Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C Airplanes, 46327-46329 [E9-21411]
Download as PDF
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
Systems and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6490; fax
(425) 917–6590; has the authority to approve
AMOCs for this AD, if requested using 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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, in the FAA Flight Standards
District Office (FSDO), or lacking a principal
inspector, your local FSDO. The AMOC
approval letter must specifically reference
this AD.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 737–27A1287, dated April 16, 2008,
to do the actions required by this AD, unless
the AD specifies otherwise.
(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 Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
31, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21412 Filed 9–8–09; 8:45 am]
jlentini on DSKJ8SOYB1PROD with RULES
BILLING CODE 4910–13–P
VerDate Nov<24>2008
16:13 Sep 08, 2009
Jkt 217001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0397; Directorate
Identifier 2008–NM–023–AD; Amendment
39–16018; AD 2009–19–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2–1C, B2–203, B2K–3C, B4–103,
B4–203, and B4–2C 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)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
An operator has reported the loss of a
centre flap inner tab on an in-service A300
aircraft. The centre flap inner tab detached
during approach to an airport. A similar
event was reported several years ago on a
pre-mod 04770 aircraft. * * *
* * * Investigations led by the
manufacturer revealed that the centre hinge
bracket developed a fatigue crack causing
complete failure of the bracket. The tab
rotated causing failure of the inboard link
followed by the failure of the outboard link.
[D]etachment of a centre flap inner tab
* * * could be a potential risk to persons on
[the] ground * * *.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
46327
SUPPLEMENTARY INFORMATION:
Discussion
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 April 30, 2009 (74 FR
19908). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
An operator has reported the loss of a
centre flap inner tab on an in-service A300
aircraft. The centre flap inner tab detached
during approach to an airport. A similar
event was reported several years ago on a
pre-mod 04770 aircraft. Previous failure at
the aft lug of the centre brackets led to the
issuance of Airbus Service Bulletin A300–
57–0205.
In the most recent case, the aircraft had
been modified in accordance with Airbus
Service Bulletin A300–57–0205 (Airbus
modification No. 04770). Investigations led
by the manufacturer revealed that the centre
hinge bracket developed a fatigue crack
causing complete failure of the bracket. The
tab rotated causing failure of the inboard link
followed by the failure of the outboard link.
To avoid a detachment of a centre flap
inner tab, which could be a potential risk to
persons on [the] ground, this AD requires a
repetitive [high frequency eddy current]
inspection of the centre flap inner tab hinge
bracket and replacement of the bracket when
cracks are detected * * * [and] reporting of
inspection results to the TC holder [and
provides] an optional terminating action.
* * *
*
*
*
*
*
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request for Clarification of Reporting
Requirement
TradeWinds Airlines points out that
although paragraph (e), ‘‘Reason,’’ of the
NPRM describes reporting inspection
results to the Type Certificate holder,
the requirements in paragraphs (f)(1),
(f)(2), and (f)(3) of the NPRM currently
have no information that describes the
reporting requirement.
We infer that TradeWinds Airlines is
asking us to clarify the reporting
requirement, and we agree that
clarification is necessary. Paragraph (e)
of the NPRM quotes European Aviation
Safety Agency (EASA) AD 2007–
0299R2, dated October 28, 2008. The
EASA AD includes reporting; however,
this AD does not require reporting. We
have updated Note 1 of this final rule
to clarify this difference. We also
removed paragraph (g)(3) of the
E:\FR\FM\09SER1.SGM
09SER1
46328
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
proposed AD because that paragraph
provides reporting requirement
information and it is unnecessary to
include that information in this final
rule.
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 change described previously.
We determined that this change 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 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
highlighted in a note within the AD.
jlentini on DSKJ8SOYB1PROD with RULES
Costs of Compliance
We estimate that this AD will affect
22 products of U.S. registry. We also
estimate that it will take about 55 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $96,800, or $4,400 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
VerDate Nov<24>2008
16:13 Sep 08, 2009
Jkt 217001
2009–19–01 Airbus: Amendment 39–16018.
Docket No. FAA–2009–0397; Directorate
Identifier 2008–NM–023–AD.
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 this AD:
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.
(a) This airworthiness directive (AD)
becomes effective October 14, 2009.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.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:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
Effective Date
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
B2–1C, B2–203, B2K–3C, B4–103, B4–203,
and B4–2C airplanes, certificated in any
category, all serial numbers, except airplanes
which have been modified in accordance
with Airbus Mandatory Service Bulletin
A300–57–0252 (Airbus Modification 13400).
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
An operator has reported the loss of a
centre flap inner tab on an in-service A300
aircraft. The centre flap inner tab detached
during approach to an airport. A similar
event was reported several years ago on a
pre-mod 04770 aircraft. Previous failure at
the aft lug of the centre brackets led to the
issuance of Airbus Service Bulletin A300–
57–0205.
In the most recent case, the aircraft had
been modified in accordance with Airbus
Service Bulletin A300–57–0205 (Airbus
modification No. 04770). Investigations led
by the manufacturer revealed that the centre
hinge bracket developed a fatigue crack
causing complete failure of the bracket. The
tab rotated causing failure of the inboard link
followed by the failure of the outboard link.
To avoid a detachment of a centre flap
inner tab, which could be a potential risk to
persons on [the] ground, this AD requires a
repetitive [high frequency eddy current]
inspection of the centre flap inner tab hinge
bracket and replacement of the bracket when
cracks are detected * * * [and] reporting of
inspection results to the TC holder [and
provides] an optional terminating action.
* * *
*
*
*
*
*
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) At the times specified in Table 1 or
Table 2 of this AD, as applicable, perform a
high frequency eddy current inspection to
detect fatigue cracks of the center hinge
bracket of the center flap inner tab (on both
wings), in accordance with Airbus
Mandatory Service Bulletin A300–57–0250,
Revision 01, dated September 29, 2008. If no
cracking is found, repeat the inspection
thereafter at intervals not to exceed 850 flight
cycles.
E:\FR\FM\09SER1.SGM
09SER1
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
46329
TABLE 1—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS NOT BEEN DONE
Flight cycles accumulated since first flight as of the effective date of
this AD
Compliance time
Less than 6,000 flight cycles ....................................................................
Prior to accumulating 6,000 flight cycles since first flight or within 90
days after the effective date of this AD, whichever occurs later.
Within 850 flight cycles after the effective date of this AD.
Within 500 flight cycles after the effective date of this AD.
6,000 flight cycles or more, but less than 12,000 flight cycles ................
12,000 flight cycles or more .....................................................................
TABLE 2—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS BEEN DONE
Flight cycles accumulated since Airbus Service Bulletin A300–57–0205
modification as of the effective date of this AD
Compliance time
Less than 6,000 flight cycles ....................................................................
Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin
A300–57–0205 modification or within 90 days after the effective date
of this AD, whichever occurs later.
Within 850 flight cycles after the effective date of this AD.
Within 500 flight cycles after the effective date of this AD.
6,000 flight cycles or more, but less than 12,000 flight cycles ................
12,000 flight cycles or more .....................................................................
(2) If any crack is detected during any
inspection required by this AD, before further
flight, replace the center hinge bracket in the
accordance with Airbus Mandatory Service
Bulletin A300–57–0250, Revision 01, dated
September 29, 2008. Within 6,000 flight
cycles after replacing the center hinge
bracket, do the inspection required by
paragraph (f)(1) of this AD, and if no cracking
is found, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles.
(3) Modifying the inboard tab of the center
flaps in accordance with Airbus Mandatory
Service Bulletin A300–57–0252, dated
August 27, 2008, terminates the requirements
of this AD.
(4) Actions accomplished before the
effective date of this AD in accordance with
Airbus Mandatory Service Bulletin A300–57–
0250, dated November 2, 2007, are
considered acceptable for compliance with
the corresponding actions specified in this
AD.
FAA AD Differences
jlentini on DSKJ8SOYB1PROD with RULES
Note 1: This AD differs from the MCAI
and/or service information as follows:
Although the European Aviation Safety
Agency AD 2007–0299R2, dated October 28,
2008 and Airbus Mandatory Service Bulletin
A300–57–0250, dated November 2, 2007,
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, 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: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
VerDate Nov<24>2008
16:13 Sep 08, 2009
Jkt 217001
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(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.
Related Information
(h) Refer to MCAI Airworthiness Directive
2007–0299R2, dated October 28, 2008;
Airbus Mandatory Service Bulletin A300–57–
0250, Revision 01, dated September 29, 2008;
and Airbus Mandatory Service Bulletin
A300–57–0252, dated August 27, 2008; for
related information.
Material Incorporated by Reference
(i) You must use Airbus Mandatory Service
Bulletin A300–57–0250, Revision 01,
excluding Appendix 1, dated September 29,
2008, to do the actions required by this AD,
unless the AD specifies otherwise. If you do
the optional terminating modification
specified by this AD, you must use Airbus
Service Bulletin A300–57–0252, dated
August 27, 2008, to perform that action,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
31, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21411 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0771; Directorate
Identifier 2009–NE–14–AD; Amendment 39–
16009; AD 2009–18–13]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc. (RR) RB211 Trent 900 Series
Turbofan Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Evidence from development testing and
flight test Trent 900 engines has identified
cracking on some HP Turbine Nozzle Guide
E:\FR\FM\09SER1.SGM
09SER1
Agencies
[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46327-46329]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-21411]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0397; Directorate Identifier 2008-NM-023-AD;
Amendment 39-16018; AD 2009-19-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-
3C, B4-103, B4-203, and B4-2C 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) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
An operator has reported the loss of a centre flap inner tab on
an in-service A300 aircraft. The centre flap inner tab detached
during approach to an airport. A similar event was reported several
years ago on a pre-mod 04770 aircraft. * * *
* * * Investigations led by the manufacturer revealed that the
centre hinge bracket developed a fatigue crack causing complete
failure of the bracket. The tab rotated causing failure of the
inboard link followed by the failure of the outboard link.
[D]etachment of a centre flap inner tab * * * could be a
potential risk to persons on [the] ground * * *.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 14,
2009.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
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 April 30, 2009 (74
FR 19908). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
An operator has reported the loss of a centre flap inner tab on
an in-service A300 aircraft. The centre flap inner tab detached
during approach to an airport. A similar event was reported several
years ago on a pre-mod 04770 aircraft. Previous failure at the aft
lug of the centre brackets led to the issuance of Airbus Service
Bulletin A300-57-0205.
In the most recent case, the aircraft had been modified in
accordance with Airbus Service Bulletin A300-57-0205 (Airbus
modification No. 04770). Investigations led by the manufacturer
revealed that the centre hinge bracket developed a fatigue crack
causing complete failure of the bracket. The tab rotated causing
failure of the inboard link followed by the failure of the outboard
link.
To avoid a detachment of a centre flap inner tab, which could be
a potential risk to persons on [the] ground, this AD requires a
repetitive [high frequency eddy current] inspection of the centre
flap inner tab hinge bracket and replacement of the bracket when
cracks are detected * * * [and] reporting of inspection results to
the TC holder [and provides] an optional terminating action. * * *
* * * * *
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request for Clarification of Reporting Requirement
TradeWinds Airlines points out that although paragraph (e),
``Reason,'' of the NPRM describes reporting inspection results to the
Type Certificate holder, the requirements in paragraphs (f)(1), (f)(2),
and (f)(3) of the NPRM currently have no information that describes the
reporting requirement.
We infer that TradeWinds Airlines is asking us to clarify the
reporting requirement, and we agree that clarification is necessary.
Paragraph (e) of the NPRM quotes European Aviation Safety Agency (EASA)
AD 2007-0299R2, dated October 28, 2008. The EASA AD includes reporting;
however, this AD does not require reporting. We have updated Note 1 of
this final rule to clarify this difference. We also removed paragraph
(g)(3) of the
[[Page 46328]]
proposed AD because that paragraph provides reporting requirement
information and it is unnecessary to include that information in this
final rule.
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 change described previously. We determined that this change
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 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 highlighted in a note within the AD.
Costs of Compliance
We estimate that this AD will affect 22 products of U.S. registry.
We also estimate that it will take about 55 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $96,800, or $4,400 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 this AD:
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.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:
2009-19-01 Airbus: Amendment 39-16018. Docket No. FAA-2009-0397;
Directorate Identifier 2008-NM-023-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
14, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B2-1C, B2-203, B2K-3C,
B4-103, B4-203, and B4-2C airplanes, certificated in any category,
all serial numbers, except airplanes which have been modified in
accordance with Airbus Mandatory Service Bulletin A300-57-0252
(Airbus Modification 13400).
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
An operator has reported the loss of a centre flap inner tab on
an in-service A300 aircraft. The centre flap inner tab detached
during approach to an airport. A similar event was reported several
years ago on a pre-mod 04770 aircraft. Previous failure at the aft
lug of the centre brackets led to the issuance of Airbus Service
Bulletin A300-57-0205.
In the most recent case, the aircraft had been modified in
accordance with Airbus Service Bulletin A300-57-0205 (Airbus
modification No. 04770). Investigations led by the manufacturer
revealed that the centre hinge bracket developed a fatigue crack
causing complete failure of the bracket. The tab rotated causing
failure of the inboard link followed by the failure of the outboard
link.
To avoid a detachment of a centre flap inner tab, which could be
a potential risk to persons on [the] ground, this AD requires a
repetitive [high frequency eddy current] inspection of the centre
flap inner tab hinge bracket and replacement of the bracket when
cracks are detected * * * [and] reporting of inspection results to
the TC holder [and provides] an optional terminating action. * * *
* * * * *
Actions and Compliance
(f) Unless already done, do the following actions.
(1) At the times specified in Table 1 or Table 2 of this AD, as
applicable, perform a high frequency eddy current inspection to
detect fatigue cracks of the center hinge bracket of the center flap
inner tab (on both wings), in accordance with Airbus Mandatory
Service Bulletin A300-57-0250, Revision 01, dated September 29,
2008. If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles.
[[Page 46329]]
Table 1--Airplanes on which Airbus Service Bulletin A300-57-0205 Has Not
Been Done
------------------------------------------------------------------------
Flight cycles accumulated since first
flight as of the effective date of this Compliance time
AD
------------------------------------------------------------------------
Less than 6,000 flight cycles.......... Prior to accumulating 6,000
flight cycles since first
flight or within 90 days after
the effective date of this AD,
whichever occurs later.
6,000 flight cycles or more, but less Within 850 flight cycles after
than 12,000 flight cycles. the effective date of this AD.
12,000 flight cycles or more........... Within 500 flight cycles after
the effective date of this AD.
------------------------------------------------------------------------
Table 2--Airplanes on Which Airbus Service Bulletin A300-57-0205 Has
Been Done
------------------------------------------------------------------------
Flight cycles accumulated since Airbus
Service Bulletin A300-57-0205
modification as of the effective date Compliance time
of this AD
------------------------------------------------------------------------
Less than 6,000 flight cycles.......... Prior to accumulating 6,000
flight cycles since Airbus
Service Bulletin A300-57-0205
modification or within 90 days
after the effective date of
this AD, whichever occurs
later.
6,000 flight cycles or more, but less Within 850 flight cycles after
than 12,000 flight cycles. the effective date of this AD.
12,000 flight cycles or more........... Within 500 flight cycles after
the effective date of this AD.
------------------------------------------------------------------------
(2) If any crack is detected during any inspection required by
this AD, before further flight, replace the center hinge bracket in
the accordance with Airbus Mandatory Service Bulletin A300-57-0250,
Revision 01, dated September 29, 2008. Within 6,000 flight cycles
after replacing the center hinge bracket, do the inspection required
by paragraph (f)(1) of this AD, and if no cracking is found, repeat
the inspection thereafter at intervals not to exceed 850 flight
cycles.
(3) Modifying the inboard tab of the center flaps in accordance
with Airbus Mandatory Service Bulletin A300-57-0252, dated August
27, 2008, terminates the requirements of this AD.
(4) Actions accomplished before the effective date of this AD in
accordance with Airbus Mandatory Service Bulletin A300-57-0250,
dated November 2, 2007, are considered acceptable for compliance
with the corresponding actions specified in this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: Although the European Aviation Safety Agency AD 2007-
0299R2, dated October 28, 2008 and Airbus Mandatory Service Bulletin
A300-57-0250, dated November 2, 2007, specify to submit certain
information to the manufacturer, this AD does not include that
requirement.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office.
(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.
Related Information
(h) Refer to MCAI Airworthiness Directive 2007-0299R2, dated
October 28, 2008; Airbus Mandatory Service Bulletin A300-57-0250,
Revision 01, dated September 29, 2008; and Airbus Mandatory Service
Bulletin A300-57-0252, dated August 27, 2008; for related
information.
Material Incorporated by Reference
(i) You must use Airbus Mandatory Service Bulletin A300-57-0250,
Revision 01, excluding Appendix 1, dated September 29, 2008, to do
the actions required by this AD, unless the AD specifies otherwise.
If you do the optional terminating modification specified by this
AD, you must use Airbus Service Bulletin A300-57-0252, dated August
27, 2008, to perform that action, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on August 31, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-21411 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P