81 FR 46002 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 136 (July 15, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 136 (July 15, 2016)
| Page Range | 46002-46004 | |
| FR Document | 2016-16749 |
[Federal Register Volume 81, Number 136 (Friday, July 15, 2016)] [Proposed Rules] [Pages 46002-46004] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16749] ----------------------------------------------------------------------- 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 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-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 [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, 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 [email protected]. 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. (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) ------------------------------------------------------------------------ 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 [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 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 [email protected]. 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
![46002 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules
within 15 engine flight cycles or at next shop Issued in Burlington, Massachusetts, on www.regulations.gov by searching for
visit, whichever occurs sooner. July 1, 2016. and locating Docket No. FAA–2016–
(E) If there is any cracking or material loss Ann C. Mollica, 8501; or in person at the Docket
found on seal support 23, replace the fairing Acting Manager, Engine & Propeller Operations Office between 9 a.m. and 5
within 15 engine flight cycles or at next shop Directorate, Aircraft Certification Service. p.m., Monday through Friday, except
visit, whichever occurs sooner.
(ii) If the visual inspection required by
[FR Doc. 2016–16646 Filed 7–14–16; 8:45 am] Federal holidays. The AD docket
paragraph (e)(3)(i) of this AD does not detect BILLING CODE 4910–13–P contains this proposed AD, the
any crack, fluorescent penetrant inspect zone economic evaluation, any comments
A. Refer to AMM TASK 70–20–02, Water received, and other information. The
Washable Fluorescent Penetrant Inspection DEPARTMENT OF TRANSPORTATION street address for the Docket Operations
(Maintenance Process 213), or OMat 632, Office (telephone 800–647–5527) is in
high sensitivity fluorescent penetrant Federal Aviation Administration the ADDRESSES section. Comments will
inspection, for guidance on fluorescent be available in the AD docket shortly
penetrant inspection. 14 CFR Part 39 after receipt.
(A) If a crack shorter than 6 mm is
[Docket No. FAA–2016–8501; Directorate For service information identified in
detected, repair or replace the fairing within
100 engine flight cycles, or at the next shop Identifier 2014–SW–042–AD] this proposed AD, contact Sikorsky
visit, whichever occurs sooner. RIN 2120–AA64
Aircraft Corporation, Customer Service
(B) If a crack longer than 6 mm is detected, Engineering, 124 Quarry Road,
repair or replace the fairing within 15 engine Airworthiness Directives; Sikorsky Trumbull, CT 06611; telephone 1–800-
flight cycles or at the next shop visit, Aircraft Corporation Helicopters Winged-S or 203–416–4299; email
whichever occurs sooner. sikorskywcs@sikorsky.com. You may
AGENCY: Federal Aviation review the referenced service
Definition
Administration (FAA), DOT. information at the FAA, Office of the
For the purpose of this AD, a ‘‘shop visit’’ ACTION: Notice of proposed rulemaking
is defined as induction of an engine into the Regional Counsel, Southwest Region,
(NPRM). 10101 Hillwood Pkwy., Room 6N–321,
shop for maintenance involving the
separation of pairs of major mating engine SUMMARY: We propose to adopt a new Fort Worth, Texas 76177.
flanges, except that the separation of engine airworthiness directive (AD) for FOR FURTHER INFORMATION CONTACT:
flanges solely for the purposes of Kristopher Greer, Aviation Safety
Sikorsky Aircraft Corporation (Sikorsky)
transportation without subsequent engine Engineer, Boston Aircraft Certification
maintenance does not constitute an engine Model S–92A helicopters. This
proposed AD would require inspecting Office, Engine & Propeller Directorate,
shop visit.
the main transmission forward (fwd) 1200 District Avenue, Burlington,
(f) Alternative Methods of Compliance and aft frame assembly and adjacent Massachusetts 01803; telephone (781)
(AMOCs) skins for a crack and loose fasteners and 238–7799; email Kristopher.Greer@
The Manager, Engine Certification Office, establishing life limits for certain frame faa.gov.
FAA, may approve AMOCs for this AD. Use assemblies. This proposed AD is SUPPLEMENTARY INFORMATION:
the procedures found in 14 CFR 39.19 to prompted by fatigue analysis indicating
make your request. You may email your Comments Invited
request to: ANE-AD-AMOC@faa.gov.
stress concentrations as well as the
discovery of a crack in the station (STA) We invite you to participate in this
(g) Related Information 362 frame and skin on a Model S–92A rulemaking by submitting written
(1) For more information about this AD, helicopter. The proposed actions are comments, data, or views. We also
contact Wego Wang, Aerospace Engineer, intended to detect a crack in a frame invite comments relating to the
Engine Certification Office, FAA, Engine & assembly and prevent failure of a frame economic, environmental, energy, or
Propeller Directorate, 1200 District Avenue, and subsequent loss of control of the federalism impacts that might result
Burlington, MA 01803; phone: 781–238– helicopter. from adopting the proposals in this
7134; fax: 781–238–7199; email: wego.wang@
faa.gov. DATES: We must receive comments on document. The most helpful comments
(2) Refer to MCAI European Aviation this proposed AD by September 13, reference a specific portion of the
Safety Agency AD 2016–0084, dated April 2016. proposal, explain the reason for any
28, 2016, for more information. You may recommended change, and include
ADDRESSES: You may send comments by
examine the MCAI in the AD docket on the supporting data. To ensure the docket
any of the following methods:
Internet at http://www.regulations.gov by does not contain duplicate comments,
searching for and locating it in Docket No. • Federal eRulemaking Docket: Go to
http://www.regulations.gov. Follow the commenters should send only one copy
FAA–2016–6692. of written comments, or if comments are
(3) RR NMSB RB.211–72–AJ165, dated online instructions for sending your
comments electronically. filed electronically, commenters should
March 31, 2016, can be obtained from RR,
using the contact information in paragraph • Fax: 202–493–2251. submit only one time.
(g)(4) of this proposed AD. • Mail: Send comments to the U.S. We will file in the docket all
(4) For service information identified in Department of Transportation, Docket comments that we receive, as well as a
this proposed AD, contact Rolls-Royce plc, Operations, M–30, West Building report summarizing each substantive
Corporate Communications, P.O. Box 31, Ground Floor, Room W12–140, 1200 public contact with FAA personnel
Derby, England, DE24 8BJ; phone: 011–44– concerning this proposed rulemaking.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
New Jersey Avenue SE., Washington,
1332–242424; fax: 011–44–1332–249936; DC 20590–0001. Before acting on this proposal, we will
email: http://www.rolls-royce.com/contact/
• Hand Delivery: Deliver to the consider all comments we receive on or
civil_team.jsp; Internet: https:// before the closing date for comments.
customers.rolls-royce.com/public/ ‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except We will consider comments filed after
rollsroycecare.
(5) You may view this service information Federal holidays. the comment period has closed if it is
at the FAA, Engine & Propeller Directorate, possible to do so without incurring
Examining the AD Docket expense or delay. We may change this
1200 District Avenue, Burlington, MA. For
information on the availability of this You may examine the AD docket on proposal in light of the comments we
material at the FAA, call 781–238–7125. the Internet at http:// receive.
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Discussion exceeded its new life limit. Frame Regulatory Findings
We propose to adopt a new AD for assemblies that are altered under We determined that this proposed AD
Sikorsky Model S–92A helicopters with Sikorsky’s service life extension would not have federalism implications
certain part-numbered frame assemblies program and re-identified with a new under Executive Order 13132. This
installed. This proposed AD is part number must be removed from proposed AD would not have a
prompted by a fatigue analysis that service upon accumulating the life limit substantial direct effect on the States, on
indicates stress concentrations may of the old part-number or within certain the relationship between the national
develop at the steel doublers on the hours TIS since the alteration, Government and the States, or on the
main transmission airframe support whichever occurs first. distribution of power and
structure top deck, adjacent to the This proposed AD would also require, responsibilities among the various
transmission feet. Additionally, a for helicopters with certain part- levels of government.
helicopter was discovered with a crack numbered frame assemblies, within 24 For the reasons discussed, I certify
in the STA 362 frame and skin. This clock-hours and thereafter before the this proposed regulation:
proposed AD would require inspecting first flight of each day or at intervals not 1. Is not a ‘‘significant regulatory
the main transmission fwd and aft frame to exceed 24 clock-hours, whichever action’’ under Executive Order 12866;
assemblies and adjacent skins for a occurs later, inspecting the top deck 2. Is not a ‘‘significant rule’’ under the
crack and loose fasteners and replacing skin, straps, and fasteners for a crack DOT Regulatory Policies and Procedures
or repairing any cracked part or loose and loose fasteners in two locations. If (44 FR 11034, February 26, 1979);
fastener. This proposed AD would also there is a loose fastener or a crack, this 3. Will not affect intrastate aviation in
require establishing life limits for proposed AD would require repairing or Alaska to the extent that it justifies
certain frame assemblies. The proposed making a regulatory distinction; and
replacing the cracked or loose part and
actions are intended to detect a crack in 4. Will not have a significant
performing additional inspections of the
the frame assemblies and to prevent economic impact, positive or negative,
STA 328 frame, STA 362 frame, and the
failure of the main transmission frame on a substantial number of small entities
butt line (BL) 16.5 beams.
assemblies and subsequent loss of under the criteria of the Regulatory
control of the helicopter. Finally, this proposed AD would Flexibility Act.
require repetitively inspecting the STA We prepared an economic evaluation
FAA’s Determination 328 frame, STA 362 frame, and the BL of the estimated costs to comply with
We are proposing this AD because we 16.5 beams once the frame assembly this proposed AD and placed it in the
evaluated all known relevant exceeds certain hours TIS. AD docket.
information and determined that an
unsafe condition exists and is likely to Differences Between This Proposed AD List of Subjects in 14 CFR Part 39
exist or develop on other helicopters of and the Service Information
Air transportation, Aircraft, Aviation
the same type design. safety, Incorporation by reference,
The service information requires
Related Service Information providing certain information to Safety.
Sikorsky issued S–92 Alert Service Sikorsky and this proposed AD would The Proposed Amendment
Bulletin (ASB) 92–53–008, Basic Issue, not. The service information specifies
performing a fluorescent penetrant Accordingly, under the authority
dated June 13, 2012 (ASB 92–53–008); delegated to me by the Administrator,
S–92 ASB 92–53–009, Basic Issue, dated inspection if there is a suspected crack
and contacting Sikorsky if there is a the FAA proposes to amend 14 CFR part
December 6, 2012 (ASB 92–53–009); 39 as follows:
and S–92 ASB 92–53–012, Basic Issue, crack, while this proposed AD would
dated February 10, 2014 (ASB 92–53– only require repairing or replacing any PART 39—AIRWORTHINESS
012). ASB 92–53–008 provides cracked part. Contacting Sikorsky would DIRECTIVES
procedures for a one-time inspection of not be required.
the main transmission frames and Costs of Compliance ■ 1. The authority citation for part 39
beams for a crack, missing or loose continues to read as follows:
fastener or collar, damage, deformation, We estimate that this proposed AD Authority: 49 U.S.C. 106(g), 40113, 44701.
and corrosion. ASB 92–53–009 specifies would affect 80 helicopters of U.S.
an inspection before the first flight of Registry. § 39.13 [Amended]
the day and a recurring 150-hour ■ 2. The FAA amends § 39.13 by adding
We estimate that operators may incur
inspection of the interior and exterior the following new airworthiness
surfaces of the upper flanges and beams. the following costs to comply with this
AD. Labor costs are estimated at $85 per directive (AD):
ASB 92–53–012 specifies altering the
fwd and aft transmission support frames work-hour. We estimate a minimal cost Sikorsky Aircraft Corporation: Docket No.
to establish and revise the life limit of FAA–2016–8501; Directorate Identifier
by replacing the fasteners in accordance 2014–SW–042–AD.
with Sikorsky Special Service the frame assembly. We estimate it
Instructions No. 92–074–E, Revision E, would take 1 work-hour to visually (a) Applicability
dated April 9, 2014. After this inspect the skin and 1 work-hour to This AD applies to Model S–92A
alteration, the parts are re-identified inspect STA 328 and 362 frames. No helicopters, certificated in any category, with
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
with a new part number. Sikorsky refers parts would be needed for a total cost a forward (fwd) station (STA) 328 or aft STA
to this alteration as a service life of $6,800 for the fleet for each 362 frame assembly with a part number
extension program modification. inspection per inspection cycle. If a (P/N) as shown in Table 1 to paragraph (e)(1),
fastener is replaced, we estimate the Table 2 to paragraph (e)(1), Table 3 to
Proposed AD Requirements cost to be minimal. If a frame is paragraph (e)(2), or Table 4 to paragraph
(e)(3) of this AD.
This proposed AD would establish a replaced, it would take 3,360 work-
life limit for certain part-numbered hours and a required parts cost of (b) Unsafe Condition
frame assemblies by removing from $296,000 for a total cost of $581,600 per This AD defines the unsafe condition as a
service any part that has reached or helicopter. crack in a main transmission airframe
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support structure. This condition could (e)(1), Table 2 to paragraph (e)(1), or Table 3 (2) For operations conducted under a 14
result in failure of a main transmission frame to paragraph (e)(2) of this AD: Within 24 CFR part 119 operating certificate or under
and subsequent loss of control of the clock-hours, and thereafter before the first 14 CFR part 91, subpart K, we suggest that
helicopter. flight of each day or at intervals not to exceed you notify your principal inspector, or
24 clock-hours, whichever occurs later, using lacking a principal inspector, the manager of
(c) Comments Due Date
a 10X or higher power magnifying glass, the local flight standards district office or
We must receive comments by September inspect the skin, straps, and fasteners of the certificate holding district office before
13, 2016. top deck for a crack and loose fasteners in operating any aircraft complying with this
(d) Compliance two locations from the STA 328 frame to the AD through an AMOC.
STA 305 frame between the right butt line
You are responsible for performing each (BL) 16.5 beam and the left BL 16.5 beam, (g) Additional Information
action required by this AD within the and from the STA 362 frame to the STA 379 Sikorsky S–92 Alert Service Bulletin (ASB)
specified compliance time unless it has frame between the right BL 16.5 beam and 92–53–008, Basic Issue, dated June 13, 2012;
already been accomplished prior to that time. the left BL 16.5 beam. If there is a loose ASB 92–53–009, Basic Issue, dated December
(e) Required Actions fastener or a crack: 6, 2012; ASB 92–53–012, Basic Issue, dated
(i) Repair or replace any cracked part and February 10, 2014, and Sikorsky Special
(1) For helicopters with a frame assembly
any loose fastener before further flight. Service Instructions No. 92–074–E, Revision
with a P/N shown in Table 1 to paragraph
(ii) Inspect the STA 328 frame and STA E, dated April 9, 2014, which are not
(e)(1) or Table 2 to paragraph (e)(1) of this
362 frame between the left and right BL16.5 incorporated by reference, contain additional
AD, before further flight, remove from service
beams and inspect the area on the left and information about the subject of this AD. For
any part that has reached or exceeded its new
life limit. Fwd STA 328 frame assemblies right BL 16.5 beams six inches on either side service information identified in this AD,
that are altered and changed to P/N 92070– of the mounting pads for a crack and loose contact Sikorsky Aircraft Corporation,
20124–064, 92070–20124–067, 92070– fasteners. If there is a loose fastener or a Customer Service Engineering, 124 Quarry
20127–045, 92070–20124–065, 92070– crack, repair or replace any cracked part and Road, Trumbull, CT 06611; telephone 1–800–
20124–047, or 92070–20127–046 must be any loose fastener before further flight. Winged–S or 203–416–4299; email
removed from service upon accumulating (iii) Inspect the STA 328 and STA 362 sikorskywcs@sikorsky.com.
12,000 hours TIS from the alteration or outboard frames, left and right sides, from the You may review a copy of information at
28,500 hours TIS total (regardless of P/N), BL 16.5 beam to water line 252.25 for a crack the FAA, Office of the Regional Counsel,
whichever occurs first. and loose fasteners. If there is a loose fastener Southwest Region, 10101 Hillwood Pkwy.,
or a crack, repair or replace any cracked part Room 6N–321, Fort Worth, Texas 76177.
and any loose fastener before further flight.
TABLE 1 TO PARAGRAPH (e)(1) (h) Subject
TABLE 3 TO PARAGRAPH (e)(2) Joint Aircraft Service Component (JASC)
Life limit hours Code: 5311 Fuselage Main, Frame.
TIS
Fwd STA 328 frame Aft STA 362 frame Issued in Fort Worth, Texas, on July 7,
Fwd STA 328 frame assem- assembly P/N assembly P/N 2016.
bly P/N: Scott A. Horn,
92070–20124–064 ............ 12,000 92209–02106–042 ........ 92070–20097–062
92209–02106–043 ........ 92080–20047–051 Acting Manager, Rotorcraft Directorate,
92070–20124–067 ............ 12,000
92070–20097–041 ........ 92209–02109–043 Aircraft Certification Service.
92070–20127–045 ............ 12,000
92070–20124–065 ............ 12,000 92080–20047–041 ........ 92209–02109–044 [FR Doc. 2016–16749 Filed 7–14–16; 8:45 am]
92070–20124–047 ............ 12,000 92070–20097–042 BILLING CODE 4910–13–P
92070–20127–046 ............ 12,000 92080–20047–042
92070–20124–063 ............ 12,000 92070–20097–064
92070–20124–066 ............ 12,000 92080–20047–052
92070–20127–041 ............ 12,000 DEPARTMENT OF THE TREASURY
Aft STA 362 frame assembly (3) For each frame assembly listed in Table
P/N: 1 to paragraph (e)(1) or Table 4 to paragraph Internal Revenue Service
92070–20124–041 ............ 10,400 (e)(3) of this AD with 1,801 or more hours
92070–20124–044 ............ 10,400 TIS, and for each frame assembly listed in 26 CFR Part 1
92070–20127–042 ............ 10,400 Table 2 to paragraph (e)(1) or Table 3 to
92070–20124–042 ............ 10,400 paragraph (e)(2) of this AD with 1,301 or [REG–134016–15]
92070–20124–045 ............ 10,400 more hours TIS, within 150 hours TIS and
92070–20127–049 ............ 10,400 thereafter at intervals not to exceed 150 hours RIN 1545–BN47
92070–20124–043 ............ 10,400 TIS, perform the inspections in paragraphs
92070–20124–046 ............ 10,400 (e)(2)(ii) and (e)(2)(iii) of this AD. Guidance Under Section 355
92070–20127–050 ............ 10,400 Concerning Device and Active Trade or
92070–20141–050 ............ 17,000 TABLE 4 TO PARAGRAPH (e)(3)
92070–20141–051 ............ 17,000
Business
92070–20141–052 ............ 17,000 Fwd STA 328 frame Aft STA 362 frame AGENCY: Internal Revenue Service (IRS),
assembly P/N assembly P/N Treasury.
TABLE 2 TO PARAGRAPH (e)(1) ACTION: Notice of proposed rulemaking.
92209–02107–042 ........ 92070–02108–042
92209–02107–103 ........ 92080–02108–103
Life limit hours SUMMARY: This document contains
TIS proposed regulations under section 355
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(f) Alternative Methods of Compliance
(AMOC)
of the Internal Revenue Code (Code).
Fwd STA 328 frame assem- The proposed regulations would clarify
bly P/N: (1) The Manager, Boston Aircraft the application of the device prohibition
92070–20097–058 ............ 28,500 Certification Office, FAA, may approve
92080–20047–047 ............ 28,500 AMOCs for this AD. Send your proposal to:
and the active business requirement of
92070–20097–060 ............ 28,500 Kristopher Greer, Aviation Safety Engineer, section 355. The proposed regulations
92080–20047–048 ............ 28,500 Engine & Propeller Directorate, 1200 District would affect corporations that distribute
Avenue, Burlington, Massachusetts 01803; the stock of controlled corporations,
(2) For helicopters with a frame assembly telephone (781) 238–7799; email their shareholders, and their security
with a P/N shown in Table 1 to paragraph Kristopher.Greer@faa.gov. holders.
VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 E:\FR\FM\15JYP1.SGM 15JYP1](https://thefederalregister.org/doc/81_FR_46138/page/3.svg)
Document Created: 2016-07-15 02:53:06
Document Modified: 2016-07-15 02:53:06
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 13, 2016. | |
| Contact | Kristopher Greer, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7799; email [email protected] | |
| FR Citation | 81 FR 46002 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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