[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)]
[Proposed Rules]
[Pages 21199-21203]
[FR Doc No: 2018-09602]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD]
RIN 2120-AA64

Airworthiness Directives; SOCATA Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-16-03
for SOCATA Models TB 9 and TB 10 airplanes. 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 fatigue cracking of the wing front attachments on the wing
and fuselage sides. We are issuing this proposed AD to require actions
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 25, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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.
     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.
    For service information identified in this proposed AD, contact
SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone:
+33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email:

[email protected]; internet: https://www.mysocata.com/login/accueil.php. You may review copies of the referenced service
information at the FAA, Policy and Innovation Division, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.

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-2018-
0326; or in person at Docket Operations 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 Docket Operations (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 Standards Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
email: [email protected].

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-2018-0326;
Product Identifier 2018-CE-006-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

    We issued AD 98-16-03, Amendment 39-10677 (63 FR 40359; July 29,
1998). That AD required actions intended to address an unsafe condition
on SOCATA Models TB 9 and TB 10 airplanes and was based on mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country.
    Since we issued AD 98-16-03, SOCATA developed improved repair
procedures and increased the applicability to include Model TB 200
airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD No. 2018-0030, dated January 31, 2018 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:

    During a scheduled maintenance inspection, cracks were found on
the wing front attachments of a TB 10 aeroplane.
    This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
    Prompted by these findings, SOCATA issued SB 10-081-57 to
provide inspection and modification instructions, and DGAC France
issued AD 94-264(A), later revised, to require repetitive
inspections of wing front attachments of TB 9 and TB 10 aeroplanes
(all MSN up to 822 inclusive, with some excluded). That [DGAC
France] AD also required installation of reinforcement kits, applied
as repair (if cracks were found) or as modification (if no cracks
were found), of the wing front attachments, on both wing and
fuselage sides, and repetitive replacement of those reinforcements
afterwards.
    Since DGAC France AD 94-264(A) R1 was issued, cracks have been
found on wing front attachments, on the wing side, on TB10
aeroplanes to which the AD did not apply, i.e. which were not
subject to repetitive inspections as required by that [DGAC France]
AD. Consequently, SOCATA revised SB 10-081-57 (now at revision (rev)
3), extending the Applicability to all TB 10 aeroplanes, as well as
to TB 200 aeroplanes, and improving the repair solution of the wing
front attachment on wing side.
    For the reason described above, this [EASA] AD retains the
requirements of DGAC France AD 94-264(A) R1, which is superseded,
expands the Applicability to all MSN for TB 9 and TB 10 aeroplanes
and includes TB 200 aeroplanes, and requires an improved repair
solution of the wing front attachment on wing side.

    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0326.

Related Service Information Under 1 CFR Part 51

    SOCATA has issued Daher Service Bulletin SB 10-081, Revision 3,
dated December 2017. The service bulletin describes procedures for
inspecting the front attachments and installing modification kits. 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 NPRM.

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.

Costs of Compliance

    We estimate that this proposed AD will affect 126 products of U.S.
registry. We also estimate that it would take about 3 work-hours per
product to comply with the inspection requirements of this proposed AD.
We also estimate that it would take about 25 work-hours per product to
comply with the replacement/modification (wing and fuselage sides)
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Required parts would cost about $3,000 per product.
    Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $677,880, or $5,380 per product.
    In addition, we estimate that any necessary follow-on actions to
replace the wing attachment on the wing side, resulting from the
repetitive inspections, would take about 9 work-hours and require parts
costing $3,000, for a cost of $3,765 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.

    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism
implications 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:
    (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.

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

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 Airworthiness Directive (AD)
98-16-03, Amendment 39-10677 (63 FR 40359; July 29, 1998), and adding
the following new AD:

SOCATA: Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD.

(a) Comments Due Date

    We must receive comments by June 25, 2018.

(b) Affected ADs

    This AD replaces AD 98-16-03, Amendment 39-10677 (63 FR 40359;
July 29, 1998) (``AD 98-16-03'').

(c) Applicability

    This AD applies to SOCATA airplanes listed in the following
groups, certificated in any category:
    (1) Group 1 airplanes: Model TB 9, all manufacturer serial
numbers (MSN); and Model TB 10, MSN 001 through 803, 805, 806, 809
through 815, and 820 through 822; and
    (2) Group 2 airplanes: Model TB 10, MSN 804, 807, 808, 816
through 819, and 823 through 2229; and Model TB 200, all MSNs.

(d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

(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 fatigue cracking
of the wing front attachments on the wing and fuselage sides. We are
issuing this AD to prevent fatigue cracking of the wing front
attachments, which could lead to structural failure of the airplane
and loss of control.

(f) Compliance

    Unless already done, do the following actions listed in
paragraphs (g) through (j) of this AD. The compliance times of this
AD are presented in landings instead of hours time-in-service (TIS).
If the number of landings is unknown, multiply the number of hours
TIS by 1.5. For the purposes of this AD, ``XX'' can be any numerical
value.

(g) Actions for Airplanes NOT EQUIPPED With Modification Kit
OPT109110XX

    (1) Within the compliance time specified in table 1 to paragraph
(g)(1) of this AD, do an initial inspection of the wing front
attachments on the wing side. Inspect repetitively thereafter at
intervals not to exceed 3,000 landings. Follow the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.019

    (2) If a crack was found during any inspection required in
paragraph (g)(1) of this AD, before further flight, install the
modification reinforcement kit OPT10911002 for the front attachment
on the wing side following the Description of Accomplishment
Instructions in SOCATA Daher Service Bulletin SB 10-081, Revision 3,
December 2017.
    (3) Within the compliance time specified in table 2 to paragraph
(g)(3) of this AD, unless already done as corrective action as
specified in paragraph (g)(2) of this AD, install the modification
reinforcement kit OPT10911002 for the front attachment on the wing
side following the Description of Accomplishment Instructions in
SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017.

[GRAPHIC] [TIFF OMITTED] TP09MY18.020

(h) Actions for Airplanes EQUIPPED With Modification Kit OPT109110XX

    (1) Within the compliance time specified in table 3 to paragraph
(h)(1) of this AD, do an initial inspection of the reinforced front
attachment on the wing side. Inspect repetitively thereafter at
intervals not to exceed 3,000 landings. Follow the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.021

    (2) Replacing kit OPT109110XX with kit OPT10911002 on an
airplane, at intervals not to exceed 6,000 landings is acceptable to
comply with the inspection requirements of paragraph (h)(1) of this
AD for that airplane. Follow the Description of Accomplishment
Instructions in SOCATA Daher Service Bulletin SB 10-081, Revision 3,
December 2017.
    (3) If a crack was found during any inspection required in
paragraph (h)(1) of this AD, before further flight, do the
applicable corrective actions following the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.

(i) Actions for Group 1 Airplanes

    (1) Within the compliance time specified in table 4 to paragraph
(i)(1) of this AD, do an initial inspection of the wing front
attachments on the fuselage side. Inspect repetitively thereafter at
intervals not to exceed 3,000 landings. Follow the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
[GRAPHIC] [TIFF OMITTED] TP09MY18.022

    (2) If a crack was found during any inspection required in
paragraph (i)(1) of this AD, before further flight, do the
applicable corrective actions following the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.
    (3) Unless already done as corrective action required in
paragraph (i)(2) of this AD, within the compliance time specified in
table 5 to paragraph (i)(3) of this AD, reinforce the front
attachment on fuselage side following the Description of
Accomplishment Instructions in SOCATA Daher Service Bulletin SB 10-
081, Revision 3, December 2017.

[GRAPHIC] [TIFF OMITTED] TP09MY18.023

    (4) Before or upon accumulating 12,000 landings after the
reinforcement modification required in paragraph (i)(2) or (3) of
this AD, replace the reinforced front attachment on the fuselage
side following the Description of Accomplishment Instructions in
SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017.

(j) Replacement of the Reinforced Front Attachment

    Replacement of the reinforced front attachment on the wing side
and/or replacement of the reinforced front attachment on the
fuselage side, does not terminate the inspections required in
paragraphs (h)(1) and (i)(1) of this AD. After replacement, the
initial and repetitive inspection cycle starts over.

(k) Credit for Previous Actions

    This AD allows credit for the initial inspection required in
paragraphs (g)(1) and (i)(1) of this AD and any replacement that may
have been required based on the initial inspection, if done before
the effective date of this AD, following Socata Service Bulletin No.
SB 10-081-57, Revison 1, dated August 1996 or Revision 2, dated
January 2017. Any inspections or replacements done after the
effective date must be done following SOCATA Daher Service Bulletin
SB 10-081, Revision 3, December 2017 as specified in the Actions and
Compliance of this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Small Airplane Standards Branch, 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 Standards Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone:<PHONE_NUMBER>; 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, Small Airplane
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA).

(m) Related Information

    Refer to MCAI EASA No. 2018-0030, dated January 31, 2018; and
Daher Service Bulletin SB 10-081, Revision 3, dated December 2017,
for related information. You may examine the MCAI on the internet at
http://www.regulations.gov by searching for and locating Docket No.
FAA-2018-0326. For service information related to this AD, contact
SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone:
+33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email:
[email protected]; internet: https://www.mysocata.com/login/accueil.php. You may review copies of the referenced service
information at the FAA, Policy and Innovation Division, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.

    Issued in Kansas City, Missouri, on April 30, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification
Service.
[FR Doc. 2018-09602 Filed 5-8-18; 8:45 am]
BILLING CODE 4910-13-P