Airworthiness Directives; Bell Helicopter Textron Canada, 38613-38615 [2015-16469]

Download as PDF 38613 Rules and Regulations Federal Register Vol. 80, No. 129 Tuesday, July 7, 2015 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0499; Directorate Identifier 2013–SW–061–AD; Amendment 39–18198; AD 2015–13–11] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters to require inspecting the tail rotor control tube assembly (control tube) and either repairing or replacing the control tube. This AD was prompted by two reports of failure of the control tube bonded clevis. The actions of this AD are intended to prevent failure of a control tube bonded clevis, which could lead to failure of the control tube and subsequent loss of helicopter control. DATES: This AD is effective August 11, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 11, 2015. ADDRESSES: 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, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is also available on the Internet at http:// srobinson on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 19:51 Jul 06, 2015 Jkt 235001 www.regulations.gov in Docket No. FAA–2014–0499. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov 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 Civil Aviation (TCCA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion On July 30, 2014, at 79 FR 44147, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to BHTC Model 430 Helicopters, serial number 49001 through 49121, with control tube part number (P/N) 430– 001–007–101 installed. The NPRM proposed to require inspecting the control tube and either repairing or replacing it. The proposed requirements were intended to prevent failure of a control tube bonded clevis, which could lead to failure of the control tube and subsequent loss of helicopter control. The NPRM was prompted by Canadian AD No. CF–2013–30, dated October 7, 2013, issued by TCCA, which is the aviation authority for Canada, to correct an unsafe condition for BHTC Model 430 helicopters with control tube P/N 430–001–007–101. TCCA advises of two failures of the control tube bonded clevis caused by cracking from control tube oscillation. TCCA states that this situation, if not corrected, could result in the loss of control of the helicopter. TCCA AD No. CF–2013–30 consequently requires a one-time PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 inspection of the control tube for damage and contacting BHTC for evaluation of the control tube if the damage exceeds allowable limits. If the tube is not damaged, the damage is within allowable limits, or BHTC Engineering determines the control tube can be returned to service, TCCA AD No. CF–2013–30 requires modifying the tube according to BHTC’s service information. TCCA AD No. CF–2013–30 also requires replacing control tubes, P/ N 430–001–007–101, with control tube, P/N 430–001–007–105, no later than 12 months from the effective date of its AD. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (79 FR 44147, July 30, 2014). 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, TCCA, its technical representative, has notified us of the unsafe condition described in the TCCA AD. We are issuing this AD because we evaluated all information provided by TCCA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Differences Between This AD and the TCCA AD The TCCA AD requires submitting sketches of a control tube damaged beyond defined limits to BHTC for evaluation. BHTC then determines if the control tube can be returned to service. We make no such requirement in this AD. Related Service Information Under 1 CFR Part 51 Bell Helicopter Alert Service Bulletin (ASB) No. 430–13–51, dated September 3, 2013, states that BHTC received two reports of control tube, P/N 430–001– 007–101, failing because the clevis failed due to fatigue caused by control tube oscillation. ASB No. 430–13–51 specifies a one-time inspection of control tube assembly, P/N 430–001– 007–101, to verify if the tube has chaffing damage and indicated that a E:\FR\FM\07JYR1.SGM 07JYR1 38614 Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations mandatory replacement would follow when sufficient parts became available. 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 AD. Other Related Service Information We reviewed Bell Helicopter Technical Bulletin 430–04–35, Revision B, dated March 20, 2009, which recommends that control tube, P/N 430– 001–007–101, be replaced with control tube, P/N 430–001–007–105, if damage exists. On June 12, 2014, Bell issued Revision A to ASB No. 430–13–51, which set a compliance date of September 30, 2014, to remove control tube, P/N 430–001–007–101. srobinson on DSK5SPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects 5 helicopters of U.S. Registry and that labor costs average $85 a work hour. Based on these estimates, we expect the following costs: • The cost of inspecting the control tube is minimal. • Repairing the control tube requires 2 work-hours for a labor cost of $170. • Replacing control tube, P/N 430– 001–007–101, with control tube, P/N 430–001–007–105, requires 3 workhours for a labor cost of $255. Parts cost $3,974 for a total cost per helicopter of $4,229. According to manufacturer’s service information, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by the manufacturer. 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 VerDate Sep<11>2014 19:51 Jul 06, 2015 Jkt 235001 helicopters identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify 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 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 adding the following new airworthiness directive (AD): ■ 2015–13–11 Bell Helicopter Textron Canada: Amendment 39–18198; Docket No. FAA–2014–0499; Directorate Identifier 2013–SW–061–AD. (a) Applicability This AD applies to Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters, serial number 49001 through 49121, with control tube assembly (control tube), part number (P/ N) 430–001–007–101 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of a tail rotor control tube PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 bonded clevis. This condition could result in failure of the tail rotor control tube and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective August 11, 2015. (d) 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. (e) Required Actions (1) Within 50 hours time-in-service (TIS), visually inspect each control tube for any damage, for any damage to the clevis, and to determine whether the clevis is correctly bonded to the control tube. (i) If a control tube and clevis have no damage or damage within acceptable limits and the clevis is correctly bonded to the control tube, repair the control tube by applying tape in accordance with the Accomplishment Instructions, Paragraph 5, of Bell Helicopter Alert Service Bulletin 430– 13–51, dated September 3, 2013. (ii) If the control tube or clevis is damaged beyond acceptable limits or if the clevis is not correctly bonded to the control tube, replace control tube, P/N 430–001–007–101, with control tube, P/N 430–001–007–105. (2) Within 250 hours TIS, replace each control tube, P/N 430–001–007–101, with control tube, P/N 430–001–007–105. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@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. (g) Additional Information (1) Bell Helicopter Technical Bulletin 430– 04–35, Revision B, dated March 20, 2009, which is not incorporated by reference, contains additional information about the subject of this AD. For service information, 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 view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in Transport Canada Civil Aviation (TCCA) AD No. CF–2013–30, dated October 7, 2013. You may view the TCCA AD on the Internet at E:\FR\FM\07JYR1.SGM 07JYR1 Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations http://www.regulations.gov in Docket No. FAA–2014–0499. (h) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor Control (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Bell Helicopter Alert Service Bulletin 430–13–51, dated September 3, 2013. (ii) Reserved. (3) For Bell Helicopter Textron Canada Limited 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/. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on June 24, 2015. Bruce E. Cain, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–16469 Filed 7–6–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0569; Directorate Identifier 2014–NM–047–AD; Amendment 39–18199; AD 2015–14–01] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. srobinson on DSK5SPTVN1PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted by a report of loose bolts that are SUMMARY: VerDate Sep<11>2014 19:51 Jul 06, 2015 Jkt 235001 intended to secure the translating door crank assembly to the outside handle shaft. This AD requires a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. We are issuing this AD to prevent loose bolts from falling out. If both bolts become loose or fall out after the door is closed and locked, the door cannot be opened from inside or outside, which could impede evacuation in the event of an emergency. DATES: This AD becomes effective August 11, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 11, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0569; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425 227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0569. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on August 15, 2014 (79 FR 48105). The NPRM was prompted by a report of loose bolts that are intended to secure the translating door crank assembly to PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 38615 the outside handle shaft. The NPRM proposed to require a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. We are issuing this AD to prevent loose bolts from falling out. If both bolts become loose or fall out after the door is closed and locked, the door cannot be opened from inside or outside, which could impede evacuation in the event of an emergency. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–08, dated February 10, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: There was one in-service report where the bolts securing the translating door crank assembly to the outside handle shaft were found loose. It was also found on another translating door that sealant was missing on these bolts. If both bolts become loose or fall out after the door is closed and locked, the door cannot be opened from inside or outside. The aft entry translating door and aft service translating door are classified as emergency exits. The inability to open an emergency exit could impede evacuation in the event of an emergency. This [Canadian] AD mandates the inspection of the translating door crank assemblies for loose bolts, as well as appropriate rectification [removal and reinstallation of the bolts]. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-05690002. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. The following presents the comment received on the NPRM (79 FR 48105, August 15, 2014), and the FAA’s response to the comment. Request To Remove Certain Requirements From the NPRM (79 FR 48105, August 15, 2014) Horizon Air requested that the job setup and close-out procedures included in Part A–INSPECTION, and Part B– RECTIFICATION, of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–75, Revision A, dated July 11, 2013, be removed as requirements in the NPRM (79 FR 48105, August 15, 2014). The commenter noted that only the procedures included in paragraph B. E:\FR\FM\07JYR1.SGM 07JYR1

Agencies

[Federal Register Volume 80, Number 129 (Tuesday, July 7, 2015)]
[Rules and Regulations]
[Pages 38613-38615]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16469]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules 
and Regulations

[[Page 38613]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD; 
Amendment 39-18198; AD 2015-13-11]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada (BHTC) Model 430 helicopters to require 
inspecting the tail rotor control tube assembly (control tube) and 
either repairing or replacing the control tube. This AD was prompted by 
two reports of failure of the control tube bonded clevis. The actions 
of this AD are intended to prevent failure of a control tube bonded 
clevis, which could lead to failure of the control tube and subsequent 
loss of helicopter control.

DATES: This AD is effective August 11, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 11, 
2015.

ADDRESSES: 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, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. It is also available on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0499.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov 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 Civil 
Aviation (TCCA) AD, any incorporated-by-reference service information, 
the economic evaluation, any comments received, and other information. 
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On July 30, 2014, at 79 FR 44147, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to BHTC Model 430 
Helicopters, serial number 49001 through 49121, with control tube part 
number (P/N) 430-001-007-101 installed. The NPRM proposed to require 
inspecting the control tube and either repairing or replacing it. The 
proposed requirements were intended to prevent failure of a control 
tube bonded clevis, which could lead to failure of the control tube and 
subsequent loss of helicopter control.
    The NPRM was prompted by Canadian AD No. CF-2013-30, dated October 
7, 2013, issued by TCCA, which is the aviation authority for Canada, to 
correct an unsafe condition for BHTC Model 430 helicopters with control 
tube P/N 430-001-007-101. TCCA advises of two failures of the control 
tube bonded clevis caused by cracking from control tube oscillation. 
TCCA states that this situation, if not corrected, could result in the 
loss of control of the helicopter. TCCA AD No. CF-2013-30 consequently 
requires a one-time inspection of the control tube for damage and 
contacting BHTC for evaluation of the control tube if the damage 
exceeds allowable limits. If the tube is not damaged, the damage is 
within allowable limits, or BHTC Engineering determines the control 
tube can be returned to service, TCCA AD No. CF-2013-30 requires 
modifying the tube according to BHTC's service information. TCCA AD No. 
CF-2013-30 also requires replacing control tubes, P/N 430-001-007-101, 
with control tube, P/N 430-001-007-105, no later than 12 months from 
the effective date of its AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (79 FR 44147, July 30, 
2014).

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, TCCA, its technical 
representative, has notified us of the unsafe condition described in 
the TCCA AD. We are issuing this AD because we evaluated all 
information provided by TCCA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Differences Between This AD and the TCCA AD

    The TCCA AD requires submitting sketches of a control tube damaged 
beyond defined limits to BHTC for evaluation. BHTC then determines if 
the control tube can be returned to service. We make no such 
requirement in this AD.

Related Service Information Under 1 CFR Part 51

    Bell Helicopter Alert Service Bulletin (ASB) No. 430-13-51, dated 
September 3, 2013, states that BHTC received two reports of control 
tube, P/N 430-001-007-101, failing because the clevis failed due to 
fatigue caused by control tube oscillation. ASB No. 430-13-51 specifies 
a one-time inspection of control tube assembly, P/N 430-001-007-101, to 
verify if the tube has chaffing damage and indicated that a

[[Page 38614]]

mandatory replacement would follow when sufficient parts became 
available. 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 
AD.

Other Related Service Information

    We reviewed Bell Helicopter Technical Bulletin 430-04-35, Revision 
B, dated March 20, 2009, which recommends that control tube, P/N 430-
001-007-101, be replaced with control tube, P/N 430-001-007-105, if 
damage exists. On June 12, 2014, Bell issued Revision A to ASB No. 430-
13-51, which set a compliance date of September 30, 2014, to remove 
control tube, P/N 430-001-007-101.

Costs of Compliance

    We estimate that this AD affects 5 helicopters of U.S. Registry and 
that labor costs average $85 a work hour. Based on these estimates, we 
expect the following costs:
     The cost of inspecting the control tube is minimal.
     Repairing the control tube requires 2 work-hours for a 
labor cost of $170.
     Replacing control tube, P/N 430-001-007-101, with control 
tube, P/N 430-001-007-105, requires 3 work-hours for a labor cost of 
$255. Parts cost $3,974 for a total cost per helicopter of $4,229.
    According to manufacturer's service information, some of the costs 
of this AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. We do not control warranty coverage by 
the manufacturer. 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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify 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):

2015-13-11 Bell Helicopter Textron Canada: Amendment 39-18198; 
Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada (BHTC) Model 
430 Helicopters, serial number 49001 through 49121, with control 
tube assembly (control tube), part number (P/N) 430-001-007-101 
installed, certificated in any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as fatigue failure of a 
tail rotor control tube bonded clevis. This condition could result 
in failure of the tail rotor control tube and subsequent loss of 
helicopter control.

(c) Effective Date

    This AD becomes effective August 11, 2015.

(d) 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.

(e) Required Actions

    (1) Within 50 hours time-in-service (TIS), visually inspect each 
control tube for any damage, for any damage to the clevis, and to 
determine whether the clevis is correctly bonded to the control 
tube.
    (i) If a control tube and clevis have no damage or damage within 
acceptable limits and the clevis is correctly bonded to the control 
tube, repair the control tube by applying tape in accordance with 
the Accomplishment Instructions, Paragraph 5, of Bell Helicopter 
Alert Service Bulletin 430-13-51, dated September 3, 2013.
    (ii) If the control tube or clevis is damaged beyond acceptable 
limits or if the clevis is not correctly bonded to the control tube, 
replace control tube, P/N 430-001-007-101, with control tube, P/N 
430-001-007-105.
    (2) Within 250 hours TIS, replace each control tube, P/N 430-
001-007-101, with control tube, P/N 430-001-007-105.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 
222-5110; email matthew.fuller@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.

(g) Additional Information

    (1) Bell Helicopter Technical Bulletin 430-04-35, Revision B, 
dated March 20, 2009, which is not incorporated by reference, 
contains additional information about the subject of this AD. For 
service information, 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 view this service information 
at FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in Transport Canada 
Civil Aviation (TCCA) AD No. CF-2013-30, dated October 7, 2013. You 
may view the TCCA AD on the Internet at

[[Page 38615]]

http://www.regulations.gov in Docket No. FAA-2014-0499.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor 
Control

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bell Helicopter Alert Service Bulletin 430-13-51, dated 
September 3, 2013.
    (ii) Reserved.
    (3) For Bell Helicopter Textron Canada Limited 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/.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on June 24, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-16469 Filed 7-6-15; 8:45 am]
 BILLING CODE 4910-13-P