82 FR 34838 - Airworthiness Directives; Sikorsky Aircraft Corporation
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 143 (July 27, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 143 (July 27, 2017)
| Page Range | 34838-34841 | |
| FR Document | 2017-15222 |
[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)] [Rules and Regulations] [Pages 34838-34841] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-15222] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073-AD; Amendment 39-18947; AD 2017-14-03] RIN 2120-AA64 Airworthiness Directives; Sikorsky Aircraft Corporation AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires an inspection and reduces the retirement lives of certain landing gear components. This AD is prompted by a revised analysis of the fatigue life of the landing gear. The actions of this AD are intended to prevent an unsafe condition on these products. DATES: This AD becomes effective August 11, 2017. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of August 11, 2017. We must receive comments on this AD by September 25, 2017. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0664; 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, any incorporated by reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this final rule, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email: [email protected]. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0664. FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7693; 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 We are adopting a new AD for Sikorsky Model S-92A helicopters. This AD is prompted by Sikorsky's updated fatigue analysis of the nose and main landing gear as part of a supplier transition project. The updated fatigue [[Page 34839]] analysis revealed that certain components--main landing gear (MLG) wheel axle part number (P/N) 2392-2334-001, MLG and nose landing gear (NLG) threaded hinge pin P/N 2392-2311-003, NLG cylinder P/N 2392-4006- 005, NLG hinge pin P/N 2392-4312-003, and landing gear actuator rod end P/N 2392-0876-901--require a reduced service life. Sikorsky updated the airworthiness limitations schedule accordingly and developed a recurring visual and ultrasonic inspection of NLG airframe fitting assembly P/N 92209-01101-041 once it has accumulated 31,600 landing cycles. Accordingly, this AD requires inspecting and reducing the life limits of these landing gear components. The actions specified by this AD are intended to detect and prevent cracks or failure of any landing gear component, which could result in damage and loss of control of the helicopter. FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of this same type design. Related Service Information Under 1 CFR Part 51 We reviewed Ultrasonic Inspection Technique No. UT 5077, Revision 0, dated July 25, 2014 (UT 5077). UT 5077 contains the inspection method, equipment and materials, calibration, and inspection procedure for performing an ultrasonic inspection of nose gear actuator fitting P/N 92209-01101-101. 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. Other Related Service Information We also reviewed Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic Issue, dated January 30, 2015 (ASB). The ASB describes procedures for conducting a visual inspection of the NLG airframe fitting assembly and an ultrasonic inspection by following the procedures in UT 5077. AD Requirements This AD requires removing the following components from service: Any MLG wheel axle P/N 2392-2334-001 that has 22,300 or more landing cycles. Any MLG or NLG threaded hinge pin P/N 2392-2311-003 that has 26,100 or more landing cycles. Any NLG cylinder P/N 2392-4006-005 that has 26,300 or more landing cycles. Any NLG hinge pin P/N 2392-4312-003 that has 26,700 or more landing cycles. Any landing gear actuator rod end P/N 2392-0876-901 that has 41,700 or more landing cycles. For helicopters that have 31,600 or more landing cycles and an NLG airframe fitting assembly P/N 92209-01101-041 installed, this AD also requires: Using a 10X or higher power magnifying glass, inspecting each bushing and all visible surfaces of mating lug fittings adjacent to each bushing for fretting, corrosion, wear, and scratches. Replacing the NLG airframe fitting assembly before further flight if there is fretting, corrosion, wear, or a scratch more than 0.0005 inch deep. Ultrasonic inspecting the NLG actuator fitting and replacing the NLG actuator fitting before further flight if there are any anomalies. Differences Between This AD and the Service Information The ASB requires a repetitive inspection of the NLG airframe fitting assemblies P/N 92209-01101-041 every 1,986 landing cycles; this AD does not. Interim Action We consider this AD to be an interim action. We are currently considering requiring a repetitive inspection of the NLG airframe fitting assemblies P/N 92209-01101-041 that would occur every 1,986 landing cycles. However, the planned compliance time for the inspections would allow enough time to provide notice and opportunity for prior public comment on the merits of the repetitive inspections. Costs of Compliance We estimate that this AD will affect 80 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per hour: Replacing a wheel axle P/N 2392-2334-001 will require 2 work-hours and required parts cost $22,000, for a cost per helicopter of $22,170. Replacing a MLG or NLG threaded hinge pin P/N 2392-2311- 003 will require 1 work-hour and required parts cost $3,800, for a cost per helicopter of $3,885. Replacing a NLG cylinder P/N 2392-4006-005 will require 1 work-hour and required parts cost $27,200, for a cost per helicopter of $27,285. Replacing a NLG hinge pin P/N 2392-4312-003 will require 1 work-hour and required parts cost $4,400, for a cost per helicopter of $4,485. Replacing a landing gear actuator rod end P/N 2392-0876- 901 will require 1 work-hour and required parts cost $900, for a cost per helicopter of $985. Inspecting the NLG airframe fitting assembly P/N 92209- 01101-041 will require 8 work-hours, and required parts cost is minimal, for a cost of $680 per helicopter and $54,400 for the U.S. fleet. If required, replacing a NLG actuator fitting P/N 92209- 01101-101 would require 70 work-hours, and required parts cost $10,000, for a cost per helicopter of $15,950. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because replacing the landing gear components affected by the life-limit reductions required by this AD must be accomplished before further flight. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and 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. [[Page 34840]] 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): 2017-14-03 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39- 18947; Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073- AD. (a) Applicability This AD applies to Sikorsky Model S-92A helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of the landing gear. This condition could result in failure of the landing gear and subsequent damage to and loss of control of the helicopter. (c) Effective Date This AD becomes effective August 11, 2017. (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) Before further flight, remove from service any part that has accumulated the number of landing cycles listed in Table 1 to paragraph (e)(1) of this AD. Thereafter, remove from service any part before accumulating the number of landing cycles listed in Table 1 to paragraph (e)(1) of this AD. For purposes of this AD, a landing cycle is counted anytime the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shut down. If the number of landing cycles in unknown, multiply the number of hours time-in- service by 4.5 to determine the number of landing cycles. Table 1 to Paragraph (e)(1) of This AD ---------------------------------------------------------------------------------------------------------------- Part name Part number Life limit ---------------------------------------------------------------------------------------------------------------- Main landing gear (MLG) wheel axle............. 2392-2334-001 22,300 landing cycles. MLG or nose landing gear (NLG) threaded hinge 2392-2311-003 26,100 landing cycles. pin. NLG cylinder................................... 2392-4006-005 26,300 landing cycles. NLG hinge pin.................................. 2392-4312-003 26,700 landing cycles. Landing gear actuator rod end.................. 2392-0876-901 41,700 landing cycles. ---------------------------------------------------------------------------------------------------------------- (2) For helicopters with 31,600 or more landing cycles and an NLG airframe fitting assembly P/N 92209-01101-041 installed, before further flight: (i) Using a 10X or higher power magnifying glass, inspect each bushing (P/N 92209-01101-102 and P/N 92209-01101-103) and all visible surfaces of mating lug fittings adjacent to each bushing for fretting, corrosion, wear, and scratches. If there is fretting, corrosion, wear, or a scratch more than 0.0005 inch deep, replace the NLG airframe fitting assembly before further flight. (ii) Ultrasonic inspect each NLG actuator fitting P/N 92209- 01101-101 in accordance with Sikorsky Ultrasonic Inspection Technique No. UT 5077, Revision 0, dated July 25, 2014 (UT 5077), except you are not required to report to or contact Sikorsky. If there are any anomalies or suspect indications, replace the NLG actuator fitting before further flight. Note 1 to paragraph (e)(2)(ii) of this AD: A copy of UT 5077 is attached to Sikorsky S-92 Helicopter Alert Service Bulletin 92-32- 004, Basic Issue, dated January 30, 2015. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Dorie Resnik, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7693; 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. (g) Additional Information Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic Issue, dated January 30, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email: [email protected]. You may review this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (h) Subject Joint Aircraft Service Component (JASC) Code: 3200 Main Landing Gear and 3220 Nose Landing Gear. (i) 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) Ultrasonic Inspection Technique No. UT 5077, Revision 0, dated July 25, 2014. Note 2 to paragraph (i)(2)(i): Ultrasonic Inspection Technique No. UT 5077, Revision 0, dated July 25, 2014, is an attachment to Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic Issue, dated [[Page 34841]] January 30, 2015, which is not incorporated by reference. (ii) Reserved. (3) For Sikorsky service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email: [email protected]. (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on June 27, 2017. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017-15222 Filed 7-26-17; 8:45 am] BILLING CODE 4910-13-P
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of any record to which such person is DEPARTMENT OF TRANSPORTATION street address for the Docket Operations
not entitled under the FOIA. Office (telephone 800–647–5527) is in
Federal Aviation Administration the ADDRESSES section. Comments will
PART 1003—IMPLEMENTATION OF be available in the AD docket shortly
THE GOVERNMENT IN THE SUNSHINE 14 CFR Part 39 after receipt.
ACT For service information identified in
[Docket No. FAA–2017–0664; Directorate
Identifier 2016–SW–073–AD; Amendment this final rule, contact Sikorsky Aircraft
■ 9. The authority citation for part 1003 Corporation, Customer Service
39–18947; AD 2017–14–03]
continues to read as follows: Engineering, 124 Quarry Road,
Authority: 5 U.S.C. 552b. RIN 2120–AA64 Trumbull, CT 06611; telephone 1–800–
■ 10. Amend § 1003.4 by revising Airworthiness Directives; Sikorsky Winged–S or 203–416–4299; email:
paragraph (c) and adding paragraphs (d) Aircraft Corporation wcs_cust_service_eng.gr-sik@lmco.com.
through (f) to read as follows: You may review the referenced service
AGENCY: Federal Aviation information at the FAA, Office of the
§ 1003.4 Procedures for public Administration (FAA), DOT. Regional Counsel, Southwest Region,
announcement of meetings. 10101 Hillwood Pkwy., Room 6N–321,
ACTION: Final rule; request for
* * * * * comments. Fort Worth, TX 76177. It is also
(c) When a meeting has been called by available on the Internet at http://
the Chairman, the notice shall contain SUMMARY: We are adopting a new www.regulations.gov by searching for
such agenda items as the Chairman airworthiness directive (AD) for and locating Docket No. FAA–2017–
designates. The notice shall be Sikorsky Aircraft Corporation (Sikorsky) 0664.
circulated to Members in advance of Model S–92A helicopters. This AD FOR FURTHER INFORMATION CONTACT:
publication and Members, by majority requires an inspection and reduces the Dorie Resnik, Aviation Safety Engineer,
vote, may add additional agenda items. retirement lives of certain landing gear Boston Aircraft Certification Office,
(d) When a meeting is called by a components. This AD is prompted by a Engine & Propeller Directorate, 1200
majority of Members, the notice shall revised analysis of the fatigue life of the District Avenue, Burlington,
contain such agenda items as have been landing gear. The actions of this AD are Massachusetts 01803; telephone (781)
approved by a majority of the Board. intended to prevent an unsafe condition 238–7693; email dorie.resnik@faa.gov.
(e) The Executive Director will ensure on these products.
SUPPLEMENTARY INFORMATION:
that the final agenda for the meeting DATES: This AD becomes effective
conforms to the notice published in the August 11, 2017. Comments Invited
Federal Register. The Director of the Federal Register This AD is a final rule that involves
(f) If public notice is provided by approved the incorporation by reference requirements affecting flight safety, and
means other than publication in the of a certain document listed in this AD we did not provide you with notice and
Federal Register, notice will be as of August 11, 2017. an opportunity to provide your
promptly submitted to the Federal We must receive comments on this comments prior to it becoming effective.
Register for publication. AD by September 25, 2017. However, we invite you to participate in
■ 11. Revise § 1003.7 to read as follows: ADDRESSES: You may send comments by this rulemaking by submitting written
§ 1003.7 Changes following public
any of the following methods: comments, data, or views. We also
announcement. • Federal eRulemaking Docket: Go to invite comments relating to the
http://www.regulations.gov. Follow the economic, environmental, energy, or
(a) The time, place, and agenda items online instructions for sending your federalism impacts that resulted from
of a meeting following the public comments electronically. adopting this AD. The most helpful
announcement described in § 1003.4, or • Fax: 202–493–2251. comments reference a specific portion of
the determination of the Board to open • Mail: Send comments to the U.S. the AD, explain the reason for any
or close a meeting, or a portion thereof, Department of Transportation, Docket recommended change, and include
to the public may be changed following Operations, M–30, West Building supporting data. To ensure the docket
public announcement only if: Ground Floor, Room W12–140, 1200 does not contain duplicate comments,
(1) A majority of all members New Jersey Avenue SE., Washington, commenters should send only one copy
determine by recorded vote that Board DC 20590–0001. of written comments, or if comments are
business so requires and that no earlier • Hand Delivery: Deliver to the filed electronically, commenters should
announcement of the change was ‘‘Mail’’ address between 9 a.m. and 5 submit them only one time. We will file
possible; and p.m., Monday through Friday, except in the docket all comments that we
(2) The Board publicly announces Federal holidays. receive, as well as a report summarizing
such change and the vote of each each substantive public contact with
member thereon at the earliest Examining the AD Docket
FAA personnel concerning this
practicable time. You may examine the AD docket on rulemaking during the comment period.
(b) Changes to the time, place and the Internet at http:// We will consider all the comments we
agenda items of a meeting called by the www.regulations.gov by searching for receive and may conduct additional
Chairman pursuant to § 1003.4(c) must and locating Docket No. FAA–2017– rulemaking based on those comments.
be made with the concurrence of the 0664; or in person at the Docket
Chairman, except that when Members Discussion
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Operations Office between 9 a.m. and 5
have, by majority vote, added additional p.m., Monday through Friday, except We are adopting a new AD for
agenda items, the addition of those Federal holidays. The AD docket Sikorsky Model S–92A helicopters. This
agenda items does not require the contains this AD, any incorporated by AD is prompted by Sikorsky’s updated
Chairman’s concurrence. reference service information, the fatigue analysis of the nose and main
[FR Doc. 2017–15660 Filed 7–26–17; 8:45 am] economic evaluation, any comments landing gear as part of a supplier
BILLING CODE 6820–B3–P received, and other information. The transition project. The updated fatigue
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Regulatory Findings List of Subjects in 14 CFR Part 39 (b) Unsafe Condition
This AD defines the unsafe condition as
We determined that this AD will not Air transportation, Aircraft, Aviation fatigue failure of the landing gear. This
have federalism implications under safety, Incorporation by reference, condition could result in failure of the
Executive Order 13132. This AD will Safety. landing gear and subsequent damage to and
not have a substantial direct effect on Adoption of the Amendment loss of control of the helicopter.
the States, on the relationship between (c) Effective Date
the national Government and the States, Accordingly, under the authority
This AD becomes effective August 11,
or on the distribution of power and delegated to me by the Administrator, 2017.
responsibilities among the various the FAA amends 14 CFR part 39 as
levels of government. follows: (d) Compliance
For the reasons discussed, I certify You are responsible for performing each
PART 39—AIRWORTHINESS action required by this AD within the
that this AD:
DIRECTIVES specified compliance time unless it has
1. Is not a ‘‘significant regulatory already been accomplished prior to that time.
action’’ under Executive Order 12866; ■ 1. The authority citation for part 39 (e) Required Actions
2. Is not a ‘‘significant rule’’ under continues to read as follows:
(1) Before further flight, remove from
DOT Regulatory Policies and Procedures Authority: 49 U.S.C. 106(g), 40113, 44701. service any part that has accumulated the
(44 FR 11034, February 26, 1979); number of landing cycles listed in Table 1 to
§ 39.13 [Amended] paragraph (e)(1) of this AD. Thereafter,
3. Will not affect intrastate aviation in
Alaska to the extent that it justifies remove from service any part before
■ 2. The FAA amends § 39.13 by adding
making a regulatory distinction; and accumulating the number of landing cycles
the following new airworthiness listed in Table 1 to paragraph (e)(1) of this
4. Will not have a significant directive (AD): AD. For purposes of this AD, a landing cycle
economic impact, positive or negative, 2017–14–03 Sikorsky Aircraft Corporation is counted anytime the helicopter lifts off
on a substantial number of small entities (Sikorsky): Amendment 39–18947; into the air and then lands again regardless
under the criteria of the Regulatory Docket No. FAA–2017–0664; Directorate of the duration of the landing and regardless
Flexibility Act. Identifier 2016–SW–073–AD. of whether the engine is shut down. If the
number of landing cycles in unknown,
We prepared an economic evaluation (a) Applicability multiply the number of hours time-in-service
of the estimated costs to comply with This AD applies to Sikorsky Model S–92A by 4.5 to determine the number of landing
this AD and placed it in the AD docket. helicopters, certificated in any category. cycles.
TABLE 1 TO PARAGRAPH (e)(1) OF THIS AD
Part name Part number Life limit
Main landing gear (MLG) wheel axle .................................................................................................... 2392–2334–001 22,300 landing cycles.
MLG or nose landing gear (NLG) threaded hinge pin .......................................................................... 2392–2311–003 26,100 landing cycles.
NLG cylinder .......................................................................................................................................... 2392–4006–005 26,300 landing cycles.
NLG hinge pin ........................................................................................................................................ 2392–4312–003 26,700 landing cycles.
Landing gear actuator rod end .............................................................................................................. 2392–0876–901 41,700 landing cycles.
(2) For helicopters with 31,600 or more (f) Alternative Methods of Compliance Trumbull, CT 06611; telephone 1–800–
landing cycles and an NLG airframe fitting (AMOCs) Winged–S or 203–416–4299; email: wcs_
assembly P/N 92209–01101–041 installed, (1) The Manager, Boston Aircraft cust_service_eng.gr-sik@lmco.com. You may
before further flight: Certification Office, FAA, may approve review this service information at the FAA,
(i) Using a 10X or higher power magnifying AMOCs for this AD. Send your proposal to: Office of the Regional Counsel, Southwest
glass, inspect each bushing (P/N 92209– Dorie Resnik, Aviation Safety Engineer, Region, 10101 Hillwood Pkwy., Room 6N–
Boston Aircraft Certification Office, Engine & 321, Fort Worth, TX 76177.
01101–102 and P/N 92209–01101–103) and
all visible surfaces of mating lug fittings Propeller Directorate, 1200 District Avenue, (h) Subject
adjacent to each bushing for fretting, Burlington, Massachusetts 01803; telephone
(781) 238–7693; email dorie.resnik@faa.gov. Joint Aircraft Service Component (JASC)
corrosion, wear, and scratches. If there is Code: 3200 Main Landing Gear and 3220
(2) For operations conducted under a 14
fretting, corrosion, wear, or a scratch more CFR part 119 operating certificate or under Nose Landing Gear.
than 0.0005 inch deep, replace the NLG 14 CFR part 91, subpart K, we suggest that (i) Material Incorporated by Reference
airframe fitting assembly before further flight. you notify your principal inspector, or
(ii) Ultrasonic inspect each NLG actuator lacking a principal inspector, the manager of (1) The Director of the Federal Register
fitting P/N 92209–01101–101 in accordance the local flight standards district office or approved the incorporation by reference of
with Sikorsky Ultrasonic Inspection certificate holding district office before the service information listed in this
operating any aircraft complying with this paragraph under 5 U.S.C. 552(a) and 1 CFR
Technique No. UT 5077, Revision 0, dated
AD through an AMOC. part 51.
July 25, 2014 (UT 5077), except you are not
(2) You must use this service information
required to report to or contact Sikorsky. If (g) Additional Information as applicable to do the actions required by
there are any anomalies or suspect this AD, unless the AD specifies otherwise.
Sikorsky S–92 Helicopter Alert Service
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indications, replace the NLG actuator fitting Bulletin 92–32–004, Basic Issue, dated (i) Ultrasonic Inspection Technique No. UT
before further flight. January 30, 2015, which is not incorporated 5077, Revision 0, dated July 25, 2014.
Note 1 to paragraph (e)(2)(ii) of this AD: by reference, contains additional information Note 2 to paragraph (i)(2)(i): Ultrasonic
A copy of UT 5077 is attached to Sikorsky about the subject of this AD. For service Inspection Technique No. UT 5077, Revision
S–92 Helicopter Alert Service Bulletin 92– information identified in this AD, contact 0, dated July 25, 2014, is an attachment to
32–004, Basic Issue, dated January 30, 2015. Sikorsky Aircraft Corporation, Customer Sikorsky S–92 Helicopter Alert Service
Service Engineering, 124 Quarry Road, Bulletin 92–32–004, Basic Issue, dated
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January 30, 2015, which is not incorporated of certain publications listed in this AD detect and correct out-of-tolerance
by reference. as of August 31, 2017. tension in the control cables, which,
(ii) Reserved. ADDRESSES: For service information with certain system failures and
(3) For Sikorsky service information identified in this final rule, contact environmental conditions, could result
identified in this AD, contact Sikorsky in reduced controllability of the
Aircraft Corporation, Customer Service
Bombardier, Inc., 400 Côte-Vertu Road
West, Dorval, Québec H4S 1Y9, Canada; airplane.
Engineering, 124 Quarry Road, Trumbull, CT
telephone: 514–855–5000; fax: 514– Transport Canada Civil Aviation
06611; telephone 1–800–Winged–S or 203–
416–4299; email: wcs_cust_service_eng.gr- 855–7401; email: thd.crj@ (TCCA), which is the aviation authority
sik@lmco.com. aero.bombardier.com; Internet: http:// for Canada, has issued Canadian
(4) You may view this service information www.bombardier.com. You may view Airworthiness Directive CF–2016–06R1,
at FAA, Office of the Regional Counsel, this referenced service information at dated July 25, 2016 (referred to after this
Southwest Region, 10101 Hillwood Pkwy, the FAA, Transport Airplane as the Mandatory Continuing
Room 6N–321, Fort Worth, TX 76177. For Directorate, 1601 Lind Avenue SW., Airworthiness Information, or ‘‘the
information on the availability of this MCAI’’), to correct an unsafe condition
material at the FAA, call (817) 222–5110.
Renton, WA. For information on the
availability of this material at the FAA, for certain Bombardier Model BD–700–
(5) You may view this service information
call 425–227–1221. It is also available 1A10 and BD–700–1A11 airplanes. The
that is incorporated by reference at the
National Archives and Records on the Internet at http:// MCAI states:
Administration (NARA). For information on www.regulations.gov by searching for Recent in-service inspections have shown
the availability of this material at NARA, call and locating Docket No. FAA–2016– that aileron and rudder control cables may
(202) 741–6030, or go to: http:// 9304. have tensions beyond allowable limits.
www.archives.gov/federal-register/cfr/ibr- Review of the technical documentation found
locations.html. Examining the AD Docket that there are no maintenance tasks to detect
and rectify out-of-tolerance tensions on these
Issued in Fort Worth, Texas, on June 27, You may examine the AD docket on
cables. Out of tolerance cables in
2017. the Internet at http:// combinations with certain system failures
Scott A. Horn, www.regulations.gov by searching for and environmental conditions could result in
Acting Manager, Rotorcraft Directorate, and locating Docket No. FAA–2016– the degraded aircraft controllability.
Aircraft Certification Service. 9304; or in person at the Docket * * * [This Canadian] AD was issued to
[FR Doc. 2017–15222 Filed 7–26–17; 8:45 am] Management Facility between 9 a.m. mandate a revision to the approved
and 5 p.m., Monday through Friday, maintenance schedule [maintenance or
BILLING CODE 4910–13–P
except Federal holidays. The AD docket inspection program, as applicable] to
introduce cable tension check [e.g.,
contains this AD, the regulatory functional test,] as [certification maintenance
DEPARTMENT OF TRANSPORTATION evaluation, any comments received, and requirement] tasks.
other information. The street address for
Federal Aviation Administration the Docket Office (telephone 800–647– You may examine the MCAI on the
5527) is Docket Management Facility, Internet at http://www.regulations.gov
14 CFR Part 39 U.S. Department of Transportation, by searching for and locating Docket No.
Docket Operations, M–30, West FAA–2016–9304.
[Docket No. FAA–2016–9304; Directorate This AD requires revisions to certain
Identifier 2016–NM–028–AD; Amendment Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE., operator maintenance documents to
39–18959; AD 2017–14–15]
Washington, DC 20590. include new actions (e.g., inspections).
RIN 2120–AA64 Compliance with these actions is
FOR FURTHER INFORMATION CONTACT:
required by 14 CFR 91.403(c). For
Airworthiness Directives; Bombardier, Cesar Gomez, Aerospace Engineer, airplanes that have been previously
Inc., Airplanes Airframe and Mechanical Systems modified, altered, or repaired in the
Branch, ANE–171, FAA, New York areas addressed by this AD, the operator
AGENCY: Federal Aviation Aircraft Certification Office (ACO), 1600
Administration (FAA), Department of may not be able to accomplish the
Stewart Avenue, Suite 410, Westbury, actions described in the revisions. In
Transportation (DOT). NY 11590; telephone: 516–228–7318; this situation, to comply with 14 CFR
ACTION: Final rule. fax: 516–794–5531. 91.403(c), the operator must request
SUPPLEMENTARY INFORMATION: approval for an alternative method of
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain Discussion compliance according to paragraph (j)(1)
Bombardier, Inc., Model BD–700–1A10 of this AD. The request should include
We issued a notice of proposed a description of changes to the required
and BD–700–1A11 airplanes. This AD rulemaking (NPRM) to amend 14 CFR
was prompted by reports of aileron and actions that will ensure the continued
part 39 by adding an AD that would operational safety of the airplane.
rudder control cables that may have apply to certain Bombardier, Inc., Model
tensions that are beyond allowable BD–700–1A10 and BD–700–1A11 Comments
limits. This AD requires a revision to airplanes. The NPRM published in the We gave the public the opportunity to
the maintenance or inspection program Federal Register on November 7, 2016 participate in developing this AD. The
to incorporate certification maintenance (81 FR 78080). The NPRM was following presents the comments
requirement tasks that introduce prompted by reports of aileron and received on the NPRM and the FAA’s
functional tests of the control cable rudder control cables that may have response to each comment.
tension. We are issuing this AD to
mstockstill on DSK30JT082PROD with RULES
tensions that are beyond allowable
address the unsafe condition on these limits. The NPRM proposed to require Request To Reference the Latest Time
products. revising the maintenance or inspection Limits/Maintenance Checks (TLMC)
DATES:This AD is effective August 31, program to incorporate certification General Revision Instead of the
2017. maintenance requirement tasks that Temporary Revision (TR)
The Director of the Federal Register introduce functional tests of the control Bombardier, Inc., and KACALP Flight
approved the incorporation by reference cable tension. We are issuing this AD to Operations requested that paragraph (g)
VerDate Sep<11>2014 17:07 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\27JYR1.SGM 27JYR1](https://thefederalregister.org/doc/82_FR_34981/page/4.svg)
Document Created: 2017-07-27 02:07:10
Document Modified: 2017-07-27 02:07:10
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective August 11, 2017. | |
| Contact | Dorie Resnik, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7693; email [email protected] | |
| FR Citation | 82 FR 34838 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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