Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes, 7576-7578 [07-670]
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<![CDATA[
7576
Federal Register / Vol. 72, No. 32 / Friday, February 16, 2007 / Rules and Regulations
Bulletin 767–28A0081, dated March 6, 2003;
are considered acceptable for compliance
with the corresponding action specified in
paragraphs (f) and (g) of this AD.
Parts Installation
(k) As of the effective date of this AD, only
main tank fuel boost pumps identified in
paragraphs (k)(1) and (k)(2) of this AD may
be installed on any airplane.
(1) Any main tank fuel boost pump that has
been inspected, and on which all applicable
corrective actions have been performed, in
accordance with paragraph (f) or (g) of this
AD.
(2) Any main tank fuel boost pump having
P/N 5006003D.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(m) You must use the applicable service
bulletin specified in Table 1 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. 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, S.W., 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.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Boeing alert service bulletin
767–28A0077
767–28A0081
767–28A0088
767–28A0089
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
Issued in Renton, Washington, on February
5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–2644 Filed 2–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26235; Directorate
Identifier 2006–CE–65–AD; Amendment 39–
14945; AD 2007–04–13]
RIN 2120–AA64
Airworthiness Directives; EADS
SOCATA Model TBM 700 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
rmajette on PROD1PC67 with RULES
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 cracks found on several
main landing gear cylinders. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
14:54 Feb 15, 2007
Jkt 211001
This AD becomes effective
March 23, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 23, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Albert J. Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
DATES:
Streamlined Issuance of AD
AGENCY:
VerDate Aug<31>2005
Revision level
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The 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
follow 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
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1 ...................
1 ...................
Original .........
Original .........
Date
July 8, 2004.
July 8, 2004.
February 24, 2005.
February 24, 2005.
MCAI and for this reason might not
follow our plain language principles.
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 December 22, 2006 (71 FR
76950). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states reports of
cracks found on several main landing
gear (MLG) cylinders. If not detected
and corrected, fatigue cracks in the
shock strut cylinder of the MLG could
result in a collapsed MLG during takeoff
or landing, and possible reduced
structural integrity of the airplane. The
MCAI requires inspecting the MLG
forging body for cracks and repairing
any cracks found.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Comment Issue No. 1: Change the
Required Parts Cost in the Compliance
Section
EADS SOCATA comments the cost for
the parts required to do the actions in
the proposed AD are totally out of
proportion. EADS SOCATA states the
application of SB 70–130, ATA No. 32,
dated January 2006, requires only two
cotter pins and this cost is negligible.
The proposed AD states it will take
approximately $125,600 to comply with
the AD.
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Federal Register / Vol. 72, No. 32 / Friday, February 16, 2007 / Rules and Regulations
In our cost estimate, we grouped all
actions required to comply with the AD,
including replacement of any MLG
found cracked. We have since learned
from EADS SOCATA that labor and
parts costs for any cracked MLG will be
provided under warranty. We will
modify the Costs of Compliance section
to reflect the 3 work-hours to do the
inspection and the warranty coverage
for the replacement MLG.
Comment Issue No. 2: Change the
Number of Work-Hours in the
Compliance Section
EADS SOCATA comments they have
established, by applying the service
bulletin, it takes 2 work-hours per
product to perform an eddy current
inspection, and it takes 3 work-hours
per product to perform a dye penetrant
or fluorescent penetrant inspection.
The proposed AD states it will take
approximately 18 work-hours to comply
with the AD.
In our cost estimate, we grouped all
actions required to comply with the AD,
including replacement of any MLG
found cracked. We have since learned
from EADS SOCATA that labor and
parts costs for any cracked MLG will be
provided under warranty. We will
modify the Costs of Compliance section
to reflect the 3 work-hours to do the
inspection and the warranty coverage
for the replacement MLG.
rmajette on PROD1PC67 with RULES
Comment Issue No. 3: Change the
Compliance Time
EADS SOCATA comments that SB
70–130, ATA No. 32, dated January
2006, specifies for MLG with forging
body totaling more than 3,500 landings
to inspect the forging body within 25
landings after issuance of the service
bulletin. However, the proposed AD
lowers the limit to 3,475 landings.
EADS SOCATA states the limit of 3,500
landings was established by analysis
considering all necessary margins.
EADS SOCATA requests the FAA
change paragraph (e)(2) to read, ‘‘For
MLG with forging body totaling more
than 3,500 landings:’’ or explain the
reason for the difference in the FAA AD
Differences section.
After evaluating the service bulletin
further, we agree with the language
presented by the commenter. We will
change the final rule AD action based on
this comment.
Conclusion
We reviewed the available data,
including the comments 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
VerDate Aug<31>2005
14:54 Feb 15, 2007
Jkt 211001
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 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
272 products of U.S. registry. We also
estimate that it will take about 3 workhours per product to comply with the
basic requirements (inspection) of this
AD. The average labor rate is $80 per
work-hour. Based on these figures, we
estimate the cost of the basic
requirements of this AD to the U.S.
operators to be $65,280, or $240 per
product.
In addition, follow-on actions
(possible MLG replacement) would be
covered by EADS SOCATA under
warranty (both parts and labor). We
have no way of determining the number
of airplanes that would need this action.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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7577
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
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 Management
Facility 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 Office (telephone (800) 647–
5227) 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
2007–04–13 EADS SOCATA: Amendment
39–14945; Docket No. FAA–2006–26235;
Directorate Identifier 2006–CE–65–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 23, 2007.
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Federal Register / Vol. 72, No. 32 / Friday, February 16, 2007 / Rules and Regulations
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model TBM 700
airplanes, serial numbers 1 through 9999,
certificated in any category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states
reports of cracks found on several main
landing gear (MLG) cylinders. If not detected
and corrected, fatigue cracks in the shock
strut cylinder of the MLG could result in a
collapsed MLG during takeoff or landing, and
possible reduced structural integrity of the
airplane.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) As of March 23, 2007 (the effective date
of this AD), for MLG with forging body
totaling more than 1,750 landings but less
than 3,501 landings since new:
(i) Inspect the forging body for cracks
within 100 landings after March 23, 2007 (the
effective date of this AD) in accordance with
the accomplishment instructions of EADS
SOCATA TBM Aircraft Mandatory Service
Bulletin SB 70–130, ATA No. 32, dated
January 2006.
(ii) If no cracks are detected, repetitively
inspect thereafter every 175 landings.
(2) As of March 23, 2007 (the effective date
of this AD), for MLG with forging body
totaling more than 3,500 landings since new:
(i) Inspect the forging body for cracks
within 25 landings after March 23, 2007 (the
effective date of this AD) in accordance with
the accomplishment instructions of EADS
SOCATA TBM Aircraft Mandatory Service
Bulletin SB 70–130, ATA No. 32, dated
January 2006.
(ii) If no cracks are detected, repetitively
inspect thereafter every 175 landings.
(3) If any cracks are detected during any
inspection required in paragraph (e) of this
AD:
(i) Before further flight, remove the affected
landing gear leg and confirm the presence of
the crack with dye penetrant inspection or
fluorescent penetrant inspection.
(ii) If the crack is confirmed, before further
flight, contact EADS SOCATA to coordinate
the landing gear repair/replacement and then
conform to any instruction stated by EADS
SOCATA.
(4) If you do not know the number of
landings, follow the instructions in the
Compliance section of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
130, ATA No. 32, dated January 2006.
FAA AD Differences
rmajette on PROD1PC67 with RULES
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Albert J. Mercado, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4119; fax: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(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
(44 U.S.C. 3501 et seq.), 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 European Aviation
Safety Agency (EASA) AD No. 2006–0085,
dated April 12, 2006, for related information.
Material Incorporated by Reference
(h) You must use EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
130, ATA No. 32, dated January 2006, 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 EADS SOCATA, Direction
des Services, 65921 Tarbes Cedex 9, France;
telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5
62.41.76.54.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; 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 Kansas City, Missouri, on
February 8, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 07–670 Filed 2–15–07; 8:45 am]
BILLING CODE 4910–13–P
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, Small Airplane Directorate, ATTN:
VerDate Aug<31>2005
14:54 Feb 15, 2007
Jkt 211001
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Document No. FAA–2007–27174;
Directorate Identifier 2007–CE–006–AD;
Amendment 39–14944; AD 2007–04–12]
RIN 2120–AA64
Airworthiness Directives; Gippsland
Aeronautics Pty. Ltd. Model GA8
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
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 the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Inspection of a high time aircraft has
revealed cracks in the Horizontal Stabiliser
rear spar splice plate and inboard main ribs
around the area of the Horizontal Stabiliser
rear pivot attachment. Additionally, failure of
some attach bolts in service may be due to
improper assembly.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
March 8, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 8, 2007.
We must receive comments on this
AD by March 19, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
E:\FR\FM\16FER1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 32 (Friday, February 16, 2007)]
[Rules and Regulations]
[Pages 7576-7578]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-670]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26235; Directorate Identifier 2006-CE-65-AD;
Amendment 39-14945; AD 2007-04-13]
RIN 2120-AA64
Airworthiness Directives; EADS SOCATA Model TBM 700 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 aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as cracks
found on several main landing gear cylinders. We are issuing this AD to
require actions to correct the unsafe condition on these products.
DATES: This AD becomes effective March 23, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 23,
2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. The 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 follow 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.
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 December 22, 2006
(71 FR 76950). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states reports of cracks found on
several main landing gear (MLG) cylinders. If not detected and
corrected, fatigue cracks in the shock strut cylinder of the MLG could
result in a collapsed MLG during takeoff or landing, and possible
reduced structural integrity of the airplane. The MCAI requires
inspecting the MLG forging body for cracks and repairing any cracks
found.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Comment Issue No. 1: Change the Required Parts Cost in the Compliance
Section
EADS SOCATA comments the cost for the parts required to do the
actions in the proposed AD are totally out of proportion. EADS SOCATA
states the application of SB 70-130, ATA No. 32, dated January 2006,
requires only two cotter pins and this cost is negligible.
The proposed AD states it will take approximately $125,600 to
comply with the AD.
[[Page 7577]]
In our cost estimate, we grouped all actions required to comply
with the AD, including replacement of any MLG found cracked. We have
since learned from EADS SOCATA that labor and parts costs for any
cracked MLG will be provided under warranty. We will modify the Costs
of Compliance section to reflect the 3 work-hours to do the inspection
and the warranty coverage for the replacement MLG.
Comment Issue No. 2: Change the Number of Work-Hours in the Compliance
Section
EADS SOCATA comments they have established, by applying the service
bulletin, it takes 2 work-hours per product to perform an eddy current
inspection, and it takes 3 work-hours per product to perform a dye
penetrant or fluorescent penetrant inspection.
The proposed AD states it will take approximately 18 work-hours to
comply with the AD.
In our cost estimate, we grouped all actions required to comply
with the AD, including replacement of any MLG found cracked. We have
since learned from EADS SOCATA that labor and parts costs for any
cracked MLG will be provided under warranty. We will modify the Costs
of Compliance section to reflect the 3 work-hours to do the inspection
and the warranty coverage for the replacement MLG.
Comment Issue No. 3: Change the Compliance Time
EADS SOCATA comments that SB 70-130, ATA No. 32, dated January
2006, specifies for MLG with forging body totaling more than 3,500
landings to inspect the forging body within 25 landings after issuance
of the service bulletin. However, the proposed AD lowers the limit to
3,475 landings. EADS SOCATA states the limit of 3,500 landings was
established by analysis considering all necessary margins.
EADS SOCATA requests the FAA change paragraph (e)(2) to read, ``For
MLG with forging body totaling more than 3,500 landings:'' or explain
the reason for the difference in the FAA AD Differences section.
After evaluating the service bulletin further, we agree with the
language presented by the commenter. We will change the final rule AD
action based on this comment.
Conclusion
We reviewed the available data, including the comments 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 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 272 products of U.S. registry.
We also estimate that it will take about 3 work-hours per product to
comply with the basic requirements (inspection) of this AD. The average
labor rate is $80 per work-hour. Based on these figures, we estimate
the cost of the basic requirements of this AD to the U.S. operators to
be $65,280, or $240 per product.
In addition, follow-on actions (possible MLG replacement) would be
covered by EADS SOCATA under warranty (both parts and labor). We have
no way of determining the number of airplanes that would need this
action.
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 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 Management Facility 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
Office (telephone (800) 647-5227) 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:
2007-04-13 EADS SOCATA: Amendment 39-14945; Docket No. FAA-2006-
26235; Directorate Identifier 2006-CE-65-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
23, 2007.
[[Page 7578]]
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model TBM 700 airplanes, serial numbers 1
through 9999, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states reports of cracks found on several main landing gear (MLG)
cylinders. If not detected and corrected, fatigue cracks in the
shock strut cylinder of the MLG could result in a collapsed MLG
during takeoff or landing, and possible reduced structural integrity
of the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) As of March 23, 2007 (the effective date of this AD), for
MLG with forging body totaling more than 1,750 landings but less
than 3,501 landings since new:
(i) Inspect the forging body for cracks within 100 landings
after March 23, 2007 (the effective date of this AD) in accordance
with the accomplishment instructions of EADS SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70-130, ATA No. 32, dated January
2006.
(ii) If no cracks are detected, repetitively inspect thereafter
every 175 landings.
(2) As of March 23, 2007 (the effective date of this AD), for
MLG with forging body totaling more than 3,500 landings since new:
(i) Inspect the forging body for cracks within 25 landings after
March 23, 2007 (the effective date of this AD) in accordance with
the accomplishment instructions of EADS SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70-130, ATA No. 32, dated January
2006.
(ii) If no cracks are detected, repetitively inspect thereafter
every 175 landings.
(3) If any cracks are detected during any inspection required in
paragraph (e) of this AD:
(i) Before further flight, remove the affected landing gear leg
and confirm the presence of the crack with dye penetrant inspection
or fluorescent penetrant inspection.
(ii) If the crack is confirmed, before further flight, contact
EADS SOCATA to coordinate the landing gear repair/replacement and
then conform to any instruction stated by EADS SOCATA.
(4) If you do not know the number of landings, follow the
instructions in the Compliance section of EADS SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70-130, ATA No. 32, dated January
2006.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(f) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, Small Airplane Directorate, ATTN: Albert J.
Mercado, Aerospace Engineer, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(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 (44
U.S.C. 3501 et seq.), 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 European Aviation Safety Agency (EASA) AD No.
2006-0085, dated April 12, 2006, for related information.
Material Incorporated by Reference
(h) You must use EADS SOCATA TBM Aircraft Mandatory Service
Bulletin SB 70-130, ATA No. 32, dated January 2006, 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 EADS
SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France;
telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; 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 Kansas City, Missouri, on February 8, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 07-670 Filed 2-15-07; 8:45 am]
BILLING CODE 4910-13-P
