[Federal Register Volume 75, Number 187 (Tuesday, September 28, 2010)]
[Proposed Rules]
[Pages 59658-59661]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-24248]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0948; Directorate Identifier 2010-CE-041-AD]
RIN 2120-AA64


Airworthiness Directives; SOCATA Model TBM 700 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly 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 power plant compartment.
    To address this condition, the AD 2008-0129-E superseded AD 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.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by November 12, 
2010.

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.

[[Page 59659]]

    <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 proposed 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0948; 
Directorate Identifier 2010-CE-041-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On September 8, 2008, we issued AD 2008-19-06, Amendment 39-15673 
(73 FR 54067; September 18, 2008). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2008-19-06, a terminating action has been 
developed through installation of newly designed alternator/compressor 
support and pulley drive assemblies.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No.: 2010-0130, dated June 29, 2010, 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 was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly 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 power plant compartment.
    To address this condition, the AD 2008-0129-E superseded 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 the AD 2008-0129-E introduced 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 SOCATA modification 
MOD 70-0240-21.
    A definitive solution has been released to production aeroplanes 
by implementation of SOCATA modification MOD 70-0243-21 or Service 
Bulleting (SB) 70-176-21 for in-service aeroplanes.
    This AD which supersedes EASA AD 2008-0129R1-E retaining its 
requirements, limits the AD applicability and requires 
accomplishment of the terminating action.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    SOCATA has issued SB 70-176, Amendment 1, dated February 2010. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed 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 proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed 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 proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 66 products of U.S. 
registry. We also estimate that it would take about 8 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $0 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 costs. 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 the proposed AD on 
U.S. operators to be $44,880, or $680 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 proposed AD would not have federalism 
implications

[[Page 59660]]

under Executive Order 13132. This proposed AD would 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 proposed 
regulation:g
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15673 (73 FR 
54067; September 18, 2008), and adding the following new AD:

SOCATA: Docket No. FAA-2010-0948; Directorate Identifier 2010-CE-
041-AD.

Comments Due Date

    (a) We must receive comments by November 12, 2010.

Affected ADs

    (b) This AD supersedes AD 2008-19-06, Amendment 39-15673.

Applicability

    (c) This AD applies to SOCATA TBM 700 airplanes, serial numbers 
(S/Ns) 434 through 509, 511 through 516, 519, 520, and 522 through 
525, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 21: Air 
Conditioning.

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 was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly 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 power plant compartment.
    To address this condition, the AD 2008-0129-E superseded 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 the AD 2008-0129-E introduced 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 SOCATA modification 
MOD 70-0240-21.
    A definitive solution has been released to production aeroplanes 
by implementation of SOCATA modification MOD 70-0243-21 or Service 
Bulleting (SB) 70-176-21 for in-service aeroplanes.
    This AD which supersedes EASA AD 2008-0129R1-E retaining its 
requirements, limits the AD applicability and requires 
accomplishment of the terminating action.

Actions and Compliance

    (f) For airplanes S/Ns 434 through 459 only, unless already 
done, before further flight as of September 18, 2008 (the effective 
date of AD 2008-19-06), do the following actions following EADS 
SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, 
amendment 2, dated July 2008:
    (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, before further flight, replace the 
pulley drive assembly following the accomplishment instructions in 
SOCATA Mandatory TBM Aircraft Service Bulletin SB 70-176, amendment 
1, dated February 2010.
    (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 time-in-service (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) Insert EADS SOCATA SB 70-161, amendment 2, dated June 2008, 
in the limitations section of the pilot's operating handbook and 
install on the instrument panel and in the pilot's primary field of 
vision a placard with the following text:

``AIR COND'' INOPERATIVE

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

and insert EADS SOCATA SB 70-161-21, amendment 2, dated June 2008, 
in the limitations section of the pilot's operating handbook.
    (g) For all S/N airplanes;
    (1) Within 100 hours TIS after September 18, 2008 (the effective 
date of AD 2008-19-06), and repetitively 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.
    (i) For airplanes S/Ns 434 through 459, the inspection required 
in paragraph (f)(2) of this AD is considered the initial inspection 
required in paragraph (g)(1) of this AD.
    (ii) 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 the inspections required 
in paragraph (g)(1) of this AD, before further flight, replace the 
assembly following SOCATA Mandatory TBM Aircraft Service Bulletin SB 
70-176, amendment 1, dated February 2010.
    (h) At the next annual inspection or within 5 months after the 
effective date of this AD, whichever occurs first, replace the 
alternator/compressor support and pulley drive assemblies with P/N 
T700G215500700100 (alternator/compressor support) and P/N 
T700G215513500000 (Pulley drive assembly), following the 
accomplishment instructions of SOCATA SB 70-176, amendment 1, dated 
February 2010.
    (1) After the effective date of this AD, do not install 
alternator/compressor support P/N T700G215500700000 and a pulley 
drive assembly P/N T700G215510000000.
    (2) Accomplishment of corrective actions as required by 
paragraph (f)(2)(i), paragraph (g)(2), or paragraph (h) of this AD 
terminates the actions required in paragraphs (f) and (g) of this 
AD.

    Note 2: SOCATA SB 70-161-21 amendment 4, dated October 2009, has 
been published by SOCATA in order to close the range of airplane S/
Ns concerned by temporary actions.

FAA AD Differences

    Note 3: 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:

[[Page 59661]]

    (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.

Special Flight Permit

    (j) We are allowing permission to ferry an airplane to a 
maintenance location to accomplish actions required by paragraph (1) 
of this AD provided that the air conditioning is switched off during 
the entire flight duration.

Related Information

    (k) Refer to MCAI EASA AD No.: 2010-0130, dated June 29, 2010; 
and SOCATA Service Bulletin SB 70-176, amendment 1, dated February 
2010, for related information.

    Issued in Kansas City, Missouri, on September 22, 2010.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-24248 Filed 9-27-10; 8:45 am]
BILLING CODE 4910-13-P