
[Federal Register Volume 79, Number 84 (Thursday, May 1, 2014)]
[Rules and Regulations]
[Pages 24556-24558]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-09421]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0031; Directorate Identifier 2013-CE-054-AD; 
Amendment 39-17838; AD 2014-09-03]
RIN 2120-AA64


Airworthiness Directives; SOCATA Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 99-07-11 for 
SOCATA Model TBM 700 airplanes. 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 on the outboard hinge fittings. We are issuing this 
AD to require actions to address the unsafe condition on these 
products.

DATES: This AD is effective June 5, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 5, 2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0031; or in person at the Docket Management Facility, U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this AD, contact 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 for North America: SOCATA 
NORTH AMERICA, North Perry Airport, 7501 South Airport Road, Pembroke 
Pines, Florida 33023; telephone: (954) 893-1400; fax: (954) 964-4141; 
email: mysocata@socata.daher.com; Internet: www.mysocata.com. You may 
view this referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For information 
on the availability of this material at the FAA, call (816) 329-4148.

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; email: 
albert.mercado@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to add an AD that would apply to certain SOCATA Model TBM 700 
airplanes. The NPRM was published in the Federal Register on January 
27, 2014 (79 FR 4300), and proposed to supersede AD 99-07-11, Amendment 
39-11096 (64 FR 14820, March 29, 1999) (``AD 99-07-11'').
    Since we issued AD 99-07-11 (64 FR 14820, March 29, 1999), SOCATA 
determined that the cause of the cracks in the horizontal stabilizer 
outboard hinge fitting was due to the incorrect installation of the 
fittings during production, which induced stress. SOCATA has issued new 
mandatory service information to require a modification to the outboard 
hinge fittings of the horizontal stabilizer to eliminate the stress.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2013-0035, dated February 22, 2013 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    During the 1990s, several occurrences were reported of finding 
cracks in the outboard hinge fittings of the horizontal stabiliser 
on TBM 700 aeroplanes.
    This condition, if not detected and corrected, could result in 
rupture of the outboard hinge fittings, which would adversely affect 
the structural integrity of the horizontal stabiliser. The in-flight 
loss of the horizontal stabiliser would result in reduced control of 
the aeroplane,
    To address this unsafe condition, DGAC France issued AD 1999-
060(A), requiring repetitive inspections of the fittings and, 
depending on findings, corrective action.
    After that AD was issued, SOCATA determined that the cause of 
the cracks was a wrong installation of the fittings during 
production, inducing stress. Consequently, DGAC France issued AD 
2000-307(A), partially retaining the requirements of DGAC France AD 
1999-060(A), which was superseded, and required, depending on 
findings, that the installation of the fittings of in-service 
aeroplanes be rectified by

[[Page 24557]]

introduction of adjusting shims, a modification which was introduced 
as standard on the production line from MSN 162. The periodical 
inspection of the fittings for cracks was still required, pending a 
better understanding of the cause of the cracks.
    Since DCAG France AD 2000-307(A) was issued, the results of the 
further analysis revealed that the final design (installation of 
shims on the outboard hinge fittings of the horizontal stabiliser) 
guarantees a service fatigue life which exceeds the one established 
for the TBM 700 during certification. Consequently, for aeroplanes 
with this modification, the repetitive inspections of the fittings 
can be discontinued. However, as the installation of the fittings 
was only required depending on findings, this modification may not 
have been accomplished on all affected aeroplanes.
    For the reasons described above, this AD supersedes (and thereby 
cancels the requirements of) DGAC France AD 2000-307(A) and requires 
installation of shims on the outboard hinge fittings of the 
horizontal stabiliser.

    You may examine the MCAI on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0031-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Request To Incorporate Amended Service Bulletin

    DAHER-SOCATA requested that we incorporate Amendment 3 of Mandatory 
Service Bulletin SB 70-080, dated September 2013, into the AD to 
replace DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-080, 
Amendment 2, dated August 2012.
    We agree with the commenter to incorporate the newer version of the 
related service information. We will also give credit for complying 
with the actions in the proposed AD if already done before the 
effective date of this AD following DAHER-SOCATA TBM Aircraft Mandatory 
Service Bulletin SB 70-080, Amendment 2, dated August 2012.
    We have changed the final rule AD action based on this comment.

Request To Change the Number of Affected Airplanes

    DAHER-SOCATA requested that we change the number of affected 
airplanes in the Cost of Compliance section from 159 to 80, which is 
the number of U.S.-registered airplanes.
    We agree with the commenter and have changed the final rule AD 
action based on this comment.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 4300, January 27, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 4300, January 27, 2014).

We also determined that these changes will not increase the economic 
burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this proposed AD will affect 80 products of U.S. 
registry. We also estimate that it would take about 6.5 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 $500 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $84,200, or $1,052.50 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0031; 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) 647-5527) 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:

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 removing Amendment 39-11096 (64 FR 
14820, March 29, 1999), and adding the following new AD:

2014-09-03 SOCATA: Amendment 39-17838; Docket No. FAA-2014-0031; 
Directorate Identifier 2013-CE-054-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 5, 
2014.

(b) Affected ADs

    This AD supersedes AD 99-07-11, Amendment 39-11096 (64 FR 14820, 
March 29, 1999).

[[Page 24558]]

(c) Applicability

    This AD applies to SOCATA TBM 700 airplanes, manufacturer serial 
numbers (MSN) 1 through 98, 100 through 156, and 158 through 161, 
certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 55: Stabilizers.

(e) Reason

    This AD was prompted by 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 cracks on the 
outboard hinge fittings. We are issuing this AD to require the use 
of new service information issued by DAHER-SOCATA to eliminate the 
stress on the outboard hinge fittings, which is causing the cracks. 
If this condition is not prevented, the outboard hinge fittings 
could fail causing reduced structural integrity of the horizontal 
stabilizer, which could result in reduced control.

(f) Actions and Compliance

    Unless already done, within the next 100 hours time-in-service 
after June 5, 2014 (the effective date of this AD) or within the 
next 12 months after June 5, 2014 (the effective date of this AD), 
whichever occurs first, install shims on the outboard hinge fittings 
of the horizontal stabilizer. Do the modification following the 
Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory 
Service Bulletin SB 70-080, Amendment 3, dated September 2013.

(g) Credit for Actions Done Following Previous Service Information

    This AD allows credit for the actions required in paragraph (f) 
of this AD if done before June 5, 2014 (the effective date of this 
AD), following DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-080, Amendment 2, dated August 2012.

(h) Other FAA AD Provisions

    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; email: 
alebert.mercado@faa.gov. 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.

(i) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2013-0035, dated February 22, 2013, for related information. You may 
examine the MCAI on the Internet http://www.regulations.gov/#!documentDetail;D=FAA-2014-0031-0002.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
080, Amendment 3, dated September 2013.
    (ii) Reserved.
    (3) For SOCATA service information identified in this AD, 
contact 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 for North America: SOCATA NORTH AMERICA, North Perry Airport, 
7501 South Airport Road, Pembroke Pines, Florida 33023; telephone: 
(954) 893-1400; fax: (954) 964-4141; email: 
mysocata@socata.daher.com; Internet: www.mysocata.com.
    (4) You may view this service information at FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.
    (5) You may view this service information that is incorporated 
by reference 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 April 17, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014-09421 Filed 4-30-14; 8:45 am]
BILLING CODE 4910-13-P


