Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters, 53171-53174 [2018-22414]

Download as PDF daltland on DSKBBV9HB2PROD with RULES Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations location must be less than 1,018 in-lb (115 Nm). iv. The upper-neck resultant shear force at the O.C. location must be less than 186 lb (825 N). g. Occupant (ES–2re ATD) retention: The pelvic restraint must remain on the ES–2re ATD’s pelvis during the impact and rebound phases of the test. The upper-torso restraint straps (if present) must remain on the ATD’s shoulder during the impact. h. Occupant (ES–2re ATD) support: i. Pelvis excursion: The load-bearing portion of the bottom of the ATD pelvis must not translate beyond the edges of its seat’s bottom seat-cushion supporting structure. ii. Upper-torso support: The lateral flexion of the ATD torso must not exceed 40 degrees from the normal upright position during the impact. 5. For seats with an airbag system in the shoulder belts, show that the airbag system in the shoulder belt will deploy and provide protection under crash conditions where it is necessary to prevent serious injury. The means of protection must take into consideration a range of stature from a 2-year-old child to a 95th percentile male. The airbag system in the shoulder belt must provide a consistent approach to energy absorption throughout that range of occupants. When the seat system includes an airbag system, that system must be included in each of the certification tests as it would be installed in the airplane. In addition, the following situations must be considered: a. The seat occupant is holding an infant. b. The seat occupant is a pregnant woman. 6. The airbag system in the shoulder belt must provide adequate protection for each occupant regardless of the number of occupants of the seat assembly, considering that unoccupied seats may have an active airbag system in the shoulder belt. 7. The design must prevent the airbag system in the shoulder belt from being either incorrectly buckled or incorrectly installed, such that the airbag system in the shoulder belt would not properly deploy. Alternatively, it must be shown that such deployment is not hazardous to the occupant, and will provide the required injury protection. 8. It must be shown that the airbag system in the shoulder belt is not susceptible to inadvertent deployment as a result of wear and tear, or inertial loads resulting from in-flight or ground maneuvers (including gusts and hard landings), and other operating and environmental conditions (vibrations, moisture, etc.) likely to occur in service. VerDate Sep<11>2014 16:28 Oct 19, 2018 Jkt 247001 9. Deployment of the airbag system in the shoulder belt must not introduce injury mechanisms to the seated occupant, or result in injuries that could impede rapid egress. This assessment should include an occupant whose belt is loosely fastened. 10. It must be shown that inadvertent deployment of the airbag system in the shoulder belt, during the most critical part of the flight, will either meet the requirement of § 25.1309(b) or not cause a hazard to the airplane or its occupants. 11. It must be shown that the airbag system in the shoulder belt will not impede rapid egress of occupants 10 seconds after airbag deployment. 12. The airbag system must be protected from lightning and highintensity radiated fields (HIRF). The threats to the airplane specified in existing regulations regarding lightning, § 25.1316, and HIRF, § 25.1317, are incorporated by reference for the purpose of measuring lightning and HIRF protection. 13. The airbag system in the shoulder belt must function properly after loss of normal aircraft electrical power, and after a transverse separation of the fuselage at the most critical location. A separation at the location of the airbag system in the shoulder belt does not have to be considered. 14. It must be shown that the airbag system in the shoulder belt will not release hazardous quantities of gas or particulate matter into the cabin. 15. The airbag system in the shoulderbelt installation must be protected from the effects of fire such that no hazard to occupants will result. 16. A means must be available for a crewmember to verify the integrity of the airbag system in the shoulder-belt activation system prior to each flight, or it must be demonstrated to reliably operate between inspection intervals. The FAA considers that the loss of the airbag-system deployment function alone (i.e., independent of the conditional event that requires airbag deployment) is a major-failure condition. 17. The inflatable material may not have an average burn rate of greater than 2.5 inches/minute when tested using the horizontal flammability test defined in part 25, appendix F, part I, paragraph (b)(5). 18. The airbag system in the shoulder belt, once deployed, must not adversely affect the emergency-lighting system (i.e., block floor proximity lights to the extent that the lights no longer meet their intended function). PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 53171 Issued in Des Moines, Washington, on October 10, 2018. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2018–22929 Filed 10–19–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0834; Product Identifier 2018–SW–058–AD; Amendment 39–19421; AD 2018–16–51] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters as Emergency AD 2018–16– 51, dated July 26, 2018, which superseded Emergency AD 2018–15–51, dated July 20, 2018. This AD requires inspecting the tail rotor (T/R) gearbox installation, inspecting the T/R gearbox retaining hardware and support attachment point areas, and replacing each nut. This AD is prompted by two reports of T/R gearbox assemblies loosely attached to the gearbox support. The actions of this AD are intended to address an unsafe condition on these products. SUMMARY: This AD becomes effective November 6, 2018 to all persons except those persons to whom it was made immediately effective by Emergency AD 2018–16–51, issued on July 26, 2018, which contains the requirements of this AD. We must receive comments on this AD by December 21, 2018. 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 DATES: E:\FR\FM\22OCR1.SGM 22OCR1 53172 Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations 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. 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. Examining the AD Docket Discussion Transport Canada, which is the aviation authority for Canada, issued Emergency AD No. CF–2018–18, dated July 11, 2018, to correct an unsafe condition for Bell Model 429 helicopters. Transport Canada advises of two reports of T/R gearbox assemblies loosely attached to the gearbox support. According to Transport Canada, this condition could lead to structural damage and possible loss of control of the helicopter. As a result, on July 20, 2018, we issued Emergency AD 2018–15–51 (Emergency AD 2018–15–51), which required inspecting the T/R gearbox installation for looseness, visually inspecting the T/R gearbox retaining hardware and support attachment point areas, and torque inspecting the gearbox retaining nuts. Depending on the inspection results, Emergency AD 2018– 15–51 required replacing or repairing the affected parts in accordance with FAA-approved procedures. Emergency AD 2018–15–51 was sent previously to all known U.S. owners and operators of these helicopters. The actions in Emergency AD 2018–15–51 were intended to prevent detachment of the T/R gearbox, loss of T/R control, and loss of control of the helicopter. After we issued Emergency AD 2018– 15–51, we discovered an error in the replacement nut P/N. The required replacement nut P/N is NAS9926–6L; not NAS9926–5L as incorrectly stated in Emergency AD 2018–15–51. Therefore, on July 26, 2018, we issued Emergency AD 2018–16–51 to supersede Emergency AD 2018–15–51 to correct the nut P/N. Emergency AD 2018–16–51 otherwise retains all of the requirements of Emergency AD 2018–15–51. Emergency AD 2018–16–51 was also sent previously to all known U.S. owners and operators of these helicopters. You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0834; 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, the economic evaluation, any comments received, and other information. The street address for Docket Operations (telephone 800- 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this final rule, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363– 8023; fax (450) 433–0272; or at http:// www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: daltland on DSKBBV9HB2PROD with RULES 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 VerDate Sep<11>2014 16:28 Oct 19, 2018 Jkt 247001 FAA’s Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its technical representative, has notified us of the unsafe condition described in the Transport Canada AD. We are issuing this AD because we PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other helicopters of the same type design. Related Service Information We reviewed Bell Alert Service Bulletin 429–18–40, dated July 6, 2018, which specifies a one-time inspection of the T/R gearbox installation and a onetime visual and torque inspection of the six installation attachment points. This service information also specifies contacting Bell Product Support Engineering with the results of the T/R gearbox installation inspection, any findings of the visual inspection, and the results of the torque inspection. AD Requirements This AD requires inspecting the T/R gearbox installation for looseness, visually inspecting the T/R gearbox retaining hardware and each support attachment point area, and torque inspecting each gearbox retaining nut. Depending on the inspection results, this AD requires replacing or repairing the affected parts in accordance with FAA-approved procedures. Differences Between This AD and the Transport Canada AD The Transport Canada AD applies to helicopters with specific serial numbers, whereas this AD applies to all Model 429 helicopters. The Transport Canada AD includes a calendar based compliance time, whereas this AD does not. The Transport Canada AD requires reporting certain information to Bell Product Support Engineering and this AD does not. If there is looseness, this AD requires performing the visual inspection and torque inspection before further flight, while the Transport Canada AD requires contacting Bell. Lastly, if the torque of a T/R gearbox retaining nut is below 160 in-lbs (19 Nm), this AD requires removing the T/R gearbox and inspecting the mounting surfaces and retaining hardware, while the Transport Canada AD requires contacting Bell. 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 90 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 $85.00 per work-hour. E:\FR\FM\22OCR1.SGM 22OCR1 Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations Inspecting the T/R gearbox installation takes about 0.25 work-hour for an estimated cost of $21 per helicopter and $1,890 for the U.S. fleet. Inspecting the T/R gearbox retaining hardware and the support attachment points takes about 0.5 work-hour for an estimated cost of $43 per helicopter and $3,870 for the U.S. fleet. Replacing the nuts takes about 1 work-hour and parts cost about $20 for an estimated cost of $105 per helicopter and $9,450 for the U.S. fleet. daltland on DSKBBV9HB2PROD with RULES FAA’s Justification and Determination of the Effective Date An unsafe condition exists that required the immediate adoption of Emergency AD 2018–16–51, issued on July 26, 2018, to all known U.S. owners and operators of these helicopters. The FAA found that the risk to the flying public justified waiving notice and comment prior to adoption of this rule because there are required actions that must be completed before further flight and within 5 hours time-in-service. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reasons stated above, we find that good cause exists for making this amendment effective in less than 30 days. 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 VerDate Sep<11>2014 16:28 Oct 19, 2018 Jkt 247001 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 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): ■ 2018–16–51 Bell Helicopter Textron Canada Limited: Amendment 39–19421; Docket No. FAA–2018–0834; Product Identifier 2018–SW–058–AD. (a) Applicability This AD applies to Model 429 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a loose tail rotor (T/R) gearbox support attachment point. This condition could result in detachment of the T/R gearbox, loss of T/R control, and loss of control of the helicopter. (c) Related ADs This AD requires the same actions as Emergency AD 2018–16–51, dated July 26, 2018, which superseded Emergency AD 2018–15–51, dated July 20, 2018. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 53173 (d) Effective Date This AD becomes effective November 6, 2018 to all persons except those persons to whom it was made immediately effective by Emergency AD 2018–16–51, issued on July 26, 2018, which contains the requirements of this AD. (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) Before further flight, inspect for looseness of the T/R gearbox installation to the T/R gearbox structural support by moving the T/R gearbox output shaft in an upward and downward direction. If the T/R gearbox installation is loose, before further flight, complete the actions required by paragraphs (f)(2)(i) and (ii) of this AD. (2) Within 5 hours time-in-service, unless already completed as required by paragraph (f)(1) of this AD: (i) Visually inspect the T/R gearbox retaining hardware and each support attachment point area for evidence of fretting, a crack, and incorrect installation. If there is any evidence of fretting, a crack, or incorrect installation, before further flight, repair in accordance with FAA-approved procedures. (ii) Inspect each T/R gearbox retaining nut by applying 160 in-lbs (19 Nm) of torque. If the torque of a T/R gearbox retaining nut is below 160 in-lbs (19 Nm), before further flight: (A) Remove the T/R gearbox and inspect each stud for proper staking, each stud thread for uniformity, each mounting surface for evidence of fretting and cracking, and each mounting hole for elongation. If a stud is not properly staked, a stud thread is not uniform, a mounting surface has evidence of fretting or cracking, or a mount hole is elongated, before further flight, replace the affected parts or repair in accordance with FAAapproved procedures. (B) Replace each nut with nut part number NAS9926–6L and apply a torque of 160 inlbs. (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: Matt Fuller, Senior 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 (1) Bell Alert Service Bulletin 429–18–40, dated July 6, 2018, which is not incorporated E:\FR\FM\22OCR1.SGM 22OCR1 53174 Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http:// www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in Transport Canada AD No. CF–2018–18, dated July 11, 2018. You may view the Transport Canada AD on the internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–2018–0834. (i) Subject Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor Gearbox. Issued in Fort Worth, Texas, on October 5, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018–22414 Filed 10–19–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 31216; Amdt. No. 3820] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide for the safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective October 22, 2018. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. daltland on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:28 Oct 19, 2018 Jkt 247001 The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 22, 2018. ADDRESSES: Availability of matter incorporated by reference in the amendment is as follows: For Examination 1. U.S. Department of Transportation, Docket Ops-M30, 1200 New Jersey Avenue SE, West Bldg., Ground Floor, Washington, DC, 20590–0001; 2. The FAA Air Traffic Organization Service Area in which the affected airport is located; 3. The office of Aeronautical Navigation Products, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. 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/code_of_federal_ regulations/ibr_locations.html. Availability All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit the National Flight Data Center online at nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from the FAA Air Traffic Organization Service Area in which the affected airport is located. FOR FURTHER INFORMATION CONTACT: Thomas J. Nichols, Flight Procedure Standards Branch (AFS–420)Flight Technologies and Procedures Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK. 73169 (Mail Address: P.O. Box 25082 Oklahoma City, OK. 73125) telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14, Code of Federal Regulations, Part 97 (14 CFR part 97) by amending the referenced SIAPs. The complete regulatory description of each SIAP is listed on the appropriate FAA Form 8260, as modified by the National Flight Data Center (NFDC)/Permanent Notice to Airmen (P–NOTAM), and is incorporated by reference under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR 97.20. The large number of SIAPs, their complex nature, and the need for a special format make their verbatim publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, but refer to their graphic PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP contained on FAA form documents is unnecessary. This amendment provides the affected CFR sections, and specifies the SIAPs and Takeoff Minimums and ODPs with their applicable effective dates. This amendment also identifies the airport and its location, the procedure and the amendment number. Availability and Summary of Material Incorporated by Reference The material incorporated by reference is publicly available as listed in the ADDRESSES section. The material incorporated by reference describes SIAPs, Takeoff Minimums and ODPs as identified in the amendatory language for part 97 of this final rule. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP and Takeoff Minimums and ODP as amended in the transmittal. For safety and timeliness of change considerations, this amendment incorporates only specific changes contained for each SIAP and Takeoff Minimums and ODP as modified by FDC permanent NOTAMs. The SIAPs and Takeoff Minimums and ODPs, as modified by FDC permanent NOTAM, and contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these changes to SIAPs and Takeoff Minimums and ODPs, the TERPS criteria were applied only to specific conditions existing at the affected airports. All SIAP amendments in this rule have been previously issued by the FAA in a FDC NOTAM as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances that created the need for these SIAP and Takeoff Minimums and ODP amendments require making them effective in less than 30 days. Because of the close and immediate relationship between these SIAPs, Takeoff Minimums and ODPs, and safety in air commerce, I find that notice and public procedure under 5 U.S.C. 553(b) are impracticable and contrary to the public interest and, where applicable, under 5 U.S.C. 553(d), good cause exists for making these SIAPs effective in less than 30 days. E:\FR\FM\22OCR1.SGM 22OCR1

Agencies

[Federal Register Volume 83, Number 204 (Monday, October 22, 2018)]
[Rules and Regulations]
[Pages 53171-53174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22414]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0834; Product Identifier 2018-SW-058-AD; Amendment 
39-19421; AD 2018-16-51]
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 publishing a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD 
was sent previously to all known U.S. owners and operators of these 
helicopters as Emergency AD 2018-16-51, dated July 26, 2018, which 
superseded Emergency AD 2018-15-51, dated July 20, 2018. This AD 
requires inspecting the tail rotor (T/R) gearbox installation, 
inspecting the T/R gearbox retaining hardware and support attachment 
point areas, and replacing each nut. This AD is prompted by two reports 
of T/R gearbox assemblies loosely attached to the gearbox support. The 
actions of this AD are intended to address an unsafe condition on these 
products.

DATES: This AD becomes effective November 6, 2018 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2018-16-51, issued on July 26, 2018, which contains the requirements of 
this AD.
    We must receive comments on this AD by December 21, 2018.

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

[[Page 53172]]

Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0834; 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, the economic evaluation, any comments 
received, and other information. The street address for Docket 
Operations (telephone 800- 647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.
    For service information identified in this final rule, contact Bell 
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 
433-0272; or at http://www.bellcustomer.com/files/. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    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-2018-18, dated July 11, 2018, to correct an 
unsafe condition for Bell Model 429 helicopters. Transport Canada 
advises of two reports of T/R gearbox assemblies loosely attached to 
the gearbox support. According to Transport Canada, this condition 
could lead to structural damage and possible loss of control of the 
helicopter.
    As a result, on July 20, 2018, we issued Emergency AD 2018-15-51 
(Emergency AD 2018-15-51), which required inspecting the T/R gearbox 
installation for looseness, visually inspecting the T/R gearbox 
retaining hardware and support attachment point areas, and torque 
inspecting the gearbox retaining nuts. Depending on the inspection 
results, Emergency AD 2018-15-51 required replacing or repairing the 
affected parts in accordance with FAA-approved procedures. Emergency AD 
2018-15-51 was sent previously to all known U.S. owners and operators 
of these helicopters. The actions in Emergency AD 2018-15-51 were 
intended to prevent detachment of the T/R gearbox, loss of T/R control, 
and loss of control of the helicopter.
    After we issued Emergency AD 2018-15-51, we discovered an error in 
the replacement nut P/N. The required replacement nut P/N is NAS9926-
6L; not NAS9926-5L as incorrectly stated in Emergency AD 2018-15-51. 
Therefore, on July 26, 2018, we issued Emergency AD 2018-16-51 to 
supersede Emergency AD 2018-15-51 to correct the nut P/N. Emergency AD 
2018-16-51 otherwise retains all of the requirements of Emergency AD 
2018-15-51. Emergency AD 2018-16-51 was also sent previously to all 
known U.S. owners and operators of these helicopters.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Canada, Transport Canada, its technical 
representative, has notified us of the unsafe condition described in 
the Transport Canada AD. We are 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 the same type design.

Related Service Information

    We reviewed Bell Alert Service Bulletin 429-18-40, dated July 6, 
2018, which specifies a one-time inspection of the T/R gearbox 
installation and a one-time visual and torque inspection of the six 
installation attachment points. This service information also specifies 
contacting Bell Product Support Engineering with the results of the T/R 
gearbox installation inspection, any findings of the visual inspection, 
and the results of the torque inspection.

AD Requirements

    This AD requires inspecting the T/R gearbox installation for 
looseness, visually inspecting the T/R gearbox retaining hardware and 
each support attachment point area, and torque inspecting each gearbox 
retaining nut. Depending on the inspection results, this AD requires 
replacing or repairing the affected parts in accordance with FAA-
approved procedures.

Differences Between This AD and the Transport Canada AD

    The Transport Canada AD applies to helicopters with specific serial 
numbers, whereas this AD applies to all Model 429 helicopters. The 
Transport Canada AD includes a calendar based compliance time, whereas 
this AD does not. The Transport Canada AD requires reporting certain 
information to Bell Product Support Engineering and this AD does not. 
If there is looseness, this AD requires performing the visual 
inspection and torque inspection before further flight, while the 
Transport Canada AD requires contacting Bell. Lastly, if the torque of 
a T/R gearbox retaining nut is below 160 in-lbs (19 Nm), this AD 
requires removing the T/R gearbox and inspecting the mounting surfaces 
and retaining hardware, while the Transport Canada AD requires 
contacting Bell.

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 90 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 $85.00 per work-hour.

[[Page 53173]]

    Inspecting the T/R gearbox installation takes about 0.25 work-hour 
for an estimated cost of $21 per helicopter and $1,890 for the U.S. 
fleet. Inspecting the T/R gearbox retaining hardware and the support 
attachment points takes about 0.5 work-hour for an estimated cost of 
$43 per helicopter and $3,870 for the U.S. fleet. Replacing the nuts 
takes about 1 work-hour and parts cost about $20 for an estimated cost 
of $105 per helicopter and $9,450 for the U.S. fleet.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that required the immediate adoption of 
Emergency AD 2018-16-51, issued on July 26, 2018, to all known U.S. 
owners and operators of these helicopters. The FAA found that the risk 
to the flying public justified waiving notice and comment prior to 
adoption of this rule because there are required actions that must be 
completed before further flight and within 5 hours time-in-service. 
These conditions still exist and the AD is hereby published in the 
Federal Register as an amendment to section 39.13 of the Federal 
Aviation Regulations (14 CFR 39.13) to make it effective to all 
persons. Therefore, we find good cause that notice and opportunity for 
prior public comment are impracticable. In addition, for the reasons 
stated above, we find that good cause exists for making this amendment 
effective in less than 30 days.

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):

2018-16-51 Bell Helicopter Textron Canada Limited: Amendment 39-
19421; Docket No. FAA-2018-0834; Product Identifier 2018-SW-058-AD.

(a) Applicability

    This AD applies to Model 429 helicopters, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a loose tail rotor (T/R) 
gearbox support attachment point. This condition could result in 
detachment of the T/R gearbox, loss of T/R control, and loss of 
control of the helicopter.

(c) Related ADs

    This AD requires the same actions as Emergency AD 2018-16-51, 
dated July 26, 2018, which superseded Emergency AD 2018-15-51, dated 
July 20, 2018.

(d) Effective Date

    This AD becomes effective November 6, 2018 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2018-16-51, issued on July 26, 2018, which contains the 
requirements of this AD.

(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) Before further flight, inspect for looseness of the T/R 
gearbox installation to the T/R gearbox structural support by moving 
the T/R gearbox output shaft in an upward and downward direction. If 
the T/R gearbox installation is loose, before further flight, 
complete the actions required by paragraphs (f)(2)(i) and (ii) of 
this AD.
    (2) Within 5 hours time-in-service, unless already completed as 
required by paragraph (f)(1) of this AD:
    (i) Visually inspect the T/R gearbox retaining hardware and each 
support attachment point area for evidence of fretting, a crack, and 
incorrect installation. If there is any evidence of fretting, a 
crack, or incorrect installation, before further flight, repair in 
accordance with FAA-approved procedures.
    (ii) Inspect each T/R gearbox retaining nut by applying 160 in-
lbs (19 Nm) of torque. If the torque of a T/R gearbox retaining nut 
is below 160 in-lbs (19 Nm), before further flight:
    (A) Remove the T/R gearbox and inspect each stud for proper 
staking, each stud thread for uniformity, each mounting surface for 
evidence of fretting and cracking, and each mounting hole for 
elongation. If a stud is not properly staked, a stud thread is not 
uniform, a mounting surface has evidence of fretting or cracking, or 
a mount hole is elongated, before further flight, replace the 
affected parts or repair in accordance with FAA-approved procedures.
    (B) Replace each nut with nut part number NAS9926-6L and apply a 
torque of 160 in-lbs.

(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: 
Matt Fuller, Senior 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

    (1) Bell Alert Service Bulletin 429-18-40, dated July 6, 2018, 
which is not incorporated

[[Page 53174]]

by reference, contains additional information about the subject of 
this AD. For service information identified in this AD, contact Bell 
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 
433-0272; or at http://www.bellcustomer.com/files/. You may review a 
copy of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177.
    (2) The subject of this AD is addressed in Transport Canada AD 
No. CF-2018-18, dated July 11, 2018. You may view the Transport 
Canada AD on the internet at http://www.regulations.gov by searching 
for and locating it in Docket No. FAA-2018-0834.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor 
Gearbox.

    Issued in Fort Worth, Texas, on October 5, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-22414 Filed 10-19-18; 8:45 am]
 BILLING CODE 4910-13-P