[Federal Register Volume 73, Number 182 (Thursday, September 18, 2008)]
[Rules and Regulations]
[Pages 54067-54069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-21429]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0974; Directorate Identifier 2008-CE-048-AD; 
Amendment 39-15673; AD 2008-19-06]
RIN 2120-AA64


Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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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:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E had been published 
to require the replacement of the pulley drive assembly by a new one 
of an improved design.
    Recent cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support have reportedly been found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the powerplant compartment.

    This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective October 8, 2008.
    On October 8, 2008, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.
    We must receive comments on this AD by October 20, 2008.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.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 this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Albert 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: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency AD No.: 2008-0129R1-E, dated July 31, 2008 (referred to after 
this as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E had been published 
to require the replacement of the pulley drive assembly by a new one 
of an improved design.
    Recent cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support have reportedly been found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the powerplant compartment.
    To address this condition, this AD supersedes AD 2008-0067-E and 
mandates the removal, as a temporary measure, of the compressor 
drive belt and of the torque limiter, the conditional replacement of 
the pulley drive shear shaft, and repetitive inspections for cracks 
of the pulley drive assembly and of the alternator/compressor 
support.
    Revision 1 of this AD introduces an alternative temporary 
solution with the aim to restore the capability to make use of the 
air conditioning system. This solution consists in replacing the 
original pulley drive assembly by a time-limited assembly of a new 
design, corresponding to the EADS SOCATA modification MOD 70-0240-
21.

    A definitive solution is still under consideration to correct this 
condition. You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    EADS SOCATA has issued EADS SOCATA Mandatory TBM Aircraft Alert 
Service Bulletin SB No. 70-161, Amendment 2, and EADS SOCATA Mandatory 
TBM Aircraft Alert Service Bulletin SB No. 70-161, Amendment 3, both 
dated July 2008. The actions described in the service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

[[Page 54068]]

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 have also 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 take 
precedence over those copied from the MCAI.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
recent cases of rupture of the alternator and vapor cycle cooling 
system compressor drive shaft and of cracks on the standby generator 
and compressor support have reportedly been found. Such failures could 
lead to loss of the alternator and of the vapor cycle cooling systems 
and could also cause mechanical damages inside the powerplant 
compartment.
    Therefore, we determined that notice and opportunity for public 
comment before issuing this AD are impracticable and that good cause 
exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2008-0974; Directorate 
Identifier 2008-CE-048-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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:

2008-19-06 EADS SOCATA: Amendment 39-15673; Docket No. FAA-2008-
0974; Directorate Identifier 2008-CE-048-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
8, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Models TBM 700 airplanes, all serial 
numbers beginning with 434, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 24: Electric 
Power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    ``Following the rupture of an alternator and vapour cycle 
cooling system pulley drive assembly, the AD 2008-0067-E had been 
published to require the replacement of the pulley drive assembly by 
a new one of an improved design.
    Recent cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support have reportedly been found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the powerplant compartment.
    To address this condition, this AD supersedes AD 2008-0067-E and 
mandates the removal, as a temporary measure, of the compressor 
drive belt and of the torque limiter, the conditional replacement of 
the pulley drive shear shaft, and repetitive inspections for cracks 
of the pulley drive assembly and of the alternator/compressor 
support.
    Revision 1 of this AD introduces an alternative temporary 
solution with the aim to restore the capability to make use of the 
air conditioning system. This solution consists in replacing the 
original pulley drive assembly by a time-limited assembly of a new 
design, corresponding to the EADS SOCATA modification MOD 70-0240-
21.''

    A definitive solution is still under consideration to correct 
this condition.

Actions and Compliance

    (f) Unless already done, for airplanes S/N 434 through 459 only, 
before further flight after October 8, 2008 (the effective date of 
this AD), do the following actions following EADS SOCATA Mandatory 
TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated 
July 2008:

[[Page 54069]]

    (1) Remove the pulley drive assembly, the torque limiter, the 
compressor drive belt, and the alternator/compressor support.
    (2) Inspect for cracks on the pulley drive surfaces and the 
alternator/compressor support welds.
    (i) If any crack is detected, replace the pulley drive assembly 
or conditionally repair the cracked unit following the 
accomplishment instructions in section D.2 of EADS SOCATA Mandatory 
TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated 
July 2008.
    (ii) Replacement of the assembly incorporates replacement of the 
pulley drive sheer shaft required by paragraph (f)(3) of this AD for 
airplanes with 30 hours TIS or more with the torque limiter 
installed on the pulley drive shear shaft.
    (3) Replace any pulley drive shear shaft that has accumulated 30 
hours TIS or more with the torque limiter installed. This action is 
not required if you replaced the whole assembly per paragraph 
(f)(2)(i) of this AD.
    (4) Re-install the pulley drive assembly and the alternator/
compressor support, without re-installing the compressor drive belt 
or the torque limiter.
    (5) Install on the instrument panel and in the pilot's primary 
field of vision, the following placard:

``AIR COND'' INOPERATIVE

RECOMMENDED ``AIR COND'' SWITCH POSITION: ``MANUAL''

and insert EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin 
SB 70-161, amendment 2, dated July 2008 in the limitations section 
of the pilot's operating handbook.
    (g) For all serial number airplanes;
    (1) Within 100 hours TIS after October 8, 2008 (the effective 
date of this AD), and thereafter at intervals not to exceed 100 
hours TIS, inspect for cracks on the pulley drive surfaces and the 
alternator/compressor support welds, following EADS SOCATA Mandatory 
TBM Aircraft Alert Service Bulletin SB 70-161, amendment 2, dated 
July 2008. For accomplishment of the repetitive inspections required 
by paragraph (g)(1) of this AD, paragraph C.2 of the accomplishment 
instructions of EADS SOCATA Mandatory TBM Aircraft Alert Service 
Bulletin SB 70-161, amendment 2, dated July 2008, does not apply 
since the torque limiter has already been removed.
    (2) If cracks are found during any of these inspections, before 
further flight, replace the assembly or conditionally repair the 
unit following EADS SOCATA Mandatory TBM Aircraft Alert Service 
Bulletin SB 70-161, amendment 2, dated July 2008. The 100-hour TIS 
repetitive inspections are still required after replacement or 
repair.
    (h) As an alternative to the requirements of paragraphs (f) and 
(g) of this AD, do the following actions before further flight after 
October 8, 2008 (the effective date of this AD), following EADS 
SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, 
amendment 3, dated July 2008:
    (1) Install a zero-timed pulley drive assembly P/N 
T700G215510000000 following the accomplishment instructions in 
section D.1, I and J of EADS SOCATA Mandatory TBM Aircraft Alert 
Service Bulletin SB 70-161, amendment 3, dated July 2008.
    (2) Within 100 hours TIS after the installation required in 
paragraph (h)(1) of this AD and repetitively thereafter at intervals 
not to exceed 100 TIS, inspect the alternator/compressor support 
welds for cracks following the accomplishment instructions in 
sections B,G, H, I, and J of EADS SOCATA Mandatory TBM Aircraft 
Alert Service Bulletin SB 70-161, amendment 3, dated July 2008.
    (3) If any crack is detected in the inspection required in 
paragraph (h)(2) of this AD, before further flight, replace or 
repair the cracked unit following EADS SOCATA Mandatory TBM Aircraft 
Alert Service Bulletin SB 70-161, amendment 3, dated July 2008.
    (4) Upon the accumulation of 400 hours TIS, replace each pulley 
drive assembly, P/N T700G215510000000, with a zero- timed one.

    Note 1: Compliance with the requirements of paragraph (h) of 
this AD restores the capability to make use of the air conditioning 
system.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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: Albert Mercado, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4119; fax: (816) 329-4090. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (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

    (j) Refer to MCAI EASA Emergency AD No.: 2008-0129R1-E, dated 
July 31, 2008; EADS SOCATA Mandatory TBM Aircraft Alert Service 
Bulletin SB 70-161, amendment 2, and EADS SOCATA Mandatory TBM 
Aircraft Alert Service Bulletin SB 70-161, amendment 3, both dated 
July 2008, for related information.

Material Incorporated by Reference

    (k) You must use EADS SOCATA Mandatory TBM Aircraft Alert 
Service Bulletin SB 70-161, amendment 2, or EADS SOCATA Mandatory 
TBM Aircraft Alert Service Bulletin SB 70-161, amendment 3, both 
dated July 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 EADS 
SOCATA--Direction des Services, 65921 Tarbes Cedex 9, France; 
telephone: +33 (0)5 62 41 73 00; fax: +33 (0)5 62 41 7-54; or in the 
United States contact EADS SOCATA North America, Inc., North Perry 
Airport, 7501 South 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on September 8, 2008.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8-21429 Filed 9-17-08; 8:45 am]
BILLING CODE 4910-13-P