Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters, 15120-15123 [2017-05967]
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15120
Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 / Rules and Regulations
(i) No Reporting Requirement
Although Airbus Service Bulletin A300–
53–6184, dated November 12, 2015, specifies
to submit certain information to the
manufacturer, and specifies that action as RC,
this AD does not include that requirement.
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(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149;
email dan.rodina@faa.gov. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (h) and (i) of this
AD: If any service information contains
procedures or tests that are identified as RC,
those procedures and tests must be done to
comply with this AD; any procedures or tests
that are not identified as RC are
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0057, dated March 18, 2016, 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–2016–9051.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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 this AD specifies otherwise.
(i) Airbus Service Bulletin A300–53–6184,
dated November 12, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) 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.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 8,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–05231 Filed 3–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9291; Directorate
Identifier 2016–SW–004–AD; Amendment
39–18840; AD 2017–07–02]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky)
Model 269D and Model 269D
Configuration A helicopters. This AD
requires reducing the life limit of and
inspecting certain drive shafts. This AD
is prompted by four incidents involving
failure of a drive shaft. The actions
specified by this AD are intended to
prevent the unsafe condition on these
products.
SUMMARY:
This AD becomes effective April
11, 2017.
DATES:
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We must receive comments on this
AD by May 26, 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.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9291; 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, 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 final 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:
Michael Schwetz, Aviation Safety
Engineer, Boston Aircraft Certification
Office, Engine & Propeller Directorate,
FAA, 1200 District Avenue, 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
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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
Sikorsky Model 269D and Model 269D
Configuration A helicopters with KAflex
drive shaft (engine side) part number (P/
N) SKCP2738–7 and KAflex drive shaft
(pulley side) P/N SKCP2738–5 installed.
This AD is prompted by four incidents
involving failure of the engine side
drive shaft. Three incidents experienced
loss of rotor drive resulting in forced
landings. The fourth incident resulted
in vibration during flight prompting an
immediate landing. A fractured engine
side drive shaft was evident in each
incident. Investigations revealed
compression of the rubber engine
mounts may lead to loss of alignment
between the lower pulley shaft and the
engine output shaft, resulting in fracture
of the engine side drive shaft.
Additionally, it has been discovered
that increased cyclic torsional loading
was inaccurately applied in previous
fatigue analysis, making it necessary to
reduce the life limit.
Accordingly, this AD requires
reducing the life limit of the engine side
drive shaft and pulley side drive shaft
to 6,000 hours time-in-service (TIS) for
Model 269D helicopters and 1,200 hours
TIS for Model 269D Configuration A
helicopters. If the drive shaft is
interchanged or has ever been
interchanged between the two model
configurations, this AD requires using
the lower life limit of 1,200 hours TIS.
This AD also requires performing
several inspections of the drive shaft
within 25 hours TIS and, depending on
the results of these inspections,
replacing both the engine side and
pulley side drive shafts.
The actions specified by this AD are
intended to prevent failure of the drive
shaft, loss of rotor drive, and subsequent
loss of control of the helicopter.
Additional inspections at longer
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intervals may also be necessary. We
plan to publish a notice of proposed
rulemaking to give the public an
opportunity to comment on those longterm requirements.
Record of Ex Parte Communication
In preparation of AD actions such as
notices of proposed rulemaking and
immediately adopted final rules, it is
the practice of the FAA to obtain
technical information and information
on the operational and economic impact
from design approval holders and
aircraft operators. We discussed certain
aspects of this AD by email and
telephone with Sikorsky. A copy of each
email contact and a discussion of each
telephone contact can be found in the
rulemaking docket. For information on
locating the docket, see ‘‘Examining the
AD Docket.’’
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 the same
type designs.
Related Service Information
We reviewed Appendix B to Sikorsky
S–330 Model 269D Helicopter Basic
Handbook of Maintenance Instructions
No. CSP–D–2, dated February 1, 1993,
and revised October 15, 2014; and
Appendix B to Sikorsky S–333 Model
269D Config. ‘‘A’’ Helicopter Basic
Handbook of Maintenance Instructions
No. CSP–D–9, dated July 20, 2001, and
revised October 15, 2014. This service
information specifies repetitive
inspection procedures, overhaul and
retirement schedules, and weight and
balance procedures. The Airworthiness
Limitations section, which is included
in this service information, contains the
life limits for drive shaft assembly P/Ns
SKCP2738–5 and SKCP2738–7.
We also reviewed Sikorsky 269D
Helicopter Alert Service Bulletin DB–
052, Basic Issue, dated January 16, 2014,
which distributes the service life
reduction information and implements a
new 1,200-hour overhaul inspection for
drive shaft assembly P/Ns SKCP2738–3,
SKCP2738–5, and SKCP2738–7.
AD Requirements
This AD requires, before further flight:
• Removing from service any engine
side drive shaft P/N SKCP2738–7 and
pulley side drive shaft P/N SKCP2738–
5 that has reached or exceeded its new
life limit as follows:
Æ 6,000 hours TIS for Model 269D
helicopters;
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Æ 1,200 hours TIS for Model 269D
Configuration A helicopters; and
Æ 1,200 hours TIS if the parts have
ever been interchanged between the two
model configurations.
This AD also requires, within 25
hours TIS:
• Inspecting the KAflex drive shaft
alignment.
• Inspecting the engine side and
pulley side drive shafts for a crack, any
corrosion or pitting, a nick, a dent, and
a scratch.
• Inspecting each bolted joint (joint)
for movement.
• Inspecting each joint for fretting
corrosion and each frame and mount
bolt torque stripe for movement.
• Inspecting each joint for fretting, for
a crack around both the bolt head and
washer side, and around the nut and
washer side, and each inside and
outside corner radii and radii edges on
both sides of each frame for a crack.
If the drive shaft fails any of the above
inspections, this AD requires replacing
both the engine side and pulley side
drive shafts before further flight.
Lastly, this AD requires within 25
hours TIS and thereafter at intervals not
to exceed 25 hours TIS:
• Inspecting the lower pulley to
engine alignment, and if there is any
interference with the rotation of the belt
drive alignment tool, adjusting the
engine elevation alignment before
further flight.
This AD also specifies installing
KAflex engine side coupling assembly
P/N SKCP2738–9 and KAflex pulley
side coupling assembly P/N SKCP2738–
101 as an optional terminating action for
the requirements of this AD.
Differences Between This AD and the
Service Information
The Sikorsky service information
specifies a drive shaft assembly service
life of 3,000 hours TIS with a 1,200 hour
overhaul inspection for Model 269D
Configuration A helicopters, while this
AD specifies a service life of 1,200 hours
TIS.
This AD specifies several inspections
with a compliance time of 25 hours TIS
that are currently recurring inspections
at 100-hour or 400-hour intervals in
Sikorsky’s service information.
The Sikorsky service information
specifies different inspection
procedures if there is spline engagement
interference or resistance while
inspecting the drive shaft alignment.
This AD specifies replacing both the
engine side and pulley side drive shafts
if there is any spline engagement
interference or resistance.
The Sikorsky service information
specifies inspecting the working
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fastener condition without any specific
succeeding action regarding the
inspection. This AD specifies replacing
both the engine side and pulley side
drive shafts if there is any joint
movement.
The Sikorsky service information
specifies returning the drive shaft
assembly to Sikorsky if there is fretting
dust or red metallic residue at a joint.
This AD specifies replacing both the
engine side and pulley side drive shafts
if there is any fretting corrosion.
Interim Action
We consider this AD interim action. If
final action is later identified, we might
consider further rulemaking then.
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Costs of Compliance
We estimate that this AD affects 18
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs to comply with this AD. Labor
costs are estimated at $85 per workhour. Removing the engine side and
pulley side drive shafts that have
reached the new life limit will take
about 4 work-hours for a cost of $340
per helicopter. Inspecting the drive shaft
alignment will take about 1 work-hour
for a cost of $85 per helicopter and
$1,530 for the U.S. fleet. Inspecting the
drive shafts for damage will take about
1 work-hour for an estimated cost of $85
per helicopter and $1,530 for the U.S.
fleet. Inspecting the joints will take
about 1 work-hour for an estimated cost
of $85 per helicopter and $1,530 for the
U.S. fleet. Replacing the engine side and
pulley side drive shafts, if required, will
take about 8 work-hours and parts will
cost about $20,000, for an estimated cost
of $20,680 per helicopter. Inspecting the
lower pulley to engine alignment will
take about 0.5 work-hour for an
estimated cost of $43 per helicopter and
$774 for the U.S. fleet per inspection
cycle. Adjusting the engine elevation
alignment will take about 0.5 work-hour
for an estimated cost of $43 per
helicopter.
FAA’s Justification and Determination
of the Effective Date
Providing an opportunity for public
comments prior to 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 prior to the adoption of
this rule because some of the required
corrective actions must be completed
before further flight.
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
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opportunity for public comment before
issuing this AD are impracticable and
contrary to the public interest 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,
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the FAA amends 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):
■
2017–07–02 Sikorsky Aircraft Corporation
(Sikorsky): Amendment 39–18840;
Docket No. FAA–2016–9291; Directorate
Identifier 2016–SW–004–AD.
(a) Applicability
This AD applies to Sikorsky Model 269D
and Model 269D Configuration A helicopters
with a KAflex engine side drive shaft part
number (P/N) SKCP2738–7 and KAflex
pulley side drive shaft P/N SKCP2738–5
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a drive shaft. This condition could
result in loss of rotor drive and subsequent
loss of control of the helicopter.
(c) Effective Date
This AD becomes effective April 11, 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
(1) Before further flight:
(i) For Model 269D helicopters, remove
from service any KAflex engine side drive
shaft P/N SKCP2738–7 and any KAflex
pulley side drive shaft P/N SKCP2738–5 that
has 6,000 or more hours time-in-service
(TIS). Thereafter, remove from service any
KAflex engine side drive shaft P/N
SKCP2738–7 and any KAflex pulley side
drive shaft P/N SKCP2738–5 before
accumulating 6,000 hours TIS.
(ii) For Model 269D Configuration A
helicopters, remove from service any KAflex
engine side drive shaft P/N SKCP2738–7 and
any KAflex pulley side drive shaft P/N
SKCP2738–5 that has 1,200 or more hours
TIS. Thereafter, remove from service any
KAflex engine side drive shaft P/N
SKCP2738–7 and any KAflex pulley side
drive shaft P/N SKCP2738–5 before
accumulating 1,200 hours TIS.
(iii) If interchanged between Model 269D
and Model 269D Configuration A helicopters,
remove from service any KAflex engine side
drive shaft P/N SKCP2738–7 and any KAflex
pulley side drive shaft P/N SKCP2738–5 that
has 1,200 or more hours TIS. Thereafter, if
interchanged between Model 269D and
Model 269D Configuration A helicopters,
remove from service any KAflex engine side
drive shaft P/N SKCP2738–7 and any KAflex
pulley side drive shaft P/N SKCP2738–5
before accumulating 1,200 hours TIS.
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(2) Within 25 hours TIS:
(i) Remove the drive shaft to adapter bolt
and inspect the drive shaft alignment. Engage
and disengage the splines a minimum of 3
times by sliding the engine power output
shaft in and out of the engine. Inspect the
alignment at each 90° interval by rotating the
lower pulley with the power shaft
disengaged. Determine whether the adapter
slides on and off the drive shaft splines
without spline engagement interference or
resistance along the entire length of
movement. If there is any spline engagement
interference or resistance, before further
flight, replace both the engine side and
pulley side drive shafts.
(ii) Inspect each drive shaft for a crack, any
corrosion or pitting, a nick, a dent, and a
scratch. If there is a crack, any corrosion or
pitting, a nick, a dent, or a scratch that
exceeds allowable limits, before further
flight, replace both the engine side and
pulley side drive shafts.
(iii) Remove the engine side drive shaft and
pulley side drive shaft and perform the
following:
(A) Inspect each flex frame (frame) bolted
joint (joint) for movement by hand. If there
is any movement, before further flight,
replace both the engine side and pulley side
drive shafts.
(B) Visually inspect each joint for fretting
corrosion (which might be indicated by
metallic particles) and each frame and mount
bolt torque stripe for movement. If there is
any fretting corrosion or torque stripe
movement, before further flight, replace both
the engine side and pulley side drive shafts.
(C) Using a 10x or higher power
magnifying glass, visually inspect each joint
for fretting and for a crack around the bolt
head and washer side, and around the nut
and washer side. Also inspect both sides of
each frame for a crack on the inside and
outside corner radii and radii edge (four). If
there is any fretting, a crack at any point over
the full circumference (360°) of the bolt head
and washer side or the nut and washer side,
or a crack in any of the corner radii edges,
before further flight, replace both the engine
side and pulley side drive shafts.
(iv) Using a belt drive alignment tool
269T3303–003, inspect the lower pulley to
engine alignment by engaging the tool on the
drive shaft and inserting in the lower pulley
bore. Rotate the tool 360° around the drive
shaft and inspect for interference. If there is
any interference with the rotation of the tool,
before further flight, adjust the engine
elevation alignment to eliminate the
interference.
(3) Thereafter, at intervals not to exceed 25
hours TIS, repeat the actions specified in
paragraph (e)(2)(iv) of this AD.
(4) As an optional terminating action to the
repetitive inspections in this AD, you may
install KAflex engine side drive shaft P/N
SKCP2738–9 and KAflex pulley side drive
shaft P/N SKCP2738–101.
(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,
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Boston Aircraft Certification Office, Engine &
Propeller Directorate, FAA, 1200 District
Avenue, 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) Additional Information
Sikorsky 269D Helicopter Alert Service
Bulletin DB–052, Basic Issue, dated January
16, 2014; Appendix B of Sikorsky S–330
Model 269D Helicopter Basic Handbook of
Maintenance Instructions, No. CSP–D–2,
dated February 1, 1993, and revised October
15, 2014; and Appendix B of Sikorsky S–330
Model 269D Config. ‘‘A’’ Helicopter Basic
Handbook of Maintenance Instructions, No.
CSP–D–9, dated July 20, 2001, and revised
October 15, 2014; which are not incorporated
by reference, contain additional information
about the subject of this AD. For service
information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer
Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email: wcs_
cust_service_eng.gr-sik@lmco.com. You may
review this service 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: 6310, Engine/Transmission Coupling.
Issued in Fort Worth, Texas, on March 20,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2017–05967 Filed 3–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8844; Directorate
Identifier 2016–NM–026–AD; Amendment
39–18833; AD 2017–06–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD was prompted by a
SUMMARY:
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15123
report indicating that the fire block in
the closets and video control stations,
and fire blocking tape in the floor panel
opening in the forward and aft main
passenger cabin, might be missing on
some airplanes. This AD requires
installing a fire block in the closets and
video control stations, as applicable,
and installing fire blocking tape in the
floor panel openings in the forward and
aft main passenger cabin. We are issuing
this AD to address the unsafe condition
on these products.
This AD is effective May 1, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 1, 2017.
DATES:
For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this referenced 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
8844.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
8844; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Susan L. Monroe, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6457;
fax: 425–917–6590; email:
susan.l.monroe@faa.gov.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\27MRR1.SGM
27MRR1
Agencies
[Federal Register Volume 82, Number 57 (Monday, March 27, 2017)]
[Rules and Regulations]
[Pages 15120-15123]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05967]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9291; Directorate Identifier 2016-SW-004-AD;
Amendment 39-18840; AD 2017-07-02]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D
Configuration A helicopters. This AD requires reducing the life limit
of and inspecting certain drive shafts. This AD is prompted by four
incidents involving failure of a drive shaft. The actions specified by
this AD are intended to prevent the unsafe condition on these products.
DATES: This AD becomes effective April 11, 2017.
We must receive comments on this AD by May 26, 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.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9291; 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, 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 final 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: Michael Schwetz, Aviation Safety
Engineer, Boston Aircraft Certification Office, Engine & Propeller
Directorate, FAA, 1200 District Avenue, 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
[[Page 15121]]
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 Sikorsky Model 269D and Model 269D
Configuration A helicopters with KAflex drive shaft (engine side) part
number (P/N) SKCP2738-7 and KAflex drive shaft (pulley side) P/N
SKCP2738-5 installed. This AD is prompted by four incidents involving
failure of the engine side drive shaft. Three incidents experienced
loss of rotor drive resulting in forced landings. The fourth incident
resulted in vibration during flight prompting an immediate landing. A
fractured engine side drive shaft was evident in each incident.
Investigations revealed compression of the rubber engine mounts may
lead to loss of alignment between the lower pulley shaft and the engine
output shaft, resulting in fracture of the engine side drive shaft.
Additionally, it has been discovered that increased cyclic torsional
loading was inaccurately applied in previous fatigue analysis, making
it necessary to reduce the life limit.
Accordingly, this AD requires reducing the life limit of the engine
side drive shaft and pulley side drive shaft to 6,000 hours time-in-
service (TIS) for Model 269D helicopters and 1,200 hours TIS for Model
269D Configuration A helicopters. If the drive shaft is interchanged or
has ever been interchanged between the two model configurations, this
AD requires using the lower life limit of 1,200 hours TIS. This AD also
requires performing several inspections of the drive shaft within 25
hours TIS and, depending on the results of these inspections, replacing
both the engine side and pulley side drive shafts.
The actions specified by this AD are intended to prevent failure of
the drive shaft, loss of rotor drive, and subsequent loss of control of
the helicopter. Additional inspections at longer intervals may also be
necessary. We plan to publish a notice of proposed rulemaking to give
the public an opportunity to comment on those long-term requirements.
Record of Ex Parte Communication
In preparation of AD actions such as notices of proposed rulemaking
and immediately adopted final rules, it is the practice of the FAA to
obtain technical information and information on the operational and
economic impact from design approval holders and aircraft operators. We
discussed certain aspects of this AD by email and telephone with
Sikorsky. A copy of each email contact and a discussion of each
telephone contact can be found in the rulemaking docket. For
information on locating the docket, see ``Examining the AD Docket.''
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 the same type designs.
Related Service Information
We reviewed Appendix B to Sikorsky S-330 Model 269D Helicopter
Basic Handbook of Maintenance Instructions No. CSP-D-2, dated February
1, 1993, and revised October 15, 2014; and Appendix B to Sikorsky S-333
Model 269D Config. ``A'' Helicopter Basic Handbook of Maintenance
Instructions No. CSP-D-9, dated July 20, 2001, and revised October 15,
2014. This service information specifies repetitive inspection
procedures, overhaul and retirement schedules, and weight and balance
procedures. The Airworthiness Limitations section, which is included in
this service information, contains the life limits for drive shaft
assembly P/Ns SKCP2738-5 and SKCP2738-7.
We also reviewed Sikorsky 269D Helicopter Alert Service Bulletin
DB-052, Basic Issue, dated January 16, 2014, which distributes the
service life reduction information and implements a new 1,200-hour
overhaul inspection for drive shaft assembly P/Ns SKCP2738-3, SKCP2738-
5, and SKCP2738-7.
AD Requirements
This AD requires, before further flight:
Removing from service any engine side drive shaft P/N
SKCP2738-7 and pulley side drive shaft P/N SKCP2738-5 that has reached
or exceeded its new life limit as follows:
[cir] 6,000 hours TIS for Model 269D helicopters;
[cir] 1,200 hours TIS for Model 269D Configuration A helicopters;
and
[cir] 1,200 hours TIS if the parts have ever been interchanged
between the two model configurations.
This AD also requires, within 25 hours TIS:
Inspecting the KAflex drive shaft alignment.
Inspecting the engine side and pulley side drive shafts
for a crack, any corrosion or pitting, a nick, a dent, and a scratch.
Inspecting each bolted joint (joint) for movement.
Inspecting each joint for fretting corrosion and each
frame and mount bolt torque stripe for movement.
Inspecting each joint for fretting, for a crack around
both the bolt head and washer side, and around the nut and washer side,
and each inside and outside corner radii and radii edges on both sides
of each frame for a crack.
If the drive shaft fails any of the above inspections, this AD
requires replacing both the engine side and pulley side drive shafts
before further flight.
Lastly, this AD requires within 25 hours TIS and thereafter at
intervals not to exceed 25 hours TIS:
Inspecting the lower pulley to engine alignment, and if
there is any interference with the rotation of the belt drive alignment
tool, adjusting the engine elevation alignment before further flight.
This AD also specifies installing KAflex engine side coupling
assembly P/N SKCP2738-9 and KAflex pulley side coupling assembly P/N
SKCP2738-101 as an optional terminating action for the requirements of
this AD.
Differences Between This AD and the Service Information
The Sikorsky service information specifies a drive shaft assembly
service life of 3,000 hours TIS with a 1,200 hour overhaul inspection
for Model 269D Configuration A helicopters, while this AD specifies a
service life of 1,200 hours TIS.
This AD specifies several inspections with a compliance time of 25
hours TIS that are currently recurring inspections at 100-hour or 400-
hour intervals in Sikorsky's service information.
The Sikorsky service information specifies different inspection
procedures if there is spline engagement interference or resistance
while inspecting the drive shaft alignment. This AD specifies replacing
both the engine side and pulley side drive shafts if there is any
spline engagement interference or resistance.
The Sikorsky service information specifies inspecting the working
[[Page 15122]]
fastener condition without any specific succeeding action regarding the
inspection. This AD specifies replacing both the engine side and pulley
side drive shafts if there is any joint movement.
The Sikorsky service information specifies returning the drive
shaft assembly to Sikorsky if there is fretting dust or red metallic
residue at a joint. This AD specifies replacing both the engine side
and pulley side drive shafts if there is any fretting corrosion.
Interim Action
We consider this AD interim action. If final action is later
identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this AD affects 18 helicopters of U.S. Registry.
We estimate that operators may incur the following costs to comply with
this AD. Labor costs are estimated at $85 per work-hour. Removing the
engine side and pulley side drive shafts that have reached the new life
limit will take about 4 work-hours for a cost of $340 per helicopter.
Inspecting the drive shaft alignment will take about 1 work-hour for a
cost of $85 per helicopter and $1,530 for the U.S. fleet. Inspecting
the drive shafts for damage will take about 1 work-hour for an
estimated cost of $85 per helicopter and $1,530 for the U.S. fleet.
Inspecting the joints will take about 1 work-hour for an estimated cost
of $85 per helicopter and $1,530 for the U.S. fleet. Replacing the
engine side and pulley side drive shafts, if required, will take about
8 work-hours and parts will cost about $20,000, for an estimated cost
of $20,680 per helicopter. Inspecting the lower pulley to engine
alignment will take about 0.5 work-hour for an estimated cost of $43
per helicopter and $774 for the U.S. fleet per inspection cycle.
Adjusting the engine elevation alignment will take about 0.5 work-hour
for an estimated cost of $43 per helicopter.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments prior to 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
prior to the adoption of this rule because some of the required
corrective actions must be completed before further flight.
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 contrary to
the public interest 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):
2017-07-02 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
18840; Docket No. FAA-2016-9291; Directorate Identifier 2016-SW-004-
AD.
(a) Applicability
This AD applies to Sikorsky Model 269D and Model 269D
Configuration A helicopters with a KAflex engine side drive shaft
part number (P/N) SKCP2738-7 and KAflex pulley side drive shaft P/N
SKCP2738-5 installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a drive
shaft. This condition could result in loss of rotor drive and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective April 11, 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
(1) Before further flight:
(i) For Model 269D helicopters, remove from service any KAflex
engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side
drive shaft P/N SKCP2738-5 that has 6,000 or more hours time-in-
service (TIS). Thereafter, remove from service any KAflex engine
side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive
shaft P/N SKCP2738-5 before accumulating 6,000 hours TIS.
(ii) For Model 269D Configuration A helicopters, remove from
service any KAflex engine side drive shaft P/N SKCP2738-7 and any
KAflex pulley side drive shaft P/N SKCP2738-5 that has 1,200 or more
hours TIS. Thereafter, remove from service any KAflex engine side
drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/
N SKCP2738-5 before accumulating 1,200 hours TIS.
(iii) If interchanged between Model 269D and Model 269D
Configuration A helicopters, remove from service any KAflex engine
side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive
shaft P/N SKCP2738-5 that has 1,200 or more hours TIS. Thereafter,
if interchanged between Model 269D and Model 269D Configuration A
helicopters, remove from service any KAflex engine side drive shaft
P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5
before accumulating 1,200 hours TIS.
[[Page 15123]]
(2) Within 25 hours TIS:
(i) Remove the drive shaft to adapter bolt and inspect the drive
shaft alignment. Engage and disengage the splines a minimum of 3
times by sliding the engine power output shaft in and out of the
engine. Inspect the alignment at each 90[deg] interval by rotating
the lower pulley with the power shaft disengaged. Determine whether
the adapter slides on and off the drive shaft splines without spline
engagement interference or resistance along the entire length of
movement. If there is any spline engagement interference or
resistance, before further flight, replace both the engine side and
pulley side drive shafts.
(ii) Inspect each drive shaft for a crack, any corrosion or
pitting, a nick, a dent, and a scratch. If there is a crack, any
corrosion or pitting, a nick, a dent, or a scratch that exceeds
allowable limits, before further flight, replace both the engine
side and pulley side drive shafts.
(iii) Remove the engine side drive shaft and pulley side drive
shaft and perform the following:
(A) Inspect each flex frame (frame) bolted joint (joint) for
movement by hand. If there is any movement, before further flight,
replace both the engine side and pulley side drive shafts.
(B) Visually inspect each joint for fretting corrosion (which
might be indicated by metallic particles) and each frame and mount
bolt torque stripe for movement. If there is any fretting corrosion
or torque stripe movement, before further flight, replace both the
engine side and pulley side drive shafts.
(C) Using a 10x or higher power magnifying glass, visually
inspect each joint for fretting and for a crack around the bolt head
and washer side, and around the nut and washer side. Also inspect
both sides of each frame for a crack on the inside and outside
corner radii and radii edge (four). If there is any fretting, a
crack at any point over the full circumference (360[deg]) of the
bolt head and washer side or the nut and washer side, or a crack in
any of the corner radii edges, before further flight, replace both
the engine side and pulley side drive shafts.
(iv) Using a belt drive alignment tool 269T3303-003, inspect the
lower pulley to engine alignment by engaging the tool on the drive
shaft and inserting in the lower pulley bore. Rotate the tool
360[deg] around the drive shaft and inspect for interference. If
there is any interference with the rotation of the tool, before
further flight, adjust the engine elevation alignment to eliminate
the interference.
(3) Thereafter, at intervals not to exceed 25 hours TIS, repeat
the actions specified in paragraph (e)(2)(iv) of this AD.
(4) As an optional terminating action to the repetitive
inspections in this AD, you may install KAflex engine side drive
shaft P/N SKCP2738-9 and KAflex pulley side drive shaft P/N
SKCP2738-101.
(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, Boston Aircraft Certification Office,
Engine & Propeller Directorate, FAA, 1200 District Avenue,
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) Additional Information
Sikorsky 269D Helicopter Alert Service Bulletin DB-052, Basic
Issue, dated January 16, 2014; Appendix B of Sikorsky S-330 Model
269D Helicopter Basic Handbook of Maintenance Instructions, No. CSP-
D-2, dated February 1, 1993, and revised October 15, 2014; and
Appendix B of Sikorsky S-330 Model 269D Config. ``A'' Helicopter
Basic Handbook of Maintenance Instructions, No. CSP-D-9, dated July
20, 2001, and revised October 15, 2014; which are not incorporated
by reference, contain additional information about the subject of
this AD. For service information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124
Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-
416-4299; email: wcs_cust_service_eng.gr-sik@lmco.com. You may
review this service 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: 6310, Engine/
Transmission Coupling.
Issued in Fort Worth, Texas, on March 20, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-05967 Filed 3-24-17; 8:45 am]
BILLING CODE 4910-13-P