Airworthiness Directives; SOCATA-Groupe Aerospatiale TB 20 and TB 21 Airplanes, 2606-2608 [E7-706]
Download as PDF
<![CDATA[
2606
Federal Register / Vol. 72, No. 13 / Monday, January 22, 2007 / Rules and Regulations
Inspection and Cleaning Procedures
(l) Use paragraphs 3.A. through 3.A.(4)(b)
of the Accomplishment Instructions of RollsRoyce plc Alert Service Bulletin No. RB.211–
72–AE302, Revision 3, dated September 20,
2006, to do borescope inspections, and
cleaning of the oil vent tubes and bearing
chamber.
Alternative Methods of Compliance
(m) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(n) You must use Rolls-Royce plc Alert
Service Bulletin No. RB.211–72–AE302,
Revision 3, dated September 20, 2006, to
perform the inspections and cleaning
required by this AD. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Rolls-Royce plc, PO Box 31,
Derby, England; telephone: 011–44–1332–
249428; fax: 011–44–1332–249223, for a copy
of this service information. You may review
copies 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.
Related Information
(o) European Aviation Safety Agency
airworthiness directive No. 2006–0355, dated
December 4, 2006, also addresses the subject
of this AD.
(p) Contact Christopher Spinney,
Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA 01803; telephone (781) 238–7175; fax
(781) 238–7199, for more information about
this AD.
Issued in Burlington, Massachusetts, on
January 12, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–684 Filed 1–19–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26236 Directorate
Identifier 2006–CE–66–AD; Amendment 39–
14891; AD 2007–02–04]
sroberts on PROD1PC70 with RULES
RIN 2120–AA64
Airworthiness Directives; SOCATAGroupe Aerospatiale TB 20 and TB 21
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
15:59 Jan 19, 2007
Jkt 211001
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 reports of interference
between the wing spar lower boom and
the wheel fairing attaching screw. We
are issuing this AD to require actions to
correct the unsafe condition on these
products.
This AD becomes effective
February 26, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 26, 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:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
DATES:
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
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Register on November 22, 2006 (71 FR
67506). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that there are
reports of interference between the wing
spar lower boom and the wheel fairing
attaching screw causing an unsafe
condition. The interference could, if left
uncorrected, reduce the fatigue life of
the wing spar with potentially
catastrophic results.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Comment Issue: Cost of Compliance
EADS SOCATA states:
Application of SB10–148–57 does not
require specific part. So, the cost is
negligible. EADS SOCATA estimates that it
would take 1 work-hour to inspect and
displace the screw. If repair is necessary, the
cost depends on the damage.
Our cost estimate included both the
inspection and screw displacement
costs as well as repair costs. We
developed the repair cost estimate based
on the information provided and
assumed the worst case scenario if a
repair was required. Since EADS
SOCATA did not provide an estimate
(work-hours or parts cost) if a repair is
required and the FAA is required to
provide this estimate to the public, we
are keeping the language the same as the
NPRM to account for worst case repair
situations.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
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 FAA policies.
Any such differences are described in a
separate paragraph of the AD, and take
precedence over the actions copied from
the MCAI.
E:\FR\FM\22JAR1.SGM
22JAR1
Federal Register / Vol. 72, No. 13 / Monday, January 22, 2007 / Rules and Regulations
Costs of Compliance
We estimate that this AD will affect
270 products of U.S. registry. We also
estimate that it will take about 15 workhours per product to comply with this
AD. The average labor rate is $80 per
work-hour. Required parts will cost
about $15,000 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
$4,374,000, or $16,200 per product.
sroberts on PROD1PC70 with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
VerDate Aug<31>2005
15:59 Jan 19, 2007
Jkt 211001
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
2007–02–04 SOCATA-Groupe
Aerospatiale: Amendment 39–14891;
Docket No. FAA–2006–26236;
Directorate Identifier 2006–CE–66–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective February 26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to SOCATA Models TB
20 and TB 21 airplanes, serial numbers 1
through 9999 without repair REP 20.031
implemented on both sides, certificated in
any category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states
there are reports of interference between the
wing spar lower boom and the wheel fairing
attaching screw causing an unsafe condition.
The interference could, if left uncorrected,
reduce the fatigue life of the wing spar with
potentially catastrophic results. The MCAI
requires inspections and repairs as necessary
to correct this unsafe condition.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Within the next 100 hours time-inservice or 12 months after the effective date
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
2607
of this AD, whichever occurs first, perform
an inspection of the wing spar lower boom
and repair it as necessary, in accordance with
the accomplishment instructions of the EADS
SOCATA TB Aircraft Mandatory Service
Bulletin SB 10–148, ATA No. 57, dated
December 2005.
(2) If defect dimensions exceed the
acceptable values given in the EADS
SOCATA TB Aircraft Mandatory Service
Bulletin SB 10–148, ATA No. 57, dated
December 2005, or if the defect is not located
in areas depicted in figure 2 of the EADS
SOCATA TB Aircraft Mandatory Service
Bulletin SB 10–148, ATA No. 57, dated
December 2005, then the Type 1 or Type 2
repair solutions are not applicable. A written
report shall be sent to the manufacturer as
mentioned in section A.5 of the EADS
SOCATA TB Aircraft Mandatory Service
Bulletin SB 10–148, ATA No. 57, dated
December 2005. In this case, all flight is
prohibited until EADS SOCATA provides a
repair solution or otherwise agrees to further
flight.
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, ATTN: Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4059; 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 European Aviation Safety
Agency (EASA) Airworthiness Directive No.:
2006–0123, dated May 16, 2006; and EADS
SOCATA TB Aircraft Mandatory Service
Bulletin SB 10–148, ATA No. 57, dated
December 2005, for related information.
Material Incorporated by Reference
(h) You must use EADS SOCATA TB
Aircraft Mandatory Service Bulletin SB 10–
148, ATA No. 57, dated December 2005, 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
E:\FR\FM\22JAR1.SGM
22JAR1
2608
Federal Register / Vol. 72, No. 13 / Monday, January 22, 2007 / Rules and Regulations
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; or SOCATA Aircraft, INC., North
Perry Airport, 7501 Airport Road, Pembroke
Pines, Florida 33023; telephone: (954) 893–
1400; fax: (954) 964–4141.
(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 January
11, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–706 Filed 1–19–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26232 Directorate
Identifier 2006–CE–62–AD; Amendment 39–
14895; AD 2007–02–08]
RIN 2120–AA64
Airworthiness Directives; EADS
SOCATA TBM 700 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
sroberts on PROD1PC70 with RULES
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 aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as a report of a master
cylinder yoke failure. We are issuing
this AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective
February 26, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 26, 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,
VerDate Aug<31>2005
15:59 Jan 19, 2007
Jkt 211001
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; 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 November 28, 2006 (71 FR
68762). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that there
was a report of a master cylinder yoke
failure. The AD requirements are to
detect defective yokes on aircraft and
replace them. The aim of this AD is to
ensure that normal braking is available
at any time to prevent possible runway
excursions in the event of failure of the
master cylinder yoke.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
EADS SOCATA gave comments
addressing the following:
Comment Issue No. 1: Cost of
Compliance
EADS SOCATA states:
The proposed AD specifies that: ‘‘Required
parts would cost about $600’’. $600
corresponds to the cost of the replacement of
all (4) the master cylinder yokes. According
to EADS Socata experience, operators
complying with EADS Socata SB70–136–32
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
had to replace only one yoke in the worst
case.
The FAA does not agree. We are using
the worst case scenario of all four yokes
being replaced. If an operator needs to
replace fewer yokes, the cost will be
less.
Comment Issue No. 2: Applicability
EADS SOCATA states:
We propose to specify: ‘‘This AD applies
to SOCATA Model TBM700 airplanes, all
serial number, certificated in any category
equipped with master cylinder assembly part
number ZOO.N6068757280 or
ZOO.N6068757281’’.
Indeed, the supplier of the master cylinder
assembly could change in the future and
aircraft equipped with another part number
would not be concerned.
The FAA does not agree. Including
the part number in the applicability is
redundant. Per the AD, the operator has
to verify whether the applicable part
number is installed and, if so, take
appropriate action. If a different part
number from a different supplier is
installed, then the AD does not apply.
Comment Issue No. 3: Actions and
Compliance, Paragraphs (e)(1)(ii)(B) and
(e)(2)
EADS SOCATA states:
Paragraph (e)(1)(ii)(B):
Yokes part number ZOO.N7134732200
(delivered since January 2006) can also be
installed on aircraft. Socata decides to
produce itself yoke part number
T700A324004810000 for logistic reasons but
the design of this yokes is the same as Parker
yoke part number ZOO.N7134732200.
Paragraph (e)(2):
During installation of master cylinder yoke
part number ZOO.N7134732200 or
installation of master cylinder assembly part
number ZOO.N6068757280 or
ZOO.N6068757281, we propose to check the
yokes in accordance with SB70–136–32 only
if these parts were delivered new before
January 2006.
The FAA does not agree. Since these
parts are not serialized and tracked,
there would be no way of knowing if the
part was delivered before or after
January 2006. In addition, EADS
SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–136, ATA No.
32, dated December 2005, requires
installation of yoke part number
T700A324004810000. If an operator
wants to use a different part numbered
component and can show that it
provides an acceptable level of safety,
the operator can make a request to the
FAA to approve an alternative method
of compliance (AMOC) using the
procedures in 14 CFR part 39 and this
AD.
E:\FR\FM\22JAR1.SGM
22JAR1
]]>Agencies
[Federal Register Volume 72, Number 13 (Monday, January 22, 2007)]
[Rules and Regulations]
[Pages 2606-2608]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-706]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26236 Directorate Identifier 2006-CE-66-AD;
Amendment 39-14891; AD 2007-02-04]
RIN 2120-AA64
Airworthiness Directives; SOCATA-Groupe Aerospatiale TB 20 and TB
21 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 reports of
interference between the wing spar lower boom and the wheel fairing
attaching screw. We are issuing this AD to require actions to correct
the unsafe condition on these products.
DATES: This AD becomes effective February 26, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 26,
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: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; 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 November 22, 2006
(71 FR 67506). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states that there are reports of
interference between the wing spar lower boom and the wheel fairing
attaching screw causing an unsafe condition. The interference could, if
left uncorrected, reduce the fatigue life of the wing spar with
potentially catastrophic results.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received.
Comment Issue: Cost of Compliance
EADS SOCATA states:
Application of SB10-148-57 does not require specific part. So,
the cost is negligible. EADS SOCATA estimates that it would take 1
work-hour to inspect and displace the screw. If repair is necessary,
the cost depends on the damage.
Our cost estimate included both the inspection and screw
displacement costs as well as repair costs. We developed the repair
cost estimate based on the information provided and assumed the worst
case scenario if a repair was required. Since EADS SOCATA did not
provide an estimate (work-hours or parts cost) if a repair is required
and the FAA is required to provide this estimate to the public, we are
keeping the language the same as the NPRM to account for worst case
repair situations.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed.
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 FAA policies. Any such differences are
described in a separate paragraph of the AD, and take precedence over
the actions copied from the MCAI.
[[Page 2607]]
Costs of Compliance
We estimate that this AD will affect 270 products of U.S. registry.
We also estimate that it will take about 15 work-hours per product to
comply with this AD. The average labor rate is $80 per work-hour.
Required parts will cost about $15,000 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 $4,374,000, or
$16,200 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 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:
2007-02-04 SOCATA-Groupe Aerospatiale: Amendment 39-14891; Docket
No. FAA-2006-26236; Directorate Identifier 2006-CE-66-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to SOCATA Models TB 20 and TB 21 airplanes,
serial numbers 1 through 9999 without repair REP 20.031 implemented
on both sides, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states there are reports of interference between the wing spar lower
boom and the wheel fairing attaching screw causing an unsafe
condition. The interference could, if left uncorrected, reduce the
fatigue life of the wing spar with potentially catastrophic results.
The MCAI requires inspections and repairs as necessary to correct
this unsafe condition.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Within the next 100 hours time-in-service or 12 months after
the effective date of this AD, whichever occurs first, perform an
inspection of the wing spar lower boom and repair it as necessary,
in accordance with the accomplishment instructions of the EADS
SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57,
dated December 2005.
(2) If defect dimensions exceed the acceptable values given in
the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148,
ATA No. 57, dated December 2005, or if the defect is not located in
areas depicted in figure 2 of the EADS SOCATA TB Aircraft Mandatory
Service Bulletin SB 10-148, ATA No. 57, dated December 2005, then
the Type 1 or Type 2 repair solutions are not applicable. A written
report shall be sent to the manufacturer as mentioned in section A.5
of the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148,
ATA No. 57, dated December 2005. In this case, all flight is
prohibited until EADS SOCATA provides a repair solution or otherwise
agrees to further flight.
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, ATTN: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; 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 European Aviation Safety Agency (EASA)
Airworthiness Directive No.: 2006-0123, dated May 16, 2006; and EADS
SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57,
dated December 2005, for related information.
Material Incorporated by Reference
(h) You must use EADS SOCATA TB Aircraft Mandatory Service
Bulletin SB 10-148, ATA No. 57, dated December 2005, 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
[[Page 2608]]
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; or SOCATA
Aircraft, INC., North Perry Airport, 7501 Airport Road, Pembroke
Pines, Florida 33023; telephone: (954) 893-1400; fax: (954) 964-
4141.
(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 January 11, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-706 Filed 1-19-07; 8:45 am]
BILLING CODE 4910-13-P
