Airworthiness Directives; Airbus Helicopters, 65285-65288 [2020-22744]
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Federal Register / Vol. 85, No. 200 / Thursday, October 15, 2020 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus SAS: Docket No. FAA–2020–0851;
Product Identifier 2020–NM–081–AD.
(a) Comments Due Date
The FAA must receive comments by
November 30, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS
airplanes specified in paragraphs (c)(1)
through (4) of this AD, certificated in any
category.
(1) Model A318–111, A318–112, A318–
121, and A318–122 airplanes.
(2) Model A319–111, A319–112, A319–
113, A319–114, A319–115, A319–131, A319–
132, and A319–133 airplanes.
(3) Model A320–211, A320–212, A320–
214, A320–216, A320–231, A320–232, and
A320–233 airplanes.
(4) Model A321–111, A321–112, A321–
131, A321–211, A321–212, A321–213, A321–
231, and A321–232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 35, Oxygen.
(e) Reason
This AD was prompted by reports that
certain oxygen supply solenoid valves are a
potential source of increased flow resistance
within the flightcrew oxygen system. The
FAA is issuing this AD to address increased
flow resistance within the flightcrew oxygen
system, which could lead to a reduced flow
of oxygen supply to the flightcrew oxygen
masks, and in combination with in-flight
depressurization, smoke in the flight deck, or
a smoke evacuation procedure, could lead to
flightcrew hypoxia and loss of useful
consciousness, resulting in loss of control of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2020–0104, dated
May 7, 2020 (‘‘EASA AD 2020–0104’’).
(h) Exceptions to EASA AD 2020–0104
(1) Where EASA AD 2020–0104 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0104 does not apply to this AD.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2020–0104 specifies
to submit certain information to the
manufacturer, 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, Large Aircraft
Section, International Validation Branch,
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 Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@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 instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2020–0104 that contains RC procedures and
tests: Except as required by paragraph (j)(2)
of this AD, RC 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
(1) For information about EASA AD 2020–
0104, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 89990 6017; email ADs@
easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this
material at the FAA, Airworthiness Products
Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2020–0851.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3223; email Sanjay.Ralhan@
faa.gov.
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Issued on September 18, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–22741 Filed 10–14–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0907; Product
Identifier 2017–SW–072–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
Airbus Helicopters Model AS350B3
helicopters. This proposed AD would
require modifying the electrical system
of the throttle twist grip, inspecting the
routing of a microswitch electrical
harness, and correcting the electrical
harness routing if it is incorrect. This
proposed AD was prompted by reports
of the engine remaining in idle when
the twist grip was turned from the
‘‘forced idle’’ position to the ‘‘flight’’
position. The actions of this proposed
AD are intended to address an unsafe
condition on these products.
DATES: The FAA must receive comments
on this proposed AD by November 30,
2020.
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.
SUMMARY:
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–2020–
0907; or in person at Docket Operations
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between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD, any
comments received and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
For service information identified in
this proposed rule, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
972–641–0000 or 800–232–0323; fax
972- 641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
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:
George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110.
SUPPLEMENTARY INFORMATION:
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Comments Invited
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views. The most
helpful comments reference a specific
portion of the proposal, explain the
reason for any recommended change,
and include supporting data. To ensure
the docket does not contain duplicate
comments, commenters should send
only one copy of written comments, or
if comments are filed electronically,
commenters should submit only one
time.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will file in the docket all
comments received, as well as a report
summarizing each substantive public
contact with FAA personnel concerning
this proposed rulemaking. Before acting
on this proposal, the FAA will consider
all comments received on or before the
closing date for comments. The FAA
will consider comments filed after the
comment period has closed if it is
possible to do so without incurring
expense or delay. The FAA may change
this proposal in light of the comments
received.
Confidential Business Information
Confidential Business Information
(CBI) is commercial or financial
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information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to George Schwab,
Aviation Safety Engineer, Safety
Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817–222–5110. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued a series of ADs, most
recently EASA AD No. 2017–0035,
dated February 20, 2017 (EASA AD
2017–0035), to correct an unsafe
condition for Airbus Helicopters
(formerly Eurocopter) Model AS 350 B3
helicopters with ARRIEL 2B engines
installed. EASA advises of an initial
report of the microswitch pin jammed in
the pushed-in position resulting in the
engine remaining in idle when the twist
grip had been turned back to the
‘‘flight’’ position during an autorotation
training exercise. This condition could
also occur during governor failure
training when the twist grip is turned in
the low flow rate direction. EASA also
advises of two later reports of this
condition, with one of those reports
related to an incorrectly routed
electrical harness. EASA advises that
this condition, if not detected and
corrected, could lead to reduced control
of the helicopter.
EASA initially issued AD No. 2006–
0094, dated April 21, 2006, which
required repetitive testing of the
microswitch and established a life limit
for the microswitch. Subsequent EASA
AD action required reducing that life
limit, inspecting the travel of the
collective lever, performing an
additional check of the collective lever
for free travel, and installing a
terminating action modification that
was available for certain helicopter
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configurations. That modification gave
priority to the HydroMechanical Unit
(HMU) flight position when the
microswitch failed to operate correctly
at forced idle. EASA most recently
issued AD 2017–0035, which prompted
this AD action, to include all of the
previous AD requirements and expand
the terminating action modification to
other helicopter configurations.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in its AD. The FAA is proposing this AD
because the FAA evaluated all known
relevant information and determined
that an unsafe condition is likely to
exist or develop on other products of the
same type designs.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Alert Service Bulletin (ASB) No.
AS350–67.00.43, Revision 3, dated June
16, 2016, which specifies procedures,
based on different configurations, to
modify the electrical operation to give
priority to the HMU flight position
when the microswitch does not operate
correctly at forced idle (corresponds to
Airbus Helicopters Modification (MOD)
073357). This service information also
specifies instructions to inspect the
routing of microswitch electrical
harness number ‘‘53K’’.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Other Related Service Information
The FAA also reviewed Eurocopter
ASB No. 05.00.49, Revision 3, dated
March 8, 2012. This service information
specifies procedures, for helicopters
without MOD 073357 installed, for
repetitive testing of the microswitch, a
life limit for the microswitch, inspecting
the travel of the collective lever, and
verifying correct wiring harness
installation.
Proposed AD Requirements
This proposed AD would require,
based on helicopter configuration,
modifying the electrical system of the
throttle twist grip. This proposed AD
would also require inspecting the
routing of a microswitch electrical
harness, and depending on the routing
of that electrical harness, correcting the
routing.
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Differences Between This Proposed AD
and the EASA AD
The EASA AD specifies a repetitive
test of the microswitch, a life limit for
the microswitch, and inspecting the
travel of the collective lever, until the
terminating action of modifying the
electrical system of the throttle twist
grip and inspecting the routing of a
microswitch electrical harness are
completed. This proposed AD would
only require modifying the electrical
system of the throttle twist grip and
inspecting the routing of a microswitch
electrical harness. The EASA AD
specifies performing that terminating
action in a compliance time of calendar
months. This proposed AD would
require performing the required actions
before the next practice autorotation,
before the next simulated governor
failure, or within 330 hours time-inservice, whichever occurs first.
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Costs of Compliance
The FAA estimates that this proposed
AD would affect 517 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD. Labor costs are estimated at $85 per
work-hour.
Modifying the electrical system and
inspecting the electrical harness routing
would take about 30 work-hours and
parts would cost about $9,692 for an
estimated cost of $12,242 per helicopter
and $6,329,114 for the U.S. fleet.
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.
The FAA is 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
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
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have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Will not affect intrastate aviation in
Alaska, and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus Helicopters: Docket No. FAA–2020–
0907; Product Identifier 2017–SW–072–
AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS350B3 helicopters, certificated in
any category, with a Turbomeca ARRIEL 2B
engine installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of the electrical operation of the
throttle twist grip, which can prevent
switching from ‘‘IDLE’’ mode to ‘‘FLIGHT’’
mode. During autorotation training or during
governor failure training (when the throttle
grip is turned in the low flow direction), this
condition prohibits recovery from a practice
autorotation and compels the pilot to
continue the autorotation to the ground. This
condition could result in unintended
touchdown to the ground at a flight-idle
power setting, damage to the helicopter, and
injury to occupants.
(c) Comments Due Date
The FAA must receive comments by
November 30, 2020.
(d) Compliance
You are responsible for performing each
action required by this AD within the
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65287
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Before the next practice autorotation,
before the next simulated governor failure, or
within 330 hours time-in-service, whichever
occurs first, modify the electrical operation of
the throttle twist grip to give priority to the
HydroMechanical Unit flight position when
the microswitch does not operate correctly at
forced idle (corresponds to Airbus
Helicopters Modification (MOD) 073357) as
follows:
(1) For helicopters without MOD 073087
and without MOD 073135 installed:
(i) Install box ‘‘69K’’ on the Full Authority
Digital Engine Control plate, relay ‘‘81K’’ on
frame X1310, install fuses on the console end
comprising circuit-breaker panels ‘‘31
ALPHA’’ and ‘‘32 ALPHA,’’ and modify the
electrical wiring by following the
Accomplishment Instructions, paragraph
3.B.2.a. of Airbus Helicopters Alert Service
Bulletin No. AS350–67.00.43, Revision 3,
dated June 16, 2016 (ASB AS350–67.00.43),
except you are not required to discard parts.
(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following paragraph 3.B.2.e. of
ASB AS350–67.00.43. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(2) For helicopters with MOD 073087
(series) and without MOD 073135 installed:
(i) Install relays ‘‘54K’’ and ‘‘81K’’ on frame
X1310 and modify the electrical wiring by
following paragraph 3.B.2.b. of ASB AS350–
67.00.43.
(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following paragraph 3.B.2.e. of
ASB AS350–67.00.43. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(3) For helicopters with MOD 073087
(retrofit) and without MOD 073135 installed:
(i) Install relay ‘‘81K’’ on frame X1310 and
modify the electrical wiring by following
paragraph 3.B.2.c. of ASB AS350–67.00.43.
(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following paragraph 3.B.2.e. of
ASB AS350–67.00.43. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(4) For helicopters with MOD 073087 and
with MOD 073135 installed:
(i) Install relay ‘‘81K’’ on frame X1310 and
modify the electrical wiring by following
paragraph 3.B.2.d. of ASB AS350–67.00.43.
(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following paragraph 3.B.2.e. of
ASB AS350–67.00.43. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(5) For helicopters with MOD 073084 and
with MOD 073222 installed:
(i) Install relay ‘‘81K’’ on frame X1310 and
modify the electrical wiring by following
paragraph 3.B.2.g. of ASB AS350–67.00.43,
except you are not required to scrap parts.
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(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following paragraph 3.B.2.e. of
ASB AS350–67.00.43. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(6) For helicopters with optional Autopilot
‘‘81K’’ and without MOD 073222 installed:
(i) Position relay ‘‘81K’’ on frame X1310 by
following paragraph 3.B.2.h. of ASB AS350–
67.00.43.
(ii) Inspect the routing of microswitch
electrical harness ‘‘53K’’ for correct
installation by following ASB AS350–
67.00.43, step 3.B.2.e. If the wiring routing is
incorrect, before further flight, correct the
wiring routing by following paragraph
3.B.2.f. of ASB AS350–67.00.43.
(f) Special Flight Permits
Special flight permits are prohibited.
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(h) Additional Information
(1) Eurocopter Alert Service Bulletin No.
05.00.49, Revision 3, dated March 8, 2012,
which is not incorporated by reference,
contains additional information about the
subject of this AD. For service information
identified in this AD, contact Airbus
Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone 972–641–0000
or 800–232–0323; fax 972–641–3775; or at
https://www.airbus.com/helicopters/services/
technical-support.html. You may view the
referenced 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
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD No. 2017–0035, dated February
20, 2017. You may view the EASA AD on the
internet at https://www.regulations.gov in the
AD Docket.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 7697, Engine Control System Wiring.
[FR Doc. 2020–22744 Filed 10–14–20; 8:45 am]
BILLING CODE 4910–13–P
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Office of the Under Secretary for
Economic Affairs
15 CFR Part 1500
[Docket No.: 200901–0230]
RIN 0605–AA56
Concrete Masonry Products Research,
Education and Promotion Order;
Referendum Procedures
Under Secretary for Economic
Affairs, United States Department of
Commerce.
ACTION: Notice of proposed rulemaking.
AGENCY:
Pursuant to the Concrete
Masonry Products Research, Education,
and Promotion Act of 2018 (the Act), the
Department of Commerce (Department)
solicits comments on proposed
procedures for conducting a referendum
to determine whether manufacturers of
concrete masonry units favor the
issuance of a proposed Concrete
Masonry Products Research, Education,
and Promotion Order (proposed order).
The purpose of the proposed order is to
strengthen the position of the concrete
masonry products industry in the
domestic marketplace; maintain,
develop, and expand markets and uses
for concrete masonry products in the
domestic marketplace; and promote the
use of concrete masonry products in
construction and building. The
Department published the proposed
order in the Federal Register on August
24, 2020. The Act requires industry to
approve the proposed order via a
referendum. If industry approves the
proposed order, the Secretary of
Commerce (Secretary) will issue a final
order and appoint a Board to carry out
the duties prescribed by that order,
which would include an industryfunded research, education, and
promotion program. The Department
also would follow these procedures for
any subsequent referendum under the
Act. This proposal also announces the
intent of the Department to request
approval by the Office of Management
and Budget (OMB) of two new
information collection requests (ICRs) to
support implementation of the
referendum.
DATES: The Department must receive
comments November 16, 2020.
ADDRESSES: Submit all electronic public
comments via the Federal e-Rulemaking
Portal. Go to
https://beta.regulations.gov/docket/
DOC-2020-0003 click the ‘‘Comment
Now!’’ icon, complete the required
fields, and enter or attach your
SUMMARY:
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: George Schwab,
Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
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.
Issued on October 6, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
DEPARTMENT OF COMMERCE
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
comments. The supporting economic
analysis is also available for comment
on regulations.gov.
All submissions, including
attachments and other supporting
materials, will become part of the public
record and subject to public disclosure.
The Department reserves the right to
publish relevant comments, unedited
and in their entirety. Do not include
personal information, such as account
numbers or Social Security numbers, or
names of other individuals. Do not
submit confidential business
information, or otherwise proprietary,
sensitive or protected information. We
will not post or consider comments that
contain profanity, vulgarity, threats, or
other inappropriate language or like
content.
Pursuant to the Paperwork Reduction
Act (PRA), send to the above address
comments regarding the accuracy of the
burden estimate, ways to minimize the
burden, including the use of automated
collection techniques or other forms of
information technology, or any other
aspect of this collection of information.
In addition, send comments concerning
the information collection to OIRA_
Submission@omb.eop.gov or online at
https://www.reginfo.gov/public/do/
PRAMain.
Mr.
Michael Thompson, Communications
for the Commerce Checkoff
Implementation Program, Office of the
Under Secretary for Economic Affairs,
telephone: (202) 482–0671 or via
electronic mail: mthompson1@doc.gov.
FOR FURTHER INFORMATION CONTACT:
I. Legal Background
Pursuant to the Concrete Masonry
Products Research, Education, and
Promotion Act of 2018, 15 U.S.C. 8701
et seq., the Department is enacting a
research, education, and promotion
program (commonly referred to as a
checkoff program) for concrete masonry
products. The Act specifically
authorizes the Secretary to conduct the
referendum, and states that ‘‘[referenda
. . . shall be conducted in a manner
determined by the Secretary.’’ 15 U.S.C.
8706(c)(1). The Act also authorizes the
Secretary to ‘‘issue such regulations as
may be necessary to carry out [the Act]
and the power vested in the Secretary
under [the Act].’’ 15 US.C. 8713.
The Department’s actions to bring the
program to fruition will include: (1)
implementing an order that will
effectuate the purpose of the Act; (2)
conducting a referendum among the
industry to determine whether the
industry approves of being subject to the
implementing order; and, upon an
affirmative vote on the order, (3) issuing
E:\FR\FM\15OCP1.SGM
15OCP1
]]>Agencies
[Federal Register Volume 85, Number 200 (Thursday, October 15, 2020)]
[Proposed Rules]
[Pages 65285-65288]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22744]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0907; Product Identifier 2017-SW-072-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Airbus Helicopters Model AS350B3 helicopters. This proposed AD
would require modifying the electrical system of the throttle twist
grip, inspecting the routing of a microswitch electrical harness, and
correcting the electrical harness routing if it is incorrect. This
proposed AD was prompted by reports of the engine remaining in idle
when the twist grip was turned from the ``forced idle'' position to the
``flight'' position. The actions of this proposed AD are intended to
address an unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by November
30, 2020.
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-2020-
0907; or in person at Docket Operations
[[Page 65286]]
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the European
Aviation Safety Agency (now European Union Aviation Safety Agency)
(EASA) AD, any comments received and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone 972-641-0000 or 800-232-0323; fax 972- 641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may view 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: George Schwab, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The most helpful comments reference a
specific portion of the proposal, explain the reason for any
recommended change, and include supporting data. To ensure the docket
does not contain duplicate comments, commenters should send only one
copy of written comments, or if comments are filed electronically,
commenters should submit only one time.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will file in the docket all comments received, as well
as a report summarizing each substantive public contact with FAA
personnel concerning this proposed rulemaking. Before acting on this
proposal, the FAA will consider all comments received on or before the
closing date for comments. The FAA will consider comments filed after
the comment period has closed if it is possible to do so without
incurring expense or delay. The FAA may change this proposal in light
of the comments received.
Confidential Business Information
Confidential Business Information (CBI) is commercial or financial
information that is both customarily and actually treated as private by
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552),
CBI is exempt from public disclosure. If your comments responsive to
this NPRM contain commercial or financial information that is
customarily treated as private, that you actually treat as private, and
that is relevant or responsive to this NPRM, it is important that you
clearly designate the submitted comments as CBI. Please mark each page
of your submission containing CBI as ``PROPIN.'' The FAA will treat
such marked submissions as confidential under the FOIA, and they will
not be placed in the public docket of this NPRM. Submissions containing
CBI should be sent to George Schwab, Aviation Safety Engineer, Safety
Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110. Any commentary
that the FAA receives which is not specifically designated as CBI will
be placed in the public docket for this rulemaking.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued a series of ADs, most recently EASA AD No.
2017-0035, dated February 20, 2017 (EASA AD 2017-0035), to correct an
unsafe condition for Airbus Helicopters (formerly Eurocopter) Model AS
350 B3 helicopters with ARRIEL 2B engines installed. EASA advises of an
initial report of the microswitch pin jammed in the pushed-in position
resulting in the engine remaining in idle when the twist grip had been
turned back to the ``flight'' position during an autorotation training
exercise. This condition could also occur during governor failure
training when the twist grip is turned in the low flow rate direction.
EASA also advises of two later reports of this condition, with one of
those reports related to an incorrectly routed electrical harness. EASA
advises that this condition, if not detected and corrected, could lead
to reduced control of the helicopter.
EASA initially issued AD No. 2006-0094, dated April 21, 2006, which
required repetitive testing of the microswitch and established a life
limit for the microswitch. Subsequent EASA AD action required reducing
that life limit, inspecting the travel of the collective lever,
performing an additional check of the collective lever for free travel,
and installing a terminating action modification that was available for
certain helicopter configurations. That modification gave priority to
the HydroMechanical Unit (HMU) flight position when the microswitch
failed to operate correctly at forced idle. EASA most recently issued
AD 2017-0035, which prompted this AD action, to include all of the
previous AD requirements and expand the terminating action modification
to other helicopter configurations.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is proposing this AD
because the FAA evaluated all known relevant information and determined
that an unsafe condition is likely to exist or develop on other
products of the same type designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. AS350-67.00.43, Revision 3, dated June 16, 2016, which specifies
procedures, based on different configurations, to modify the electrical
operation to give priority to the HMU flight position when the
microswitch does not operate correctly at forced idle (corresponds to
Airbus Helicopters Modification (MOD) 073357). This service information
also specifies instructions to inspect the routing of microswitch
electrical harness number ``53K''.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Other Related Service Information
The FAA also reviewed Eurocopter ASB No. 05.00.49, Revision 3,
dated March 8, 2012. This service information specifies procedures, for
helicopters without MOD 073357 installed, for repetitive testing of the
microswitch, a life limit for the microswitch, inspecting the travel of
the collective lever, and verifying correct wiring harness
installation.
Proposed AD Requirements
This proposed AD would require, based on helicopter configuration,
modifying the electrical system of the throttle twist grip. This
proposed AD would also require inspecting the routing of a microswitch
electrical harness, and depending on the routing of that electrical
harness, correcting the routing.
[[Page 65287]]
Differences Between This Proposed AD and the EASA AD
The EASA AD specifies a repetitive test of the microswitch, a life
limit for the microswitch, and inspecting the travel of the collective
lever, until the terminating action of modifying the electrical system
of the throttle twist grip and inspecting the routing of a microswitch
electrical harness are completed. This proposed AD would only require
modifying the electrical system of the throttle twist grip and
inspecting the routing of a microswitch electrical harness. The EASA AD
specifies performing that terminating action in a compliance time of
calendar months. This proposed AD would require performing the required
actions before the next practice autorotation, before the next
simulated governor failure, or within 330 hours time-in-service,
whichever occurs first.
Costs of Compliance
The FAA estimates that this proposed AD would affect 517
helicopters of U.S. Registry. The FAA estimates that operators may
incur the following costs in order to comply with this proposed AD.
Labor costs are estimated at $85 per work-hour.
Modifying the electrical system and inspecting the electrical
harness routing would take about 30 work-hours and parts would cost
about $9,692 for an estimated cost of $12,242 per helicopter and
$6,329,114 for the U.S. fleet.
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.
The FAA is 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Will not affect intrastate aviation in Alaska, and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
Airbus Helicopters: Docket No. FAA-2020-0907; Product Identifier
2017-SW-072-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS350B3 helicopters,
certificated in any category, with a Turbomeca ARRIEL 2B engine
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of the
electrical operation of the throttle twist grip, which can prevent
switching from ``IDLE'' mode to ``FLIGHT'' mode. During autorotation
training or during governor failure training (when the throttle grip
is turned in the low flow direction), this condition prohibits
recovery from a practice autorotation and compels the pilot to
continue the autorotation to the ground. This condition could result
in unintended touchdown to the ground at a flight-idle power
setting, damage to the helicopter, and injury to occupants.
(c) Comments Due Date
The FAA must receive comments by November 30, 2020.
(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
Before the next practice autorotation, before the next simulated
governor failure, or within 330 hours time-in-service, whichever
occurs first, modify the electrical operation of the throttle twist
grip to give priority to the HydroMechanical Unit flight position
when the microswitch does not operate correctly at forced idle
(corresponds to Airbus Helicopters Modification (MOD) 073357) as
follows:
(1) For helicopters without MOD 073087 and without MOD 073135
installed:
(i) Install box ``69K'' on the Full Authority Digital Engine
Control plate, relay ``81K'' on frame X1310, install fuses on the
console end comprising circuit-breaker panels ``31 ALPHA'' and ``32
ALPHA,'' and modify the electrical wiring by following the
Accomplishment Instructions, paragraph 3.B.2.a. of Airbus
Helicopters Alert Service Bulletin No. AS350-67.00.43, Revision 3,
dated June 16, 2016 (ASB AS350-67.00.43), except you are not
required to discard parts.
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following paragraph 3.B.2.e. of
ASB AS350-67.00.43. If the wiring routing is incorrect, before
further flight, correct the wiring routing by following paragraph
3.B.2.f. of ASB AS350-67.00.43.
(2) For helicopters with MOD 073087 (series) and without MOD
073135 installed:
(i) Install relays ``54K'' and ``81K'' on frame X1310 and modify
the electrical wiring by following paragraph 3.B.2.b. of ASB AS350-
67.00.43.
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following paragraph 3.B.2.e. of
ASB AS350-67.00.43. If the wiring routing is incorrect, before
further flight, correct the wiring routing by following paragraph
3.B.2.f. of ASB AS350-67.00.43.
(3) For helicopters with MOD 073087 (retrofit) and without MOD
073135 installed:
(i) Install relay ``81K'' on frame X1310 and modify the
electrical wiring by following paragraph 3.B.2.c. of ASB AS350-
67.00.43.
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following paragraph 3.B.2.e. of
ASB AS350-67.00.43. If the wiring routing is incorrect, before
further flight, correct the wiring routing by following paragraph
3.B.2.f. of ASB AS350-67.00.43.
(4) For helicopters with MOD 073087 and with MOD 073135
installed:
(i) Install relay ``81K'' on frame X1310 and modify the
electrical wiring by following paragraph 3.B.2.d. of ASB AS350-
67.00.43.
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following paragraph 3.B.2.e. of
ASB AS350-67.00.43. If the wiring routing is incorrect, before
further flight, correct the wiring routing by following paragraph
3.B.2.f. of ASB AS350-67.00.43.
(5) For helicopters with MOD 073084 and with MOD 073222
installed:
(i) Install relay ``81K'' on frame X1310 and modify the
electrical wiring by following paragraph 3.B.2.g. of ASB AS350-
67.00.43, except you are not required to scrap parts.
[[Page 65288]]
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following paragraph 3.B.2.e. of
ASB AS350-67.00.43. If the wiring routing is incorrect, before
further flight, correct the wiring routing by following paragraph
3.B.2.f. of ASB AS350-67.00.43.
(6) For helicopters with optional Autopilot ``81K'' and without
MOD 073222 installed:
(i) Position relay ``81K'' on frame X1310 by following paragraph
3.B.2.h. of ASB AS350-67.00.43.
(ii) Inspect the routing of microswitch electrical harness
``53K'' for correct installation by following ASB AS350-67.00.43,
step 3.B.2.e. If the wiring routing is incorrect, before further
flight, correct the wiring routing by following paragraph 3.B.2.f.
of ASB AS350-67.00.43.
(f) Special Flight Permits
Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: George Schwab, 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, the FAA suggests
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) Eurocopter Alert Service Bulletin No. 05.00.49, Revision 3,
dated March 8, 2012, which is not incorporated by reference,
contains additional information about the subject of this AD. For
service information identified in this AD, contact Airbus
Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone
972-641-0000 or 800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may
view the referenced 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 European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
No. 2017-0035, dated February 20, 2017. You may view the EASA AD on
the internet at https://www.regulations.gov in the AD Docket.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 7697, Engine
Control System Wiring.
Issued on October 6, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-22744 Filed 10-14-20; 8:45 am]
BILLING CODE 4910-13-P
