Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters, 25748-25750 [2017-11128]
Download as PDF
25748
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
For the reasons discussed above, 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; 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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Bombardier, Inc.: Docket No. FAA–2017–
0528; Directorate Identifier 2017–NM–
028–AD.
(a) Comments Due Date
We must receive comments by July 20,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model CL–600–2B16 (CL–604 Variant)
airplanes, certificated in any category, serial
numbers 5301 through 5665 inclusive; 5701
through 5988 inclusive; and 6050 through
6080 inclusive.
nlaroche on DSK30NT082PROD with PROPOSALS
(d) Subject
Air Transport Association (ATA) of
America Code 34, Navigation.
(e) Reason
This AD was prompted by reports of inservice incidents regarding the loss of all air
data system information provided to the
flightcrew. We are issuing this AD to provide
the flightcrew with procedures for
‘‘Unreliable Airspeed’’ that stabilize the
airplane’s airspeed and attitude for continued
safe flight and landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
(g) Revision of the Airplane Flight Manual
(AFM)
Within 30 days after the effective date of
this AD: Revise the Emergency Procedures
section of the AFM to include the
information in Unreliable Airspeed, of
Section 03–15, Instruments System, of
Chapter 3, Emergency Procedures, of the
applicable AFM specified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD. These revisions
incorporate a procedure for ‘‘Unreliable
Airspeed.’’ Thereafter, operate the airplane
according to the limitation and procedure in
the applicable revision.
(1) For airplanes having serial numbers
5301 through 5665 inclusive: Bombardier
Challenger 604 AFM, PSP 604–1, Revision
103, dated November 28, 2016.
(2) For airplanes having serial numbers
5701 through 5988 inclusive (Marketing
Designation—Challenger 605): Bombardier
Challenger 605 AFM, PSP 605–1, Revision
41, dated November 28, 2016.
(3) For airplanes having serial numbers
6050 through 6080 inclusive (Marketing
Designation—Challenger 650): Bombardier
Challenger 650 AFM, PSP 650–1, Revision 6,
dated November 28, 2016.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the manager of the New York
ACO, send it to: ATTN: the Program
Manager, Continuing Operational Safety,
New York ACO, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. Before
using any approved AMOC, notify your
appropriate principal inspector, or lacking a
principal inspector, the manager of the local
flight standards district office/certificate
holding district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2017–01, dated
January 6, 2017, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0528.
(2) For more information about this AD,
contact Assata Dessaline, Aerospace
Engineer, Avionics and Services Branch,
ANE–172, FAA, New York Aircraft
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7301; fax 516–794–5531.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone: 514–855–5000; fax: 514–
855–7401; email: thd.crj@
aero.bombardier.com; Internet: https://
www.bombardier.com. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on May 23,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–11256 Filed 6–2–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0491; Directorate
Identifier 2016–SW–020–AD]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky)
Model S–76A, S–76B, S–76C, and S–
76D helicopters. This proposed AD
would require inspecting the main rotor
(M/R) servo pushrod (pushrod)
assembly and applying slippage marks.
This proposed AD is prompted by an
accident of a Sikorsky Model S–76C
helicopter caused by a failed pushrod
assembly. The proposed actions are
intended to prevent an unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by August 4, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
SUMMARY:
E:\FR\FM\05JNP1.SGM
05JNP1
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0491; 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 rule, contact Sikorsky
Aircraft Corporation, Customer Service
Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email:
wcs_cust_service_eng.gr-sik@lmco.com.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT:
Blaine Williams, Aerospace Engineer,
Boston Aircraft Certification Office,
Engine & Propeller Directorate, 1200
District Avenue, Burlington,
Massachusetts 01803; telephone (781)
238–7161; email
blaine.williams@faa.gov.
SUPPLEMENTARY INFORMATION:
nlaroche on DSK30NT082PROD with PROPOSALS
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
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
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.
Discussion
We propose to adopt a new AD for
Sikorsky Model S–76A, S–76B, S–76C,
and S–76D helicopters with a serial
number up to and including 761075 and
with an M/R pushrod assembly part
number (P/N) 76400–00034–059,
76400–00014–074, 76400–00014–076,
or 76400–00014–077 installed. This
proposed AD would not affect the
requirements of AD 2015–19–51, which
was issued as an emergency AD on
September 14, 2015, and published in
the Federal Register on October 26,
2015 (80 FR 65128). AD 2015–19–51
applies to Sikorsky Model S–76A, S–
76B, S–76C, and S–76D helicopters with
M/R pushrod assembly P/N 76400–
00034–059 or tail rotor pushrod
assembly P/N 76400–00014–071. AD
2015–19–51 requires inspecting the
pushrod assemblies and jamnuts, and
applying slippage marks across the
pushrod tubes and jamnuts. This new
proposed AD would apply to M/R
pushrod assembly P/N 76400–00034–
059 as well as M/R pushrod assemblies
that are installed farther away from the
servo actuators. Further flight testing
has revealed additional data regarding
the vibration environment of these M/R
pushrod assemblies making it necessary
to inspect the pushrod assemblies and
jamnuts and apply torque to the
jamnuts.
This proposed AD would require
inspecting the M/R forward, aft, and
lateral pushrod assembly control rods
and jamnuts, applying torque to the
jamnuts, and applying slippage marks
across the control rods and jamnuts.
This proposed AD is prompted by an
accident of a Sikorsky Model S–76C
helicopter caused by a loose jamnut and
subsequent failure of the pushrod
assembly. Separation of the control rod
and the rod end was found. The
proposed actions are intended to detect
a loose jamnut and prevent failure of the
pushrod assembly, loss of M/R flight
control, 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
these same type designs.
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
25749
Related Service Information
We reviewed Sikorksy S–76
Helicopter Alert Service Bulletin 76–
67–58, Basic Issue, dated November 19,
2015 (ASB), which specifies a one-time
inspection of the M/R forward, aft, and
lateral pushrod assemblies and jamnuts
for proper installation, condition, and
security. If a pushrod or jamnut does not
meet criteria specified in the
inspections, the ASB specifies replacing
the assembly. The ASB also specifies
applying torque to each jamnut and
applying two slippage marks across
each control rod and jamnut.
Proposed AD Requirements
This proposed AD would require,
within 300 hours time-in-service,
inspecting each pushrod assembly by
inspecting the position of the rod end in
the control rod. If the lockwire passes
through the inspection hole, this
proposed AD would require replacing
the pushrod assembly. If the lockwire
does not pass through the inspection
hole, this proposed AD would require
inspecting the jamnut to determine
seating position against the control rod
and whether the jamnut can be turned
with finger pressure. If the jamnut is not
seated against the control rod or is
loose, this proposed AD would require
replacing the pushrod assembly. If the
jamnut is seated against the control rod
and cannot be turned with finger
pressure, this proposed AD would
require applying 140 inch-pounds of
torque to the jamnut while using a
pushrod tool. This proposed AD would
also require, both for those pushrod
assemblies that are replaced and for
those that pass the inspections, applying
two slippage marks across each control
rod and jamnut.
Differences Between This Proposed AD
and the Service Information
The Sikorsky ASB specifies returning
any removed M/R pushrod assembly to
Sikorsky. This proposed AD does not
require returning any parts to Sikorsky.
Costs of Compliance
We estimate that this proposed AD
would affect 198 helicopters of U.S.
Registry.
We estimate that operators may incur
the following costs in order to comply
with this AD. Labor costs are estimated
at $85 per work-hour. Inspecting the M/
R pushrod assemblies would take about
2.2 work-hours for an estimated cost of
$187 per helicopter and $37,026 for the
U.S. fleet. Replacing an M/R pushrod
assembly would take about 2 workhours for a labor cost of $170. Parts to
replace M/R pushrod assembly P/N
76400–00034–059 would cost about
E:\FR\FM\05JNP1.SGM
05JNP1
25750
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
$2,411 for a total estimated replacement
cost of $2,581.
Parts to replace M/R pushrod
assembly P/N 76400–00014–074 would
cost about $2,224 for a total estimated
replacement cost of $2,394. Parts to
replace M/R pushrod assembly P/N
76400–00014–076 would cost about
$2,488 for a total estimated replacement
cost of $2,658. Parts to replace M/R
pushrod assembly P/N 76400–00014–
077 would cost about $2,414 for a total
estimated replacement cost of $2,584. It
takes a minimal amount of time to apply
the slippage marks for a negligible cost.
nlaroche on DSK30NT082PROD with PROPOSALS
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 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
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Sikorsky Aircraft Corporation: Docket No.
FAA–2017–0491; Directorate Identifier
2016–SW–020–AD.
(a) Applicability
This AD applies to Model S–76A, S–76B,
S–76C, and S–76D helicopters, serial
numbers up to and including 761075, with a
main rotor (M/R) servo pushrod (pushrod)
assembly part number (P/N) 76400–00034–
059, 76400–00014–074, 76400–00014–076, or
76400–00014–077 installed, certificated in
any category.
Note 1 to paragraph (a) of this AD: M/R
pushrod P/N 76400–00034–059 is included
in the Applicability section of AD 2015–19–
51, Amendment 39–18300 (80 FR 65128,
October 26, 2015). This AD does not affect
AD 2015–19–51.
(b) Unsafe Condition
This AD defines the unsafe condition as a
loose jamnut. This condition could result in
failure of a pushrod assembly, loss of M/R
flight control, and subsequent loss of control
of the helicopter.
(c) Comments Due Date
We must receive comments by August 4,
2017.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 300 hours time-in-service:
(1) Inspect the control rod of each pushrod
assembly (control rod) to determine whether
0.020 inch diameter lockwire can pass
through the inspection hole.
(i) If the lockwire passes through the
inspection hole, before further flight, replace
the pushrod assembly.
(ii) If the lockwire does not pass through
the inspection hole, inspect the jamnut to
determine whether it is seated against the
PO 00000
Frm 00009
Fmt 4702
Sfmt 9990
control rod and whether it can be turned
with finger pressure.
(A) If the jamnut is not seated against the
control rod or can be turned with finger
pressure, before further flight, replace the
pushrod assembly.
(B) If the jamnut is seated against the
control rod and cannot be turned with finger
pressure, using a pushrod tool, apply 140
inch-pounds of torque to the jamnut.
(2) Apply two slippage marks across each
control rod and jamnut as follows:
(i) Clean the area where a slippage mark is
to be applied.
(ii) Apply two slippage marks across the
control rod and jamnut, parallel and on
opposite sides of each other. Each slippage
mark must extend at least 0.5 inch onto the
control rod and must not cover the
inspection hole. Figure 1 (Sheet 2) of
Sikorsky S–76 Helicopter Alert Service
Bulletin 76–67–58, Basic Issue, dated
November 19, 2015, illustrates a slippage
mark across a control rod and jamnut.
(f) Alternative Methods of Compliance
(AMOC)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Blaine Williams, Aerospace Engineer, Boston
Aircraft Certification Office, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, Massachusetts 01803; telephone
(781) 238–7161; email
blaine.williams@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
Sikorksy S–76 Helicopter Alert Service
Bulletin 76–67–58, Basic Issue, dated
November 19, 2015, which is not
incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Sikorsky Aircraft
Corporation, Customer Service Engineering,
124 Quarry Road, Trumbull, CT 06611;
telephone 1–800–Winged–S or 203–416–
4299; email: wcs_cust_service_eng.grsik@lmco.com. You may review a copy of
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6700, Rotorcraft Flight Control.
Issued in Fort Worth, Texas, on May 17,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2017–11128 Filed 6–2–17; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\05JNP1.SGM
05JNP1
Agencies
[Federal Register Volume 82, Number 106 (Monday, June 5, 2017)]
[Proposed Rules]
[Pages 25748-25750]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11128]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0491; Directorate Identifier 2016-SW-020-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-76A, S-76B, S-76C, and
S-76D helicopters. This proposed AD would require inspecting the main
rotor (M/R) servo pushrod (pushrod) assembly and applying slippage
marks. This proposed AD is prompted by an accident of a Sikorsky Model
S-76C helicopter caused by a failed pushrod assembly. The proposed
actions are intended to prevent an unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 4, 2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
[[Page 25749]]
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0491; 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 rule, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299;
email: wcs_cust_service_eng.gr-sik@lmco.com. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort
Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer,
Boston Aircraft Certification Office, Engine & Propeller Directorate,
1200 District Avenue, Burlington, Massachusetts 01803; telephone (781)
238-7161; email blaine.williams@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
We propose to adopt a new AD for Sikorsky Model S-76A, S-76B, S-
76C, and S-76D helicopters with a serial number up to and including
761075 and with an M/R pushrod assembly part number (P/N) 76400-00034-
059, 76400-00014-074, 76400-00014-076, or 76400-00014-077 installed.
This proposed AD would not affect the requirements of AD 2015-19-51,
which was issued as an emergency AD on September 14, 2015, and
published in the Federal Register on October 26, 2015 (80 FR 65128). AD
2015-19-51 applies to Sikorsky Model S-76A, S-76B, S-76C, and S-76D
helicopters with M/R pushrod assembly P/N 76400-00034-059 or tail rotor
pushrod assembly P/N 76400-00014-071. AD 2015-19-51 requires inspecting
the pushrod assemblies and jamnuts, and applying slippage marks across
the pushrod tubes and jamnuts. This new proposed AD would apply to M/R
pushrod assembly P/N 76400-00034-059 as well as M/R pushrod assemblies
that are installed farther away from the servo actuators. Further
flight testing has revealed additional data regarding the vibration
environment of these M/R pushrod assemblies making it necessary to
inspect the pushrod assemblies and jamnuts and apply torque to the
jamnuts.
This proposed AD would require inspecting the M/R forward, aft, and
lateral pushrod assembly control rods and jamnuts, applying torque to
the jamnuts, and applying slippage marks across the control rods and
jamnuts. This proposed AD is prompted by an accident of a Sikorsky
Model S-76C helicopter caused by a loose jamnut and subsequent failure
of the pushrod assembly. Separation of the control rod and the rod end
was found. The proposed actions are intended to detect a loose jamnut
and prevent failure of the pushrod assembly, loss of M/R flight
control, 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 these same type
designs.
Related Service Information
We reviewed Sikorksy S-76 Helicopter Alert Service Bulletin 76-67-
58, Basic Issue, dated November 19, 2015 (ASB), which specifies a one-
time inspection of the M/R forward, aft, and lateral pushrod assemblies
and jamnuts for proper installation, condition, and security. If a
pushrod or jamnut does not meet criteria specified in the inspections,
the ASB specifies replacing the assembly. The ASB also specifies
applying torque to each jamnut and applying two slippage marks across
each control rod and jamnut.
Proposed AD Requirements
This proposed AD would require, within 300 hours time-in-service,
inspecting each pushrod assembly by inspecting the position of the rod
end in the control rod. If the lockwire passes through the inspection
hole, this proposed AD would require replacing the pushrod assembly. If
the lockwire does not pass through the inspection hole, this proposed
AD would require inspecting the jamnut to determine seating position
against the control rod and whether the jamnut can be turned with
finger pressure. If the jamnut is not seated against the control rod or
is loose, this proposed AD would require replacing the pushrod
assembly. If the jamnut is seated against the control rod and cannot be
turned with finger pressure, this proposed AD would require applying
140 inch-pounds of torque to the jamnut while using a pushrod tool.
This proposed AD would also require, both for those pushrod assemblies
that are replaced and for those that pass the inspections, applying two
slippage marks across each control rod and jamnut.
Differences Between This Proposed AD and the Service Information
The Sikorsky ASB specifies returning any removed M/R pushrod
assembly to Sikorsky. This proposed AD does not require returning any
parts to Sikorsky.
Costs of Compliance
We estimate that this proposed AD would affect 198 helicopters of
U.S. Registry.
We estimate that operators may incur the following costs in order
to comply with this AD. Labor costs are estimated at $85 per work-hour.
Inspecting the M/R pushrod assemblies would take about 2.2 work-hours
for an estimated cost of $187 per helicopter and $37,026 for the U.S.
fleet. Replacing an M/R pushrod assembly would take about 2 work-hours
for a labor cost of $170. Parts to replace M/R pushrod assembly P/N
76400-00034-059 would cost about
[[Page 25750]]
$2,411 for a total estimated replacement cost of $2,581.
Parts to replace M/R pushrod assembly P/N 76400-00014-074 would
cost about $2,224 for a total estimated replacement cost of $2,394.
Parts to replace M/R pushrod assembly P/N 76400-00014-076 would cost
about $2,488 for a total estimated replacement cost of $2,658. Parts to
replace M/R pushrod assembly P/N 76400-00014-077 would cost about
$2,414 for a total estimated replacement cost of $2,584. It takes a
minimal amount of time to apply the slippage marks for a negligible
cost.
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 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-2017-0491; Directorate
Identifier 2016-SW-020-AD.
(a) Applicability
This AD applies to Model S-76A, S-76B, S-76C, and S-76D
helicopters, serial numbers up to and including 761075, with a main
rotor (M/R) servo pushrod (pushrod) assembly part number (P/N)
76400-00034-059, 76400-00014-074, 76400-00014-076, or 76400-00014-
077 installed, certificated in any category.
Note 1 to paragraph (a) of this AD: M/R pushrod P/N 76400-00034-
059 is included in the Applicability section of AD 2015-19-51,
Amendment 39-18300 (80 FR 65128, October 26, 2015). This AD does not
affect AD 2015-19-51.
(b) Unsafe Condition
This AD defines the unsafe condition as a loose jamnut. This
condition could result in failure of a pushrod assembly, loss of M/R
flight control, and subsequent loss of control of the helicopter.
(c) Comments Due Date
We must receive comments by August 4, 2017.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
Within 300 hours time-in-service:
(1) Inspect the control rod of each pushrod assembly (control
rod) to determine whether 0.020 inch diameter lockwire can pass
through the inspection hole.
(i) If the lockwire passes through the inspection hole, before
further flight, replace the pushrod assembly.
(ii) If the lockwire does not pass through the inspection hole,
inspect the jamnut to determine whether it is seated against the
control rod and whether it can be turned with finger pressure.
(A) If the jamnut is not seated against the control rod or can
be turned with finger pressure, before further flight, replace the
pushrod assembly.
(B) If the jamnut is seated against the control rod and cannot
be turned with finger pressure, using a pushrod tool, apply 140
inch-pounds of torque to the jamnut.
(2) Apply two slippage marks across each control rod and jamnut
as follows:
(i) Clean the area where a slippage mark is to be applied.
(ii) Apply two slippage marks across the control rod and jamnut,
parallel and on opposite sides of each other. Each slippage mark
must extend at least 0.5 inch onto the control rod and must not
cover the inspection hole. Figure 1 (Sheet 2) of Sikorsky S-76
Helicopter Alert Service Bulletin 76-67-58, Basic Issue, dated
November 19, 2015, illustrates a slippage mark across a control rod
and jamnut.
(f) Alternative Methods of Compliance (AMOC)
(1) The Manager, Boston Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Blaine Williams,
Aerospace Engineer, Boston Aircraft Certification Office, Engine &
Propeller Directorate, 1200 District Avenue, Burlington,
Massachusetts 01803; telephone (781) 238-7161; email
blaine.williams@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
Sikorksy S-76 Helicopter Alert Service Bulletin 76-67-58, Basic
Issue, dated November 19, 2015, which is not incorporated by
reference, contains additional information about the subject of this
AD. For service information identified in this AD, contact Sikorsky
Aircraft Corporation, Customer Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email:
wcs_cust_service_eng.gr-sik@lmco.com. You may review a copy of
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft
Flight Control.
Issued in Fort Worth, Texas, on May 17, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-11128 Filed 6-2-17; 8:45 am]
BILLING CODE 4910-13-P