Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters, 23349-23351 [2018-10491]

Download as PDF 23349 Rules and Regulations Federal Register Vol. 83, No. 98 Monday, May 21, 2018 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0667; 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 AD, the Transport Canada AD, any incorporatedby-reference service information, the economic evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR 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 david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: We are adopting a new airworthiness directive (AD) for Bell Model 407 helicopters. This AD requires repetitive inspections of the tail rotor (TR) driveshaft segment assemblies and a torque check of the TR adapter retention nuts. This AD was prompted by a report of an in-flight failure of the TR drive system. The actions of this AD are intended to detect and correct an unsafe condition on these products. DATES: This AD is effective June 25, 2018. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of June 25, 2018. ADDRESSES: 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 https://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. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0667. Discussion On July 7, 2017, at 82 FR 31535, 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 Bell Model 407 helicopters. The NPRM proposed to require repetitively inspecting each TR driveshaft segment assembly for rotational and axial play between the adapter and the TR driveshaft. The NPRM also proposed a one-time verification of the installation torque of each adapter retention nut. The proposed requirements were intended to detect a loose TR driveshaft splined connection, which if not corrected could result in wear in the splines, failure of the TR drive system, and subsequent loss of directional control of the helicopter. The NPRM was prompted by AD No. CF–2016–21, dated July 7, 2016 (AD CF–2016–21), issued by Transport Canada, which is the aviation authority for Canada, to correct an unsafe condition for Bell Model 407 helicopters. Transport Canada advises that a Model 407 helicopter experienced in-flight failure of the TR drive system, which resulted in loss of directional control. According to Transport Canada, the splines connecting the adapter part 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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0667; Product Identifier 2016–SW–053–AD; Amendment 39–19281; AD 2018–10–06] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters AGENCY: sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 number (P/N) 406–040–328–105 to the shaft assembly P/N 407–040–330–107 were ‘‘severely worn and no longer capable of performing their function.’’ The investigation revealed other Model 407 helicopters with the same axial and radial play or looseness of some splined connections. AD CF–2016–21 states that these parts should be clamped together with threaded fasteners with no detectable looseness. Transport Canada advises that undetected looseness at the splined connection could result in wear of the parts and eventual loss of directional control of the helicopter. For these reasons, AD CF–2016–21 requires a repetitive inspection of the TR driveshaft assemblies for play and a one-time torque verification of the TR adapter retention nuts. Since the NPRM was issued, the FAA’s Aircraft Certification Service has changed its organization structure. The new structure replaces product directorates with functional divisions. We have revised some of the office titles and nomenclature throughout this Final rule to reflect the new organizational changes. Additional information about the new structure can be found in the Notice published on July 25, 2017 (82 FR 34564). Comments After our NPRM was published, we received comments from two commenters. Request Westwind Helicopters questioned the need for the AD. In support, it stated that the AD inspections are identical to the periodic and progressive inspections in the Bell maintenance manual and to the one-time inspection in Bell Alert Service Bulletin (ASB) 407–16–113, dated February 12, 2016 (ASB 407–16– 113). The commenter noted the AD would result in multiple documentation requirements for operators for the same maintenance item. The commenter did not request a change to the AD. We partially agree. The commenter is correct that the AD may result in additional documentation. However, while an operator may incorporate the procedures described in the Bell maintenance manuals and ASB into its maintenance program, not all operators are required to do so. In order for the inspections to become mandatory, and to correct the unsafe condition E:\FR\FM\21MYR1.SGM 21MYR1 23350 Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations identified in the NPRM, the FAA must issue an AD. Bell requested that a statement be added to the AD that accomplishing the Bell ASB meets the intent of the AD and that no further action is required. We partially agree. Operators may take credit for inspections previously accomplished in accordance with ASB 407–16–113 under paragraph (d) of the AD. However, we disagree that no further action is required because this AD requires repetitive inspections of the TR driveshaft, whereas ASB 407–16– 113 specifies a one-time inspection. Determining the torque of the four adapter retention nuts requires about 3 work-hours for a cost per helicopter of $255 and a cost of $170,085 to the U.S. fleet. If required, repairing a worn driveshaft adapter would require about 3 work-hours, and required parts cost about $1,259, for a cost per helicopter of $1,514. Replacing an adapter retention nut requires about 1 work-hour, and required parts cost are negligible, for a cost of $85 per helicopter and $56,695 for the U.S. fleet per inspection cycle. 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 its AD. We are issuing this AD because we evaluated all information provided by Transport Canada, reviewed the relevant information, considered the comments received, 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. 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. sradovich on DSK3GMQ082PROD with RULES Related Service Information Under 1 CFR Part 51 We reviewed ASB 407–16–113, which specifies procedures for inspecting the TR driveshaft assemblies for noticeable rotational or axial play between each adapter and TR driveshaft. ASB 407– 16–113 also specifies procedures for performing a torque check of each TR adapter retention nut on the four TR driveshaft segments. 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. 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. Costs of Compliance We estimate this AD affects 667 helicopters of U.S. Registry. We estimate that operators will incur the following costs in order to comply with this AD. At an average labor rate of $85 per workhour, inspecting the TR driveshaft segments and adapters for play requires about 1 work-hour, for a cost per helicopter of $85, and a cost of $56,695 to the U.S. fleet per inspection cycle. VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 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. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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): ■ 2018–10–06 Bell Helicopter Textron Canada Limited (Bell): Amendment 39– 19281; Docket No. FAA–2017–0667; Product Identifier 2017–SW–053–AD. (a) Applicability This AD applies to Bell Model 407 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a loose tail rotor (TR) driveshaft splined connection, which if not corrected could result in wear in the splines, failure of the TR drive system, and subsequent loss of directional control of the helicopter. (c) Effective Date This AD becomes effective June 25, 2018. (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 For helicopters with less than 4,000 hours time-in-service (TIS), within 100 hours TIS, and for helicopters with 4,000 or more hours TIS, within 50 hours TIS: (1) Inspect each TR driveshaft segment assembly for rotational and axial play between the adapter and the TR driveshaft at the four positions depicted in Figure 1 of Bell Alert Service Bulletin (ASB) 407–16–113, dated February 12, 2016 (ASB 407–16–113). If there is any axial or rotational play, remove the adapter from the TR driveshaft segment assembly and inspect the adapter, washers, and TR driveshaft for damage. Replace the adapter retention nut and apply a torque of 30 to 50 inch-pounds (5.7 to 7.9 Nm). Replace any part with damage or repair the part if the damage is within the maximum repair damage limitations. (2) Determine the torque of each TR adapter retention nut at each of the four segment assembly positions depicted in Figure 1 of Bell ASB 407–16–113. If the torque is less than 30 inch-pounds (5.7 Nm), remove the adapter from the TR driveshaft E:\FR\FM\21MYR1.SGM 21MYR1 Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations segment assembly and inspect the adapter, washers, and TR driveshaft for damage. Replace the adapter retention nut and apply a torque of 30 to 50 inch-pounds (5.7 to 7.9 Nm). Replace any part with damage or repair the part if the damage is within the maximum repair damage limitations. (3) Repeat the actions specified in paragraph (e)(1) of this AD at intervals not to exceed 330 hours TIS. (f) Special Flight Permits Special flight permits are prohibited. (g) 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 9-ASWFTW-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 The subject of this AD is addressed in Transport Canada AD No. CF–2016–21, dated July 7, 2016. You may view the Transport Canada AD on the internet at https:// www.regulations.gov in Docket No. FAA– 2017–0667. sradovich on DSK3GMQ082PROD with RULES (i) Subject Joint Aircraft Service Component (JASC) Code: 6510 Tail Rotor Drive Shaft. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 Alert Service Bulletin 407–16–113, dated February 12, 2016. (ii) Reserved. (3) For Bell service information identified in this AD, 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 https://www.bellcustomer.com/files/. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. 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: https:// VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on May 7, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018–10491 Filed 5–18–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0907; Product Identifier 2017–NM–069–AD; Amendment 39–19274; AD 2018–09–17] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601 Variant), and CL–600–2B16 (CL–601– 3A, CL–601–3R, and CL–604 Variants) airplanes. This AD was prompted by reports of fractured rudder pedal tubes on the pilot-side rudder bar assembly. This AD requires repetitive inspections of the rudder pedal tubes for cracking and corrective actions if necessary. Replacement of both pilot-side rudder bar assemblies terminates the inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 25, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 25, 2018. ADDRESSES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote-Vertu Road ´ West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1–514–855–2999; fax 514–855–7401; email ac.yul@aero.bombardier.com; internet https://www.bombardier.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available SUMMARY: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 23351 on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0907. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0907; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; 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 CL–600–1A11 (CL–600), CL–600–2A12 (CL–601 Variant), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. The NPRM published in the Federal Register on October 19, 2017 (82 FR 48668) (‘‘the NPRM’’). The NPRM was prompted by reports of fractured rudder pedal tubes on the pilot-side rudder bar assembly. The NPRM proposed to require repetitive inspections of the rudder pedal tubes for cracking and corrective actions if necessary. Replacement of both pilot-side rudder bar assemblies terminates the inspections. We are issuing this AD to address cracking of the pilot-side rudder pedal tubes. Loss of pilot rudder pedal input during flight could result in reduced yaw controllability of the airplane. Loss of pilot rudder pedal input during takeoff or landing could lead to a runway excursion. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2017–09, dated February 22, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the E:\FR\FM\21MYR1.SGM 21MYR1

Agencies

[Federal Register Volume 83, Number 98 (Monday, May 21, 2018)]
[Rules and Regulations]
[Pages 23349-23351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10491]



========================================================================
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. 

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


Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and 
Regulations

[[Page 23349]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0667; Product Identifier 2016-SW-053-AD; Amendment 
39-19281; AD 2018-10-06]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Limited 
(Bell) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Model 407 helicopters. This AD requires repetitive inspections of the 
tail rotor (TR) driveshaft segment assemblies and a torque check of the 
TR adapter retention nuts. This AD was prompted by a report of an in-
flight failure of the TR drive system. The actions of this AD are 
intended to detect and correct an unsafe condition on these products.

DATES: This AD is effective June 25, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of June 25, 2018.

ADDRESSES: 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 https://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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0667.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0667; 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 AD, the Transport Canada AD, any incorporated-by-reference service 
information, the economic evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR 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: 

Discussion

    On July 7, 2017, at 82 FR 31535, 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 Bell Model 407 helicopters. 
The NPRM proposed to require repetitively inspecting each TR driveshaft 
segment assembly for rotational and axial play between the adapter and 
the TR driveshaft. The NPRM also proposed a one-time verification of 
the installation torque of each adapter retention nut. The proposed 
requirements were intended to detect a loose TR driveshaft splined 
connection, which if not corrected could result in wear in the splines, 
failure of the TR drive system, and subsequent loss of directional 
control of the helicopter.
    The NPRM was prompted by AD No. CF-2016-21, dated July 7, 2016 (AD 
CF-2016-21), issued by Transport Canada, which is the aviation 
authority for Canada, to correct an unsafe condition for Bell Model 407 
helicopters. Transport Canada advises that a Model 407 helicopter 
experienced in-flight failure of the TR drive system, which resulted in 
loss of directional control. According to Transport Canada, the splines 
connecting the adapter part number (P/N) 406-040-328-105 to the shaft 
assembly P/N 407-040-330-107 were ``severely worn and no longer capable 
of performing their function.'' The investigation revealed other Model 
407 helicopters with the same axial and radial play or looseness of 
some splined connections. AD CF-2016-21 states that these parts should 
be clamped together with threaded fasteners with no detectable 
looseness. Transport Canada advises that undetected looseness at the 
splined connection could result in wear of the parts and eventual loss 
of directional control of the helicopter.
    For these reasons, AD CF-2016-21 requires a repetitive inspection 
of the TR driveshaft assemblies for play and a one-time torque 
verification of the TR adapter retention nuts.
    Since the NPRM was issued, the FAA's Aircraft Certification Service 
has changed its organization structure. The new structure replaces 
product directorates with functional divisions. We have revised some of 
the office titles and nomenclature throughout this Final rule to 
reflect the new organizational changes. Additional information about 
the new structure can be found in the Notice published on July 25, 2017 
(82 FR 34564).

Comments

    After our NPRM was published, we received comments from two 
commenters.

Request

    Westwind Helicopters questioned the need for the AD. In support, it 
stated that the AD inspections are identical to the periodic and 
progressive inspections in the Bell maintenance manual and to the one-
time inspection in Bell Alert Service Bulletin (ASB) 407-16-113, dated 
February 12, 2016 (ASB 407-16-113). The commenter noted the AD would 
result in multiple documentation requirements for operators for the 
same maintenance item. The commenter did not request a change to the 
AD.
    We partially agree. The commenter is correct that the AD may result 
in additional documentation. However, while an operator may incorporate 
the procedures described in the Bell maintenance manuals and ASB into 
its maintenance program, not all operators are required to do so. In 
order for the inspections to become mandatory, and to correct the 
unsafe condition

[[Page 23350]]

identified in the NPRM, the FAA must issue an AD.
    Bell requested that a statement be added to the AD that 
accomplishing the Bell ASB meets the intent of the AD and that no 
further action is required.
    We partially agree. Operators may take credit for inspections 
previously accomplished in accordance with ASB 407-16-113 under 
paragraph (d) of the AD. However, we disagree that no further action is 
required because this AD requires repetitive inspections of the TR 
driveshaft, whereas ASB 407-16-113 specifies a one-time inspection.

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 
its AD. We are issuing this AD because we evaluated all information 
provided by Transport Canada, reviewed the relevant information, 
considered the comments received, 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.

Related Service Information Under 1 CFR Part 51

    We reviewed ASB 407-16-113, which specifies procedures for 
inspecting the TR driveshaft assemblies for noticeable rotational or 
axial play between each adapter and TR driveshaft. ASB 407-16-113 also 
specifies procedures for performing a torque check of each TR adapter 
retention nut on the four TR driveshaft segments.
    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.
    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.

Costs of Compliance

    We estimate this AD affects 667 helicopters of U.S. Registry. We 
estimate that operators will incur the following costs in order to 
comply with this AD. At an average labor rate of $85 per work-hour, 
inspecting the TR driveshaft segments and adapters for play requires 
about 1 work-hour, for a cost per helicopter of $85, and a cost of 
$56,695 to the U.S. fleet per inspection cycle. Determining the torque 
of the four adapter retention nuts requires about 3 work-hours for a 
cost per helicopter of $255 and a cost of $170,085 to the U.S. fleet.
    If required, repairing a worn driveshaft adapter would require 
about 3 work-hours, and required parts cost about $1,259, for a cost 
per helicopter of $1,514.
    Replacing an adapter retention nut requires about 1 work-hour, and 
required parts cost are negligible, for a cost of $85 per helicopter 
and $56,695 for the U.S. fleet per inspection cycle.

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):

2018-10-06 Bell Helicopter Textron Canada Limited (Bell): Amendment 
39-19281; Docket No. FAA-2017-0667; Product Identifier 2017-SW-053-
AD.

(a) Applicability

    This AD applies to Bell Model 407 helicopters, certificated in 
any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a loose tail rotor (TR) 
driveshaft splined connection, which if not corrected could result 
in wear in the splines, failure of the TR drive system, and 
subsequent loss of directional control of the helicopter.

(c) Effective Date

    This AD becomes effective June 25, 2018.

(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

    For helicopters with less than 4,000 hours time-in-service 
(TIS), within 100 hours TIS, and for helicopters with 4,000 or more 
hours TIS, within 50 hours TIS:
    (1) Inspect each TR driveshaft segment assembly for rotational 
and axial play between the adapter and the TR driveshaft at the four 
positions depicted in Figure 1 of Bell Alert Service Bulletin (ASB) 
407-16-113, dated February 12, 2016 (ASB 407-16-113). If there is 
any axial or rotational play, remove the adapter from the TR 
driveshaft segment assembly and inspect the adapter, washers, and TR 
driveshaft for damage. Replace the adapter retention nut and apply a 
torque of 30 to 50 inch-pounds (5.7 to 7.9 Nm). Replace any part 
with damage or repair the part if the damage is within the maximum 
repair damage limitations.
    (2) Determine the torque of each TR adapter retention nut at 
each of the four segment assembly positions depicted in Figure 1 of 
Bell ASB 407-16-113. If the torque is less than 30 inch-pounds (5.7 
Nm), remove the adapter from the TR driveshaft

[[Page 23351]]

segment assembly and inspect the adapter, washers, and TR driveshaft 
for damage. Replace the adapter retention nut and apply a torque of 
30 to 50 inch-pounds (5.7 to 7.9 Nm). Replace any part with damage 
or repair the part if the damage is within the maximum repair damage 
limitations.
    (3) Repeat the actions specified in paragraph (e)(1) of this AD 
at intervals not to exceed 330 hours TIS.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) 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.

(h) Additional Information

    The subject of this AD is addressed in Transport Canada AD No. 
CF-2016-21, dated July 7, 2016. You may view the Transport Canada AD 
on the internet at https://www.regulations.gov in Docket No. FAA-
2017-0667.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6510 Tail Rotor 
Drive Shaft.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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 Alert Service Bulletin 407-16-113, dated February 12, 
2016.
    (ii) Reserved.
    (3) For Bell service information identified in this AD, 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 https://www.bellcustomer.com/files/.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on May 7, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-10491 Filed 5-18-18; 8:45 am]
 BILLING CODE 4910-13-P

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