this AD: It takes
between 3 and 8 work hours per
airplane for the initial inspections and
about 2 work hours per airplane for each
repetitive inspection. Parts cost $190 for
each kit; two kits are required for
installing the new fasteners. Based on
these figures, the estimated cost of the
initial actions is between $620 and
$1,020 per airplane; and the estimated
cost of the repeat inspection is $160 per
airplane, per inspection cycle.
For the new actions required by this
AD: It takes between 14 and 29 work
hours per airplane to do the inspections
and modifications. Parts cost between
$1,250 and $1,680 per kit. Based on
these figures, the estimated cost of these
actions is between $2,370 and $4,000
per airplane.
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Difference Between AD and Service
Bulletin A340–57–4099
Service Bulletin A340–57–4099
specifies contacting the manufacturer
for disposition of certain repair
conditions; however, this AD would
require the repair of those conditions to
be accomplished per a method approved
by either the FAA or the EASA (or its
delegated agent). In light of the type of
repair that would be required to address
the identified unsafe condition, and in
consonance with existing bilateral
airworthiness agreements, the FAA has
determined that, for this AD, a repair
approved by either the FAA or the
EASA (or its delegated agent) would be
acceptable for compliance with the
requirements of paragraph (j) of this AD.
Explanation of Change Made to
Requirements of Existing AD
Paragraph (h) of the existing AD
specifies making repairs using a method
approved by the FAA or the Direction
Generale De L’Aviation Civile (DGAC)
(or its delegated agent). The European
Aviation Safety Agency (EASA) has
assumed responsibility for the airplane
models that would be subject to this AD.
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FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28354; Directorate Identifier
2006–NM–245–AD’’ at the beginning of
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your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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
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the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this 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:
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 39–14324 (70
FR 59233, October 12, 2005) and adding
the following new airworthiness
directive (AD):
I
2007–12–08 Airbus: Amendment 39–15086.
Docket No. FAA–2007–28354;
Directorate Identifier 2006–NM–245–AD.
Effective Date
(a) This AD becomes effective June 21,
2007.
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Affected ADs
(b) This AD supersedes AD 2005–20–27.
Applicability
(c) This AD applies to Airbus Model A340–
211, –212, –311, and –312 airplanes,
certificated in any category; serial numbers
0006, 0007 (right-hand side of the airplane
only), 0008 (left-hand side only), 0013, 0020,
0024 (left-hand side only), 0027 through 0029
inclusive, 0031, 0033, 0035, 0038 through
0040 inclusive, 0043, 0047, 0049, and 0052.
Unsafe Condition
(d) This AD results from a report that
certain inspections, done before
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15:16 Jun 05, 2007
Jkt 211001
accomplishing the modification of the lower
keel beam fitting and forward lower shell
connection, revealed cracking that was
outside the modification limits specified in
the service bulletin; the cracking was
repaired by installing a titanium doubler. We
are issuing this AD to prevent discrepancies
of the fastener holes of the horizontal flange
of the keel beam, which could result in
reduced structural integrity of the fuselage.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2005–
20–27
Initial/Repetitive Nondestructive Test
Inspections/Repair
(f) Within 5,420 flight cycles or 26,200
flight hours after accomplishing Airbus
Modification 43577, whichever is first:
Perform an initial rotating probe inspection
for discrepancies of the first fastener hole of
the horizontal flange of the keel beam by
doing all the actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–57–4087, dated
November 21, 2003; or Revision 01, dated
February 15, 2005. If no cracking is found,
before further flight, inspect for correct
fastener diameter tolerance; if the fastener
diameter is out of tolerance, before further
flight, ream to oversize the fastener holes and
install oversize fasteners in accordance with
the Accomplishment Instructions of the
service bulletin. Accomplishing the
modifications specified in paragraph (i) of
this AD ends the requirement for these
inspections.
(g) If no cracking is found during any
inspection required by paragraph (f) of this
AD: Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after accomplishing
the inspection, perform an initial ultrasonic
inspection for discrepancies of the first
fastener hole of the horizontal flange of the
keel beam by doing all the actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
57–4087, dated November 21, 2003; or
Revision 01, dated February 15, 2005. If no
cracking is found, repeat the ultrasonic
inspection thereafter at intervals not to
exceed 1,480 flight cycles or 7,400 flight
hours, whichever is first; until the
modifications required by paragraph (i) of
this AD are accomplished.
Repair Per the FAA; the Direction Generale
De L’Aviation Civile (DGAC); or the
European Aviation Safety Agency (EASA)
(h) If any cracking is found during any
inspection required by this AD: Before
further flight, repair per a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA;
the DGAC (or its delegated agent); or the
EASA (or its delegated agent). Within 1,480
flight cycles or 7,400 flight hours, whichever
is first, after repair of any cracking, perform
an ultrasonic inspection as required by
paragraph (g) of this AD. Repeat the
ultrasonic inspection thereafter at intervals
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31173
not to exceed 1,480 flight cycles or 7,400
flight hours, whichever is first; until the
actions required by paragraph (i) of this AD
are accomplished.
New Requirements of This AD
Modifications
(i) Within 118 months after the effective
date of this AD: Disconnect the keel beam
from the center wing box panel at fastener
hole 5, do applicable rotating probe
inspections, and do cold work and install
interference fit fasteners in two adjacent
fastener holes of the center wing box panel;
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
57–4099, dated March 27, 2006, except as
required by paragraph (j) of this AD.
Accomplishing these actions terminates the
inspection requirements of paragraphs (f), (g),
and (h) of this AD.
Repair
(j) If any crack is found during any action
required by paragraph (i) of this AD and
Service Bulletin A340–57–4099 specifies to
contact Airbus: Before further flight, repair
per a method approved by the Manager,
International Branch, ANM–116; the DGAC
(or its delegated agent); or the EASA (or its
delegated agent).
No Reporting Required
(k) Although Airbus Service Bulletin
A340–57–4087, dated November 21, 2003;
and Revision 01, dated February 15, 2005,
specify submitting an inspection report to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(m) The European Aviation Safety Agency
airworthiness directive 2006–0314, dated
October 13, 2006, also addresses the subject
of this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin
A340–57–4099, dated March 27, 2006;
Airbus Service Bulletin A340–57–4087,
including Appendix 01, dated November 21,
2003, and Airbus Service Bulletin A340–57–
4087, Revision 01, excluding Appendix 01,
dated February 15, 2005; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Airbus Service Bulletin A340–57–4099,
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dated March 27, 2006; and Airbus Service
Bulletin A340–57–4087, Revision 01,
excluding Appendix 01, dated February 15,
2005; in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On October 27, 2005 (70 FR 59233,
October 12, 2005), the Director of the Federal
Register approved the incorporation by
reference of Airbus Service Bulletin A340–
57–4087, including Appendix 01, dated
November 21, 2003.
(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 FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or 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/
cfr/ibr-locations.html.
Issued in Renton, Washington, on May 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10754 Filed 6–5–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25738; Directorate
Identifier 2006–NE–27–AD; Amendment 39–
15085; AD 2007–12–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2B
Series Turbofan Engines
Examining the AD Docket
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
rmajette on PROD1PC64 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF6–80C2B series turbofan engines with
electronic control units (ECUs),
installed on Boeing 747 and 767 series
airplanes. This AD requires installing
software version 8.2.Q1 to the engine
ECU, which increases the engine’s
margin to flameout. This AD results
from reports of engine flameout events
during flight, including reports of events
where all engines simultaneously
experienced a flameout or other adverse
operation. Though the root cause
investigation is not yet complete, we
believe exposure to ice crystals during
flight is associated with these flameout
events. We are issuing this AD to
provide increased margin to flameout,
which will minimize the potential of an
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15:16 Jun 05, 2007
Jkt 211001
all-engine flameout event caused by ice
accretion and shedding during flight.
DATES: This AD becomes effective July
11, 2007. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of July 11, 2007.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Company via Lockheed
Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax
(513) 672–8422.
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
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: John
Golinski, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: john.golinski@faa.gov;
telephone: (781) 238–7135, fax: (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80C2B series
turbofan engines with ECUs, installed
on Boeing 747 and 767 series airplanes.
We published the proposed AD in the
Federal Register on October 24, 2006
(71 FR 62215). That action proposed to
require installing software version
8.2.Q1 to the engine ECU, which
increases the engine’s margin to
flameout.
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located on the plaza
level of the Department of
Transportation Nassif Building at the
street address stated in ADDRESSES.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Comment That Corrective Actions
Should Be Expanded
One commenter, the Airline Pilots
Association, International, states that
the corrective action should be
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expanded in this AD to be fully
effective. The commenter states that the
prescribed modification addresses only
the flameout and restart issues, while
the problems of engine ice accretion and
compressor blade damage due to ice
shedding during operations, remain.
The commenter states that, due to the
severity of single- and dual-engine
flameout events, the FAA and GE must
examine the engine certification and
operating envelope to determine the
causes of ice accretions and compressor
blade damage while operating in an ice
crystal environment and continue to
develop a more comprehensive solution.
We do not agree. This AD considers
the ice accretion location, quantity, and
the potential of compressor blade
damage caused by impact with ice.
Paragraph (f) of this AD states that these
AD actions are interim actions due to
the on-going investigation, and that we
may take further rulemaking actions in
the future based on the results of the
investigation and field experience.
Request To Eliminate Certain Wording
Japan Airlines International (JAL)
requests that we eliminate ‘‘at the next
shop visit of the engine’’ in the
compliance section. Doing this would:
• Then allow operators to accomplish
the retrofit program on Boeing 767
series airplanes more aggressively; and
• Would facilitate completing the
program in the proposed 5-year
compliance period, without causing
aircraft on the ground (AOG) situations,
due to a shortage of spare ECUs.
JAL is concerned that there might be a
shortage of spare ECUs that could result
in grounded aircraft. JAL provided
information and data on their planned
retrofit for their fleet of Boeing 767 and
747 series airplanes.
We partially agree. Eliminating the
proposed wording would result in a less
aggressive replacement program for the
total population of engines. JAL did not
provide any supporting data of how this
change would result in a more
aggressive compliance program for
engines installed on the Boeing 767
airplanes. Our risk assessment indicates
that the risk presented by this unsafe
condition can be successfully managed
within the current and expected parts
availability. Therefore, we did not
change the AD.
In reviewing JAL’s comment, we
noted that our intent could be clarified.
We changed the AD to clarify that ECUs
installed with previous versions of
software can be installed on an engine
for a period of time.
The added paragraph in the AD
discusses two possible conditions: (1)
Reverting to previous versions of
E:\FR\FM\06JNR1.SGM
06JNR1
Agencies
[Federal Register Volume 72, Number 108 (Wednesday, June 6, 2007)]
[Rules and Regulations]
[Pages 31171-31174]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10754]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules
and Regulations
[[Page 31171]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28354; Directorate Identifier 2006-NM-245-AD;
Amendment 39-15086; AD 2007-12-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A340-211, -212, -311, and
-312 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to certain Airbus Model A340-211, -212, -311, and -
312 airplanes. The existing AD currently requires an initial rotating
probe inspection and initial and repetitive ultrasonic inspections for
discrepancies of the first fastener hole of the horizontal flange of
the keel beam on previously modified airplanes, installation of new
fasteners, and corrective action if necessary. This AD retains the
actions required by the existing AD and adds new rotating probe
inspections and a terminating action for the repetitive inspections of
the existing AD. This AD results from a report that certain
inspections, done before accomplishing the modification of the lower
keel beam fitting and forward lower shell connection, revealed cracking
that was outside the modification limits specified in the service
bulletin; the cracking was repaired by installing a titanium doubler.
We are issuing this AD to prevent discrepancies of the fastener holes
of the horizontal flange of the keel beam, which could result in
reduced structural integrity of the fuselage.
DATES: This AD becomes effective June 21, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 21, 2007.
On October 27, 2005 (70 FR 59233, October 12, 2005), the Director
of the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A340-57-4087, including Appendix 01, dated
November 21, 2003.
We must receive comments on this AD by August 6, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On September 28, 2005, the FAA issued AD 2005-20-27, amendment 39-
14324 (70 FR 59233, October 12, 2005). That AD applies to certain
Airbus Model A340-211, -212, -311, and -312 airplanes. That AD requires
an initial rotating probe inspection and initial and repetitive
ultrasonic inspections for discrepancies of the first fastener hole of
the horizontal flange of the keel beam on previously modified
airplanes, installation of new fasteners, and corrective action if
necessary. That AD resulted from a report that certain inspections done
before accomplishing the modification of the lower keel beam fitting
and forward lower shell connection revealed cracking that was outside
the modification limits specified in the service bulletin; the cracking
was repaired by installing a titanium doubler. The actions specified in
that AD are intended to find and fix discrepancies of the fastener
holes of the horizontal flange of the keel beam, which could result in
reduced structural integrity of the fuselage.
Actions Since AD Was Issued
Since we issued that AD, further manufacturer analysis of the keel
beam/center wing box (CWB) interface determined that cold working of
additional fastener holes and modifications of the CWB lower panel/keel
beam interface was needed to adequately ensure structural integrity of
the airplane. These modifications would provide terminating action for
the repetitive inspections required by the existing AD.
Relevant Service Information
Airbus has issued Service Bulletin A340-57-4099, dated March 27,
2006. The service bulletin describes procedures for disconnecting one
fastener from the keel beam/bottom skin panel junction by reaming a
hole in the keel beam and oversizing fastener 5 of the CWB lower panel,
and for cold-working two adjacent fastener holes of the CWB lower panel
to install interference fit fasteners. These modifications include
rotating probe inspections, if applicable. Accomplishing the actions
specified in the service information is intended to adequately address
the unsafe condition.
We have also reviewed Airbus Service Bulletin A340-57-4087,
Revision 01, including Appendix 01, dated February 15, 2005. (Service
Bulletin A340-57-4087, including Appendix 01, dated November 21, 2003,
was cited as the appropriate source of service information in AD 2005-
20-27.) Revision 01 is technically the same as the original issue;
revisions were made only to the effectivity and certain descriptive
paragraphs.
The European Aviation Safety Agency (EASA), which is the
airworthiness authority for the European Union,
[[Page 31172]]
mandated the service information and issued airworthiness directive
2006-0314, dated October 13, 2006, to ensure the continued
airworthiness of these airplanes in the European Union.
FAA's Determination and Requirements of This AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States. Therefore, we are issuing this AD to
supersede AD 2005-20-27. This new AD retains the requirements of the
existing AD. This AD also requires accomplishing the actions specified
in Service Bulletin A340-57-4099, described previously, except as
discussed under ``Difference Between AD and Service Bulletin A340-57-
4099.''
Difference Between AD and Service Bulletin A340-57-4099
Service Bulletin A340-57-4099 specifies contacting the manufacturer
for disposition of certain repair conditions; however, this AD would
require the repair of those conditions to be accomplished per a method
approved by either the FAA or the EASA (or its delegated agent). In
light of the type of repair that would be required to address the
identified unsafe condition, and in consonance with existing bilateral
airworthiness agreements, the FAA has determined that, for this AD, a
repair approved by either the FAA or the EASA (or its delegated agent)
would be acceptable for compliance with the requirements of paragraph
(j) of this AD.
Explanation of Change Made to Requirements of Existing AD
Paragraph (h) of the existing AD specifies making repairs using a
method approved by the FAA or the Direction Generale De L'Aviation
Civile (DGAC) (or its delegated agent). The European Aviation Safety
Agency (EASA) has assumed responsibility for the airplane models that
would be subject to this AD. Therefore, we have revised paragraph (h)
of this AD to specify making repairs using a method approved by either
the FAA, the DGAC (or its delegated agent), or the EASA (or its
delegated agent).
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future. For any affected airplane imported and placed on the U.S.
Register in the future, the estimated costs to accomplish the specified
actions, at an average labor rate of $80 per work hour, are as follows:
For the actions required by AD 2005-20-27 and retained by this AD:
It takes between 3 and 8 work hours per airplane for the initial
inspections and about 2 work hours per airplane for each repetitive
inspection. Parts cost $190 for each kit; two kits are required for
installing the new fasteners. Based on these figures, the estimated
cost of the initial actions is between $620 and $1,020 per airplane;
and the estimated cost of the repeat inspection is $160 per airplane,
per inspection cycle.
For the new actions required by this AD: It takes between 14 and 29
work hours per airplane to do the inspections and modifications. Parts
cost between $1,250 and $1,680 per kit. Based on these figures, the
estimated cost of these actions is between $2,370 and $4,000 per
airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2007-
28354; Directorate Identifier 2006-NM-245-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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
[[Page 31173]]
the States, on the relationship between the national government and the
States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this 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 39-14324 (70 FR 59233, October 12, 2005) and adding
the following new airworthiness directive (AD):
2007-12-08 Airbus: Amendment 39-15086. Docket No. FAA-2007-28354;
Directorate Identifier 2006-NM-245-AD.
Effective Date
(a) This AD becomes effective June 21, 2007.
Affected ADs
(b) This AD supersedes AD 2005-20-27.
Applicability
(c) This AD applies to Airbus Model A340-211, -212, -311, and -
312 airplanes, certificated in any category; serial numbers 0006,
0007 (right-hand side of the airplane only), 0008 (left-hand side
only), 0013, 0020, 0024 (left-hand side only), 0027 through 0029
inclusive, 0031, 0033, 0035, 0038 through 0040 inclusive, 0043,
0047, 0049, and 0052.
Unsafe Condition
(d) This AD results from a report that certain inspections, done
before accomplishing the modification of the lower keel beam fitting
and forward lower shell connection, revealed cracking that was
outside the modification limits specified in the service bulletin;
the cracking was repaired by installing a titanium doubler. We are
issuing this AD to prevent discrepancies of the fastener holes of
the horizontal flange of the keel beam, which could result in
reduced structural integrity of the fuselage.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2005-20-27
Initial/Repetitive Nondestructive Test Inspections/Repair
(f) Within 5,420 flight cycles or 26,200 flight hours after
accomplishing Airbus Modification 43577, whichever is first: Perform
an initial rotating probe inspection for discrepancies of the first
fastener hole of the horizontal flange of the keel beam by doing all
the actions in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A340-57-4087, dated November 21, 2003; or
Revision 01, dated February 15, 2005. If no cracking is found,
before further flight, inspect for correct fastener diameter
tolerance; if the fastener diameter is out of tolerance, before
further flight, ream to oversize the fastener holes and install
oversize fasteners in accordance with the Accomplishment
Instructions of the service bulletin. Accomplishing the
modifications specified in paragraph (i) of this AD ends the
requirement for these inspections.
(g) If no cracking is found during any inspection required by
paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after accomplishing the inspection,
perform an initial ultrasonic inspection for discrepancies of the
first fastener hole of the horizontal flange of the keel beam by
doing all the actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340-57-4087, dated November
21, 2003; or Revision 01, dated February 15, 2005. If no cracking is
found, repeat the ultrasonic inspection thereafter at intervals not
to exceed 1,480 flight cycles or 7,400 flight hours, whichever is
first; until the modifications required by paragraph (i) of this AD
are accomplished.
Repair Per the FAA; the Direction Generale De L'Aviation Civile (DGAC);
or the European Aviation Safety Agency (EASA)
(h) If any cracking is found during any inspection required by
this AD: Before further flight, repair per a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or
its delegated agent). Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after repair of any cracking, perform an
ultrasonic inspection as required by paragraph (g) of this AD.
Repeat the ultrasonic inspection thereafter at intervals not to
exceed 1,480 flight cycles or 7,400 flight hours, whichever is
first; until the actions required by paragraph (i) of this AD are
accomplished.
New Requirements of This AD
Modifications
(i) Within 118 months after the effective date of this AD:
Disconnect the keel beam from the center wing box panel at fastener
hole 5, do applicable rotating probe inspections, and do cold work
and install interference fit fasteners in two adjacent fastener
holes of the center wing box panel; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-57-4099,
dated March 27, 2006, except as required by paragraph (j) of this
AD. Accomplishing these actions terminates the inspection
requirements of paragraphs (f), (g), and (h) of this AD.
Repair
(j) If any crack is found during any action required by
paragraph (i) of this AD and Service Bulletin A340-57-4099 specifies
to contact Airbus: Before further flight, repair per a method
approved by the Manager, International Branch, ANM-116; the DGAC (or
its delegated agent); or the EASA (or its delegated agent).
No Reporting Required
(k) Although Airbus Service Bulletin A340-57-4087, dated
November 21, 2003; and Revision 01, dated February 15, 2005, specify
submitting an inspection report to the manufacturer, this AD does
not include that requirement.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(m) The European Aviation Safety Agency airworthiness directive
2006-0314, dated October 13, 2006, also addresses the subject of
this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin A340-57-4099, dated
March 27, 2006; Airbus Service Bulletin A340-57-4087, including
Appendix 01, dated November 21, 2003, and Airbus Service Bulletin
A340-57-4087, Revision 01, excluding Appendix 01, dated February 15,
2005; as applicable; to perform the actions that are required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Airbus Service Bulletin A340-57-4099,
[[Page 31174]]
dated March 27, 2006; and Airbus Service Bulletin A340-57-4087,
Revision 01, excluding Appendix 01, dated February 15, 2005; in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On October 27, 2005 (70 FR 59233, October 12, 2005), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A340-57-4087, including
Appendix 01, dated November 21, 2003.
(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 FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10754 Filed 6-5-07; 8:45 am]
BILLING CODE 4910-13-P