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2018-21-06 SOCATA: Amendment 39-19464; Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD.
(a) EFFECTIVE DATE

    This AD becomes effective December 10, 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, the "XX" in the kit numbers 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  paragraphs  B(1)  through  B(4)  under   the
    Description  of Accomplishment  Instructions in  SOCATA Daher  Service
    Bulletin SB 10-081, Revision 3, December 2017 (SB 10-081, Revision 3).

     TABLE 1 TO PARAGRAPH (G)(1) OF THIS AD  FRONT WING ATTACHMENT, WING 
                                              SIDE, INITIAL INSPECTION    
    ______________________________________________________________________
     COMPLIANCE TIME FOR INITIAL INSPECTION OF THE FRONT WING ATTACHMENT,
     WING SIDE (WHICHEVER OCCURS LATER, A OR B)
    ______________________________________________________________________
     A     Before or upon accumulating 3,000 landings on the airplane; or

     B     Group 1 airplanes: Within the next 100 landings after September
           21, 1998 (the effective date retained from AD 98-16-03). See
           paragraph (k) of this AD.

           Group 2 airplanes: Within 13 months after the effective date of
           this AD.
    ______________________________________________________________________

(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. Follow  paragraph B(5)  under the  Description of Accomplishment
    Instructions in SB 10-081, Revision 3.

(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.  Follow
    paragraph B(5) under the Description of Accomplishment Instructions in
    SB 10-081, Revision 3.

    TABLE 2 TO PARAGRAPH (G)(3) OF THIS AD  FRONT WING ATTACHMENT, WING  
                                             SIDE, INSTALLATION OF THE RE-
                                             INFORCEMENT MODIFICATION KIT 
    ______________________________________________________________________
    COMPLIANCE TIME FOR INSTALLATION OF THE REINFORCEMENT MODIFICATION KIT
    (WHICHEVER OCCURS LATER, A OR B)
    ______________________________________________________________________
    A     Before or upon accumulating 12,000 landings on the airplane; or

    B     Within the next 75 landings after the effective date of this AD.
    ______________________________________________________________________

(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  paragraphs B(1) through B(4)  under the
    Description of Accomplishment Instructions in SB 10-081, Revision 3.

     TABLE 3 TO PARAGRAPH (H)(1) OF THIS AD  FRONT WING ATTACHMENT, WING 
                                              SIDE, REINFORCEMENT KIT     
                                              INITIAL INSPECTION          
    ______________________________________________________________________
    COMPLIANCE TIME FOR INITIAL INSPECTION OF THE REINFORCEMENT KIT (WHICH
    -EVER OCCURS LATER, A OR B)
    ______________________________________________________________________
    A     Before or upon accumulating 6,000 landings on the airplane after
          installation of the reinforcement modification kit OPT109110XX;
          or

    B     Within the next 75 landings after the effective date of this AD.
    ______________________________________________________________________

(2) Replacing kit OPT109110XX with kit OPT10911002 on an airplane,  at in-
    tervals 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   paragraph   B(5)   under   the   Description   of
    Accomplishment Instructions in SB 10-081, Revision 3.

(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. Follow paragraph B(5) under the Description of Accomplishment
    Instructions in SB 10-081, Revision 3.

(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  paragraphs B(1) through B(4)  under the
    Description of Accomplishment Instructions in SB 10-081, Revision 3.

       TABLE 4 TO PARAGRAPH (I)(1) OF THIS AD  FRONT WING ATTACHMENT,    
                                                FUSELAGE SIDE, INITIAL    
                                                INSPECTION                
    ______________________________________________________________________
     COMPLIANCE TIME FOR INITIAL INSPECTION OF THE FRONT WING ATTACHMENT,
     FUSELAGE SIDE (WHICHEVER OCCURS LATER, A OR B)
    ______________________________________________________________________
    A       Before or upon accumulating 3,000 landings on the airplane; or

    B       Within the next 100 landings after September 21, 1998 (the
            effective date of this AD retained from AD 98-16-03). See
            paragraph (k) of this AD.
    ______________________________________________________________________

(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. Follow paragraph B(5) under the Description of Accomplishment
    Instructions in SB 10-081, Revision 3.

(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.  Follow  paragraph B(5)(b)  under  the  Description of
    Accomplishment Instructions in SB 10-081, Revision 3.

    TABLE 5 TO PARAGRAPH (I)(3) OF THIS AD  FRONT WING ATTACHMENT,       
                                             FUSELAGE SIDE, REINFORCEMENT 
                                             MODIFICATION                 
    ______________________________________________________________________
    AIRPLANE MODELS        MSN AND CONFIGURATION          COMPLIANCE TIME
    ______________________________________________________________________
    TB 9              MSN 001 to 399 and 413 airplanes    Before or upon
    TB 10             that do not have SOCATA Technical   accumulating
                      Instruction OPT10-9081-53 (Kit      6,000 landings
                      OPT908100) installed                on the airplane.

    TB 9              MSN 001 to 399 and 413 airplanes    Before or upon
    TB 10             that do have SOCATA Technical       accumulating
                      Instruction OPT 10-9081-53 (Kit     12,000 landings
                      OPT908100) installed                on the airplane.

    TB 9              MSN 400 to 412 and 414 to 2229      Before or upon
                                                          accumulating
                                                          12,000 landings
                                                          on the airplane.

    TB 10             MSN 400 to 412, 414 to 803, 805,    Before or upon
                      806, 809 to 815, and 820 to 822     accumulating
                                                          12,000 landings
                                                          on the airplane.
    ______________________________________________________________________

(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. Follow paragraph
    B(5)(c) under the Description of Accomplishment Instructions in SB  10
    -081, Revision 3.

(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  inspections  required  in
    paragraphs (g)(1), (h)(1),  and (i)(1) of  this AD if  done before the
    effective date of this AD by following Socata Service Bulletin No.  SB
    10-081-57, Revision 1, dated August 1996 or Revision 2, dated  January
    2017. This  AD also  allows credit  for any  replacement that may have
    been required based on  the initial inspection required  in paragraphs
    (g)(1), (h)(1),  and (i)(1)  of this  AD if  done before the effective
    date of this AD by following Socata Service Bulletin No. SB 10-081-57,
    Revision 1, dated August 1996 or Revision 2, dated January 2017. After
    the  effective  date  of  this AD,  you  must  do  any inspections  or
    replacements by following SB 10-081, Revision 3.

(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: Quentin  Coon, Aerospace  Engineer,  901 Locust,
    Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4168; fax:
    (816) 329-4090; email: quentin.coon@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) Contacting the Manufacturer:  For any requirement in this AD to obtain
    corrective actions  from a  manufacturer, the  action must  instead 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 Socata
    Service Bulletin No. SB 10-081-57,  Revision 1,  dated August 1996, or
    Revision 2, dated January 2017, for related information.  The MCAI can
    be found in the AD docket on the internet at: https://www.regulations.
    gov/document?D=FAA-2018-0326-0003.

(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.

(i) SOCATA Daher Service Bulletin SB 10-081, Revision 3, December 2017.

(ii) [Reserved]

(3) For  service  information  identified  in  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: info@socata.daher.com;
    internet: https://www.mysocata.com/login/accueil.php.

(4) You may view this service information at FAA,  Policy  and  Innovation
    Division, 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-2018-0326.

(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 October 26, 2018.  Melvin J. Johnson,
Aircraft  Certification Service,  Deputy Director,  Policy and  Innovation
Division, AIR-601.

FOR FURTHER INFORMATION CONTACT:  Quentin Coon,  Aerospace  Engineer,  901
Locust, Room 301, Kansas City, Missouri 64106;  telephone: (816) 329-4168;
fax: (816) 329-4090; email: quentin.coon@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0326; Product Identifier 2018-CE-006-AD; Amendment
39-19464; AD 2018-21-06]
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) 98-16-03 for
SOCATA Model TB 9 and Model TB 10 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 fatigue cracking of the wing front attachments on the wing
and fuselage sides. We are issuing this AD to require actions to
address the unsafe condition on these products.

DATES: This AD is effective December 10, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 10,
2018.

ADDRESSES: 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, 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; phone: +33 (0) 5
62 41 73 00; fax: +33 (0) 5 62 41 76 54; email: info@socata.daher.com;
internet: https://www.mysocata.com/login/accueil.php. You may view this
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 (816) 329-4148. It
is also available on the internet at http://www.regulations.gov by
searching for Docket No. FAA-2018-0326.

FOR FURTHER INFORMATION CONTACT: Quentin Coon, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-
4168; fax: (816) 329-4090; email: quentin.coon@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 98-16-03, Amendment 39-10677 (63 FR 40359, July
29, 1998) (``AD 98-16-03''). The NPRM was published in the Federal
Register on May 9, 2018 (83 FR 21199), and proposed to correct an
unsafe condition for SOCATA Model TB 9, Model TB 10, and Model TB 200
airplanes. We based the NPRM on MCAI originated by an aviation
authority of another country. The European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, issued EASA AD No. 2018-0030, dated January 31,
2018 (referred to after this as ``the MCAI''). The MCAI states that:

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.

The MCAI can be found in the AD docket on the internet at: https://www.regulations.gov/document?D=FAA-2018-0326-0003.

Comments

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

Request for an Explanation of Compliance Time

Daher requested that we explain why the compliance times in the
NPRM are presented in landings and do not match the compliance times in
the EASA AD, which uses both hours time-in-service (TIS) and number of
landings.
The NPRM retained the compliance times from AD 98-16-03, which were
based in landings instead of hours TIS. The NPRM also retained the
formula for converting hours TIS to landings from AD 98-16-03 for
airplanes with an unknown number of landings. Because we also retained
the effective date of AD 98-16-03 for certain actions, we determined the
NPRM would not use both landings and hours TIS, as in the EASA AD.

Change to the Final Rule

In the NPRM, in table 1 to paragraph (g)(1) and table 4 to
paragraph (i)(1), we inadvertently referenced the incorrect paragraph
designator in the retained compliance times as, ``See paragraph (g) of
this AD.'' In this AD, we corrected the paragraph designator to read,
``See paragraph (k) of this AD.''
We also revised the incorporation by reference of the service
information to specify the provisions required for each action, instead
of the entire service document.

Conclusion

We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed except for the changes previously described and other
minor editorial changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

We reviewed 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.

Costs of Compliance

We estimate that this 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 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
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 this 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 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-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
the NPRM, 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.

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

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