AD 2018-21-06

[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)]
[Rules and Regulations]
[Pages 55258-55263]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-24007]


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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; 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.

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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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#f891969e97b88b979b998c99d69c99909d8ad69b9795"><span class="__cf_email__" data-cfemail="91f8fff7fed1e2fef2f0e5f0bff5f0f9f4e3bff2fefc">[email&#160;protected]</span></a>; 
internet: <a href="https://www.mysocata.com/login/accueil.php">https://www.mysocata.com/login/accueil.php</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#bacbcfdfd4ced3d494d9d5d5d4fadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="255450404b514c4b0b464a4a4b654344440b424a53">[email&#160;protected]</span></a>.

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: <a href="https://www.regulations.gov/document?D=FAA-2018-0326-0003">https://www.regulations.gov/document?D=FAA-2018-0326-0003</a>.

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

[[Page 55259]]

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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

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:

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.

[[Page 55260]]

(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).
[GRAPHIC] [TIFF OMITTED] TR05NO18.003

    (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.
[GRAPHIC] [TIFF OMITTED] TR05NO18.004

(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.

[[Page 55261]]

[GRAPHIC] [TIFF OMITTED] TR05NO18.005

    (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 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.
[GRAPHIC] [TIFF OMITTED] TR05NO18.006

    (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.

[[Page 55262]]

[GRAPHIC] [TIFF OMITTED] TR05NO18.007

    (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: <a href="/cdn-cgi/l/email-protection#2657534348524f4808454949486640474708414950"><span class="__cf_email__" data-cfemail="f786829299839e99d994989899b7919696d9909881">[email&#160;protected]</span></a>. 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: <a href="https://www.regulations.gov/document?D=FAA-2018-0326-0003">https://www.regulations.gov/document?D=FAA-2018-0326-0003</a>.

(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: 
<a href="/cdn-cgi/l/email-protection#e38a8d858ca3908c80829782cd87828b8691cd808c8e"><span class="__cf_email__" data-cfemail="4b22252d240b3824282a3f2a652f2a232e3965282426">[email&#160;protected]</span></a>; internet: <a href="https://www.mysocata.com/login/accueil.php">https://www.mysocata.com/login/accueil.php</a>.
    (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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


[[Page 55263]]


    Issued in Kansas City, Missouri, on October 26, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation 
Division, AIR-601.
[FR Doc. 2018-24007 Filed 11-2-18; 8:45 am]
 BILLING CODE 4910-13-P