Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters, 46002-46004 [2016-16749]

Download as PDF 46002 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules within 15 engine flight cycles or at next shop visit, whichever occurs sooner. (E) If there is any cracking or material loss found on seal support 23, replace the fairing within 15 engine flight cycles or at next shop visit, whichever occurs sooner. (ii) If the visual inspection required by paragraph (e)(3)(i) of this AD does not detect any crack, fluorescent penetrant inspect zone A. Refer to AMM TASK 70–20–02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), or OMat 632, high sensitivity fluorescent penetrant inspection, for guidance on fluorescent penetrant inspection. (A) If a crack shorter than 6 mm is detected, repair or replace the fairing within 100 engine flight cycles, or at the next shop visit, whichever occurs sooner. (B) If a crack longer than 6 mm is detected, repair or replace the fairing within 15 engine flight cycles or at the next shop visit, whichever occurs sooner. Definition For the purpose of this AD, a ‘‘shop visit’’ is defined as induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (g) Related Information (1) For more information about this AD, contact Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7134; fax: 781–238–7199; email: wego.wang@ faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2016–0084, dated April 28, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2016–6692. (3) RR NMSB RB.211–72–AJ165, dated March 31, 2016, can be obtained from RR, using the contact information in paragraph (g)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44– 1332–242424; fax: 011–44–1332–249936; email: https://www.rolls-royce.com/contact/ civil_team.jsp; Internet: https:// customers.rolls-royce.com/public/ rollsroycecare. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 Issued in Burlington, Massachusetts, on July 1, 2016. Ann C. Mollica, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–16646 Filed 7–14–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8501; Directorate Identifier 2014–SW–042–AD] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S–92A helicopters. This proposed AD would require inspecting the main transmission forward (fwd) and aft frame assembly and adjacent skins for a crack and loose fasteners and establishing life limits for certain frame assemblies. This proposed AD is prompted by fatigue analysis indicating stress concentrations as well as the discovery of a crack in the station (STA) 362 frame and skin on a Model S–92A helicopter. The proposed actions are intended to detect a crack in a frame assembly and prevent failure of a frame and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 13, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 www.regulations.gov by searching for and locating Docket No. FAA–2016– 8501; 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 proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800Winged-S or 203–416–4299; email sikorskywcs@sikorsky.com. 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, Texas 76177. FOR FURTHER INFORMATION CONTACT: Kristopher Greer, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7799; email Kristopher.Greer@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited 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 might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. E:\FR\FM\15JYP1.SGM 15JYP1 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules Discussion We propose to adopt a new AD for Sikorsky Model S–92A helicopters with certain part-numbered frame assemblies installed. This proposed AD is prompted by a fatigue analysis that indicates stress concentrations may develop at the steel doublers on the main transmission airframe support structure top deck, adjacent to the transmission feet. Additionally, a helicopter was discovered with a crack in the STA 362 frame and skin. This proposed AD would require inspecting the main transmission fwd and aft frame assemblies and adjacent skins for a crack and loose fasteners and replacing or repairing any cracked part or loose fastener. This proposed AD would also require establishing life limits for certain frame assemblies. The proposed actions are intended to detect a crack in the frame assemblies and to prevent failure of the main transmission frame assemblies and subsequent loss of control of the helicopter. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS FAA’s Determination We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of the same type design. Related Service Information Sikorsky issued S–92 Alert Service Bulletin (ASB) 92–53–008, Basic Issue, dated June 13, 2012 (ASB 92–53–008); S–92 ASB 92–53–009, Basic Issue, dated December 6, 2012 (ASB 92–53–009); and S–92 ASB 92–53–012, Basic Issue, dated February 10, 2014 (ASB 92–53– 012). ASB 92–53–008 provides procedures for a one-time inspection of the main transmission frames and beams for a crack, missing or loose fastener or collar, damage, deformation, and corrosion. ASB 92–53–009 specifies an inspection before the first flight of the day and a recurring 150-hour inspection of the interior and exterior surfaces of the upper flanges and beams. ASB 92–53–012 specifies altering the fwd and aft transmission support frames by replacing the fasteners in accordance with Sikorsky Special Service Instructions No. 92–074–E, Revision E, dated April 9, 2014. After this alteration, the parts are re-identified with a new part number. Sikorsky refers to this alteration as a service life extension program modification. Proposed AD Requirements This proposed AD would establish a life limit for certain part-numbered frame assemblies by removing from service any part that has reached or VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 46003 exceeded its new life limit. Frame assemblies that are altered under Sikorsky’s service life extension program and re-identified with a new part number must be removed from service upon accumulating the life limit of the old part-number or within certain hours TIS since the alteration, whichever occurs first. This proposed AD would also require, for helicopters with certain partnumbered frame assemblies, within 24 clock-hours and thereafter before the first flight of each day or at intervals not to exceed 24 clock-hours, whichever occurs later, inspecting the top deck skin, straps, and fasteners for a crack and loose fasteners in two locations. If there is a loose fastener or a crack, this proposed AD would require repairing or replacing the cracked or loose part and performing additional inspections of the STA 328 frame, STA 362 frame, and the butt line (BL) 16.5 beams. Finally, this proposed AD would require repetitively inspecting the STA 328 frame, STA 362 frame, and the BL 16.5 beams once the frame assembly exceeds certain hours TIS. Regulatory Findings Differences Between This Proposed AD and the Service Information List of Subjects in 14 CFR Part 39 The service information requires providing certain information to Sikorsky and this proposed AD would not. The service information specifies performing a fluorescent penetrant inspection if there is a suspected crack and contacting Sikorsky if there is a crack, while this proposed AD would only require repairing or replacing any cracked part. Contacting Sikorsky would not be required. Fmt 4702 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: We estimate that this proposed AD would affect 80 helicopters of U.S. Registry. We estimate that operators may incur the following costs to comply with this AD. Labor costs are estimated at $85 per work-hour. We estimate a minimal cost to establish and revise the life limit of the frame assembly. We estimate it would take 1 work-hour to visually inspect the skin and 1 work-hour to inspect STA 328 and 362 frames. No parts would be needed for a total cost of $6,800 for the fleet for each inspection per inspection cycle. If a fastener is replaced, we estimate the cost to be minimal. If a frame is replaced, it would take 3,360 workhours and a required parts cost of $296,000 for a total cost of $581,600 per helicopter. Frm 00020 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. ■ Costs of Compliance PO 00000 We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed AD and placed it in the AD docket. Sfmt 4702 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): ■ Sikorsky Aircraft Corporation: Docket No. FAA–2016–8501; Directorate Identifier 2014–SW–042–AD. (a) Applicability This AD applies to Model S–92A helicopters, certificated in any category, with a forward (fwd) station (STA) 328 or aft STA 362 frame assembly with a part number (P/N) as shown in Table 1 to paragraph (e)(1), Table 2 to paragraph (e)(1), Table 3 to paragraph (e)(2), or Table 4 to paragraph (e)(3) of this AD. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a main transmission airframe E:\FR\FM\15JYP1.SGM 15JYP1 46004 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules support structure. This condition could result in failure of a main transmission frame and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by September 13, 2016. (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) For helicopters with a frame assembly with a P/N shown in Table 1 to paragraph (e)(1) or Table 2 to paragraph (e)(1) of this AD, before further flight, remove from service any part that has reached or exceeded its new life limit. Fwd STA 328 frame assemblies that are altered and changed to P/N 92070– 20124–064, 92070–20124–067, 92070– 20127–045, 92070–20124–065, 92070– 20124–047, or 92070–20127–046 must be removed from service upon accumulating 12,000 hours TIS from the alteration or 28,500 hours TIS total (regardless of P/N), whichever occurs first. TABLE 1 TO PARAGRAPH (e)(1) (e)(1), Table 2 to paragraph (e)(1), or Table 3 to paragraph (e)(2) of this AD: Within 24 clock-hours, and thereafter before the first flight of each day or at intervals not to exceed 24 clock-hours, whichever occurs later, using a 10X or higher power magnifying glass, inspect the skin, straps, and fasteners of the top deck for a crack and loose fasteners in two locations from the STA 328 frame to the STA 305 frame between the right butt line (BL) 16.5 beam and the left BL 16.5 beam, and from the STA 362 frame to the STA 379 frame between the right BL 16.5 beam and the left BL 16.5 beam. If there is a loose fastener or a crack: (i) Repair or replace any cracked part and any loose fastener before further flight. (ii) Inspect the STA 328 frame and STA 362 frame between the left and right BL16.5 beams and inspect the area on the left and right BL 16.5 beams six inches on either side of the mounting pads for a crack and loose fasteners. If there is a loose fastener or a crack, repair or replace any cracked part and any loose fastener before further flight. (iii) Inspect the STA 328 and STA 362 outboard frames, left and right sides, from the BL 16.5 beam to water line 252.25 for a crack and loose fasteners. If there is a loose fastener or a crack, repair or replace any cracked part and any loose fastener before further flight. TABLE 3 TO PARAGRAPH (e)(2) Life limit hours TIS Fwd STA 328 frame assembly P/N: 92070–20124–064 ............ 92070–20124–067 ............ 92070–20127–045 ............ 92070–20124–065 ............ 92070–20124–047 ............ 92070–20127–046 ............ 92070–20124–063 ............ 92070–20124–066 ............ 92070–20127–041 ............ Aft STA 362 frame assembly P/N: 92070–20124–041 ............ 92070–20124–044 ............ 92070–20127–042 ............ 92070–20124–042 ............ 92070–20124–045 ............ 92070–20127–049 ............ 92070–20124–043 ............ 92070–20124–046 ............ 92070–20127–050 ............ 92070–20141–050 ............ 92070–20141–051 ............ 92070–20141–052 ............ Fwd STA 328 frame assembly P/N 12,000 12,000 12,000 12,000 12,000 12,000 12,000 12,000 12,000 10,400 10,400 10,400 10,400 10,400 10,400 10,400 10,400 10,400 17,000 17,000 17,000 asabaliauskas on DSK3SPTVN1PROD with PROPOSALS TABLE 2 TO PARAGRAPH (e)(1) Life limit hours TIS Fwd STA 328 frame assembly P/N: 92070–20097–058 ............ 92080–20047–047 ............ 92070–20097–060 ............ 92080–20047–048 ............ 28,500 28,500 28,500 28,500 (2) For helicopters with a frame assembly with a P/N shown in Table 1 to paragraph VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 92209–02106–042 92209–02106–043 92070–20097–041 92080–20047–041 Aft STA 362 frame assembly P/N ........ ........ ........ ........ 92070–20097–062 92080–20047–051 92209–02109–043 92209–02109–044 92070–20097–042 92080–20047–042 92070–20097–064 92080–20047–052 (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 Alert Service Bulletin (ASB) 92–53–008, Basic Issue, dated June 13, 2012; ASB 92–53–009, Basic Issue, dated December 6, 2012; ASB 92–53–012, Basic Issue, dated February 10, 2014, and Sikorsky Special Service Instructions No. 92–074–E, Revision E, dated April 9, 2014, which are not incorporated by reference, contain 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 sikorskywcs@sikorsky.com. You may review a copy of information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, Texas 76177. (h) Subject Joint Aircraft Service Component (JASC) Code: 5311 Fuselage Main, Frame. Issued in Fort Worth, Texas, on July 7, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–16749 Filed 7–14–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY (3) For each frame assembly listed in Table 1 to paragraph (e)(1) or Table 4 to paragraph (e)(3) of this AD with 1,801 or more hours TIS, and for each frame assembly listed in Table 2 to paragraph (e)(1) or Table 3 to paragraph (e)(2) of this AD with 1,301 or more hours TIS, within 150 hours TIS and thereafter at intervals not to exceed 150 hours TIS, perform the inspections in paragraphs (e)(2)(ii) and (e)(2)(iii) of this AD. TABLE 4 TO PARAGRAPH (e)(3) Fwd STA 328 frame assembly P/N Aft STA 362 frame assembly P/N 92209–02107–042 ........ 92209–02107–103 ........ 92070–02108–042 92080–02108–103 (f) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kristopher Greer, Aviation Safety Engineer, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7799; email Kristopher.Greer@faa.gov. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 Internal Revenue Service 26 CFR Part 1 [REG–134016–15] RIN 1545–BN47 Guidance Under Section 355 Concerning Device and Active Trade or Business Internal Revenue Service (IRS), Treasury. ACTION: Notice of proposed rulemaking. AGENCY: This document contains proposed regulations under section 355 of the Internal Revenue Code (Code). The proposed regulations would clarify the application of the device prohibition and the active business requirement of section 355. The proposed regulations would affect corporations that distribute the stock of controlled corporations, their shareholders, and their security holders. SUMMARY: E:\FR\FM\15JYP1.SGM 15JYP1

Agencies

[Federal Register Volume 81, Number 136 (Friday, July 15, 2016)]
[Proposed Rules]
[Pages 46002-46004]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16749]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8501; Directorate Identifier 2014-SW-042-AD]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft Corporation
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This
proposed AD would require inspecting the main transmission forward
(fwd) and aft frame assembly and adjacent skins for a crack and loose
fasteners and establishing life limits for certain frame assemblies.
This proposed AD is prompted by fatigue analysis indicating stress
concentrations as well as the discovery of a crack in the station (STA)
362 frame and skin on a Model S-92A helicopter. The proposed actions
are intended to detect a crack in a frame assembly and prevent failure
of a frame and subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by September 13,
2016.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8501; 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 proposed AD, the economic evaluation, any comments
received, and other information. The street address for the Docket
Operations Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
For service information identified in this proposed AD, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299;
email sikorskywcs@sikorsky.com. 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, Texas 76177.

FOR FURTHER INFORMATION CONTACT: Kristopher Greer, Aviation Safety
Engineer, Boston Aircraft Certification Office, Engine & Propeller
Directorate, 1200 District Avenue, Burlington, Massachusetts 01803;
telephone (781) 238-7799; email Kristopher.Greer@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.

[[Page 46003]]

Discussion

We propose to adopt a new AD for Sikorsky Model S-92A helicopters
with certain part-numbered frame assemblies installed. This proposed AD
is prompted by a fatigue analysis that indicates stress concentrations
may develop at the steel doublers on the main transmission airframe
support structure top deck, adjacent to the transmission feet.
Additionally, a helicopter was discovered with a crack in the STA 362
frame and skin. This proposed AD would require inspecting the main
transmission fwd and aft frame assemblies and adjacent skins for a
crack and loose fasteners and replacing or repairing any cracked part
or loose fastener. This proposed AD would also require establishing
life limits for certain frame assemblies. The proposed actions are
intended to detect a crack in the frame assemblies and to prevent
failure of the main transmission frame assemblies and subsequent loss
of control of the helicopter.

FAA's Determination

We are proposing this AD because we evaluated all known relevant
information and determined that an unsafe condition exists and is
likely to exist or develop on other helicopters of the same type
design.

Related Service Information

Sikorsky issued S-92 Alert Service Bulletin (ASB) 92-53-008, Basic
Issue, dated June 13, 2012 (ASB 92-53-008); S-92 ASB 92-53-009, Basic
Issue, dated December 6, 2012 (ASB 92-53-009); and S-92 ASB 92-53-012,
Basic Issue, dated February 10, 2014 (ASB 92-53-012). ASB 92-53-008
provides procedures for a one-time inspection of the main transmission
frames and beams for a crack, missing or loose fastener or collar,
damage, deformation, and corrosion. ASB 92-53-009 specifies an
inspection before the first flight of the day and a recurring 150-hour
inspection of the interior and exterior surfaces of the upper flanges
and beams. ASB 92-53-012 specifies altering the fwd and aft
transmission support frames by replacing the fasteners in accordance
with Sikorsky Special Service Instructions No. 92-074-E, Revision E,
dated April 9, 2014. After this alteration, the parts are re-identified
with a new part number. Sikorsky refers to this alteration as a service
life extension program modification.

Proposed AD Requirements

This proposed AD would establish a life limit for certain part-
numbered frame assemblies by removing from service any part that has
reached or exceeded its new life limit. Frame assemblies that are
altered under Sikorsky's service life extension program and re-
identified with a new part number must be removed from service upon
accumulating the life limit of the old part-number or within certain
hours TIS since the alteration, whichever occurs first.
This proposed AD would also require, for helicopters with certain
part-numbered frame assemblies, within 24 clock-hours and thereafter
before the first flight of each day or at intervals not to exceed 24
clock-hours, whichever occurs later, inspecting the top deck skin,
straps, and fasteners for a crack and loose fasteners in two locations.
If there is a loose fastener or a crack, this proposed AD would require
repairing or replacing the cracked or loose part and performing
additional inspections of the STA 328 frame, STA 362 frame, and the
butt line (BL) 16.5 beams.
Finally, this proposed AD would require repetitively inspecting the
STA 328 frame, STA 362 frame, and the BL 16.5 beams once the frame
assembly exceeds certain hours TIS.

Differences Between This Proposed AD and the Service Information

The service information requires providing certain information to
Sikorsky and this proposed AD would not. The service information
specifies performing a fluorescent penetrant inspection if there is a
suspected crack and contacting Sikorsky if there is a crack, while this
proposed AD would only require repairing or replacing any cracked part.
Contacting Sikorsky would not be required.

Costs of Compliance

We estimate that this proposed AD would affect 80 helicopters of
U.S. Registry.
We estimate that operators may incur the following costs to comply
with this AD. Labor costs are estimated at $85 per work-hour. We
estimate a minimal cost to establish and revise the life limit of the
frame assembly. We estimate it would take 1 work-hour to visually
inspect the skin and 1 work-hour to inspect STA 328 and 362 frames. No
parts would be needed for a total cost of $6,800 for the fleet for each
inspection per inspection cycle. If a fastener is replaced, we estimate
the cost to be minimal. If a frame is replaced, it would take 3,360
work-hours and a required parts cost of $296,000 for a total cost of
$581,600 per helicopter.

Regulatory Findings

We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):

Sikorsky Aircraft Corporation: Docket No. FAA-2016-8501; Directorate
Identifier 2014-SW-042-AD.

(a) Applicability

This AD applies to Model S-92A helicopters, certificated in any
category, with a forward (fwd) station (STA) 328 or aft STA 362
frame assembly with a part number (P/N) as shown in Table 1 to
paragraph (e)(1), Table 2 to paragraph (e)(1), Table 3 to paragraph
(e)(2), or Table 4 to paragraph (e)(3) of this AD.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a main
transmission airframe

[[Page 46004]]

support structure. This condition could result in failure of a main
transmission frame and subsequent loss of control of the helicopter.

We must receive comments by September 13, 2016.

(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) For helicopters with a frame assembly with a P/N shown in
Table 1 to paragraph (e)(1) or Table 2 to paragraph (e)(1) of this
AD, before further flight, remove from service any part that has
reached or exceeded its new life limit. Fwd STA 328 frame assemblies
that are altered and changed to P/N 92070-20124-064, 92070-20124-
067, 92070-20127-045, 92070-20124-065, 92070-20124-047, or 92070-
20127-046 must be removed from service upon accumulating 12,000
hours TIS from the alteration or 28,500 hours TIS total (regardless
of P/N), whichever occurs first.

Table 1 to Paragraph (e)(1)
------------------------------------------------------------------------
Life limit
hours TIS
------------------------------------------------------------------------
Fwd STA 328 frame assembly P/N:
92070-20124-064....................................... 12,000
92070-20124-067....................................... 12,000
92070-20127-045....................................... 12,000
92070-20124-065....................................... 12,000
92070-20124-047....................................... 12,000
92070-20127-046....................................... 12,000
92070-20124-063....................................... 12,000
92070-20124-066....................................... 12,000
92070-20127-041....................................... 12,000
Aft STA 362 frame assembly P/N:
92070-20124-041....................................... 10,400
92070-20124-044....................................... 10,400
92070-20127-042....................................... 10,400
92070-20124-042....................................... 10,400
92070-20124-045....................................... 10,400
92070-20127-049....................................... 10,400
92070-20124-043....................................... 10,400
92070-20124-046....................................... 10,400
92070-20127-050....................................... 10,400
92070-20141-050....................................... 17,000
92070-20141-051....................................... 17,000
92070-20141-052....................................... 17,000
------------------------------------------------------------------------

Table 2 to Paragraph (e)(1)
------------------------------------------------------------------------
Life limit
hours TIS
------------------------------------------------------------------------
Fwd STA 328 frame assembly P/N:
92070-20097-058....................................... 28,500
92080-20047-047....................................... 28,500
92070-20097-060....................................... 28,500
92080-20047-048....................................... 28,500
------------------------------------------------------------------------

(2) For helicopters with a frame assembly with a P/N shown in
Table 1 to paragraph (e)(1), Table 2 to paragraph (e)(1), or Table 3
to paragraph (e)(2) of this AD: Within 24 clock-hours, and
thereafter before the first flight of each day or at intervals not
to exceed 24 clock-hours, whichever occurs later, using a 10X or
higher power magnifying glass, inspect the skin, straps, and
fasteners of the top deck for a crack and loose fasteners in two
locations from the STA 328 frame to the STA 305 frame between the
right butt line (BL) 16.5 beam and the left BL 16.5 beam, and from
the STA 362 frame to the STA 379 frame between the right BL 16.5
beam and the left BL 16.5 beam. If there is a loose fastener or a
crack:
(i) Repair or replace any cracked part and any loose fastener
before further flight.
(ii) Inspect the STA 328 frame and STA 362 frame between the
left and right BL16.5 beams and inspect the area on the left and
right BL 16.5 beams six inches on either side of the mounting pads
for a crack and loose fasteners. If there is a loose fastener or a
crack, repair or replace any cracked part and any loose fastener
before further flight.
(iii) Inspect the STA 328 and STA 362 outboard frames, left and
right sides, from the BL 16.5 beam to water line 252.25 for a crack
and loose fasteners. If there is a loose fastener or a crack, repair
or replace any cracked part and any loose fastener before further
flight.

Table 3 to Paragraph (e)(2)
------------------------------------------------------------------------
Aft STA 362 frame
Fwd STA 328 frame assembly P/N assembly P/N
------------------------------------------------------------------------
92209-02106-042..................................... 92070-20097-062
92209-02106-043..................................... 92080-20047-051
92070-20097-041..................................... 92209-02109-043
92080-20047-041..................................... 92209-02109-044
92070-20097-042
92080-20047-042
92070-20097-064
92080-20047-052
------------------------------------------------------------------------

(3) For each frame assembly listed in Table 1 to paragraph
(e)(1) or Table 4 to paragraph (e)(3) of this AD with 1,801 or more
hours TIS, and for each frame assembly listed in Table 2 to
paragraph (e)(1) or Table 3 to paragraph (e)(2) of this AD with
1,301 or more hours TIS, within 150 hours TIS and thereafter at
intervals not to exceed 150 hours TIS, perform the inspections in
paragraphs (e)(2)(ii) and (e)(2)(iii) of this AD.

Table 4 to Paragraph (e)(3)
------------------------------------------------------------------------
Aft STA 362 frame
Fwd STA 328 frame assembly P/N assembly P/N
------------------------------------------------------------------------
92209-02107-042..................................... 92070-02108-042
92209-02107-103..................................... 92080-02108-103
------------------------------------------------------------------------

(f) Alternative Methods of Compliance (AMOC)

(1) The Manager, Boston Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Kristopher Greer,
Aviation Safety Engineer, Engine & Propeller Directorate, 1200
District Avenue, Burlington, Massachusetts 01803; telephone (781)
238-7799; email Kristopher.Greer@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(g) Additional Information

Sikorsky S-92 Alert Service Bulletin (ASB) 92-53-008, Basic
Issue, dated June 13, 2012; ASB 92-53-009, Basic Issue, dated
December 6, 2012; ASB 92-53-012, Basic Issue, dated February 10,
2014, and Sikorsky Special Service Instructions No. 92-074-E,
Revision E, dated April 9, 2014, which are not incorporated by
reference, contain 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
sikorskywcs@sikorsky.com.
You may review a copy of information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, Texas 76177.

(h) Subject

Joint Aircraft Service Component (JASC) Code: 5311 Fuselage
Main, Frame.

Issued in Fort Worth, Texas, on July 7, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-16749 Filed 7-14-16; 8:45 am]
BILLING CODE 4910-13-P

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