80 FR 51456 - Airworthiness Directives; SOCATA Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 164 (August 25, 2015)

Page Range		51456-51459
FR Document		2015-20588
We are superseding Airworthiness Directive (AD) 2007-04-13 for certain SOCATA Model TBM 700 airplaness (type certificate previously held by EADS SOCATA). 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 found on the main landing gear cylinders. We are issuing this AD to require actions to address the unsafe condition on these products.
Federal Register, Volume 80 Issue 164 (Tuesday, August 25, 2015)
[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)]
[Rules and Regulations]
[Pages 51456-51459]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-20588]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2047; Directorate Identifier 2015-CE-013-AD; 
Amendment 39-18243; AD 2015-17-10]
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) 2007-04-13 for 
certain SOCATA Model TBM 700 airplaness (type certificate previously 
held by EADS SOCATA). 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 
found on the main landing gear cylinders. We are issuing this AD to 
require actions to address the unsafe condition on these products.

DATES: This AD is effective September 29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
23, 2007 (72 FR 7576, February 16, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2047; 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 SOCATA North America, 
North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, 
telephone: (954) 893-1400; fax: (954) 964-4141; Internet: http://www.socata.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. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA-2015-2047.

FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
make changes to an NPRM (80 FR 8821, February 19, 2015), which would 
amend 14 CFR part 39 to add an AD that would apply to certain SOCATA 
Model TBM 700 airplaness (type certificate previously held by EADS 
SOCATA). That SNPRM was published in the Federal Register on June 11, 
2015 (80 FR 33208), and proposed to supersede

[[Page 51457]]

AD 2007-04-13, Amendment 39-14945, (72 FR 7576, February 16, 2007) 
(``AD 2007-04-13'').
    Since we issued AD 2007-04-13, it has been determined that the time 
between repetitive inspections should be extended and an optional 
terminating action for the repetitive inspections is now available.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2006-0085R2, dated January 16, 2015 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Cracks on several main landing gear (MLG) cylinders have been 
reported in service.
    This condition, if not to detected and corrected, could lead to 
fatigue cracks in the shock strut cylinder of the MLG, which could 
result in a collapsed MLG during take-off or landing runs, and 
possibly reduce the structural integrity of the aeroplane.
    To address this unsafe condition, EASA issued AD 2006-0085 to 
require repetitive special detailed inspections (SDI) for cracks of 
the MLG shock strut cylinder and, depending on findings, relevant 
investigative and corrective actions.
    After that AD was issued, SOCATA performed an analysis to 
demonstrate that the inspection interval could be extended, and 
developed a reinforced MLG less prone to fatigue, which is embodied 
in production through SOCATA modification (MOD) 70-0190-32 and can 
be introduced in service through SOCATA Service Bulletin (SB) 70-
130-32 at Revision 03.
    Prompted by these developments, EASA issued AD 2006-0085R1 to 
increase the inspection interval and to introduce the installation 
of a reinforced MLG on the right hand (RH) side and left hand (LH) 
side as an optional terminating action for the repetitive SDI 
required by this AD.
    Since that AD was issued, it was found that aeroplanes MSN 639 
to 683 (inclusive) are not affected by this AD. The applicability 
has therefore been revised to remove those MSN.

The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.
    In addition, we have determined that airplanes with MLG with 
forging body that had not reached 1,750 landings as of March 23, 2007 
(the effective date of AD 2007-04-13) were not affected by the AD. This 
is not the intent and allows airplanes to fly indefinitely with the 
unsafe condition. This AD includes those airplanes with MLG with 
forging body either at or under 1,750 landings as of March 23, 2007, 
and extends the time between the repetitive inspections until a 
reinforced landing gear is installed, which terminates the repetitive 
inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received one supportive comment to the NPRM (80 FR 8821, 
February 19, 2015) and no comments on the SNPRM (80 FR 33208, June 11, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (80 FR 33208, June 11, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (80 FR 33208, June 11, 2015).

Related Service Information Under 1 CFR Part 51

    EADS SOCATA has issued TBM Aircraft Mandatory Service Bulletin SB 
70-130, ATA No. 32, dated January 2006, and SOCATA has issued DAHER-
SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, 
dated December 2014. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI. 
The DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014, incorporates procedures for replacing 
cracked MLG with a reinforced MLG as a terminating action for the 
repetitive inspections. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD will affect 431 products of U.S. registry. 
We also estimate that it will take about 3 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $109,905, or $255 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $6,000, for a cost of 
$6,340 per product. We have no way of determining the number of 
products that may need these actions.

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-2015-
2047; 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 SNPRM, 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.

[[Page 51458]]

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 39-14945 (72 FR 
7576, February 16, 2007), and adding the following new AD:

2015-17-10 SOCATA (type certificate previously held by EADS SOCATA): 
Amendment 39-18243; Docket No. FAA-2015-2047; Directorate Identifier 
2015-CE-013-AD.

(a) Effective Date

    This AD becomes effective September 29, 2015.

(b) Affected ADs

    This AD supersedes AD 2007-04-13, Amendment 39-14945, (72 FR 
7576, February 16, 2007) (``AD 2007-04-13'').

(c) Applicability

    This AD applies to SOCATA Model TBM 700 airplanes, serial 
numbers 1 through 638 and 687, that:
    (1) are not equipped with a left-hand main landing gear (MLG) 
body part number (P/N) D68161 or D68161-1 and a right-hand MLG body 
P/N D68162 or D68162-1; and
    (2) are certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 32: Landing 
gear.

(e) Reason

    This AD was prompted 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 cracks found on 
the main landing gear cylinders. In addition, the FAA determined 
that airplanes with MLG with forging body that had not reached 1,750 
landings as of March 23, 2007 (the effective date of AD 2007-04-13) 
were not affected by AD 2007-04-13. This is not the intent and 
allows airplanes to fly indefinitely with the unsafe condition. This 
AD increases the scope of the affected airplanes by including those 
airplanes with MLG with forging body either at or under 1,750 
landings as of March 23, 2007, increases the time between the 
repetitive inspections, and incorporates a modification to terminate 
the required repetitive inspections. We are issuing this AD to 
detect and correct cracks in the shock strut cylinder of the MLG, 
which could cause the MLG to fail. Failure of the shock strut 
cylinder of the MLG could result in a collapsed MLG during takeoff 
or landing and possible reduced structural integrity of the 
airplane.

(f) Actions and Compliance for Airplanes Not Previously Affected by AD 
2007-04-13

    Unless already done, do the actions in paragraphs (f)(1), 
(f)(2), and (h) of this AD:
    (1) For MLG with forging body that were either at or under 1,750 
landings as of March 23, 2007 (the effective date of (AD 2007-04-
13): Upon or before accumulating 1,750 landings on the MLG with 
forging body since new or within the next 100 landings after 
September 29, 2015 (the effective date of this AD), whichever occurs 
later, inspect the forging body for cracks. Do the inspection 
following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (2) If no cracks are detected during the inspection required in 
paragraph (f)(1) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.

(g) Actions and Compliance for Airplanes Previously Affected by AD 
2007-04-13

    Unless already done, do the actions in paragraphs (g)(1), 
(g)(2), and (h) of this AD, including all subparagraphs:
    (1) As of March 23, 2007 (the effective date retained from AD 
2007-04-13), for MLG with forging body totaling more than 1,750 
landings but less than 3,501 landings since new:
    (i) Inspect the forging body for cracks within 100 landings 
after March 23, 2007 (the effective date retained from AD 2007-04-
13), following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in 
paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.
    (2) As of March 23, 2007 (the effective date retained from AD 
2007-04-13), for MLG with forging body totaling more than 3,500 
landings since new:
    (i) Inspect the forging body for cracks within 25 landings after 
March 23, 2007 (the effective date retained from AD 2007-04-13), 
following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in 
paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.

(h) Actions and Compliance for All Affected Airplanes

    If any cracks are detected during any inspection required in 
paragraphs (f)(1) through (g)(2) of this AD, including all 
subparagraphs:
    (1) Before further flight, remove the affected landing gear leg 
and confirm the presence of the crack with dye penetrant inspection 
or fluorescent penetrant inspection.
    (2) If the crack is confirmed, before further flight, contact 
SOCATA at the address in paragraph (l)(5) of this AD to coordinate 
the FAA-approved landing gear repair/replacement and implement any 
FAA-approved repair/replacement instructions obtained from SOCATA, 
or replace the cracked landing gear with a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014. This replacement 
terminates the repetitive inspections required by this AD.

(i) Calculating Unknown Number of Landings for Compliance

    The compliance times of this AD are presented in landings 
instead of hours time-in-service (TIS). If the number of landings is 
unknown, hours TIS may be used by dividing the number of hours TIS 
by 1.35.

 (j) 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 J. Mercado, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; 
email: [email protected]. 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.

[[Page 51459]]

(k) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2006-0085R2, dated January 16, 2015, for related information. You 
may examine the MCAI on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.

(l) 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.
    (3) The following service information was approved for IBR on 
September 29, 2015.
    (i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, Revision 3, dated December 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
March 23, 2007 (72 FR 7576, February 16, 2007).
    (i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, dated January 2006.
    (ii) Reserved.
    (5) 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 
SOCATA North America, North Perry Airport, 7501 S Airport Rd., 
Pembroke Pines, Florida 33023, telephone: (954) 893-1400; fax: (954) 
964-4141; Internet: http://www.socata.com.
    (6) 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. In addition, you can access this service information 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-2047.
    (7) 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 August 14, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-20588 Filed 8-24-15; 8:45 am]
 BILLING CODE 4910-13-P
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51457

AD 2007–04–13, Amendment 39–14945, Comments Authority for This Rulemaking
(72 FR 7576, February 16, 2007) (‘‘AD
We gave the public the opportunity to Title 49 of the United States Code
2007–04–13’’).
Since we issued AD 2007–04–13, it participate in developing this AD. We specifies the FAA’s authority to issue
has been determined that the time received one supportive comment to the rules on aviation safety. Subtitle I,
between repetitive inspections should NPRM (80 FR 8821, February 19, 2015) section 106, describes the authority of
be extended and an optional terminating and no comments on the SNPRM (80 FR the FAA Administrator. ‘‘Subtitle VII:
action for the repetitive inspections is 33208, June 11, 2015) or on the Aviation Programs,’’ describes in more
now available. determination of the cost to the public. detail the scope of the Agency’s
The European Aviation Safety Agency authority.
Conclusion
(EASA), which is the Technical Agent We are issuing this rulemaking under
for the Member States of the European We reviewed the relevant data and the authority described in ‘‘Subtitle VII,
Community, has issued AD No. 2006– determined that air safety and the Part A, Subpart III, section 44701:
0085R2, dated January 16, 2015 public interest require adopting the AD General requirements.’’ Under that
(referred to after this as ‘‘the MCAI’’), to as proposed except for minor editorial section, Congress charges the FAA with
correct an unsafe condition for the changes. We have determined that these promoting safe flight of civil aircraft in
specified products. The MCAI states: minor changes: air commerce by prescribing regulations
Cracks on several main landing gear (MLG)
• Are consistent with the intent that for practices, methods, and procedures
was proposed in the SNPRM (80 FR the Administrator finds necessary for
cylinders have been reported in service.
This condition, if not to detected and 33208, June 11, 2015) for correcting the safety in air commerce. This regulation
corrected, could lead to fatigue cracks in the unsafe condition; and is within the scope of that authority
shock strut cylinder of the MLG, which could • Do not add any additional burden because it addresses an unsafe condition
result in a collapsed MLG during take-off or upon the public than was already that is likely to exist or develop on
landing runs, and possibly reduce the proposed in the SNPRM (80 FR 33208, products identified in this rulemaking
structural integrity of the aeroplane. action.
June 11, 2015).
To address this unsafe condition, EASA
issued AD 2006–0085 to require repetitive Related Service Information Under 1 Regulatory Findings
special detailed inspections (SDI) for cracks CFR Part 51 We determined that this AD will not
of the MLG shock strut cylinder and,
depending on findings, relevant investigative EADS SOCATA has issued TBM have federalism implications under
and corrective actions. Aircraft Mandatory Service Bulletin SB Executive Order 13132. This AD will
After that AD was issued, SOCATA 70–130, ATA No. 32, dated January not have a substantial direct effect on
performed an analysis to demonstrate that 2006, and SOCATA has issued DAHER– the States, on the relationship between
the inspection interval could be extended, SOCATA TBM Aircraft Mandatory the national government and the States,
and developed a reinforced MLG less prone or on the distribution of power and
to fatigue, which is embodied in production
Service Bulletin SB 70–130, Revision 3,
dated December 2014. The actions responsibilities among the various
through SOCATA modification (MOD) 70– levels of government.
0190–32 and can be introduced in service described in this service information are
through SOCATA Service Bulletin (SB) 70– intended to correct the unsafe condition For the reasons discussed above, I
130–32 at Revision 03. identified in the MCAI. The DAHER– certify this AD:
Prompted by these developments, EASA SOCATA TBM Aircraft Mandatory (1) Is not a ‘‘significant regulatory
issued AD 2006–0085R1 to increase the Service Bulletin SB 70–130, Revision 3, action’’ under Executive Order 12866,
inspection interval and to introduce the dated December 2014, incorporates (2) Is not a ‘‘significant rule’’ under
installation of a reinforced MLG on the right procedures for replacing cracked MLG the DOT Regulatory Policies and
hand (RH) side and left hand (LH) side as an
optional terminating action for the repetitive
with a reinforced MLG as a terminating Procedures (44 FR 11034, February 26,
SDI required by this AD. action for the repetitive inspections. 1979),
Since that AD was issued, it was found that This service information is reasonably (3) Will not affect intrastate aviation
aeroplanes MSN 639 to 683 (inclusive) are available because the interested parties in Alaska, and
not affected by this AD. The applicability has have access to it through their normal (4) Will not have a significant
therefore been revised to remove those MSN. course of business or by the means economic impact, positive or negative,
The MCAI can be found in the AD identified in the ADDRESSES section of on a substantial number of small entities
docket on the Internet at: http:// this AD. under the criteria of the Regulatory
www.regulations.gov/ Costs of Compliance Flexibility Act.
#!documentDetail;D=FAA-2015-2047- Examining the AD Docket
0002. We estimate that this AD will affect
In addition, we have determined that 431 products of U.S. registry. We also You may examine the AD docket on
airplanes with MLG with forging body estimate that it will take about 3 work- the Internet at http://
that had not reached 1,750 landings as hours per product to comply with the www.regulations.gov by searching for
of March 23, 2007 (the effective date of basic requirements of this AD. The and locating Docket No. FAA–2015–
AD 2007–04–13) were not affected by average labor rate is $85 per work-hour. 2047; or in person at the Docket
the AD. This is not the intent and allows Based on these figures, we estimate the Management Facility between 9 a.m.
airplanes to fly indefinitely with the cost of this AD on U.S. operators to be and 5 p.m., Monday through Friday,
unsafe condition. This AD includes $109,905, or $255 per product. except Federal holidays. The AD docket
those airplanes with MLG with forging In addition, we estimate that any contains the SNPRM, the regulatory
Lhorne on DSK5TPTVN1PROD with RULES

body either at or under 1,750 landings necessary follow-on actions will take evaluation, any comments received, and
as of March 23, 2007, and extends the about 4 work-hours and require parts other information. The street address for
time between the repetitive inspections costing $6,000, for a cost of $6,340 per the Docket Office (telephone (800) 647–
until a reinforced landing gear is product. We have no way of 5527) is in the ADDRESSES section.
installed, which terminates the determining the number of products Comments will be available in the AD
repetitive inspections. that may need these actions. docket shortly after receipt.

VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\25AUR1.SGM 25AUR1
51458 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations

List of Subjects in 14 CFR Part 39 inspections. We are issuing this AD to detect Service Bulletin SB 70–130, dated January
and correct cracks in the shock strut cylinder 2006, or DAHER–SOCATA TBM Aircraft
Air transportation, Aircraft, Aviation of the MLG, which could cause the MLG to Mandatory Service Bulletin SB 70–130,
safety, Incorporation by reference, fail. Failure of the shock strut cylinder of the Revision 3, dated December 2014.
Safety. MLG could result in a collapsed MLG during (ii) If no cracks are detected during the
takeoff or landing and possible reduced inspection required in paragraph (g)(2)(i) of
Adoption of the Amendment this AD, repetitively thereafter inspect at
structural integrity of the airplane.
Accordingly, under the authority intervals not to exceed 240 landings until a
(f) Actions and Compliance for Airplanes reinforced landing gear specified in
delegated to me by the Administrator,
Not Previously Affected by AD 2007–04–13 paragraph E. Terminating Solution of the
the FAA amends 14 CFR part 39 as
Unless already done, do the actions in Accomplishment Instructions in DAHER–
follows:
paragraphs (f)(1), (f)(2), and (h) of this AD: SOCATA TBM Aircraft Mandatory Service
(1) For MLG with forging body that were Bulletin SB 70–130, Revision 3, dated
PART 39—AIRWORTHINESS December 2014, is installed.
either at or under 1,750 landings as of March
DIRECTIVES
23, 2007 (the effective date of (AD 2007–04– (h) Actions and Compliance for All Affected
■ 1. The authority citation for part 39 13): Upon or before accumulating 1,750 Airplanes
landings on the MLG with forging body since
continues to read as follows: new or within the next 100 landings after If any cracks are detected during any
Authority: 49 U.S.C. 106(g), 40113, 44701. September 29, 2015 (the effective date of this inspection required in paragraphs (f)(1)
AD), whichever occurs later, inspect the through (g)(2) of this AD, including all
§ 39.13 [Amended] forging body for cracks. Do the inspection subparagraphs:
following the Accomplishment Instructions (1) Before further flight, remove the
■ 2. The FAA amends § 39.13 by affected landing gear leg and confirm the
removing Amendment 39–14945 (72 FR of EADS SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–130, dated January presence of the crack with dye penetrant
7576, February 16, 2007), and adding inspection or fluorescent penetrant
2006, or DAHER–SOCATA TBM Aircraft
the following new AD: Mandatory Service Bulletin SB 70–130, inspection.
2015–17–10 SOCATA (type certificate Revision 3, dated December 2014. (2) If the crack is confirmed, before further
previously held by EADS SOCATA): (2) If no cracks are detected during the flight, contact SOCATA at the address in
Amendment 39–18243; Docket No. inspection required in paragraph (f)(1) of this paragraph (l)(5) of this AD to coordinate the
FAA–2015–2047; Directorate Identifier AD, repetitively thereafter inspect at intervals FAA-approved landing gear repair/
2015–CE–013–AD. not to exceed 240 landings until a reinforced replacement and implement any FAA-
landing gear specified in paragraph E. approved repair/replacement instructions
(a) Effective Date obtained from SOCATA, or replace the
Terminating Solution of the Accomplishment
This AD becomes effective September 29, cracked landing gear with a reinforced
Instructions in DAHER–SOCATA TBM
2015. landing gear specified in paragraph E.
Aircraft Mandatory Service Bulletin SB 70–
Terminating Solution of the Accomplishment
(b) Affected ADs 130, Revision 3, dated December 2014, is
Instructions in DAHER–SOCATA TBM
installed.
This AD supersedes AD 2007–04–13, Aircraft Mandatory Service Bulletin SB 70–
Amendment 39–14945, (72 FR 7576, (g) Actions and Compliance for Airplanes 130, Revision 3, dated December 2014. This
February 16, 2007) (‘‘AD 2007–04–13’’). Previously Affected by AD 2007–04–13 replacement terminates the repetitive
Unless already done, do the actions in inspections required by this AD.
(c) Applicability
paragraphs (g)(1), (g)(2), and (h) of this AD, (i) Calculating Unknown Number of
This AD applies to SOCATA Model TBM including all subparagraphs:
700 airplanes, serial numbers 1 through 638 Landings for Compliance
(1) As of March 23, 2007 (the effective date The compliance times of this AD are
and 687, that:
retained from AD 2007–04–13), for MLG with presented in landings instead of hours time-
(1) are not equipped with a left-hand main
forging body totaling more than 1,750 in-service (TIS). If the number of landings is
landing gear (MLG) body part number (P/N)
landings but less than 3,501 landings since unknown, hours TIS may be used by dividing
D68161 or D68161–1 and a right-hand MLG
new: the number of hours TIS by 1.35.
body P/N D68162 or D68162–1; and
(i) Inspect the forging body for cracks
(2) are certificated in any category.
within 100 landings after March 23, 2007 (the (j) Other FAA AD Provisions
(d) Subject effective date retained from AD 2007–04–13), The following provisions also apply to this
Air Transport Association of America following the Accomplishment Instructions AD:
(ATA) Code 32: Landing gear. of EADS SOCATA TBM Aircraft Mandatory (1) Alternative Methods of Compliance
Service Bulletin SB 70–130, dated January (AMOCs): The Manager, Standards Office,
(e) Reason 2006, or DAHER–SOCATA TBM Aircraft FAA, has the authority to approve AMOCs
This AD was prompted from mandatory Mandatory Service Bulletin SB 70–130, for this AD, if requested using the procedures
continuing airworthiness information (MCAI) Revision 3, dated December 2014. found in 14 CFR 39.19. Send information to
originated by an aviation authority of another (ii) If no cracks are detected during the ATTN: Albert J. Mercado, Aerospace
country to identify and correct an unsafe inspection required in paragraph (g)(1)(i) of Engineer, FAA, Small Airplane Directorate,
condition on an aviation product. The MCAI this AD, repetitively thereafter inspect at 901 Locust, Room 301, Kansas City, Missouri
describes the unsafe condition as cracks intervals not to exceed 240 landings until a 64106; telephone: (816) 329–4119; fax: (816)
found on the main landing gear cylinders. In reinforced landing gear specified in 329–4090; email: albert.mercado@faa.gov.
addition, the FAA determined that airplanes paragraph E. Terminating Solution of the Before using any approved AMOC on any
with MLG with forging body that had not Accomplishment Instructions in DAHER– airplane to which the AMOC applies, notify
reached 1,750 landings as of March 23, 2007 SOCATA TBM Aircraft Mandatory Service your appropriate principal inspector (PI) in
(the effective date of AD 2007–04–13) were Bulletin SB 70–130, Revision 3, dated the FAA Flight Standards District Office
not affected by AD 2007–04–13. This is not December 2014, is installed. (FSDO), or lacking a PI, your local FSDO.
the intent and allows airplanes to fly (2) As of March 23, 2007 (the effective date (2) Airworthy Product: For any requirement
indefinitely with the unsafe condition. This retained from AD 2007–04–13), for MLG with in this AD to obtain corrective actions from
Lhorne on DSK5TPTVN1PROD with RULES

AD increases the scope of the affected forging body totaling more than 3,500 a manufacturer or other source, use these
airplanes by including those airplanes with landings since new: actions if they are FAA-approved. Corrective
MLG with forging body either at or under (i) Inspect the forging body for cracks actions are considered FAA-approved if they
1,750 landings as of March 23, 2007, within 25 landings after March 23, 2007 (the are approved by the State of Design Authority
increases the time between the repetitive effective date retained from AD 2007–04–13), (or their delegated agent). You are required
inspections, and incorporates a modification following the Accomplishment Instructions to assure the product is airworthy before it
to terminate the required repetitive of EADS SOCATA TBM Aircraft Mandatory is returned to service.

VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\25AUR1.SGM 25AUR1
Document Created: 2018-02-23 11:02:36
Document Modified: 2018-02-23 11:02:36
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective September 29, 2015.
Contact		Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: [email protected]
FR Citation		80 FR 51456
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 51456 - Airworthiness Directives; SOCATA Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 164 (August 25, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
