Document ID: FAA-2015-0397-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Sikorsky Aircraft Corporation (Sikorsky) Helicopters
Posted Date: 2015-02-25T05:00Z

[Federal Register Volume 80, Number 37 (Wednesday, February 25, 2015)]
[Rules and Regulations]
[Pages 9985-9987]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-03703]

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  Federal Register / Vol. 80, No. 37 / Wednesday, February 25, 2015 / 
Rules and Regulations  

[[Page 9985]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0397; Directorate Identifier 2014-SW-048-AD; 
Amendment 39-18107; AD 2015-04-05]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft Corporation 
(Sikorsky) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Sikorsky Model S-76A, B, C, and D helicopters. This AD requires 
inspecting the tail rotor drive shaft (TDS) flange-to-shaft attachment 
hardware for correct assembly and correct torque of the fasteners. If 
there is a discrepancy, this AD requires, before further flight, 
applying an index mark to the flange and TDS, inspecting the flange and 
shaft for a crack, fracture, wear, and certain measurements, and 
replacing any part that does not meet the approved criteria before 
further flight. This AD is prompted by a partial loss of tail rotor 
drive resulting in a forced landing. The actions specified by this AD 
are intended to prevent failure at the flange-to-shaft attachment, loss 
of a tail rotor drive, and subsequent loss of control of the 
helicopter.

DATES: This AD becomes effective March 12, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document as of March 12, 2015.
    We must receive comments on this AD by April 27, 2015.

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 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 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, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is 
also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0397.

FOR FURTHER INFORMATION CONTACT: Michael Schwetz, Aviation Safety 
Engineer, Boston Aircraft Certification Office, Engine & Propeller 
Directorate, FAA, 12 New England Executive Park, Burlington, 
Massachusetts 01803; telephone (781) 238-7761; email 
michael.schwetz@faa.gov.

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 certain Sikorsky Model S-76A, B, C, 
and D helicopters. This AD requires inspecting the TDS flange-to-shaft 
attachment hardware at four locations for correct installation and 
correct torque of the fasteners. If there is movement, misalignment of 
the torque stripe, a misassembled part, or torque of less than 105 
inch-pounds on any nut, this AD requires applying an index mark to the 
flange and shaft to make sure the flange is reinstalled in the same 
position to maintain shaft balance, and, before further flight, 
inspecting the flange and shaft for a crack, fracture, wear on the 
mounting hole, and diameter measurements, and replacing the TDS if the 
flange or stub does not meet the inspection criteria. This AD is 
prompted by a partial loss of tail rotor drive resulting in a forced 
landing, and instances where TDS flange-to-shaft attachment hardware 
was found to be loose or fractured. The actions specified by this AD 
are intended to detect loose or fractured hardware and prevent failure 
of the TDS at the flange-to-shaft attachment, loss of a tail rotor 
drive, and

[[Page 9986]]

subsequent 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 these same type 
designs.

Related Service Information Under 1 CFR Part 51

    Sikorsky issued Alert Service Bulletin ASB 76-66-52, Basic Issue, 
on April 1, 2014, which specifies a one-time inspection of the TDS 
flange-to-shaft attachment hardware for proper installation and torque. 
If there is movement, torque stripe misalignment, or misassembled 
hardware, the ASB specifies removing and returning the hardware to 
Sikorsky with certain forms and replacing hardware with airworthy TDS 
hardware before returning the helicopter to service. The ASB also 
specifies either replacing the TDS or inspecting the flange and shaft 
for a crack, fracture, wear of the mounting hole, and diameter and 
replacing any part that does not meet the approved criteria. The ASB 
states there were instances where the TDS flange-to-shaft attachment 
hardware was found loose or fractured. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

AD Requirements

    This AD requires, within 30 days:
     Inspecting each TDS flange attachment hardware at all four 
locations for looseness and torque stripe misalignment, inspecting each 
nut to determine whether it can be rotated by hand, determining whether 
the hardware is assembled correctly, and determining the torque of each 
nut.
     If there is no looseness, torque stripe misalignment, 
incorrect hardware assembly, and if no nut can be rotated by hand and 
the torque of any nut is not less than 105 inch-pounds, no further 
action is required by this AD.
     If there is looseness, torque stripe misalignment, 
incorrect hardware assembly, a nut rotated by hand, or the torque of 
any nut is less than 105 inch-pounds:
    [cir] Applying an index mark to the flange and shaft, unbolting and 
removing the flange from the shaft, visually inspecting each radius 
washer for wear or fretting, and replacing any washer with wear or 
fretting.
    [cir] Inspecting the flange and shaft for a crack, fracture, wear 
on the mounting hole, and diameter, and replacing the TDS with an 
airworthy TDS if the flange and shaft fail any of the inspection 
criteria.
    [cir] Aligning index marks, installing the flange on the shaft, and 
coating the grip length of each bolt and the contact surfaces on each 
radius washer and washer with epoxy polyamide primer.
    [cir] Torquing each nut.

Differences Between This AD and the Service Information

    The AD does not require returning the unairworthy parts with 
certain forms to the manufacturer as does the service information.

Costs of Compliance

    We estimate that this AD affects 260 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. We estimate $85 per work-hour for labor. We 
estimate 2.2 work-hours to inspect the hardware assembly and torque at 
a cost of $187 per helicopter and $48,620 for the fleet. We estimate 
2.2 work-hours if the hardware is replaced and $1,200 for the required 
parts, for a total cost of $1,387 per helicopter.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before 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 before 
adopting this rule because the required corrective actions must be done 
within 30 days, a very short time period based on the average flight-
hour utilization rate of these helicopters used for commuter, air 
ambulance, and offshore operations.
    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.

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):

2015-04-05 Sikorsky Aircraft Corporation: Amendment 39-18107; Docket 
No. FAA-2015-0397; Directorate Identifier 2014-SW-048-AD.

[[Page 9987]]

(a) Applicability

    This AD applies to Model S-76A, S-76B, S-76C, and S-76D 
helicopters, serial numbers (S/N) up to and including 761050, 
certificated in any category, with a tail drive shaft (TDS) part 
number (P/N) and S/N as follows:
    (a) P/N 76361-04004 (all dash numbers) with an S/N up to and 
including A127-01092; or
    (b) P/N 76361-04604 (all dash numbers) with an S/N with a prefix 
A240 or B240, or with an S/N C240-00001 through C240-00880.

(b) Unsafe Condition

    This AD defines the unsafe condition as loose or fractured TDS 
flange-to-shaft attachment hardware. This condition could result in 
loss of a tail rotor drive and subsequent loss of control of the 
helicopter.

(c) Effective Date

    This AD becomes effective March 12, 2015.

(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

    Within 30 hours time-in-service:
    (1) Inspect each TDS flange attachment hardware at all four 
locations for looseness and torque stripe misalignment as depicted 
in Figure 1 and shown in Figure 2 of Sikorsky Aircraft Corporation 
Alert Service Bulletin ASB 76-66-52, Basic Issue, dated April 1, 
2014 (ASB). Inspect each nut to determine whether it can be rotated 
by hand. Determine whether the hardware is assembled correctly by 
following the Accomplishment Instructions, paragraph B.(3)(a) 
through B.(3)(b) of the ASB. Determine the torque of each nut.
    (2) If there is no looseness, torque stripe misalignment, 
incorrect hardware assembly, and if no nut can be rotated by hand 
and the torque of any nut is not less than 105 inch-pounds, no 
further action is required by this AD.
    (3) If there is looseness, torque stripe misalignment, incorrect 
hardware assembly, a nut rotated by hand, or the torque of any nut 
is less than 105 inch-pounds, do the following:
    (i) Apply an index mark to the flange and shaft to make sure the 
flange is reinstalled in the same position and to maintain shaft 
balance, unbolt and remove the flange from the shaft, and visually 
inspect each radius washer for wear or fretting. Replace any washer 
with wear or fretting.
    (ii) Inspect the flange and shaft for a crack, fracture, wear on 
the mounting hole, and diameter by following the Accomplishment 
Instructions, paragraph 3.D.(5)(a) through 3.D.(5)(e), of the ASB. 
If the flange and shaft fail any of the inspection criteria, before 
further flight, replace the TDS with an airworthy TDS.
    (iii) Align index marks, install the flange on the shaft, and 
coat the grip length of each bolt and the contact surfaces on each 
radius washer and washer with epoxy polyamide primer.
    (iv) Torque each nut by following either paragraph D.(9) or 
D.(10) of the Accomplishment Instructions of the ASB.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Schwetz, 
Aviation Safety Engineer, Engine & Propeller Directorate, FAA, 12 
New England Executive Park, Burlington, Massachusetts 01803; 
telephone (781) 238-7761; email michael.schwetz@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) Subject

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

(h) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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) Sikorsky Aircraft Corporation Alert Service Bulletin ASB 76-
66-52, Basic issue, dated April 1, 2014.
    (ii) Reserved.
    (3) For Sikorsky Aircraft Corporation 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. 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 February 9, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-03703 Filed 2-24-15; 8:45 am]
BILLING CODE 4910-13-P