Airworthiness Directives; SOCATA Airplanes, 21199-21203 [2018-09602]
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Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
CLG that has not exceeded the applicable life
limit specified in paragraph (g)(2)(i), (g)(2)(ii),
or (g)(2)(iii) of this AD, since first installation
on an airplane.
(i) The life limit specified in the applicable
service information identified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD.
(ii) The life limit specified in Airbus A330
Airworthiness Limitations Section (ALS) Part
1, ‘‘Safe Life Airworthiness Limitation Items
(SL–ALI),’’ Revision 09, dated September 18,
2017, and A330 ALS Part 1, ‘‘Safe Life
Airworthiness Limitation Items (SL–ALI),’’
Variation 9.2, dated November 28, 2017.
(iii) The life limit specified in Airbus A340
Airworthiness Limitations Section (ALS) Part
1, ‘‘Safe Life Airworthiness Limitation Items
(SL–ALI),’’ Revision 09, dated September 18,
2017, and A340 ALS Part 1, ‘‘Safe Life
Airworthiness Limitation Items (SL–ALI),’’
Variation 9.2, dated November 28, 2017.
(h) Identification of Part Number, Serial
Number, Weight Variant, and Reduced Life
Limit
Within 3 months after the effective date of
this AD: Identify the part number and serial
number of each main fitting, bogie beam, and
sliding piston of the MLG, NLG, and CLG
installed on the airplane; identify the
airplane’s weight variant; and determine the
applicable reduced life limit; in accordance
with the Accomplishment Instructions of the
applicable service information identified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD.
A review of airplane maintenance records is
acceptable for identification of the installed
main fittings, bogie beams, and sliding
pistons of the MLG, NLG, and CLG, provided
the part number and serial number of each
component can be conclusively identified by
that review.
(1) Airbus Service Bulletin A330–32–3281,
Revision 02, dated June 16, 2017, including
Appendixes 01 through 06.
(2) Airbus Service Bulletin A340–32–4310,
Revision 02, dated June 16, 2017, including
Appendixes 01 through 06.
(3) Airbus Service Bulletin A340–32–5119,
Revision 01, dated January 31, 2017,
including Appendixes 01 through 07.
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(i) Replacement of Affected Parts
Prior to exceeding the applicable life limit,
as specified in the applicable service
information identified in paragraph (h)(1),
(h)(2), or (h)(3) of this AD, or within 3
months after the effective date of this AD,
whichever occurs later: Replace each affected
part (as defined in paragraph (g)(1) of this
AD) with a serviceable part (as defined in
paragraph (g)(2) of this AD).
(j) Parts Installation Specification
As of the effective date of this AD, any
affected part (as defined in paragraph (g)(1)
of this AD) may be used as a replacement
part, provided the affected part is also a
serviceable part (as defined in paragraph
(g)(2) of this AD), and following installation,
the affected part is replaced prior to
exceeding the applicable life limit as
specified in paragraph (g)(2) of this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
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(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(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, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0185, dated September 22, 2017, for
related information. This MCAI may be
found in the AD docket on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2018–0395.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198–6547; telephone
and fax 206–231–3229.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
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Issued in Des Moines, Washington, on
April 30, 2018.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–09743 Filed 5–8–18; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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.
SUMMARY:
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• 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:
DATES:
(l) Related Information
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Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
info@socata.daher.com; 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 (816) 329–4148.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
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: (816) 329–
4119; fax: (816) 329–4090; email:
albert.mercado@faa.gov.
SUPPLEMENTARY INFORMATION:
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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 https://
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.
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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 https://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.
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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 workhours 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.
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Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
Regulatory Findings
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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.
(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
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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.
The Proposed Amendment
(d) Subject
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Air Transport Association of America
(ATA) Code 57: Wings.
List of Subjects in 14 CFR Part 39
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.
§ 39.13
[Amended]
2. The FAA amends § 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,
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
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(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 timein-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.
wing side following the Description of
Accomplishment Instructions in SOCATA
Daher Service Bulletin SB 10–081, Revision
3, December 2017.
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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.
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Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
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.
(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
(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.
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(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.
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(1) Within the compliance time specified
in table 3 to paragraph (h)(1) of this AD, do
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(h) Actions for Airplanes EQUIPPED With
Modification Kit OPT109110XX
Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
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(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
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17:09 May 08, 2018
Jkt 244001
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:
(816) 329–4119; fax: (816) 329–4090; email:
albert.mercado@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) 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).
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
(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 https://
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: info@socata.daher.com; 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,
Proposed Commission Interpretation
Regarding Standard of Conduct for
Investment Advisers; Request for
Comment on Enhancing Investment
Adviser Regulation
PO 00000
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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
SECURITIES AND EXCHANGE
COMMISSION
17 CFR Part 275
[Release No. IA–4889; File No. S7–09–18]
RIN 3235–AM36
Securities and Exchange
Commission.
ACTION: Proposed interpretation; request
for comment.
AGENCY:
The Securities and Exchange
Commission (the ‘‘SEC’’ or the
‘‘Commission’’) is publishing for
comment a proposed interpretation of
the standard of conduct for investment
SUMMARY:
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(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.
21203
]]>Agencies
[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)]
[Proposed Rules]
[Pages 21199-21203]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
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:
[[Page 21200]]
[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 (816) 329-4148.
Examining the AD Docket
You may examine the AD docket on the internet at https://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: (816) 329-4119; fax: (816) 329-4090;
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 https://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 https://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.
[[Page 21201]]
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.
[[Page 21202]]
[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.
[[Page 21203]]
[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: (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) 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
https://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 (816) 329-4148.
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
