80 FR 9985 - Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 37 (February 25, 2015)

Page Range		9985-9987
FR Document		2015-03703

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.

Federal Register, Volume 80 Issue 37 (Wednesday, February 25, 2015)

[Federal Register Volume 80, Number 37 (Wednesday, February 25, 2015)]
[Rules and Regulations]
[Pages 9985-9987]
From the Federal Register Online  [www.thefederalregister.org]
[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.

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

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 
[email protected]. 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 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for 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 [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) 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 
[email protected].
    (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

9985

Rules and Regulations Federal Register
Vol. 80, No. 37

Wednesday, February 25, 2015

This section of the FEDERAL REGISTER ADDRESSES: You may send comments by Comments Invited
contains regulatory documents having general any of the following methods:
applicability and legal effect, most of which This AD is a final rule that involves
are keyed to and codified in the Code of • Federal eRulemaking Docket: Go to requirements affecting flight safety, and
Federal Regulations, which is published under http://www.regulations.gov. Follow the we did not provide you with notice and
50 titles pursuant to 44 U.S.C. 1510. online instructions for sending your an opportunity to provide your
comments electronically. comments prior to it becoming effective.
The Code of Federal Regulations is sold by
• Fax: 202–493–2251. However, we invite you to participate in
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL • Mail: Send comments to the U.S. this rulemaking by submitting written
REGISTER issue of each week. Department of Transportation, Docket comments, data, or views. We also
Operations, M–30, West Building invite comments relating to the
Ground Floor, Room W12–140, 1200 economic, environmental, energy, or
DEPARTMENT OF TRANSPORTATION New Jersey Avenue SE., Washington, federalism impacts that resulted from
DC 20590–0001. adopting this AD. The most helpful
Federal Aviation Administration comments reference a specific portion of
• Hand Delivery: Deliver to the
the AD, explain the reason for any
14 CFR Part 39 ‘‘Mail’’ address between 9 a.m. and 5
recommended change, and include
p.m., Monday through Friday, except
supporting data. To ensure the docket
Federal holidays.
[Docket No. FAA–2015–0397; Directorate does not contain duplicate comments,
Identifier 2014–SW–048–AD; Amendment Examining the AD Docket commenters should send only one copy
39–18107; AD 2015–04–05] of written comments, or if comments are
You may examine the AD docket on filed electronically, commenters should
RIN 2120–AA64 the Internet at http:// submit them only one time. We will file
www.regulations.gov or in person at the in the docket all comments that we
Airworthiness Directives; Sikorsky Docket Operations Office between 9 receive, as well as a report summarizing
Aircraft Corporation (Sikorsky) a.m. and 5 p.m., Monday through each substantive public contact with
Helicopters Friday, except Federal holidays. The AD FAA personnel concerning this
AGENCY: Federal Aviation docket contains this AD, any rulemaking during the comment period.
Administration (FAA), DOT. incorporated by reference service We will consider all the comments we
information, the economic evaluation, receive and may conduct additional
ACTION: Final rule; request for
any comments received, and other rulemaking based on those comments.
comments. information. The street address for the
Docket Operations Office (telephone Discussion
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain 800–647–5527) is in the ADDRESSES
We are adopting a new AD for certain
Sikorsky Model S–76A, B, C, and D section. Comments will be available in
Sikorsky Model S–76A, B, C, and D
helicopters. This AD requires inspecting the AD docket shortly after receipt.
helicopters. This AD requires inspecting
the tail rotor drive shaft (TDS) flange-to- For service information identified in the TDS flange-to-shaft attachment
shaft attachment hardware for correct this AD, contact Sikorsky Aircraft hardware at four locations for correct
assembly and correct torque of the Corporation, Customer Service installation and correct torque of the
fasteners. If there is a discrepancy, this Engineering, 124 Quarry Road, fasteners. If there is movement,
AD requires, before further flight, Trumbull, CT 06611; telephone 1–800– misalignment of the torque stripe, a
applying an index mark to the flange Winged–S or 203–416–4299; email misassembled part, or torque of less
and TDS, inspecting the flange and shaft sikorskywcs@sikorsky.com. You may than 105 inch-pounds on any nut, this
for a crack, fracture, wear, and certain review the referenced service AD requires applying an index mark to
measurements, and replacing any part information at the FAA, Office of the the flange and shaft to make sure the
that does not meet the approved criteria Regional Counsel, Southwest Region, flange is reinstalled in the same position
before further flight. This AD is 2601 Meacham Blvd., Room 663, Fort to maintain shaft balance, and, before
prompted by a partial loss of tail rotor Worth, Texas 76137. It is also available further flight, inspecting the flange and
drive resulting in a forced landing. The on the Internet at http:// shaft for a crack, fracture, wear on the
actions specified by this AD are www.regulations.gov by searching for mounting hole, and diameter
intended to prevent failure at the flange- and locating Docket No. FAA–2015– measurements, and replacing the TDS if
to-shaft attachment, loss of a tail rotor 0397. the flange or stub does not meet the
drive, and subsequent loss of control of inspection criteria. This AD is prompted
the helicopter. FOR FURTHER INFORMATION CONTACT:
by a partial loss of tail rotor drive
Michael Schwetz, Aviation Safety
DATES: This AD becomes effective resulting in a forced landing, and
wreier-aviles on DSK5TPTVN1PROD with RULES

Engineer, Boston Aircraft Certification
March 12, 2015. instances where TDS flange-to-shaft
Office, Engine & Propeller Directorate,
The Director of the Federal Register attachment hardware was found to be
FAA, 12 New England Executive Park,
approved the incorporation by reference loose or fractured. The actions specified
Burlington, Massachusetts 01803;
of a certain document as of March 12, by this AD are intended to detect loose
telephone (781) 238–7761; email
2015. or fractured hardware and prevent
michael.schwetz@faa.gov.
We must receive comments on this failure of the TDS at the flange-to-shaft
AD by April 27, 2015. SUPPLEMENTARY INFORMATION: attachment, loss of a tail rotor drive, and

VerDate Sep<11>2014 15:08 Feb 24, 2015 Jkt 235001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\25FER1.SGM 25FER1

9986 Federal Register / Vol. 80, No. 37 / Wednesday, February 25, 2015 / Rules and Regulations

subsequent loss of control of the and shaft fail any of the inspection section, Congress charges the FAA with
helicopter. criteria. promoting safe flight of civil aircraft in
Æ Aligning index marks, installing the air commerce by prescribing regulations
FAA’s Determination flange on the shaft, and coating the grip for practices, methods, and procedures
We are issuing this AD because we length of each bolt and the contact the Administrator finds necessary for
evaluated all the relevant information surfaces on each radius washer and safety in air commerce. This regulation
and determined the unsafe condition washer with epoxy polyamide primer. is within the scope of that authority
described previously is likely to exist or Æ Torquing each nut. because it addresses an unsafe condition
develop in other products of these same that is likely to exist or develop on
type designs. Differences Between This AD and the
Service Information products identified in this rulemaking
Related Service Information Under 1 action.
The AD does not require returning the
CFR Part 51 unairworthy parts with certain forms to Regulatory Findings
Sikorsky issued Alert Service Bulletin the manufacturer as does the service We determined that this AD will not
ASB 76–66–52, Basic Issue, on April 1, information. have federalism implications under
2014, which specifies a one-time Executive Order 13132. This AD will
inspection of the TDS flange-to-shaft Costs of Compliance
not have a substantial direct effect on
attachment hardware for proper We estimate that this AD affects 260 the States, on the relationship between
installation and torque. If there is helicopters of U.S. Registry. We estimate the national Government and the States,
movement, torque stripe misalignment, that operators may incur the following or on the distribution of power and
or misassembled hardware, the ASB costs in order to comply with this AD. responsibilities among the various
specifies removing and returning the We estimate $85 per work-hour for levels of government.
hardware to Sikorsky with certain forms labor. We estimate 2.2 work-hours to
For the reasons discussed, I certify
and replacing hardware with airworthy inspect the hardware assembly and
that this AD:
TDS hardware before returning the torque at a cost of $187 per helicopter
helicopter to service. The ASB also and $48,620 for the fleet. We estimate 1. Is not a ‘‘significant regulatory
specifies either replacing the TDS or 2.2 work-hours if the hardware is action’’ under Executive Order 12866;
inspecting the flange and shaft for a replaced and $1,200 for the required 2. Is not a ‘‘significant rule’’ under
crack, fracture, wear of the mounting parts, for a total cost of $1,387 per DOT Regulatory Policies and Procedures
hole, and diameter and replacing any helicopter. (44 FR 11034, February 26, 1979);
part that does not meet the approved 3. Will not affect intrastate aviation in
FAA’s Justification and Determination Alaska to the extent that it justifies
criteria. The ASB states there were of the Effective Date
instances where the TDS flange-to-shaft making a regulatory distinction; and
attachment hardware was found loose or Providing an opportunity for public 4. Will not have a significant
fractured. This service information is comments before adopting these AD economic impact, positive or negative,
reasonably available; see ADDRESSES for requirements would delay on a substantial number of small entities
ways to access this service information. implementing the safety actions needed under the criteria of the Regulatory
to correct this known unsafe condition. Flexibility Act.
AD Requirements Therefore, we find that the risk to the We prepared an economic evaluation
This AD requires, within 30 days: flying public justifies waiving notice of the estimated costs to comply with
• Inspecting each TDS flange and comment before adopting this rule this AD and placed it in the AD docket.
attachment hardware at all four because the required corrective actions
locations for looseness and torque stripe must be done within 30 days, a very List of Subjects in 14 CFR Part 39
misalignment, inspecting each nut to short time period based on the average Air transportation, Aircraft, Aviation
determine whether it can be rotated by flight-hour utilization rate of these safety, Incorporation by reference,
hand, determining whether the helicopters used for commuter, air Safety.
hardware is assembled correctly, and ambulance, and offshore operations.
determining the torque of each nut. Since an unsafe condition exists that Adoption of the Amendment
• If there is no looseness, torque requires the immediate adoption of this Accordingly, under the authority
stripe misalignment, incorrect hardware AD, we determined that notice and delegated to me by the Administrator,
assembly, and if no nut can be rotated opportunity for public comment before the FAA amends 14 CFR part 39 as
by hand and the torque of any nut is not issuing this AD are impracticable and follows:
less than 105 inch-pounds, no further that good cause exists for making this
action is required by this AD. amendment effective in less than 30 PART 39—AIRWORTHINESS
• If there is looseness, torque stripe days. DIRECTIVES
misalignment, incorrect hardware
assembly, a nut rotated by hand, or the Authority for This Rulemaking
■ 1. The authority citation for part 39
torque of any nut is less than 105 inch- Title 49 of the United States Code continues to read as follows:
pounds: specifies the FAA’s authority to issue
Authority: 49 U.S.C. 106(g), 40113, 44701.
Æ Applying an index mark to the rules on aviation safety. Subtitle I,
flange and shaft, unbolting and section 106, describes the authority of § 39.13 [Amended]
wreier-aviles on DSK5TPTVN1PROD with RULES

removing the flange from the shaft, the FAA Administrator. ‘‘Subtitle VII:
visually inspecting each radius washer Aviation Programs,’’ describes in more ■ 2. The FAA amends § 39.13 by adding
for wear or fretting, and replacing any detail the scope of the Agency’s the following new airworthiness
washer with wear or fretting. authority. directive (AD):
Æ Inspecting the flange and shaft for We are issuing this rulemaking under 2015–04–05 Sikorsky Aircraft Corporation:
a crack, fracture, wear on the mounting the authority described in ‘‘Subtitle VII, Amendment 39–18107; Docket No.
hole, and diameter, and replacing the Part A, Subpart III, Section 44701: FAA–2015–0397; Directorate Identifier
TDS with an airworthy TDS if the flange General requirements.’’ Under that 2014–SW–048–AD.

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Federal Register / Vol. 80, No. 37 / Wednesday, February 25, 2015 / Rules and Regulations 9987

(a) Applicability (iv) Torque each nut by following either DEPARTMENT OF JUSTICE
This AD applies to Model S–76A, S–76B, paragraph D.(9) or D.(10) of the
S–76C, and S–76D helicopters, serial Accomplishment Instructions of the ASB. 28 CFR Part 0
numbers (S/N) up to and including 761050,
certificated in any category, with a tail drive (f) Alternative Methods of Compliance [AG Order No. 3495–2015]
shaft (TDS) part number (P/N) and S/N as (AMOCs)
follows: (1) The Manager, Boston Aircraft
Authorization To Seize Property
(a) P/N 76361–04004 (all dash numbers) Certification Office, FAA, may approve Involved in Drug Offenses for
with an S/N up to and including A127– AMOCs for this AD. Send your proposal to: Administrative Forfeiture (2012R–9P)
01092; or Michael Schwetz, Aviation Safety Engineer,
(b) P/N 76361–04604 (all dash numbers) AGENCY: Department of Justice.
Engine & Propeller Directorate, FAA, 12 New
with an S/N with a prefix A240 or B240, or ACTION: Final rule.
with an S/N C240–00001 through C240– England Executive Park, Burlington,
00880. Massachusetts 01803; telephone (781) 238– SUMMARY: The Department of Justice is
7761; email michael.schwetz@faa.gov. amending its regulations to delegate to
(b) Unsafe Condition (2) For operations conducted under a 14 the Director of the Bureau of Alcohol,
This AD defines the unsafe condition as CFR part 119 operating certificate or under Tobacco, Firearms, and Explosives
loose or fractured TDS flange-to-shaft 14 CFR part 91, subpart K, we suggest that
attachment hardware. This condition could (ATF) authority to seize and
you notify your principal inspector, or administratively forfeit property
result in loss of a tail rotor drive and
lacking a principal inspector, the manager of involved in controlled substance
subsequent loss of control of the helicopter.
the local flight standards district office or offenses.
(c) Effective Date certificate holding district office before
This AD becomes effective March 12, 2015. operating any aircraft complying with this DATES: This rule is effective February
AD through an AMOC. 25, 2015.
(d) Compliance
FOR FURTHER INFORMATION CONTACT:
You are responsible for performing each (g) Subject
Denise Brown, Enforcement Programs
action required by this AD within the Joint Aircraft Service Component (JASC) and Services, Bureau of Alcohol,
specified compliance time unless it has Code: 6510 Tail Rotor Drive Shaft.
already been accomplished prior to that time. Tobacco, Firearms, and Explosives, U.S.
(h) Material Incorporated by Reference Department of Justice, 99 New York
(e) Required Actions Avenue NE., Washington, DC 20226,
Within 30 hours time-in-service: (1) The Director of the Federal Register
telephone: (202) 648–7070.
(1) Inspect each TDS flange attachment approved the incorporation by reference
(IBR) of the service information listed in this SUPPLEMENTARY INFORMATION:
hardware at all four locations for looseness
and torque stripe misalignment as depicted paragraph under 5 U.S.C. 552(a) and 1 CFR Background
in Figure 1 and shown in Figure 2 of part 51.
Sikorsky Aircraft Corporation Alert Service (2) You must use this service information
After the Bureau of Alcohol, Tobacco,
Bulletin ASB 76–66–52, Basic Issue, dated as applicable to do the actions required by
Firearms, and Explosives (ATF) became
April 1, 2014 (ASB). Inspect each nut to this AD, unless the AD specifies otherwise. part of the Department of Justice (DOJ)
determine whether it can be rotated by hand.
(i) Sikorsky Aircraft Corporation Alert in January 2003, pursuant to the
Determine whether the hardware is Homeland Security Act of 2002 (Pub. L.
assembled correctly by following the Service Bulletin ASB 76–66–52, Basic issue,
dated April 1, 2014. 107–296), the Attorney General
Accomplishment Instructions, paragraph delegated to ATF the authority to
B.(3)(a) through B.(3)(b) of the ASB. (ii) Reserved.
Determine the torque of each nut. (3) For Sikorsky Aircraft Corporation investigate, seize, and forfeit property
(2) If there is no looseness, torque stripe service information identified in this AD, involved in a violation or attempted
misalignment, incorrect hardware assembly, contact Sikorsky Aircraft Corporation, violation within its investigative
and if no nut can be rotated by hand and the Customer Service Engineering, 124 Quarry jurisdiction. See 28 CFR 0.130(b)(1).
torque of any nut is not less than 105 inch- Road, Trumbull, CT 06611; telephone 1–800– ATF investigations focusing on violent
pounds, no further action is required by this Winged–S or 203–416–4299; email crime frequently involve complex
AD. criminal organizations with multiple
sikorskywcs@sikorsky.com.
(3) If there is looseness, torque stripe criminal enterprises and uncover drug-
misalignment, incorrect hardware assembly, (4) You may view this service information
a nut rotated by hand, or the torque of any at FAA, Office of the Regional Counsel, related offenses in addition to offenses
nut is less than 105 inch-pounds, do the Southwest Region, 2601 Meacham Blvd., within ATF’s primary jurisdiction, such
following: Room 663, Fort Worth, Texas 76137. For as violations of the Gun Control Act, 18
(i) Apply an index mark to the flange and information on the availability of this U.S.C. Chapter 44, the National
shaft to make sure the flange is reinstalled in material at the FAA, call (817) 222–5110. Firearms Act, 26 U.S.C. Chapter 53, or
the same position and to maintain shaft (5) You may view this service information the Contraband Cigarette Trafficking
balance, unbolt and remove the flange from that is incorporated by reference at the Act, 18 U.S.C. Chapter 114. In such
the shaft, and visually inspect each radius National Archives and Records investigations, ATF historically did not
washer for wear or fretting. Replace any
washer with wear or fretting.
Administration (NARA). For information on have authority under 21 U.S.C. Chapter
(ii) Inspect the flange and shaft for a crack, the availability of this material at NARA, call 13 to seize for administrative forfeiture
fracture, wear on the mounting hole, and (202) 741–6030, or go to: http:// property involved in controlled
diameter by following the Accomplishment www.archives.gov/federal-register/cfr/ibr- substance offenses. Instead, ATF
Instructions, paragraph 3.D.(5)(a) through locations.html. generally referred such property to the
3.D.(5)(e), of the ASB. If the flange and shaft Drug Enforcement Administration
wreier-aviles on DSK5TPTVN1PROD with RULES

Issued in Fort Worth, Texas, on February
fail any of the inspection criteria, before (DEA), which is primarily responsible
9, 2015.
further flight, replace the TDS with an for investigating violations of drug laws
airworthy TDS. Bruce E. Cain,
(iii) Align index marks, install the flange
contained in title 21 of the United States
Acting Directorate Manager, Rotorcraft Code. DEA would then initiate, process,
on the shaft, and coat the grip length of each Directorate, Aircraft Certification Service.
bolt and the contact surfaces on each radius and conclude all necessary
[FR Doc. 2015–03703 Filed 2–24–15; 8:45 am] administrative forfeiture actions for the
washer and washer with epoxy polyamide
primer. BILLING CODE 4910–13–P controlled substance-related property.

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Document Created: 2015-12-18 13:09:35
Document Modified: 2015-12-18 13:09:35

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule; request for comments.
Dates		This AD becomes effective March 12, 2015.
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 [email protected]
FR Citation		80 FR 9985
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 9985 - Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 37 (February 25, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration