[Federal Register: October 12, 2005 (Volume 70, Number 196)]
[Rules and Regulations]
[Page 59240-59242]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12oc05-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21464; Directorate Identifier 2005-CE-32-AD;
Amendment 39-14320; AD 2005-20-24]
RIN 2120-AA64
Airworthiness Directives; SOCATA--Groupe AEROSPATIALE Model TBM
700 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD
requires you to inspect the fuselage skin in the VHF1 antenna mounting
area for cracks and loose rivets. This AD also requires you to modify
the area if you find cracks or loose rivets. This AD results from
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for France. We are issuing this AD to detect
and correct cracks in the fuselage skin, which could result in loss of
aircraft pressurization. Loss of aircraft pressurization could lead to
flight crew incapacitation.
DATES: This AD becomes effective on November 9, 2005.
As of November 9, 2005, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact EADS SOCATA Tarbes, Direction des Services, 65921 Tarbes Cedex
9, France; telephone: 33 (0)5 62.41.73.00; facsimile: 33 (0)5
62.41.76.54; or SOCATA AIRCRAFT, North Perry Airport, 7501 Pembroke
Road, Pembroke Pines, Florida 33023.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400
[[Page 59241]]
Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC
20590-001 or on the Internet at http://dms.dot.gov. The docket number
is FAA-2005-21464; Directorate Identifier 2005-CE-32-AD.
FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4135; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Direction
G[eacute]n[eacute]rale de L'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified FAA that an unsafe
condition may exist on certain SOCATA Model TBM 700 airplanes. The DGAC
reports cracks in the fuselage skin by the passenger door on the
affected airplanes. These airplanes have a VHF1 antenna mounted under
the fuselage between frame C12 and C13 or C13 and C13bis.
Investigations reveal that antenna vibrations are causing the
cracks.
What is the potential impact if FAA took no action? If not detected
and corrected, cracks in the fuselage skin could cause loss of aircraft
pressurization. Loss of pressurization could lead to flight crew
incapacitation.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to certain SOCATA Model TBM 700
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on July 7, 2005 (70 FR 39204). The
NPRM proposed to require you to inspect the fuselage skin where the
VHF1 antenna mounts under the fuselage between frame C12 and C13 or C13
and C13bis for cracks and loose rivets. The NPRM also proposes to
require you to modify the VHF1 antenna bracket and the antenna/fuselage
interface.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 185 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the
inspection:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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1 work hour x $65 per hour = Not applicable............ $65 $65 x $185 = $12,025
$65.
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We estimate the following costs to do the modification.
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Total cost per
Labor cost Parts cost airplane
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4 work hours x $65 per hour = $260....... $181 $441
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Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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 AD.
Regulatory Findings
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD will not have a substantial direct effect on 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.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of
[[Page 59242]]
this summary by sending a request to us at the address listed under
ADDRESSES. Include ``Docket No. FAA-2005-21464; Directorate Identifier
2005-CE-32-AD'' in your request.
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 Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2005-20-24 Socata--Groupe Aerospatiale: Amendment 39-14320; Docket
No. FAA-2005-21464; Directorate Identifier 2005-CE-32-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on November 9, 2005.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following Model TBM 700 airplanes,
serial numbers 1 through 255; 257 through 267; and 270, that are:
(1) equipped with a VHF1 antenna mounted under the fuselage
between frame C12 and C13 or C13 and C13bis; and
(2) certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for France.
The actions specified in this AD are intended to detect and correct
cracks in the fuselage skin, which could result in loss of aircraft
pressurization. Loss of aircraft pressurization could lead to flight
crew incapacitation.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
Note: The EADS SOCATA Mandatory Service Bulletin TBM Aircraft,
SB 70-103, Amendment 1, ATA No. 53, dated September 2003, allows the
pilot to perform the visual inspection of the fuselage skin in the
VHF1 antenna mount area for cracks and loose rivets. The Federal
Aviation Regulations (14 CFR 43.3) only allow the pilot to perform
preventive maintenance as described in 14 CFR part 43, App. A,
paragraph (c). These visual inspections are not considered
preventive maintenance under 14 CFR part 43, App. A, paragraph (c).
Therefore, an appropriately-rated mechanic must perform all actions
of this AD.
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Actions Compliance Procedures
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(1) Inspect the fuselage skin in the VHF1 Within the next 50 hours time-in- Follow EADS SOCATA Mandatory
antenna mount area between frame C12 and service (TIS) after November 9, Service Bulletin TBM Aircraft,
C13 or C13 and C13bis for cracks and 2005, (the effective date of this SB 70-103, Amendment 1, ATA No.
loose rivets. AD). Repetitively inspect 53, dated September 2003.
thereafter at intervals not to
exceed 50 hours TIS until the
modification in paragraph (e)(2)
of this AD is done. Modifying the
VHF1 antenna bracket and interface
area terminates the repetitive
inspection requirement of this AD.
(2) Modify the VHF1 antenna bracket and At whichever of the following that Follow EADS SOCATA Recommended
the antenna/fuselage interface. occurs first: Service Bulletin TBM Aircraft,
(i) Before further flight anytime a SB 70-111, ATA No. 53, dated
crack or loose rivet is found October 2003, and the
during any inspection required in applicable maintenance manual.
paragraph (e)(1) of this AD.
(ii) Within 100 hours TIS or 12
months after November 9, 2005 (the
effective date of this AD),
whichever occurs later.
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May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Peter L. Rouse, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4135; facsimile:
(816) 329-4090.
Is There Other Information That Relates to This Subject?
(g) French AD Number F-2003-367 R1, Distribution A, Issue date:
February 4, 2004, also addresses the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in EADS SOCATA Mandatory Service Bulletin TBM Aircraft,
SB 70-103, Amendment 1, ATA No. 53, dated September 2003, and EADS
SOCATA Recommended Service Bulletin TBM Aircraft, SB 70-111, ATA No.
53, dated October 2003. 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. To get a copy of
this service information, contact EADS SOCATA Tarbes, Direction des
Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5
62.41.73.00; facsimile: 33 (0)5 62.41.76.54; or SOCATA AIRCRAFT,
North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida
33023. To review copies of this service information, go to the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
or call (202) 741-6030. To view the AD docket,
go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov.
The docket number is FAA-2005-21464; Directorate
Identifier 2005-CE-32-AD.
Issued in Kansas City, Missouri, on September 28, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19930 Filed 10-11-05; 8:45 am]
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