80 FR 65618 - Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 207 (October 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 207 (October 27, 2015)
| Page Range | 65618-65620 | |
| FR Document | 2015-27137 |
[Federal Register Volume 80, Number 207 (Tuesday, October 27, 2015)] [Rules and Regulations] [Pages 65618-65620] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-27137] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4345; Directorate Identifier 2015-SW-049-AD; Amendment 39-18306; AD 2015-22-02] RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding emergency airworthiness directive (AD) No. 2015-16-51 (Emergency AD 2015-16-51) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. Emergency AD 2015-16-51 required inspections of each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play, and if there was axial or radial bearing play, removing the tail rotor pitch link and inspecting for wear. Emergency AD 2015-16-51 was prompted by several reports of worn tail rotor pitch link spherical bearings. We are issuing this supersedure to retain the inspection requirements in Emergency AD 2015- 16-51 while revising the applicability and compliance time to clarify that all Bell Model 429 helicopters require recurring inspections regardless of hours time-in-service (TIS) accumulated on the helicopter. These actions are intended to prevent pitch link failure and subsequent loss of control of the helicopter. DATES: This AD becomes effective November 12, 2015. We must receive comments on this AD by December 28, 2015. ADDRESSES: You may send comments by any of the following methods: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-2015- 4345; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the Transport Canada Emergency AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (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 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 the referenced service information at the FAA, Office of the [[Page 65619]] 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 Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, 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 resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion Transport Canada, which is the aviation authority for Canada, issued Emergency AD No. CF-2015-16, dated July 2, 2015, to correct an unsafe condition for Bell Model 429 helicopters. Transport Canada advised that in-service reports showed that the tail rotor pitch link spherical bearings have experienced early and accelerated wear. On three occasions, bearings were found worn beyond limits during pre- flight inspections, showing a radial and axial play that was easily detectable. In one case, the spherical bearing separated from the tail rotor pitch link, resulting in damage to the tail rotor blade pitch horn assembly. In another case, the spherical bearing had been inspected and found acceptable during a maintenance inspection; about ``1 hour air time'' later, it was found worn beyond limits during a pre-flight inspection. On August 6, 2015, we issued Emergency AD 2015-16-51, which was made immediately effective to all known U.S. owners and operators of Bell Model 429 helicopters. Emergency AD 2015-16-51 required, before further flight and thereafter at intervals not to exceed 50 hours TIS, inspecting each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play. Emergency AD 2015-16-51 also required, if there was axial or radial bearing play, removing the tail rotor pitch link and performing a dimensional inspection for wear. Finally, Emergency AD 2015-16-51 required, if wear exceeded the allowable limits, replacing the tail rotor pitch link assembly. Actions Since Emergency AD 2015-16-51 Was Issued On the same day that we issued Emergency AD 2015-16-51, Transport Canada issued a revised Emergency AD No. CF-2015-16R1, dated August 6, 2015, changing the applicability and compliance time to clarify that the inspections are required for all Model 429 helicopters. Transport Canada advises of the possibility that some operators would conclude that no action was required for low time helicopters. Transport Canada Emergency AD No. CF-2015-16R1 removes the following language from the applicability so that it applies to all Model 429 helicopters regardless of time: ``that have accumulated 50 hours air time or more.'' It also adds language to the compliance time so that the corrective actions must be accomplished within 10 hours air time ``or before exceeding 60 hours air time since new, whichever occurs later.'' Therefore, we are issuing this AD to make similar revisions. FAA's Determination These helicopters have been approved by Transport 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 its Emergency AD. We are issuing 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 helicopters of this same type design. Related Service Information Bell issued Alert Service Bulletin 429-15-16, dated February 18, 2015 (ASB) for Bell Model 429 helicopters, S/N 57001 and subsequent, which have accumulated more than 50 hours. The ASB specifies inspecting both inboard and outboard tail rotor pitch link assemblies for axial and radial play. If abnormal wear or bearing play is detected, the ASB specifies removing the affected tail rotor pitch link, performing a dimensional check of both axial and radial play, and replacing any tail rotor pitch link assembly 429-012-112-101 or -103 or pitch link bearing 429-312-107-103 that exceeds the allowable limits. AD Requirements This AD retains the inspection requirements of Emergency AD 2015- 16-51 but revises the applicability and compliance time. This AD applies to Model 429 helicopters regardless of accumulated TIS. The inspections in this AD are required before further flight for helicopters with 50 or more hours TIS and before accumulating 50 hours TIS for helicopters with less than 50 hours TIS. Differences Between This AD and the Transport Canada Emergency AD The Transport Canada Emergency AD requires compliance within 10 hours TIS or before exceeding 60 hours air time, whichever occurs later. This AD requires compliance before further flight for helicopters with 50 or more hours TIS. For helicopters with less than 50 hours TIS, this AD requires compliance before the helicopter accumulates 50 hours TIS. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this AD affects 54 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work hour. It will take about 2 work hours to do the inspections at an estimated cost of $170 per helicopter or $9,180 for the fleet per inspection cycle. Replacing a tail rotor pitch link assembly will take 4 work hours and required parts will cost $2,685 for a total cost of $3,025 per helicopter. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we found and continue to find that the risk to the flying public justifies waiving notice and comment prior to adopting this rule because the previously described unsafe condition can adversely affect the controllability [[Page 65620]] of the helicopter, and the initial required corrective actions must be accomplished before further flight or before accumulating 50 hours TIS, depending upon the hours TIS accumulated on the helicopter. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment before issuing this AD were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by Emergency AD 2015-16- 51, issued on August 6, 2015, to all known U.S. owners and operators of these helicopters. These conditions still exist and the Emergency AD is hereby superseded. 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 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, I certify that this AD: 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 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. 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 adding the following new airworthiness directive (AD): 2015-22-02 Bell Helicopter Textron Canada Limited: Amendment 39- 18306; Docket No. FAA-2015-4345; Directorate Identifier 2015-SW-049- AD. (a) Applicability This AD applies to Model 429 helicopters with a pitch link assembly part number 429-012-112-101 or -103 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a worn pitch link. This condition, if not detected and corrected, could result in pitch link failure and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes Emergency AD 2015-16-51, Directorate Identifier 2015-SW-23-AD, dated August 6, 2015. (d) Effective Date This AD becomes effective November 12, 2015. (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) For helicopters with 50 or more hours time-in-service (TIS), before further flight, and for helicopters with less than 50 hours TIS, before accumulating 50 hours TIS, inspect each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play. If there is axial or radial bearing play, remove the tail rotor pitch link and perform a dimensional inspection for wear. If there is wear that exceeds the allowable limits, replace the tail rotor pitch link assembly. (2) Thereafter, at intervals not to exceed 50 hours TIS, repeat the inspections required by paragraph (f)(1) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. (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. (h) Additional Information (1) Bell Helicopter Alert Service Bulletin 429-15-16, dated February 18, 2015, 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 the referenced 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 Emergency AD No. CF-2015-16R1, dated August 6, 2015. You may view the Transport Canada Emergency AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-4345. (i) Subject Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor Control System. Issued in Fort Worth, Texas, on October 16, 2015. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-27137 Filed 10-26-15; 8:45 am] BILLING CODE 4910-13P
![65618 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations
the procedures specified in paragraph (k) of (2) Service information identified in this required inspections of each inboard
this AD. AD that is not incorporated by reference is and outboard tail rotor pitch link
available at the addresses specified in assembly for axial or radial bearing play,
(i) Exception to the Service Information paragraphs (m)(3) and (m)(4) of this AD.
(1) Where Boeing Alert Service Bulletin and if there was axial or radial bearing
747–53A2451, Revision 2, dated June 13, (m) Material Incorporated by Reference play, removing the tail rotor pitch link
2014, specifies a compliance time ‘‘after the (1) The Director of the Federal Register and inspecting for wear. Emergency AD
Revision 2 date of this service bulletin,’’ this approved the incorporation by reference 2015–16–51 was prompted by several
AD requires compliance within the specified (IBR) of the service information listed in this reports of worn tail rotor pitch link
time after the effective date of this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR spherical bearings. We are issuing this
(2) The Condition column of paragraph part 51. supersedure to retain the inspection
1.E., ‘‘Compliance,’’ of the Boeing Alert (2) You must use this service information requirements in Emergency AD 2015–
Service Bulletin 747–53A2451, Revision 2, as applicable to do the actions required by
dated June 13, 2014, refers to total flight 16–51 while revising the applicability
this AD, unless the AD specifies otherwise.
cycles ‘‘as of the Revision 2 date of this (i) Boeing Alert Service Bulletin 747– and compliance time to clarify that all
service bulletin.’’ This AD, however applies 53A2451, Revision 2, dated June 13, 2014. Bell Model 429 helicopters require
to airplanes with the specified total flight (ii) Reserved. recurring inspections regardless of
cycles or total flight hours as of the effective (3) For service information identified in hours time-in-service (TIS) accumulated
date of this AD. this AD, contact Boeing Commercial on the helicopter. These actions are
(j) Credit for Previous Actions Airplanes, Attention: Data & Services intended to prevent pitch link failure
Management, P.O. Box 3707, MC 2H–65, and subsequent loss of control of the
This paragraph provides credit for the Seattle, WA 98124–2207; telephone 206–
inspections and repairs of the inner chord helicopter.
544–5000, extension 1; fax 206–766–5680;
strap and angles of the station 800 frame Internet https://www.myboeingfleet.com. DATES: This AD becomes effective
assembly between stringer 14 and stringer 18 (4) You may view this service information November 12, 2015.
required by paragraphs (g) and (h) of this AD, at FAA, Transport Airplane Directorate, 1601 We must receive comments on this
if those actions were performed before the Lind Avenue SW., Renton, WA. For
effective date of this AD using Boeing Alert
AD by December 28, 2015.
information on the availability of this
Service Bulletin 747–53A2451, Revision 1, ADDRESSES: You may send comments by
material at the FAA, call 425–227–1221.
dated November 10, 2005, which was (5) You may view this service information any of the following methods:
incorporated by reference in AD 2006–12–12, that is incorporated by reference at the • Federal eRulemaking Docket: Go to
Amendment 39–14638 (71 FR 33595, June National Archives and Records http://www.regulations.gov. Follow the
12, 2006). Administration (NARA). For information on online instructions for sending your
(k) Alternative Methods of Compliance the availability of this material at NARA, call comments electronically.
(AMOCs) 202–741–6030, or go to: http:// • Fax: 202–493–2251.
(1) The Manager, Seattle Aircraft www.archives.gov/federal-register/cfr/ibr- • Mail: Send comments to the U.S.
Certification Office (ACO), FAA, has the locations.html. Department of Transportation, Docket
authority to approve AMOCs for this AD, if Issued in Renton, Washington, on October Operations, M–30, West Building
requested using the procedures found in 14 19, 2015. Ground Floor, Room W12–140, 1200
CFR 39.19. In accordance with 14 CFR 39.19, Jeffrey E. Duven, New Jersey Avenue SE., Washington,
send your request to your principal inspector DC 20590–0001.
Manager, Transport Airplane Directorate,
or local Flight Standards District Office, as • Hand Delivery: Deliver to the
Aircraft Certification Service.
appropriate. If sending information directly
[FR Doc. 2015–26979 Filed 10–26–15; 8:45 am] ‘‘Mail’’ address between 9 a.m. and 5
to the manager of the ACO, send it to the
attention of the person identified in BILLING CODE 4910–13–P
p.m., Monday through Friday, except
paragraph (l)(1) of this AD. Information may Federal holidays.
be emailed to: 9-ANM-Seattle-ACO-AMOC- Examining the AD Docket
Requests@faa.gov. DEPARTMENT OF TRANSPORTATION
(2) Before using any approved AMOC, You may examine the AD docket on
notify your appropriate principal inspector, Federal Aviation Administration the Internet at http://
or lacking a principal inspector, the manager www.regulations.gov by searching for
of the local flight standards district office/ and locating Docket No. FAA–2015–
14 CFR Part 39
certificate holding district office.
4345; or in person at the Docket
(3) An AMOC that provides an acceptable [Docket No. FAA–2015–4345; Directorate
level of safety may be used for any repair Operations Office between 9 a.m. and 5
Identifier 2015–SW–049–AD; Amendment
required by this AD if it is approved by the 39–18306; AD 2015–22–02] p.m., Monday through Friday, except
Boeing Commercial Airplanes Organization Federal holidays. The AD docket
Designation Authorization (ODA) that has RIN 2120–AA64 contains this AD, the Transport Canada
been authorized by the Manager, Seattle Emergency AD, the economic
ACO, to make those findings. For a repair Airworthiness Directives; Bell evaluation, any comments received, and
method to be approved, the repair must meet Helicopter Textron Canada Limited other information. The street address for
the certification basis of the airplane, and the Helicopters the Docket Operations Office (telephone
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2007–16–08, AGENCY: Federal Aviation 800–647–5527) is in the ADDRESSES
Amendment 39–15147 (72 FR 44728, August Administration (FAA), Department of section. Comments will be available in
9, 2007), are approved as AMOCs for the Transportation (DOT). the AD docket shortly after receipt. For
corresponding provisions of this AD. ACTION: Final rule; request for service information identified in this
(l) Related Information comments. AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
tkelley on DSK3SPTVN1PROD with RULES
(1) For more information about this AD, SUMMARY: We are superseding Mirabel, Quebec J7J1R4; telephone (450)
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
emergency airworthiness directive (AD) 437–2862 or (800) 363–8023; fax (450)
Aircraft Certification Office (ACO), 1601 Lind No. 2015–16–51 (Emergency AD 2015– 433–0272; or at http://
Avenue SW., Renton, WA 98057–3356; 16–51) for Bell Helicopter Textron www.bellcustomer.com/files/. You may
phone: 425–917–6432; fax: 425–917–6590; Canada Limited (Bell) Model 429 review the referenced service
email: bill.ashforth@faa.gov. helicopters. Emergency AD 2015–16–51 information at the FAA, Office of the
VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1](https://thefederalregister.org/doc/80_FR_65825/page/1.svg)
![65620 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations
of the helicopter, and the initial under the criteria of the Regulatory (2) Thereafter, at intervals not to exceed 50
required corrective actions must be Flexibility Act. hours TIS, repeat the inspections required by
accomplished before further flight or We prepared an economic evaluation paragraph (f)(1) of this AD.
before accumulating 50 hours TIS, of the estimated costs to comply with (g) Alternative Methods of Compliance
depending upon the hours TIS this AD and placed it in the AD docket. (AMOCs)
accumulated on the helicopter.
List of Subjects in 14 CFR Part 39 (1) The Manager, Safety Management
Since it was found that immediate
Group, FAA, may approve AMOCs for this
corrective action was required, notice Air transportation, Aircraft, Aviation
AD. Send your proposal to: David Hatfield,
and opportunity for prior public safety, Incorporation by reference,
Aviation Safety Engineer, Safety Management
comment before issuing this AD were Safety.
Group, Rotorcraft Directorate, FAA, 10101
impracticable and contrary to the public Adoption of the Amendment Hillwood Pkwy., Fort Worth, TX 76177;
interest, and good cause existed to make telephone (817) 222–5110; email 9-ASW-
the AD effective immediately by Accordingly, under the authority
FTW-AMOC-Requests@faa.gov.
Emergency AD 2015–16–51, issued on delegated to me by the Administrator,
(2) For operations conducted under a 14
August 6, 2015, to all known U.S. the FAA amends 14 CFR part 39 as
CFR part 119 operating certificate or under
owners and operators of these follows: 14 CFR part 91, subpart K, we suggest that
helicopters. These conditions still exist you notify your principal inspector, or
and the Emergency AD is hereby PART 39—AIRWORTHINESS
DIRECTIVES lacking a principal inspector, the manager of
superseded. the local flight standards district office or
Authority for This Rulemaking ■ 1. The authority citation for part 39 certificate holding district office, before
continues to read as follows: operating any aircraft complying with this
Title 49 of the United States Code AD through an AMOC.
specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701.
rules on aviation safety. Subtitle I, (h) Additional Information
§ 39.13 [Amended]
section 106, describes the authority of (1) Bell Helicopter Alert Service Bulletin
the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by adding 429–15–16, dated February 18, 2015, which
Aviation Programs,’’ describes in more the following new airworthiness is not incorporated by reference, contains
detail the scope of the Agency’s directive (AD): additional information about the subject of
authority. 2015–22–02 Bell Helicopter Textron this AD. For service information identified in
We are issuing this rulemaking under Canada Limited: Amendment 39–18306; this AD, contact Bell Helicopter Textron
the authority described in ‘‘Subtitle VII, Docket No. FAA–2015–4345; Directorate Canada Limited, 12,800 Rue de l’Avenir,
Part A, Subpart III, Section 44701: Identifier 2015–SW–049–AD. Mirabel, Quebec J7J1R4; telephone (450)
General requirements.’’ Under that 437–2862 or (800) 363–8023; fax (450) 433–
(a) Applicability
section, Congress charges the FAA with 0272; or at http://www.bellcustomer.com/
This AD applies to Model 429 helicopters files/. You may review the referenced service
promoting safe flight of civil aircraft in with a pitch link assembly part number 429–
air commerce by prescribing regulations information at the FAA, Office of the
012–112–101 or –103 installed, certificated
for practices, methods, and procedures Regional Counsel, Southwest Region, 10101
in any category.
the Administrator finds necessary for Hillwood Pkwy., Room 6N–321, Fort Worth,
(b) Unsafe Condition TX 76177.
safety in air commerce. This regulation
is within the scope of that authority This AD defines the unsafe condition as a (2) The subject of this AD is addressed in
because it addresses an unsafe condition worn pitch link. This condition, if not Transport Canada Emergency AD No. CF–
detected and corrected, could result in pitch 2015–16R1, dated August 6, 2015. You may
that is likely to exist or develop on
link failure and subsequent loss of control of view the Transport Canada Emergency AD on
products identified in this rulemaking the helicopter. the Internet at http://www.regulations.gov in
action.
(c) Affected ADs Docket No. FAA–2015–4345.
Regulatory Findings
This AD supersedes Emergency AD 2015– (i) Subject
We determined that this AD will not 16–51, Directorate Identifier 2015–SW–23–
Joint Aircraft Service Component (JASC)
have federalism implications under AD, dated August 6, 2015.
Code: 6720 Tail Rotor Control System.
Executive Order 13132. This AD will (d) Effective Date
not have a substantial direct effect on Issued in Fort Worth, Texas, on October 16,
This AD becomes effective November 12, 2015.
the States, on the relationship between 2015.
the national Government and the States, Lance T. Gant,
or on the distribution of power and (e) Compliance Manager, Rotorcraft Directorate, Aircraft
responsibilities among the various You are responsible for performing each Certification Service.
levels of government. action required by this AD within the [FR Doc. 2015–27137 Filed 10–26–15; 8:45 am]
For the reasons discussed, I certify specified compliance time unless it has
BILLING CODE 4910–13P
already been accomplished prior to that time.
that this AD:
1. Is not a ‘‘significant regulatory (f) Required Actions
action’’ under Executive Order 12866; (1) For helicopters with 50 or more hours
2. Is not a ‘‘significant rule’’ under time-in-service (TIS), before further flight,
DOT Regulatory Policies and Procedures and for helicopters with less than 50 hours
(44 FR 11034, February 26, 1979); TIS, before accumulating 50 hours TIS,
tkelley on DSK3SPTVN1PROD with RULES
3. Will not affect intrastate aviation in inspect each inboard and outboard tail rotor
pitch link assembly for axial or radial bearing
Alaska to the extent that it justifies play. If there is axial or radial bearing play,
making a regulatory distinction; and remove the tail rotor pitch link and perform
4. Will not have a significant a dimensional inspection for wear. If there is
economic impact, positive or negative, wear that exceeds the allowable limits,
on a substantial number of small entities replace the tail rotor pitch link assembly.
VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 9990 E:\FR\FM\27OCR1.SGM 27OCR1](https://thefederalregister.org/doc/80_FR_65825/page/3.svg)
Document Created: 2015-12-14 15:36:23
Document Modified: 2015-12-14 15:36:23
| 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 | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective November 12, 2015. | |
| Contact | David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 65618 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2024 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR