83 FR 39004 - Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 153 (August 8, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 153 (August 8, 2018)
| Page Range | 39004-39007 | |
| FR Document | 2018-16637 |
[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)] [Proposed Rules] [Pages 39004-39007] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-16637] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede airworthiness directive (AD) 2015-22- 02 for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. AD 2015-22-02 requires inspecting the tail rotor (TR) pitch link assemblies. This proposed AD would retain the inspections of AD 2015-22-02 and would require replacing certain pitch link bearings. Since we issued AD 2015-22-02, Bell has introduced a new design bearing. The actions of this proposed AD are intended to prevent an unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 9, 2018. ADDRESSES: You may send comments by any of the following methods: [[Page 39005]]Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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- 0722; 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 Transport Canada AD, the economic 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 service information identified in this final rule, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion We issued AD 2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015) (AD 2015-22-02), for Bell Model 429 helicopters with a TR pitch link assembly part number (P/N) 429-112-101 or 429-112-103 installed. AD 2015-22-02 requires repetitively inspecting each inboard and outboard TR pitch link assembly for axial or radial bearing play every 50 hours time-in-service (TIS), performing a dimensional inspection of the TR pitch link if there is axial or radial bearing play, and replacing the TR pitch link before further flight if there is any wear beyond allowable limits. AD 2015-22-02 was prompted by Emergency AD No. CF-2015-16, dated July 2, 2015, and Emergency AD No. CF-2015-16R1, dated August 6, 2015, issued by Transport Canada, to correct an unsafe condition for Bell Model 429 helicopters. Transport Canada advised of several occasions where the TR pitch link spherical bearings experienced early and accelerated wear. Actions Since AD 2015-22-02 Was Issued Since we issued AD 2015-22-02, Transport Canada has issued AD No. CF-2015-16R2, dated April 17, 2017, which supersedes AD CF-2015-16R1. According to Transport Canada, Bell has reported that the TR pitch link assembly can be rotated during the 50-hour inspections to extend the serviceability life of the bearings. Transport Canada AD No. CF-2015- 16R2 requires modified inspection procedures for the spherical bearings and requires replacing the TR pitch link bearings (or the TR pitch link assembly) with spherical bearings manufactured after January 12, 2015. Transport Canada AD No. CF-2015-16R2 also requires re-identifying TR pitch link assemblies with a different P/N after installing the new bearings. We propose to issue this AD to make similar changes. FAA's Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its technical representative, has notified us of the unsafe condition described in the Transport Canada AD. We are proposing this AD because we evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Related Service Information Bell has issued Alert Service Bulletin No. 429-15-16, Revision B, dated June 15, 2016. This service information contains procedures for repetitively inspecting the TR pitch link assembly until it is upgraded by replacing the TR pitch link bearings. AD Requirements This proposed AD would require performing a dimensional inspection of the spherical bearings for axial and radial play and inspecting the TR pitch link assembly sealant for pin holes, voids, and excessive thickness. These inspections would be required within 50 hours TIS and thereafter at intervals not exceeding 50 hours TIS. This proposed AD would also require replacing any spherical bearing manufactured before January 13, 2015, that has exceeded 250 hours TIS or that has an unknown number of hours TIS, and re-identifying the P/N of the TR pitch link assembly. Differences Between This Proposed AD and the Transport Canada AD The Transport Canada AD requires the bearing inspection within 10 hours TIS or before exceeding 60 hours TIS since new, whichever occurs later. This proposed AD would require the bearing inspection within 50 hours TIS. The Transport Canada AD also requires replacing certain bearings within 200 hours TIS after the initial bearing inspection or within 250 hours TIS since new, whichever occurs first. This proposed AD would require replacing the bearing within 200 hours of the initial inspection or at the next 50 hour TIS inspection if the hours TIS of a pitch link assembly exceed 250 hours TIS or are unknown. Interim Action We consider this proposed AD to be an interim action. If final action is later [[Page 39006]] identified, we might consider further rulemaking then. Costs of Compliance We estimate that this proposed AD would affect 85 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this proposed AD. At an average labor rate of $85 per hour, inspecting the TR pitch link assemblies would require 2 work-hours for a cost of $170 per helicopter and $14,450 for the U.S. fleet per inspection cycle. Replacing both spherical bearings in each TR pitch link assembly would require 3 work-hours, and required parts would cost $3,088, for a cost of $3,343 per helicopter and $284,155 for the U.S. fleet. According to Bell's service information some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by Bell. Accordingly, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD will not have federalism implications under Executive Order 13132. This proposed 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, I certify that this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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) 2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015), and adding the following new AD: Bell Helicopter Textron Canada Limited: Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD. (a) Applicability This AD applies to Model 429 helicopters with a pitch link assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429- 012-112-101FM, or 429-012-112-103FM installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a worn pitch link. This condition, if not corrected, could result in pitch link failure and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces AD 2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015). (d) Comments Due Date We must receive comments by October 9, 2018. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Within 50 hours time-in-service (TIS) and thereafter at intervals not to exceed 50 hours TIS: (i) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10X or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing. (ii) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing. (2) For pitch link assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within 200 hours TIS following the initial inspection required by paragraph (f)(1) of this AD, or if the hours TIS of a pitch link assembly exceed 250 hours TIS or are unknown, at the next 50 hour TIS inspection required by paragraph (f)(1) of this AD: (i) Replace each bearing P/N 429-312-107-103 with a date of manufacture before January 13, 2015, with a bearing P/N 429-312-107- 103 that was manufactured on or after January 13, 2015. (ii) Using a white permanent fine point marker or equivalent, re-identify the pitch link assembly: (A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as 429-012-112-111FM. (B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as 429-012-112-113FM. (iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over the new P/N. (g) Special Flight Permits Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. [[Page 39007]] (i) Additional Information (1) Bell Alert Service Bulletin No. 429-15-16, Revision B, dated June 15, 2016, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in Transport Canada AD No. CF-2015-16R2, dated April 17, 2017. You may view the Transport Canada AD on the internet at http://www.regulations.gov in the AD Docket. (j) Subject Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor Control System. Issued in Fort Worth, Texas, on July 23, 2018. Scott A. Horn, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018-16637 Filed 8-7-18; 8:45 am] BILLING CODE 4910-13-P
![39004 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
information collection. The NCUA may Affairs, Office of Management and List of Subjects in 12 CFR Part 702
not conduct or sponsor, and the Budget, Attention: Desk Officer for Credit unions, Reporting and
respondent is not required to respond NCUA, New Executive Office Building, recordkeeping requirements.
to, an information collection unless it Room 10235, Washington, DC 20503, or
displays a currently valid Office of email at By the National Credit Union
Management and Budget (OMB) control OIRA_Submission,@OMB.EOP.gov. Administration Board on August 2, 2018.
number. Submission of comments. The NCUA Gerard Poliquin,
The proposed changes to part 702 considers comments by the public on Secretary of the Board.
would increase the asset size of credit this proposed collection of information For the reasons discussed above, the
unions identified as complex from in: Board proposes to further amend 12
greater than $100 million to greater than • Evaluating whether the proposed CFR part 702, as amended in a final rule
$500 million. This change would reduce collection of information is necessary at 80 FR 66625 (Oct. 29, 2015), effective
the number of credit unions who must for the proper performance of the January 1, 2019, as follows:
comply with recordkeeping functions of the NCUA, including
requirements prescribed by § 702.101(b). whether the information will have a PART 702—CAPITAL ADEQUACY
Therefore, the burden cleared under practical use;
OMB number 3133–0191 will be revised • Evaluating the accuracy of the ■ 1. The authority citation for part 702
to reflect the reduction in the number of NCUA’s estimate of the burden of the continues to read as follows:
respondents.50 proposed collection of information, Authority: 12 U.S.C. 1766(a), 1790d.
Title of Information Collection: including the validity of the
Prompt Corrective Action—Risk-Based methodology and assumptions used; § 702.103 [Amended]
Capital. • Enhancing the quality, usefulness,
OMB Control Number: 3133–0191. ■ 2. Amend § 702.103 by removing the
and clarity of the information to be words ‘‘one hundred million dollars
Affected Public: Private Sector: Not- collected; and
for-profit institutions—Complex Credit ($100,000,000)’’ and add in their place
• Minimizing the burden of collection ‘‘five hundred million dollars
Unions. of information on those who are to
Estimated Number of Respondents: ($500,000,000).’’
respond, including through the use of
531. [FR Doc. 2018–16888 Filed 8–7–18; 8:45 am]
appropriate automated, electronic,
Estimated Number of Responses per BILLING CODE 7535–01–P
mechanical, or other technological
Respondent: 1.
collection techniques or other forms of
Estimated Hours per Response: 40.
Estimated Total Annual Burden information technology; e.g., permitting
electronic submission of responses. DEPARTMENT OF TRANSPORTATION
Hours: 21,240.
By exempting credit unions with Executive Order 13132 Federal Aviation Administration
assets between $100 million and $500
Executive Order 13132 encourages
million, the NCUA estimates that the 14 CFR Part 39
independent regulatory agencies to
burden under this proposed rule would [Docket No. FAA–2018–0722; Product
consider the impact of their actions on
be 41,040 fewer hours. Identifier 2017–SW–104–AD
The Board invites comment on (a) state and local interests. The NCUA, an
whether the collections of information independent regulatory agency as RIN 2120–AA64
are necessary for the proper defined in 44 U.S.C. 3502(5), voluntarily
performance of the agency’s function, complies with the principles of the Airworthiness Directives; Bell
including practical utility; (b) the executive order to adhere to Helicopter Textron Canada Limited
accuracy of estimates of the burden of fundamental federalism principles. This Helicopters
the information collections, including proposed rule reduces the number of
federally insured natural-person credit AGENCY: Federal Aviation
the validity of the methodology and Administration (FAA), Department of
assumptions used; (c) ways to enhance unions, including federally insured,
state-chartered natural-person credit Transportation (DOT).
the quality, utility, and clarity of the ACTION: Notice of proposed rulemaking
information being collected, and (d) unions that would be subject to the 2015
Final Rule. It may have, to some degree, (NPRM).
ways to minimize the burden of the
information collection on respondents, a direct effect on the states, on the
relationship between the national SUMMARY: We propose to supersede
including through the use of automated airworthiness directive (AD) 2015–22–
collection techniques or other forms of government and the states, or on the
distribution of power and 02 for Bell Helicopter Textron Canada
information technology. Limited (Bell) Model 429 helicopters.
All comments are a matter of public responsibilities among the various
levels of government. It does not, AD 2015–22–02 requires inspecting the
record. Comments regarding the tail rotor (TR) pitch link assemblies.
information collection requirements of however, rise to the level of material
impact for purposed of Executive Order This proposed AD would retain the
this rule should be sent to (1) Dawn inspections of AD 2015–22–02 and
Wolfgang, NCUA PRA Clearance 13132.
would require replacing certain pitch
Officer, National Credit Union Assessment of Federal Regulations and link bearings. Since we issued AD
Administration, 1775 Duke Street, Suite Policies on Families 2015–22–02, Bell has introduced a new
amozie on DSK3GDR082PROD with PROPOSALS
5080, Alexandria, Virginia 22314, or Fax design bearing. The actions of this
The NCUA has determined that this
No. 703–519–8572, or Email at proposed AD are intended to prevent an
proposed rule will not affect family
PRAcomments@ncua.gov and the (2) unsafe condition on these products.
well-being within the meaning of
Office of Information and Regulatory DATES: We must receive comments on
section 654 of the Treasury and General
50 Proposed revisions to OMB control number Government Appropriations Act, 1999, this proposed AD by October 9, 2018.
3133–0191 have been submitted to OMB for Public Law 105–277, 112 Stat. 2681 ADDRESSES: You may send comments by
approval in accordance with 5 CFR 1320.11. (1998). any of the following methods:
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![39006 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
identified, we might consider further 2. Is not a ‘‘significant rule’’ under (f) Required Actions
rulemaking then. DOT Regulatory Policies and Procedures (1) Within 50 hours time-in-service (TIS)
(44 FR 11034, February 26, 1979); and thereafter at intervals not to exceed 50
Costs of Compliance
3. Will not affect intrastate aviation in hours TIS:
We estimate that this proposed AD Alaska to the extent that it justifies (i) Perform a dimensional inspection of
would affect 85 helicopters of U.S. making a regulatory distinction; and each inboard and outboard pitch link
Registry. We estimate that operators 4. Will not have a significant assembly for axial and radial bearing play.
may incur the following costs in order With a 10X or higher power magnifying glass,
economic impact, positive or negative,
to comply with this proposed AD. At an inspect the bearing liner for a crack,
on a substantial number of small entities deterioration of the liner, and extrusion of
average labor rate of $85 per hour, under the criteria of the Regulatory the liner from the plane. If there is axial or
inspecting the TR pitch link assemblies Flexibility Act. radial play that exceeds allowable limits, or
would require 2 work-hours for a cost of We prepared an economic evaluation if there is a crack, deterioration of the liner,
$170 per helicopter and $14,450 for the of the estimated costs to comply with or extrusion of the liner, before further flight,
U.S. fleet per inspection cycle. this proposed AD and placed it in the replace the bearing.
Replacing both spherical bearings in AD docket. (ii) Inspect the pitch link assembly sealant
each TR pitch link assembly would for pin holes and voids and to determine if
require 3 work-hours, and required parts List of Subjects in 14 CFR Part 39 the sealant thickness is 0.025 inch (0.64 mm)
would cost $3,088, for a cost of $3,343 Air transportation, Aircraft, Aviation or less, extends over the roll staked lip by
per helicopter and $284,155 for the U.S. 0.030 inch (0.76 mm) or more, and is clear
safety, Incorporation by reference,
of the bearing ball. If there is a pin hole or
fleet. Safety. void, or if the sealant exceeds 0.026 inch
According to Bell’s service
The Proposed Amendment (0.66 mm), does not extend over the roll
information some of the costs of this staked lip by 0.030 inch (0.76 mm) or more,
proposed AD may be covered under Accordingly, under the authority or is not clear of the bearing ball, before
warranty, thereby reducing the cost delegated to me by the Administrator, further flight, replace the bearing.
impact on affected individuals. We do the FAA proposes to amend 14 CFR part (2) For pitch link assembly part number
not control warranty coverage by Bell. 39 as follows: (P/N) 429–012–112–101, 429–012–112–103,
Accordingly, we have included all costs 429–012–112–101FM, and 429–012–112–
in our cost estimate. PART 39—AIRWORTHINESS 103FM, within 200 hours TIS following the
DIRECTIVES initial inspection required by paragraph (f)(1)
Authority for This Rulemaking of this AD, or if the hours TIS of a pitch link
Title 49 of the United States Code ■ 1. The authority citation for part 39 assembly exceed 250 hours TIS or are
specifies the FAA’s authority to issue continues to read as follows: unknown, at the next 50 hour TIS inspection
required by paragraph (f)(1) of this AD:
rules on aviation safety. Subtitle I, Authority: 49 U.S.C. 106(g), 40113, 44701. (i) Replace each bearing P/N 429–312–107–
section 106, describes the authority of 103 with a date of manufacture before
the FAA Administrator. ‘‘Subtitle VII: § 39.13 [Amended]
January 13, 2015, with a bearing P/N 429–
Aviation Programs,’’ describes in more ■ 2. The FAA amends § 39.13 by 312–107–103 that was manufactured on or
detail the scope of the Agency’s removing Airworthiness Directive (AD) after January 13, 2015.
authority. 2015–22–02, Amendment 39–18306 (80 (ii) Using a white permanent fine point
We are issuing this rulemaking under FR 65618, October 27, 2015), and marker or equivalent, re-identify the pitch
the authority described in ‘‘Subtitle VII, adding the following new AD: link assembly:
Part A, Subpart III, Section 44701: (A) Re-identify P/N 429–012–112–101 and
Bell Helicopter Textron Canada Limited:
General requirements.’’ Under that 429–012–112–101FM as 429–012–112–
Docket No. FAA–2018–0722; Product
section, Congress charges the FAA with 111FM.
Identifier 2017–SW–104–AD.
(B) Re-identify P/N 429–012–112–103 and
promoting safe flight of civil aircraft in 429–012–112–103FM as 429–012–112–
(a) Applicability
air commerce by prescribing regulations 113FM.
for practices, methods, and procedures This AD applies to Model 429 helicopters
with a pitch link assembly part number (iii) Apply a coating of DEVCON 2–TON
the Administrator finds necessary for (C–298) or equivalent over the new P/N.
(P/N) 429–012–112–101, 429–012–112–103,
safety in air commerce. This regulation 429–012–112–101FM, or 429–012–112– (g) Special Flight Permits
is within the scope of that authority 103FM installed, certificated in any category.
because it addresses an unsafe condition Special flight permits are prohibited.
that is likely to exist or develop on (b) Unsafe Condition
(h) Alternative Methods of Compliance
products identified in this rulemaking This AD defines the unsafe condition as a (AMOCs)
action. worn pitch link. This condition, if not
corrected, could result in pitch link failure (1) The Manager, Safety Management
Regulatory Findings and subsequent loss of control of the Section, Rotorcraft Standards Branch, FAA,
helicopter. may approve AMOCs for this AD. Send your
We determined that this proposed AD proposal to: David Hatfield, Aviation Safety
will not have federalism implications (c) Affected ADs Engineer, Safety Management Section,
under Executive Order 13132. This This AD replaces AD 2015–22–02, Rotorcraft Standards Branch, FAA, 10101
proposed AD will not have a substantial Amendment 39–18306 (80 FR 65618, October Hillwood Pkwy., Fort Worth, TX 76177;
direct effect on the States, on the 27, 2015). telephone (817) 222–5110; email 9-ASW-
relationship between the national FTW-AMOC-Requests@faa.gov.
(d) Comments Due Date
amozie on DSK3GDR082PROD with PROPOSALS
Government and the States, or on the (2) For operations conducted under a 14
We must receive comments by October 9, CFR part 119 operating certificate or under
distribution of power and 14 CFR part 91, subpart K, we suggest that
2018.
responsibilities among the various you notify your principal inspector, or
levels of government. (e) Compliance lacking a principal inspector, the manager of
For the reasons discussed, I certify You are responsible for performing each the local flight standards district office or
that this proposed regulation: action required by this AD within the certificate holding district office, before
1. Is not a ‘‘significant regulatory specified compliance time unless it has operating any aircraft complying with this
action’’ under Executive Order 12866; already been accomplished prior to that time. AD through an AMOC.
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![Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 39007
(i) Additional Information • Federal eRulemaking Docket: Go to does not contain duplicate comments,
(1) Bell Alert Service Bulletin No. 429–15– http://www.regulations.gov. Follow the commenters should send only one copy
16, Revision B, dated June 15, 2016, which online instructions for sending your of written comments, or if comments are
is not incorporated by reference, contains comments electronically. filed electronically, commenters should
additional information about the subject of • Fax: 202–493–2251. submit only one time.
this AD. For service information identified in • Mail: Send comments to the U.S. We will file in the docket all
this AD, contact Bell Helicopter Textron comments that we receive, as well as a
Canada Limited, 12,800 Rue de l’Avenir,
Department of Transportation, Docket
Mirabel, Quebec J7J1R4; telephone (450) Operations, M–30, West Building report summarizing each substantive
437–2862 or (800) 363–8023; fax (450) 433– Ground Floor, Room W12–140, 1200 public contact with FAA personnel
0272; or at http://www.bellcustomer.com/ New Jersey Avenue SE, Washington, DC concerning this proposed rulemaking.
files/. You may review a copy of the service 20590–0001. Before acting on this proposal, we will
information at the FAA, Office of the • Hand Delivery: Deliver to the consider all comments we receive on or
Regional Counsel, Southwest Region, 10101 ‘‘Mail’’ address between 9 a.m. and 5 before the closing date for comments.
Hillwood Pkwy., Room 6N–321, Fort Worth, p.m., Monday through Friday, except We will consider comments filed after
TX 76177. the comment period has closed if it is
(2) The subject of this AD is addressed in Federal holidays.
Transport Canada AD No. CF–2015–16R2, possible to do so without incurring
Examining the AD Docket expense or delay. We may change this
dated April 17, 2017. You may view the
Transport Canada AD on the internet at You may examine the AD docket on proposal in light of the comments we
http://www.regulations.gov in the AD Docket. the internet at http:// receive.
(j) Subject
www.regulations.gov by searching for Discussion
and locating Docket No. FAA–2018–
Joint Aircraft Service Component (JASC) We issued AD 2016–25–19,
0669; or in person at Docket Operations
Code: 6720 Tail Rotor Control System. Amendment 39–18745 (81 FR 95854,
between 9 a.m. and 5 p.m., Monday
Issued in Fort Worth, Texas, on July 23, through Friday, except Federal holidays. December 29, 2016) (AD 2016–25–19),
2018. The AD docket contains this proposed for Airbus Helicopters Model AS350B3
Scott A. Horn, AD, the European Aviation Safety and EC130B4 helicopters with the
Deputy Director for Regulatory Operations, Agency (EASA) AD, the economic ARRIEL 2B1 engine with the two-
Compliance & Airworthiness Division, evaluation, any comments received and channel Full Authority Digital Engine
Aircraft Certification Service. Control (FADEC) and with new twist
other information. The street address for
[FR Doc. 2018–16637 Filed 8–7–18; 8:45 am] Docket Operations (telephone 800–647– grip modification (MOD) 073254 (for the
BILLING CODE 4910–13–P 5527) is in the ADDRESSES section. Model AS350B3 helicopter) or MOD
Comments will be available in the AD 073773 (for the Model EC130B4
docket shortly after receipt. helicopter). AD 2016–25–19 requires
DEPARTMENT OF TRANSPORTATION For service information identified in repetitively inspecting the wiring,
this proposed rule, contact Airbus performing an insulation test, inspecting
Federal Aviation Administration the pilot and copilot throttle twist grip
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone controls, and testing the pilot and
14 CFR Part 39 copilot throttle twist grip controls for
(972) 641–0000 or (800) 232–0323; fax
[Docket No. FAA–2018–0669; Product (972) 641–3775; or at http:// proper functioning. AD 2016–25–19 was
Identifier 2017–SW–041–AD] www.helicopters.airbus.com/website/ prompted by AD No. 2013–0191–E,
en/ref/Technical-Support_73.html. You dated August 22, 2013 (EASA AD 2013–
RIN 2120–AA64
may review service information at the 0191–E), issued by EASA, which is the
Airworthiness Directives; Airbus FAA, Office of the Regional Counsel, Technical Agent for the Member States
Helicopters (Previously Eurocopter Southwest Region, 10101 Hillwood of the European Union. EASA advised
France) Pkwy, Room 6N–321, Fort Worth, TX that the switches in the engine ‘‘IDLE’’
76177. or ‘‘FLIGHT’’ control system could be
AGENCY: Federal Aviation affected by the corrosive effects of a salt-
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: laden atmosphere, which could lead to
ACTION: Notice of proposed rulemaking George Schwab, Aviation Safety engine power loss. EASA AD 2013–
(NPRM). Engineer, Safety Management Section, 0191–E required repetitive inspections
Rotorcraft Standards Branch, FAA, for corrosion, application of corrosion
SUMMARY: We propose to supersede 10101 Hillwood Pkwy., Fort Worth, TX protection on the switches, and testing
Airworthiness Directive (AD) 2016–25– 76177; telephone (817) 222–5110; email
19 for Airbus Helicopters (previously of the insulation and switches of the
george.schwab@faa.gov. engine idle and flight control system.
Eurocopter France) Model AS350B3 and
SUPPLEMENTARY INFORMATION: The actions required in AD 2016–25–19
EC130B4 helicopters. AD 2016–25–19
requires inspecting the pilot’s and co- Comments Invited are intended to prevent unintended
pilot’s throttle twist for proper touchdown to the ground at a flight-idle
We invite you to participate in this power setting during a practice
operation. This proposed AD would rulemaking by submitting written
retain the requirements of AD 2016–25– autorotation, damage to the helicopter,
comments, data, or views. We also and injury to occupants.
19 and add certain model helicopters to invite comments relating to the
the applicability. The actions of this Actions Since AD 2016–25–19 Was
amozie on DSK3GDR082PROD with PROPOSALS
economic, environmental, energy, or
proposed AD are intended to address federalism impacts that might result Issued
the unsafe condition on these from adopting the proposals in this Since we issued AD 2016–25–19,
helicopters. document. The most helpful comments EASA issued AD No. 2017–0052, dated
DATES: We must receive comments on reference a specific portion of the March 24, 2017, which superseded
this proposed AD by October 9, 2018. proposal, explain the reason for any EASA AD No. 2013–0191–E, dated
ADDRESSES: You may send comments by recommended change, and include August 22, 2013. EASA advised that
any of the following methods: supporting data. To ensure the docket Airbus Helicopters had added
VerDate Sep<11>2014 18:59 Aug 07, 2018 Jkt 244001 PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 E:\FR\FM\08AUP1.SGM 08AUP1](https://thefederalregister.org/doc/83_FR_39157/page/4.svg)
Document Created: 2018-08-08 02:04:59
Document Modified: 2018-08-08 02:04:59
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by October 9, 2018. | |
| Contact | David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 83 FR 39004 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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