Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 Airplanes; and Model A340-200 and -300 Series Airplanes, 44731-44734 [E7-14866]
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<![CDATA[
Federal Register / Vol. 72, No. 153 / Thursday, August 9, 2007 / Rules and Regulations
(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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
(4) AMOCs approved previously in
accordance with AD 2001–14–22, are
approved as AMOCs for the corresponding
provisions of paragraphs (f) and (j) of this
AD.
(5) AMOCS approved previously in
accordance with AD 2006–12–12, are
approved as alternative methods of
compliance with this AD.
Material Incorporated by Reference
jlentini on PROD1PC65 with RULES
(m) You must use Boeing Alert Service
Bulletin 747–53A2451, including Appendix
A, dated October 5, 2000; or Boeing Alert
Service Bulletin 747–53A2451, Revision 1,
dated November 10, 2005; as applicable, to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) On July 17, 2006 (71 FR 33595, June 12,
2006), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2451,
Revision 1, dated November 10, 2005.
(2) On August 30, 2001 (66 FR 38891, July
26, 2001), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, 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/ibrlocations.html.
Issued in Renton, Washington, on July 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–15416 Filed 8–8–07; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
17:01 Aug 08, 2007
Jkt 211001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27741; Directorate
Identifier 2006–NM–261–AD; Amendment
39–15141; AD 2007–16–02]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–201, –202, –203, –223, –243,
–301, –321, –322, –323, –341, –342, and
–343 Airplanes; and Model A340–200
and –300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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 airworthiness authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as keel beam rupture, which
affects the structural integrity of the
area. We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
September 13, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 13, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
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
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
allow all FAA AD issuance processes to
meet legal, economic, Administrative
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Fmt 4700
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44731
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
We issued a 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 March 30, 2007 (72 FR
15067). That NPRM proposed to require
a repetitive special detailed inspection
on the horizontal flange of the keel
beam in the area of the first fastener
hole aft of FR (frame) 40, follow-up
actions (further inspections, installation
of new fasteners, and sealing the
fasteners), and repair if necessary. The
MCAI states that during the A330 and
A340 aircraft fatigue test, cracks
appeared on the right and left sides
between the crossing area of the keel
beam fitting and the front spar on the
center wing box (CWB). This situation if
not corrected can lead in the worst case
to keel beam rupture, which affects the
structural integrity of the area.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Refer to Revised MCAI
Airbus requests we refer to European
Aviation Safety Agency (EASA)
Airworthiness Directive 2006–0315 R1,
dated October 26, 2006, in the AD. (We
referred to EASA Airworthiness
Directive 2006–0315, dated October 13,
2006, in the NPRM.) Airbus notes that
Revision 1 of the EASA airworthiness
directive adds an optional terminating
action for the repetitive inspections.
We agree with Airbus, and have
revised this AD to refer to Revision 1 of
the EASA Airworthiness Directive.
Revision 1 refers to the following Airbus
Service Bulletins as the appropriate
sources of service information for doing
the optional terminating action: A330–
57–3090, dated March 27, 2006; and
A340–57–4098, dated March 27, 2006.
The modification can be done only on
airplanes without Airbus Modification
41652.
The optional terminating action is a
modification that involves
disconnecting one or more fasteners
from the keel beam/bottom skin panel
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Federal Register / Vol. 72, No. 153 / Thursday, August 9, 2007 / Rules and Regulations
junction, removing two adjacent
fasteners in order to perform cold
working, and installing interference fit
fasteners. The modification also
involves inspections and repairing any
cracking detected during the
modification; in some instances the
repair for cracking or for any bushing
that has a diameter beyond certain
limits specified in the service bulletin is
contacting Airbus for repair
instructions. We have added paragraph
(e)(6) to this AD, and revised paragraph
(d) of this AD to include the optional
terminating action. We have revised
paragraph (g) of this AD to refer to
Revision 1 of the MCAI.
Explanation of Change to Paragraph
(c)(3) ‘‘Applicability’’
When we issued the NPRM we noted
in paragraph (c)(3) that we were
considering rulemaking regarding EASA
airworthiness directive 2006–0314.
EASA airworthiness directive 2006–
0314 applies to Model A340–200 and
–300 series airplanes repaired in
accordance with certain Airbus repair
drawings, and paragraph (c)(3) of the
NPRM notes that those airplanes are not
affected by the current action. We have
since issued AD 2007–12–08,
amendment 39–15086 (72 FR 31171,
June 6, 2007), which is the parallel FAA
AD to EASA airworthiness directive
2006–0314. We have changed paragraph
(c)(3) of this AD to refer to AD 2007–12–
08.
jlentini on PROD1PC65 with RULES
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable in a U.S.
court of law. In making these changes,
we do not intend to differ substantively
from the information provided in the
MCAI and related service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
described in a separate paragraph of the
AD. These requirements, if any, take
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17:01 Aug 08, 2007
Jkt 211001
precedence over the actions copied from
the MCAI.
Costs of Compliance
We estimate that this AD will affect
about 9 products of U.S. registry. We
also estimate that it will take about 12
work-hours per product to comply with
this AD. The average labor rate is $80
per work-hour. Required parts will cost
about $382 per product. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$12,078, or $1,342 per product.
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 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.
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We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains the NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
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 FAA amends § 39.13 by adding
the following new AD:
I
2007–16–02 Airbus: Amendment 39–15141.
Docket No. FAA–2007–27741;
Directorate Identifier 2006–NM–261–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 13, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –321, –322, –323, –341,
–342, and –343 airplanes, all serial numbers,
except those on which Airbus modification
49202 has been embodied in production, or
Airbus Service Bulletin A330–57–3090 has
been embodied in service.
(2) Airbus Model A340–200 and –300
series airplanes, all certified models, all
serial numbers, except those on which
Airbus modification 49202 has been
embodied in production or Airbus Service
Bulletin A340–57–4098 has been embodied
in service.
(3) This AD does not apply to Model
A340–200 and –300 series airplanes repaired
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09AUR1
Federal Register / Vol. 72, No. 153 / Thursday, August 9, 2007 / Rules and Regulations
in accordance with Airbus Repair Drawing
R57115053, R57115051, or R57115047
(installation of titanium doubler). These
airplanes are covered by European Aviation
Safety Agency (EASA) airworthiness
directive 2006–0314, dated October 13, 2006.
On May 25, 2007, we issued AD 2007–12–08,
amendment 39–15086 (72 FR 31171, June 6,
2007), which is the parallel FAA AD to EASA
airworthiness directive 2006–0314.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states that
during the A330 and A340 aircraft fatigue
test, cracks appeared on the right and left
sides between the crossing area of the keel
beam fitting and the front spar on the center
wing box (CWB). This situation if not
corrected can lead in the worst case to keel
beam rupture which affects the structural
integrity of the area. In order to maintain the
structural integrity of the aircraft, the MCAI
requires a repetitive special detailed
inspection on the horizontal flange of the
keel beam in the area of the first fastener hole
aft of FR (frame) 40, follow-up actions, and
repair if necessary. The MCAI also includes
an optional terminating action for the
repetitive inspections.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Within the mandatory threshold (flight
cycles or flight hours) mentioned in the
paragraph 1.E.(2) of Airbus Service Bulletin
A340–57–4089, Revision 02; or A330–57–
3081, Revision 02; both dated January 24,
2006, depending on the configuration of the
aircraft model; or within 3 months after the
effective date of this AD; whichever occurs
later: Carry out the NDT (non-destructive
test) inspection of the hole(s) of the
horizontal flange of the keel beam located on
FR 40 datum on RH (right-hand) and/or LH
(left-hand) side of the fuselage, in accordance
with the instructions of Airbus Service
Bulletin A340–57–4089, Revision 02; or
A330–57–3081, Revision 02; as applicable.
Inspection in accordance with Airbus A330/
A340 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003; or 582.0651/
2002, Issue A, dated October 17, 2002;
satisfies the inspection requirements for the
first rotating probe inspection which is
specified at the inspection threshold of this
AD.
Note 1: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above inspection according to
recommended thresholds mentioned in
paragraph 1.E.(2) of Airbus Service Bulletin
A340–57–4089, Revision 02; or Airbus
Service Bulletin A330–57–3081, Revision 02;
both dated January 24, 2006.
(2) In case of any crack finding, before
further flight, contact Airbus in order to get
repair instructions before next flight, and
repair before further flight.
(3) Should no crack be detected:
(i) Before further flight: Follow up the
actions indicated in the flow charts, figure 7,
8, or 9, of Airbus Service Bulletin A340–57–
4089, including Appendix 01, Revision 02,
dated January 24, 2006; or figure 5, 6, or 7,
of Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006; in accordance with the
instructions of the applicable service
bulletin.
(ii) Within 30 days after the effective date
of this AD, or within 30 days after doing the
inspection required by paragraph (e)(1) of
this AD, whichever occurs later: Send the
report of actions carried out in paragraph
(e)(3)(i) of this AD to Airbus.
(iii) Renew the inspection at mandatory
intervals given in paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, Revision 02,
dated January 24, 2006; or Airbus Service
Bulletin A330–57–3081, Revision 02, dated
January 24, 2006; as applicable; in
accordance with the instructions of Service
Bulletin A340–57–4089, Revision 02, or
Service Bulletin A330–57–3081, Revision 02;
as applicable, and send the inspection results
to Airbus.
Note 2: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above repetitive inspection
according to recommended intervals
mentioned in paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, Revision 02,
dated January 24, 2006; or Airbus Service
Bulletin A330–57–3081, Revision 02, dated
January 24, 2006.
(4) Upon detection of a crack during a
repetitive inspection, before further flight,
contact Airbus to get repair instructions, and
repair before further flight.
(5) No additional work is required for
aircraft inspected in accordance with the
instructions of Airbus Service Bulletin A330–
57–3081, dated October 30, 2003, or Revision
01, dated May 18, 2004; or Airbus Service
Bulletin A340–57–4089, dated October 30,
2003, or Revision 01, dated March 2, 2004.
Nevertheless, the operators must check that
their inspection program is in accordance
with paragraph 1.E.(2) of Airbus Service
Bulletin A340–57–4089, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin
A330–57–3081, Revision 02, dated January
24, 2006; as applicable; for the repetitive
inspection.
44733
(6) For aircraft on which Airbus
Modification 41652 is not embodied: When
the aircraft has been modified in accordance
with Airbus Service Bulletin A330–57–3090,
dated March 27, 2006; or Airbus Service
Bulletin A340–57–4098, dated March 27,
2006; as applicable; the repetitive inspections
required by this AD are cancelled. In case of
any crack finding during the modification:
Where the applicable service bulletin
specifies to contact Airbus, before further
flight, contact Airbus to get repair
instructions, and repair.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows. The MCAI
did not have a required action if cracks are
found during a repetitive inspection. This AD
requires contacting Airbus for repair
instructions and repairing before further
flight.
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
Transport Airplane Directorate, 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: Tim
Backman, Aerospace Engineer, International
Branch, ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington 98057–3356. 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.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(g) Refer to MCAI EASA Airworthiness
Directive 2006–0315 R1, dated October 26,
2006, and the service information listed in
Table 1 of this AD, for related information.
TABLE 1.—RELATED SERVICE INFORMATION
jlentini on PROD1PC65 with RULES
Airbus Service Bulletin
A330–57–3081
A330–57–3090
A340–57–4089
A340–57–4098
VerDate Aug<31>2005
Revision level
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
17:01 Aug 08, 2007
Jkt 211001
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E:\FR\FM\09AUR1.SGM
02 ....................
Original ...........
02 ....................
Original ...........
09AUR1
Date
January 24, 2006.
March 27, 2006.
January 24, 2006.
March 27, 2006.
44734
Federal Register / Vol. 72, No. 153 / Thursday, August 9, 2007 / Rules and Regulations
Material Incorporated by Reference
(h) You must use the applicable service
information specified in Table 2 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise. If you
accomplish the optional terminating
modification specified in this AD, you must
use the applicable service information
specified in Table 3 of this AD.
TABLE 2.—REQUIRED MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision
A330–57–3081, including Appendix 01 ......................................................................................................
A340–57–4089, including Appendix 01 ......................................................................................................
TABLE 3.—OPTIONAL MATERIAL
INCORPORATED BY REFERENCE
Airbus Service Bulletin
Date
A330–57–3090 .................
A340–57–4098 .................
March 27, 2006.
March 27, 2006.
(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, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) 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/ibrlocations.html.
Issued in Renton, Washington, on July 24,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–14866 Filed 8–8–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28094; Directorate
Identifier 2006–NM–258–AD; Amendment
39–15148; AD 2007–16–09]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model ERJ 170 Airplanes
and Model ERJ 190 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
jlentini on PROD1PC65 with RULES
Examining the Docket
The FAA is superseding an
existing airworthiness directive (AD),
which applies to all EMBRAER Model
ERJ 170–100 LR, –100 STD, –100 SE,
and –100 SU airplanes. That AD
currently requires repetitively replacing
SUMMARY:
VerDate Aug<31>2005
17:01 Aug 08, 2007
Jkt 211001
the low-stage check valve and
associated seals of the right-hand engine
bleed system. This new AD adds new
airplanes to that existing requirement.
For all airplanes, this AD also requires
repetitively replacing the low-stage
check valve and associated seals of the
left-hand engine bleed system with a
new check valve and new seals. This
AD results from a report that an engine
shut down during flight due to the
failure of the low-stage check valve to
close. We are issuing this AD to prevent
failure of the low-stage check valve,
which could result in an engine shutting
down during flight.
DATES: This AD becomes effective
September 13, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 13, 2007.
On November 29, 2005 (70 FR 69075,
November 14, 2005), the Director of the
Federal Register approved the
incorporation by reference of a certain
service bulletin.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
Contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343–CEP 12.225, Sao Jose dos Campos—
SP, Brazil, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
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Date
02
02
January 24, 2006.
January 24, 2006.
ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2005–23–14, amendment
39–14372 (70 FR 69075, November 14,
2005). The existing AD applies to all
EMBRAER Model ERJ 170–100 LR, –100
STD, –100 SE, and –100 SU airplanes.
That NPRM was published in the
Federal Register on May 8, 2007 (72 FR
26008). That NPRM proposed to
continue to require repetitively
replacing the low-stage check valve and
associated seals of the right-hand (RH)
engine bleed system. That NPRM also
proposed to add new airplanes to that
existing requirement. For all airplanes,
that NPRM also proposed to require
repetitively replacing the low-stage
check valve and associated seals of the
left-hand (LH) engine bleed system with
a new check valve and new seals.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the NPRM or on
the determination of the cost to the
public.
Changes to This AD
We have reviewed Revision 01 of
EMBRAER Service Bulletin 190–36–
0004, dated November 14, 2006, and
have determined that the
accomplishment instructions of
Revision 01 are the same as those in the
original issue of the service bulletin. In
the NPRM, we referred to the original
issue of EMBRAER Service Bulletin
190–36–0004, dated October 18, 2006,
as the appropriate source of service
information for replacing the low-stage
check valves and associated seals of the
RH and LH engine bleed system, on
Model ERJ 190–100 STD, –100 LR, and
–100 IGW airplanes. Therefore, we have
revised paragraphs (j) and (k) of this AD
to also refer to Revision 01 of EMBRAER
Service Bulletin 190–36–0004, dated
November 14, 2006, as an appropriate
source of service information. We have
E:\FR\FM\09AUR1.SGM
09AUR1
]]>Agencies
[Federal Register Volume 72, Number 153 (Thursday, August 9, 2007)]
[Rules and Regulations]
[Pages 44731-44734]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-14866]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27741; Directorate Identifier 2006-NM-261-AD;
Amendment 39-15141; AD 2007-16-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, -243, -301, -321, -322, -323, -341, -342, and -343 Airplanes; and
Model A340-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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 airworthiness authority
of another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as keel beam
rupture, which affects the structural integrity of the area. We are
issuing this AD to require actions to correct the unsafe condition on
these products.
DATES: This AD becomes effective September 13, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 13,
2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC.
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
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to allow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This AD references the MCAI and related service information that we
considered in forming the engineering basis to correct the unsafe
condition. The AD contains text copied from the MCAI and for this
reason might not follow our plain language principles.
We issued a 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 March 30, 2007 (72
FR 15067). That NPRM proposed to require a repetitive special detailed
inspection on the horizontal flange of the keel beam in the area of the
first fastener hole aft of FR (frame) 40, follow-up actions (further
inspections, installation of new fasteners, and sealing the fasteners),
and repair if necessary. The MCAI states that during the A330 and A340
aircraft fatigue test, cracks appeared on the right and left sides
between the crossing area of the keel beam fitting and the front spar
on the center wing box (CWB). This situation if not corrected can lead
in the worst case to keel beam rupture, which affects the structural
integrity of the area.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Refer to Revised MCAI
Airbus requests we refer to European Aviation Safety Agency (EASA)
Airworthiness Directive 2006-0315 R1, dated October 26, 2006, in the
AD. (We referred to EASA Airworthiness Directive 2006-0315, dated
October 13, 2006, in the NPRM.) Airbus notes that Revision 1 of the
EASA airworthiness directive adds an optional terminating action for
the repetitive inspections.
We agree with Airbus, and have revised this AD to refer to Revision
1 of the EASA Airworthiness Directive. Revision 1 refers to the
following Airbus Service Bulletins as the appropriate sources of
service information for doing the optional terminating action: A330-57-
3090, dated March 27, 2006; and A340-57-4098, dated March 27, 2006. The
modification can be done only on airplanes without Airbus Modification
41652.
The optional terminating action is a modification that involves
disconnecting one or more fasteners from the keel beam/bottom skin
panel
[[Page 44732]]
junction, removing two adjacent fasteners in order to perform cold
working, and installing interference fit fasteners. The modification
also involves inspections and repairing any cracking detected during
the modification; in some instances the repair for cracking or for any
bushing that has a diameter beyond certain limits specified in the
service bulletin is contacting Airbus for repair instructions. We have
added paragraph (e)(6) to this AD, and revised paragraph (d) of this AD
to include the optional terminating action. We have revised paragraph
(g) of this AD to refer to Revision 1 of the MCAI.
Explanation of Change to Paragraph (c)(3) ``Applicability''
When we issued the NPRM we noted in paragraph (c)(3) that we were
considering rulemaking regarding EASA airworthiness directive 2006-
0314. EASA airworthiness directive 2006-0314 applies to Model A340-200
and -300 series airplanes repaired in accordance with certain Airbus
repair drawings, and paragraph (c)(3) of the NPRM notes that those
airplanes are not affected by the current action. We have since issued
AD 2007-12-08, amendment 39-15086 (72 FR 31171, June 6, 2007), which is
the parallel FAA AD to EASA airworthiness directive 2006-0314. We have
changed paragraph (c)(3) of this AD to refer to AD 2007-12-08.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable in a U.S. court of
law. In making these changes, we do not intend to differ substantively
from the information provided in the MCAI and related service
information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are described in a separate paragraph of the AD. These requirements, if
any, take precedence over the actions copied from the MCAI.
Costs of Compliance
We estimate that this AD will affect about 9 products of U.S.
registry. We also estimate that it will take about 12 work-hours per
product to comply with this AD. The average labor rate is $80 per work-
hour. Required parts will cost about $382 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these parts.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of this AD to the U.S. operators to be
$12,078, or $1,342 per product.
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 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains the NPRM, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
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 FAA amends Sec. 39.13 by adding the following new AD:
2007-16-02 Airbus: Amendment 39-15141. Docket No. FAA-2007-27741;
Directorate Identifier 2006-NM-261-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 13, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, all serial numbers,
except those on which Airbus modification 49202 has been embodied in
production, or Airbus Service Bulletin A330-57-3090 has been
embodied in service.
(2) Airbus Model A340-200 and -300 series airplanes, all
certified models, all serial numbers, except those on which Airbus
modification 49202 has been embodied in production or Airbus Service
Bulletin A340-57-4098 has been embodied in service.
(3) This AD does not apply to Model A340-200 and -300 series
airplanes repaired
[[Page 44733]]
in accordance with Airbus Repair Drawing R57115053, R57115051, or
R57115047 (installation of titanium doubler). These airplanes are
covered by European Aviation Safety Agency (EASA) airworthiness
directive 2006-0314, dated October 13, 2006. On May 25, 2007, we
issued AD 2007-12-08, amendment 39-15086 (72 FR 31171, June 6,
2007), which is the parallel FAA AD to EASA airworthiness directive
2006-0314.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states that during the A330 and A340 aircraft fatigue test, cracks
appeared on the right and left sides between the crossing area of
the keel beam fitting and the front spar on the center wing box
(CWB). This situation if not corrected can lead in the worst case to
keel beam rupture which affects the structural integrity of the
area. In order to maintain the structural integrity of the aircraft,
the MCAI requires a repetitive special detailed inspection on the
horizontal flange of the keel beam in the area of the first fastener
hole aft of FR (frame) 40, follow-up actions, and repair if
necessary. The MCAI also includes an optional terminating action for
the repetitive inspections.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Within the mandatory threshold (flight cycles or flight
hours) mentioned in the paragraph 1.E.(2) of Airbus Service Bulletin
A340-57-4089, Revision 02; or A330-57-3081, Revision 02; both dated
January 24, 2006, depending on the configuration of the aircraft
model; or within 3 months after the effective date of this AD;
whichever occurs later: Carry out the NDT (non-destructive test)
inspection of the hole(s) of the horizontal flange of the keel beam
located on FR 40 datum on RH (right-hand) and/or LH (left-hand) side
of the fuselage, in accordance with the instructions of Airbus
Service Bulletin A340-57-4089, Revision 02; or A330-57-3081,
Revision 02; as applicable. Inspection in accordance with Airbus
A330/A340 Technical Disposition F57D03012810, Issue B, dated August
18, 2003; or 582.0651/2002, Issue A, dated October 17, 2002;
satisfies the inspection requirements for the first rotating probe
inspection which is specified at the inspection threshold of this
AD.
Note 1: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above inspection according to
recommended thresholds mentioned in paragraph 1.E.(2) of Airbus
Service Bulletin A340-57-4089, Revision 02; or Airbus Service
Bulletin A330-57-3081, Revision 02; both dated January 24, 2006.
(2) In case of any crack finding, before further flight, contact
Airbus in order to get repair instructions before next flight, and
repair before further flight.
(3) Should no crack be detected:
(i) Before further flight: Follow up the actions indicated in
the flow charts, figure 7, 8, or 9, of Airbus Service Bulletin A340-
57-4089, including Appendix 01, Revision 02, dated January 24, 2006;
or figure 5, 6, or 7, of Airbus Service Bulletin A330-57-3081,
including Appendix 01, Revision 02, dated January 24, 2006; in
accordance with the instructions of the applicable service bulletin.
(ii) Within 30 days after the effective date of this AD, or
within 30 days after doing the inspection required by paragraph
(e)(1) of this AD, whichever occurs later: Send the report of
actions carried out in paragraph (e)(3)(i) of this AD to Airbus.
(iii) Renew the inspection at mandatory intervals given in
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision
02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081,
Revision 02, dated January 24, 2006; as applicable; in accordance
with the instructions of Service Bulletin A340-57-4089, Revision 02,
or Service Bulletin A330-57-3081, Revision 02; as applicable, and
send the inspection results to Airbus.
Note 2: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above repetitive inspection
according to recommended intervals mentioned in paragraph 1.E.(2) of
Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24,
2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated
January 24, 2006.
(4) Upon detection of a crack during a repetitive inspection,
before further flight, contact Airbus to get repair instructions,
and repair before further flight.
(5) No additional work is required for aircraft inspected in
accordance with the instructions of Airbus Service Bulletin A330-57-
3081, dated October 30, 2003, or Revision 01, dated May 18, 2004; or
Airbus Service Bulletin A340-57-4089, dated October 30, 2003, or
Revision 01, dated March 2, 2004. Nevertheless, the operators must
check that their inspection program is in accordance with paragraph
1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision
02, dated January 24, 2006; as applicable; for the repetitive
inspection.
(6) For aircraft on which Airbus Modification 41652 is not
embodied: When the aircraft has been modified in accordance with
Airbus Service Bulletin A330-57-3090, dated March 27, 2006; or
Airbus Service Bulletin A340-57-4098, dated March 27, 2006; as
applicable; the repetitive inspections required by this AD are
cancelled. In case of any crack finding during the modification:
Where the applicable service bulletin specifies to contact Airbus,
before further flight, contact Airbus to get repair instructions,
and repair.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows. The MCAI did not have a required action if cracks are
found during a repetitive inspection. This AD requires contacting
Airbus for repair instructions and repairing before further flight.
Other FAA AD Provisions
(f) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, Transport Airplane Directorate, 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: Tim Backman, Aerospace
Engineer, International Branch, ANM-116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356.
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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(g) Refer to MCAI EASA Airworthiness Directive 2006-0315 R1,
dated October 26, 2006, and the service information listed in Table
1 of this AD, for related information.
Table 1.--Related Service Information
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-57-3081............................. 02............................. January 24, 2006.
A330-57-3090............................. Original....................... March 27, 2006.
A340-57-4089............................. 02............................. January 24, 2006.
A340-57-4098............................. Original....................... March 27, 2006.
----------------------------------------------------------------------------------------------------------------
[[Page 44734]]
Material Incorporated by Reference
(h) You must use the applicable service information specified in
Table 2 of this AD to do the actions required by this AD, unless the
AD specifies otherwise. If you accomplish the optional terminating
modification specified in this AD, you must use the applicable
service information specified in Table 3 of this AD.
Table 2.--Required Material Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
------------------------------------------------------------------------
A330-57-3081, including 02 January 24, 2006.
Appendix 01.
A340-57-4089, including 02 January 24, 2006.
Appendix 01.
------------------------------------------------------------------------
Table 3.--Optional Material Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin Date
------------------------------------------------------------------------
A330-57-3090........................... March 27, 2006.
A340-57-4098........................... March 27, 2006.
------------------------------------------------------------------------
(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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) 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 July 24, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-14866 Filed 8-8-07; 8:45 am]
BILLING CODE 4910-13-P
