Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters, 53171-53174 [2018-22414]
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Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations
location must be less than 1,018 in-lb
(115 Nm).
iv. The upper-neck resultant shear
force at the O.C. location must be less
than 186 lb (825 N).
g. Occupant (ES–2re ATD) retention:
The pelvic restraint must remain on the
ES–2re ATD’s pelvis during the impact
and rebound phases of the test. The
upper-torso restraint straps (if present)
must remain on the ATD’s shoulder
during the impact.
h. Occupant (ES–2re ATD) support:
i. Pelvis excursion: The load-bearing
portion of the bottom of the ATD pelvis
must not translate beyond the edges of
its seat’s bottom seat-cushion
supporting structure.
ii. Upper-torso support: The lateral
flexion of the ATD torso must not
exceed 40 degrees from the normal
upright position during the impact.
5. For seats with an airbag system in
the shoulder belts, show that the airbag
system in the shoulder belt will deploy
and provide protection under crash
conditions where it is necessary to
prevent serious injury. The means of
protection must take into consideration
a range of stature from a 2-year-old child
to a 95th percentile male. The airbag
system in the shoulder belt must
provide a consistent approach to energy
absorption throughout that range of
occupants. When the seat system
includes an airbag system, that system
must be included in each of the
certification tests as it would be
installed in the airplane. In addition, the
following situations must be considered:
a. The seat occupant is holding an
infant.
b. The seat occupant is a pregnant
woman.
6. The airbag system in the shoulder
belt must provide adequate protection
for each occupant regardless of the
number of occupants of the seat
assembly, considering that unoccupied
seats may have an active airbag system
in the shoulder belt.
7. The design must prevent the airbag
system in the shoulder belt from being
either incorrectly buckled or incorrectly
installed, such that the airbag system in
the shoulder belt would not properly
deploy. Alternatively, it must be shown
that such deployment is not hazardous
to the occupant, and will provide the
required injury protection.
8. It must be shown that the airbag
system in the shoulder belt is not
susceptible to inadvertent deployment
as a result of wear and tear, or inertial
loads resulting from in-flight or ground
maneuvers (including gusts and hard
landings), and other operating and
environmental conditions (vibrations,
moisture, etc.) likely to occur in service.
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9. Deployment of the airbag system in
the shoulder belt must not introduce
injury mechanisms to the seated
occupant, or result in injuries that could
impede rapid egress. This assessment
should include an occupant whose belt
is loosely fastened.
10. It must be shown that inadvertent
deployment of the airbag system in the
shoulder belt, during the most critical
part of the flight, will either meet the
requirement of § 25.1309(b) or not cause
a hazard to the airplane or its occupants.
11. It must be shown that the airbag
system in the shoulder belt will not
impede rapid egress of occupants 10
seconds after airbag deployment.
12. The airbag system must be
protected from lightning and highintensity radiated fields (HIRF). The
threats to the airplane specified in
existing regulations regarding lightning,
§ 25.1316, and HIRF, § 25.1317, are
incorporated by reference for the
purpose of measuring lightning and
HIRF protection.
13. The airbag system in the shoulder
belt must function properly after loss of
normal aircraft electrical power, and
after a transverse separation of the
fuselage at the most critical location. A
separation at the location of the airbag
system in the shoulder belt does not
have to be considered.
14. It must be shown that the airbag
system in the shoulder belt will not
release hazardous quantities of gas or
particulate matter into the cabin.
15. The airbag system in the shoulderbelt installation must be protected from
the effects of fire such that no hazard to
occupants will result.
16. A means must be available for a
crewmember to verify the integrity of
the airbag system in the shoulder-belt
activation system prior to each flight, or
it must be demonstrated to reliably
operate between inspection intervals.
The FAA considers that the loss of the
airbag-system deployment function
alone (i.e., independent of the
conditional event that requires airbag
deployment) is a major-failure
condition.
17. The inflatable material may not
have an average burn rate of greater than
2.5 inches/minute when tested using the
horizontal flammability test defined in
part 25, appendix F, part I, paragraph
(b)(5).
18. The airbag system in the shoulder
belt, once deployed, must not adversely
affect the emergency-lighting system
(i.e., block floor proximity lights to the
extent that the lights no longer meet
their intended function).
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53171
Issued in Des Moines, Washington, on
October 10, 2018.
Victor Wicklund,
Manager, Transport Standards Branch, Policy
and Innovation Division, Aircraft
Certification Service.
[FR Doc. 2018–22929 Filed 10–19–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0834; Product
Identifier 2018–SW–058–AD; Amendment
39–19421; AD 2018–16–51]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Limited
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are publishing a new
airworthiness directive (AD) for Bell
Helicopter Textron Canada Limited
(Bell) Model 429 helicopters. This AD
was sent previously to all known U.S.
owners and operators of these
helicopters as Emergency AD 2018–16–
51, dated July 26, 2018, which
superseded Emergency AD 2018–15–51,
dated July 20, 2018. This AD requires
inspecting the tail rotor (T/R) gearbox
installation, inspecting the T/R gearbox
retaining hardware and support
attachment point areas, and replacing
each nut. This AD is prompted by two
reports of T/R gearbox assemblies
loosely attached to the gearbox support.
The actions of this AD are intended to
address an unsafe condition on these
products.
SUMMARY:
This AD becomes effective
November 6, 2018 to all persons except
those persons to whom it was made
immediately effective by Emergency AD
2018–16–51, issued on July 26, 2018,
which contains the requirements of this
AD.
We must receive comments on this
AD by December 21, 2018.
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
DATES:
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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.
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.
Examining the AD Docket
Discussion
Transport Canada, which is the
aviation authority for Canada, issued
Emergency AD No. CF–2018–18, dated
July 11, 2018, to correct an unsafe
condition for Bell Model 429
helicopters. Transport Canada advises of
two reports of T/R gearbox assemblies
loosely attached to the gearbox support.
According to Transport Canada, this
condition could lead to structural
damage and possible loss of control of
the helicopter.
As a result, on July 20, 2018, we
issued Emergency AD 2018–15–51
(Emergency AD 2018–15–51), which
required inspecting the T/R gearbox
installation for looseness, visually
inspecting the T/R gearbox retaining
hardware and support attachment point
areas, and torque inspecting the gearbox
retaining nuts. Depending on the
inspection results, Emergency AD 2018–
15–51 required replacing or repairing
the affected parts in accordance with
FAA-approved procedures. Emergency
AD 2018–15–51 was sent previously to
all known U.S. owners and operators of
these helicopters. The actions in
Emergency AD 2018–15–51 were
intended to prevent detachment of the
T/R gearbox, loss of T/R control, and
loss of control of the helicopter.
After we issued Emergency AD 2018–
15–51, we discovered an error in the
replacement nut P/N. The required
replacement nut P/N is NAS9926–6L;
not NAS9926–5L as incorrectly stated in
Emergency AD 2018–15–51. Therefore,
on July 26, 2018, we issued Emergency
AD 2018–16–51 to supersede
Emergency AD 2018–15–51 to correct
the nut P/N. Emergency AD 2018–16–51
otherwise retains all of the requirements
of Emergency AD 2018–15–51.
Emergency AD 2018–16–51 was also
sent previously to all known U.S.
owners and operators of these
helicopters.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0834; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
Transport Canada AD, the economic
evaluation, any comments received, and
other information. The street address for
Docket Operations (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 Bell Helicopter
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4;
telephone (450) 437–2862 or (800) 363–
8023; fax (450) 433–0272; or at https://
www.bellcustomer.com/files/. 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: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
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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
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FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, Transport
Canada, its technical representative, has
notified us of the unsafe condition
described in the Transport Canada AD.
We are issuing this AD because we
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evaluated all information provided by
Transport Canada and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type design.
Related Service Information
We reviewed Bell Alert Service
Bulletin 429–18–40, dated July 6, 2018,
which specifies a one-time inspection of
the T/R gearbox installation and a onetime visual and torque inspection of the
six installation attachment points. This
service information also specifies
contacting Bell Product Support
Engineering with the results of the T/R
gearbox installation inspection, any
findings of the visual inspection, and
the results of the torque inspection.
AD Requirements
This AD requires inspecting the T/R
gearbox installation for looseness,
visually inspecting the T/R gearbox
retaining hardware and each support
attachment point area, and torque
inspecting each gearbox retaining nut.
Depending on the inspection results,
this AD requires replacing or repairing
the affected parts in accordance with
FAA-approved procedures.
Differences Between This AD and the
Transport Canada AD
The Transport Canada AD applies to
helicopters with specific serial numbers,
whereas this AD applies to all Model
429 helicopters. The Transport Canada
AD includes a calendar based
compliance time, whereas this AD does
not. The Transport Canada AD requires
reporting certain information to Bell
Product Support Engineering and this
AD does not. If there is looseness, this
AD requires performing the visual
inspection and torque inspection before
further flight, while the Transport
Canada AD requires contacting Bell.
Lastly, if the torque of a T/R gearbox
retaining nut is below 160 in-lbs (19
Nm), this AD requires removing the
T/R gearbox and inspecting the
mounting surfaces and retaining
hardware, while the Transport Canada
AD requires contacting Bell.
Interim Action
We consider this AD to be an interim
action. If final action is later identified,
we might consider further rulemaking
then.
Costs of Compliance
We estimate that this AD affects 90
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 $85.00 per
work-hour.
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Inspecting the T/R gearbox
installation takes about 0.25 work-hour
for an estimated cost of $21 per
helicopter and $1,890 for the U.S. fleet.
Inspecting the T/R gearbox retaining
hardware and the support attachment
points takes about 0.5 work-hour for an
estimated cost of $43 per helicopter and
$3,870 for the U.S. fleet. Replacing the
nuts takes about 1 work-hour and parts
cost about $20 for an estimated cost of
$105 per helicopter and $9,450 for the
U.S. fleet.
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FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
required the immediate adoption of
Emergency AD 2018–16–51, issued on
July 26, 2018, to all known U.S. owners
and operators of these helicopters. The
FAA found that the risk to the flying
public justified waiving notice and
comment prior to adoption of this rule
because there are required actions that
must be completed before further flight
and within 5 hours time-in-service.
These conditions still exist and the AD
is hereby published in the Federal
Register as an amendment to section
39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it
effective to all persons. Therefore, we
find good cause that notice and
opportunity for prior public comment
are impracticable. In addition, for the
reasons stated above, we find 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
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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
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):
■
2018–16–51 Bell Helicopter Textron
Canada Limited: Amendment 39–19421;
Docket No. FAA–2018–0834; Product
Identifier 2018–SW–058–AD.
(a) Applicability
This AD applies to Model 429 helicopters,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
loose tail rotor (T/R) gearbox support
attachment point. This condition could result
in detachment of the T/R gearbox, loss of
T/R control, and loss of control of the
helicopter.
(c) Related ADs
This AD requires the same actions as
Emergency AD 2018–16–51, dated July 26,
2018, which superseded Emergency AD
2018–15–51, dated July 20, 2018.
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53173
(d) Effective Date
This AD becomes effective November 6,
2018 to all persons except those persons to
whom it was made immediately effective by
Emergency AD 2018–16–51, issued on July
26, 2018, which contains the requirements of
this AD.
(e) 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.
(f) Required Actions
(1) Before further flight, inspect for
looseness of the T/R gearbox installation to
the T/R gearbox structural support by moving
the T/R gearbox output shaft in an upward
and downward direction. If the T/R gearbox
installation is loose, before further flight,
complete the actions required by paragraphs
(f)(2)(i) and (ii) of this AD.
(2) Within 5 hours time-in-service, unless
already completed as required by paragraph
(f)(1) of this AD:
(i) Visually inspect the T/R gearbox
retaining hardware and each support
attachment point area for evidence of fretting,
a crack, and incorrect installation. If there is
any evidence of fretting, a crack, or incorrect
installation, before further flight, repair in
accordance with FAA-approved procedures.
(ii) Inspect each T/R gearbox retaining nut
by applying 160 in-lbs (19 Nm) of torque. If
the torque of a T/R gearbox retaining nut is
below 160 in-lbs (19 Nm), before further
flight:
(A) Remove the T/R gearbox and inspect
each stud for proper staking, each stud thread
for uniformity, each mounting surface for
evidence of fretting and cracking, and each
mounting hole for elongation. If a stud is not
properly staked, a stud thread is not uniform,
a mounting surface has evidence of fretting
or cracking, or a mount hole is elongated,
before further flight, replace the affected
parts or repair in accordance with FAAapproved procedures.
(B) Replace each nut with nut part number
NAS9926–6L and apply a torque of 160 inlbs.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@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.
(h) Additional Information
(1) Bell Alert Service Bulletin 429–18–40,
dated July 6, 2018, which is not incorporated
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by reference, contains additional information
about the subject of this AD. For service
information identified in this AD, contact
Bell Helicopter Textron Canada Limited,
12,800 Rue de l’Avenir, Mirabel, Quebec
J7J1R4; telephone (450) 437–2862 or (800)
363–8023; fax (450) 433–0272; or at https://
www.bellcustomer.com/files/. You may
review a copy of the service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
Transport Canada AD No. CF–2018–18, dated
July 11, 2018. You may view the Transport
Canada AD on the internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2018–0834.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6520, Tail Rotor Gearbox.
Issued in Fort Worth, Texas, on October 5,
2018.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018–22414 Filed 10–19–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 31216; Amdt. No. 3820]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule amends, suspends,
or removes Standard Instrument
Approach Procedures (SIAPs) and
associated Takeoff Minimums and
Obstacle Departure Procedures for
operations at certain airports. These
regulatory actions are needed because of
the adoption of new or revised criteria,
or because of changes occurring in the
National Airspace System, such as the
commissioning of new navigational
facilities, adding new obstacles, or
changing air traffic requirements. These
changes are designed to provide for the
safe and efficient use of the navigable
airspace and to promote safe flight
operations under instrument flight rules
at the affected airports.
DATES: This rule is effective October 22,
2018. The compliance date for each
SIAP, associated Takeoff Minimums,
and ODP is specified in the amendatory
provisions.
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SUMMARY:
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The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of October 22,
2018.
ADDRESSES: Availability of matter
incorporated by reference in the
amendment is as follows:
For Examination
1. U.S. Department of Transportation,
Docket Ops-M30, 1200 New Jersey
Avenue SE, West Bldg., Ground Floor,
Washington, DC, 20590–0001;
2. The FAA Air Traffic Organization
Service Area in which the affected
airport is located;
3. The office of Aeronautical
Navigation Products, 6500 South
MacArthur Blvd., Oklahoma City, OK
73169 or,
4. 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/code_of_federal_
regulations/ibr_locations.html.
Availability
All SIAPs and Takeoff Minimums and
ODPs are available online free of charge.
Visit the National Flight Data Center
online at nfdc.faa.gov to register.
Additionally, individual SIAP and
Takeoff Minimums and ODP copies may
be obtained from the FAA Air Traffic
Organization Service Area in which the
affected airport is located.
FOR FURTHER INFORMATION CONTACT:
Thomas J. Nichols, Flight Procedure
Standards Branch (AFS–420)Flight
Technologies and Procedures Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK. 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK. 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This rule
amends Title 14, Code of Federal
Regulations, Part 97 (14 CFR part 97) by
amending the referenced SIAPs. The
complete regulatory description of each
SIAP is listed on the appropriate FAA
Form 8260, as modified by the National
Flight Data Center (NFDC)/Permanent
Notice to Airmen (P–NOTAM), and is
incorporated by reference under 5
U.S.C. 552(a), 1 CFR part 51, and 14
CFR 97.20. The large number of SIAPs,
their complex nature, and the need for
a special format make their verbatim
publication in the Federal Register
expensive and impractical. Further,
airmen do not use the regulatory text of
the SIAPs, but refer to their graphic
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depiction on charts printed by
publishers of aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP contained on FAA form
documents is unnecessary.
This amendment provides the affected
CFR sections, and specifies the SIAPs
and Takeoff Minimums and ODPs with
their applicable effective dates. This
amendment also identifies the airport
and its location, the procedure and the
amendment number.
Availability and Summary of Material
Incorporated by Reference
The material incorporated by
reference is publicly available as listed
in the ADDRESSES section.
The material incorporated by
reference describes SIAPs, Takeoff
Minimums and ODPs as identified in
the amendatory language for part 97 of
this final rule.
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP and Takeoff Minimums
and ODP as amended in the transmittal.
For safety and timeliness of change
considerations, this amendment
incorporates only specific changes
contained for each SIAP and Takeoff
Minimums and ODP as modified by
FDC permanent NOTAMs.
The SIAPs and Takeoff Minimums
and ODPs, as modified by FDC
permanent NOTAM, and contained in
this amendment are based on the
criteria contained in the U.S. Standard
for Terminal Instrument Procedures
(TERPS). In developing these changes to
SIAPs and Takeoff Minimums and
ODPs, the TERPS criteria were applied
only to specific conditions existing at
the affected airports. All SIAP
amendments in this rule have been
previously issued by the FAA in a FDC
NOTAM as an emergency action of
immediate flight safety relating directly
to published aeronautical charts.
The circumstances that created the
need for these SIAP and Takeoff
Minimums and ODP amendments
require making them effective in less
than 30 days.
Because of the close and immediate
relationship between these SIAPs,
Takeoff Minimums and ODPs, and
safety in air commerce, I find that notice
and public procedure under 5 U.S.C.
553(b) are impracticable and contrary to
the public interest and, where
applicable, under 5 U.S.C. 553(d), good
cause exists for making these SIAPs
effective in less than 30 days.
E:\FR\FM\22OCR1.SGM
22OCR1
]]>Agencies
[Federal Register Volume 83, Number 204 (Monday, October 22, 2018)]
[Rules and Regulations]
[Pages 53171-53174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22414]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0834; Product Identifier 2018-SW-058-AD; Amendment
39-19421; AD 2018-16-51]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Limited
Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are publishing a new airworthiness directive (AD) for Bell
Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD
was sent previously to all known U.S. owners and operators of these
helicopters as Emergency AD 2018-16-51, dated July 26, 2018, which
superseded Emergency AD 2018-15-51, dated July 20, 2018. This AD
requires inspecting the tail rotor (T/R) gearbox installation,
inspecting the T/R gearbox retaining hardware and support attachment
point areas, and replacing each nut. This AD is prompted by two reports
of T/R gearbox assemblies loosely attached to the gearbox support. The
actions of this AD are intended to address an unsafe condition on these
products.
DATES: This AD becomes effective November 6, 2018 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2018-16-51, issued on July 26, 2018, which contains the requirements of
this AD.
We must receive comments on this AD by December 21, 2018.
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
[[Page 53172]]
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-2018-
0834; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this AD, the Transport Canada AD, the economic evaluation, any comments
received, and other information. The street address for Docket
Operations (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 Bell
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450)
433-0272; or at https://www.bellcustomer.com/files/. 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: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
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
Transport Canada, which is the aviation authority for Canada,
issued Emergency AD No. CF-2018-18, dated July 11, 2018, to correct an
unsafe condition for Bell Model 429 helicopters. Transport Canada
advises of two reports of T/R gearbox assemblies loosely attached to
the gearbox support. According to Transport Canada, this condition
could lead to structural damage and possible loss of control of the
helicopter.
As a result, on July 20, 2018, we issued Emergency AD 2018-15-51
(Emergency AD 2018-15-51), which required inspecting the T/R gearbox
installation for looseness, visually inspecting the T/R gearbox
retaining hardware and support attachment point areas, and torque
inspecting the gearbox retaining nuts. Depending on the inspection
results, Emergency AD 2018-15-51 required replacing or repairing the
affected parts in accordance with FAA-approved procedures. Emergency AD
2018-15-51 was sent previously to all known U.S. owners and operators
of these helicopters. The actions in Emergency AD 2018-15-51 were
intended to prevent detachment of the T/R gearbox, loss of T/R control,
and loss of control of the helicopter.
After we issued Emergency AD 2018-15-51, we discovered an error in
the replacement nut P/N. The required replacement nut P/N is NAS9926-
6L; not NAS9926-5L as incorrectly stated in Emergency AD 2018-15-51.
Therefore, on July 26, 2018, we issued Emergency AD 2018-16-51 to
supersede Emergency AD 2018-15-51 to correct the nut P/N. Emergency AD
2018-16-51 otherwise retains all of the requirements of Emergency AD
2018-15-51. Emergency AD 2018-16-51 was also sent previously to all
known U.S. owners and operators of these helicopters.
FAA's Determination
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
our bilateral agreement with Canada, Transport Canada, its technical
representative, has notified us of the unsafe condition described in
the Transport Canada AD. We are issuing this AD because we evaluated
all information provided by Transport Canada and determined the unsafe
condition exists and is likely to exist or develop on other helicopters
of the same type design.
Related Service Information
We reviewed Bell Alert Service Bulletin 429-18-40, dated July 6,
2018, which specifies a one-time inspection of the T/R gearbox
installation and a one-time visual and torque inspection of the six
installation attachment points. This service information also specifies
contacting Bell Product Support Engineering with the results of the T/R
gearbox installation inspection, any findings of the visual inspection,
and the results of the torque inspection.
AD Requirements
This AD requires inspecting the T/R gearbox installation for
looseness, visually inspecting the T/R gearbox retaining hardware and
each support attachment point area, and torque inspecting each gearbox
retaining nut. Depending on the inspection results, this AD requires
replacing or repairing the affected parts in accordance with FAA-
approved procedures.
Differences Between This AD and the Transport Canada AD
The Transport Canada AD applies to helicopters with specific serial
numbers, whereas this AD applies to all Model 429 helicopters. The
Transport Canada AD includes a calendar based compliance time, whereas
this AD does not. The Transport Canada AD requires reporting certain
information to Bell Product Support Engineering and this AD does not.
If there is looseness, this AD requires performing the visual
inspection and torque inspection before further flight, while the
Transport Canada AD requires contacting Bell. Lastly, if the torque of
a T/R gearbox retaining nut is below 160 in-lbs (19 Nm), this AD
requires removing the T/R gearbox and inspecting the mounting surfaces
and retaining hardware, while the Transport Canada AD requires
contacting Bell.
Interim Action
We consider this AD to be an interim action. If final action is
later identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this AD affects 90 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 $85.00 per work-hour.
[[Page 53173]]
Inspecting the T/R gearbox installation takes about 0.25 work-hour
for an estimated cost of $21 per helicopter and $1,890 for the U.S.
fleet. Inspecting the T/R gearbox retaining hardware and the support
attachment points takes about 0.5 work-hour for an estimated cost of
$43 per helicopter and $3,870 for the U.S. fleet. Replacing the nuts
takes about 1 work-hour and parts cost about $20 for an estimated cost
of $105 per helicopter and $9,450 for the U.S. fleet.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that required the immediate adoption of
Emergency AD 2018-16-51, issued on July 26, 2018, to all known U.S.
owners and operators of these helicopters. The FAA found that the risk
to the flying public justified waiving notice and comment prior to
adoption of this rule because there are required actions that must be
completed before further flight and within 5 hours time-in-service.
These conditions still exist and the AD is hereby published in the
Federal Register as an amendment to section 39.13 of the Federal
Aviation Regulations (14 CFR 39.13) to make it effective to all
persons. Therefore, we find good cause that notice and opportunity for
prior public comment are impracticable. In addition, for the reasons
stated above, we find 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):
2018-16-51 Bell Helicopter Textron Canada Limited: Amendment 39-
19421; Docket No. FAA-2018-0834; Product Identifier 2018-SW-058-AD.
(a) Applicability
This AD applies to Model 429 helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a loose tail rotor (T/R)
gearbox support attachment point. This condition could result in
detachment of the T/R gearbox, loss of T/R control, and loss of
control of the helicopter.
(c) Related ADs
This AD requires the same actions as Emergency AD 2018-16-51,
dated July 26, 2018, which superseded Emergency AD 2018-15-51, dated
July 20, 2018.
(d) Effective Date
This AD becomes effective November 6, 2018 to all persons except
those persons to whom it was made immediately effective by Emergency
AD 2018-16-51, issued on July 26, 2018, which contains the
requirements of this AD.
(e) 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.
(f) Required Actions
(1) Before further flight, inspect for looseness of the T/R
gearbox installation to the T/R gearbox structural support by moving
the T/R gearbox output shaft in an upward and downward direction. If
the T/R gearbox installation is loose, before further flight,
complete the actions required by paragraphs (f)(2)(i) and (ii) of
this AD.
(2) Within 5 hours time-in-service, unless already completed as
required by paragraph (f)(1) of this AD:
(i) Visually inspect the T/R gearbox retaining hardware and each
support attachment point area for evidence of fretting, a crack, and
incorrect installation. If there is any evidence of fretting, a
crack, or incorrect installation, before further flight, repair in
accordance with FAA-approved procedures.
(ii) Inspect each T/R gearbox retaining nut by applying 160 in-
lbs (19 Nm) of torque. If the torque of a T/R gearbox retaining nut
is below 160 in-lbs (19 Nm), before further flight:
(A) Remove the T/R gearbox and inspect each stud for proper
staking, each stud thread for uniformity, each mounting surface for
evidence of fretting and cracking, and each mounting hole for
elongation. If a stud is not properly staked, a stud thread is not
uniform, a mounting surface has evidence of fretting or cracking, or
a mount hole is elongated, before further flight, replace the
affected parts or repair in accordance with FAA-approved procedures.
(B) Replace each nut with nut part number NAS9926-6L and apply a
torque of 160 in-lbs.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; 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.
(h) Additional Information
(1) Bell Alert Service Bulletin 429-18-40, dated July 6, 2018,
which is not incorporated
[[Page 53174]]
by reference, contains additional information about the subject of
this AD. For service information identified in this AD, contact Bell
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450)
433-0272; or at https://www.bellcustomer.com/files/. You may review a
copy of the service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177.
(2) The subject of this AD is addressed in Transport Canada AD
No. CF-2018-18, dated July 11, 2018. You may view the Transport
Canada AD on the internet at https://www.regulations.gov by searching
for and locating it in Docket No. FAA-2018-0834.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor
Gearbox.
Issued in Fort Worth, Texas, on October 5, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2018-22414 Filed 10-19-18; 8:45 am]
BILLING CODE 4910-13-P
