Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 11315-11319 [2020-03932]
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Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules
determinations which were previously
made in connection with the issuance of
the marketing order; and all said
previous findings and determinations
are hereby ratified and affirmed, except
insofar as such findings and
determinations may be in conflict with
the findings and determinations set
forth herein.
1. The Order, as amended, and as
hereby proposed to be further amended,
and all of the terms and conditions
thereof, would tend to effectuate the
declared policy of the Act;
2. The Order, as amended, and as
hereby proposed to be further amended,
regulates the handling of olives grown
in California in the same manner as, and
are applicable only to, persons in the
respective classes of commercial and
industrial activity specified in the
Order;
3. The Order, as amended, and as
hereby proposed to be further amended,
is limited in application to the smallest
regional production area which is
practicable, consistent with carrying out
the declared policy of the Act, and the
issuance of several orders applicable to
subdivisions of the production area
would not effectively carry out the
declared policy of the Act;
4. The Order, as amended, and as
hereby proposed to be further amended,
prescribe, insofar as practicable, such
different terms applicable to different
parts of the production area as are
necessary to give due recognition to the
differences in the production and
marketing of olives produced in the
production area; and
5. All handling of olives produced in
the production area as defined in the
Order is in the current of interstate or
foreign commerce or directly burdens,
obstructs, or affects such commerce.
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Order Relative to Handling
It is therefore ordered, that on and
after the effective date hereof, all
handling of olives grown in California
shall be in conformity to, and in
compliance with, the terms and
conditions of the said order as hereby
proposed to be amended as follows:
The provisions of the proposed
marketing order amending the Order
contained in the proposed rule issued
by the Administrator on November 1,
2019, and published in the Federal
Register (84 FR 59736) on November 6,
2019, will be and are the terms and
provisions of this order amending the
Order and are set forth in full herein.
formulate marketing agreements and marketing
orders have been met.
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PART 932—OLIVES GROWN IN
CALIFORNIA
1. The authority citation for 7 CFR
part 932 continues to read as follows:
■
■
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shall be required for adoption and, if the
committee is increased by the addition
of a public member, the number of
affirmative votes required for adoption
shall be increased by 1.
Authority: 7 U.S.C. 601–674.
[FR Doc. 2020–03893 Filed 2–26–20; 8:45 am]
2. Revise § 932.36 to read as follows:
BILLING CODE 3410–02–P
§ 932.36
Procedure.
Decisions of the committee shall be by
majority vote of the members, including
alternates acting as members, present
and voting, and a quorum must be
present: Provided, That decisions
requiring a recommendation to the
Secretary on matters pertaining to grade
and size regulations shall require at
least 10 affirmative votes, at least 5 of
which must be from producer members
and at least 5 of which must be from
handler members and, if the committee
is increased by the addition of a public
member, at least 11 affirmative votes
shall be required, at least 5 of which
must be from producer members and at
least 5 of which must be from handler
members. A quorum shall consist of at
least 10 members, including alternates
acting as members, and, if the
committee is increased by the addition
of a public member, a quorum shall
consist of at least 11 members,
including alternates acting as members.
Except in case of an emergency, a
minimum of 5 days advance notice shall
be given with respect to any meeting of
the committee. In case of an emergency,
to be determined within the discretion
of the chairman of the committee, as
much advance notice of a meeting as is
practicable in the circumstances shall be
given. The committee may vote by mail
or telegram upon due notice to all
members, but any proposition to be so
voted upon first shall be explained
accurately, fully, and identically by mail
or telegram to all members. When voted
on by such method, at least 14
affirmative votes, of which seven shall
be producer member votes and seven
shall be handler member votes, shall be
required for adoption and, if the
committee is increased by the addition
of a public member, votes by mail or
telegram shall require at least 15
affirmative votes, of which at least 7
shall be producer member votes and at
least 7 shall be handler member votes.
The committee may recommend for the
Secretary’s approval changes in the
number of affirmative votes required for
adoption of any proposition voted upon
by means of a mail or telegram ballot:
Provided, That the number of
affirmative votes required for adoption
shall not be less than 10, and in any
case an equal number of producer
member and handler member votes
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1123; Product
Identifier 2017–SW–013–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
The FAA is revising an earlier
proposal for Airbus Helicopters
Deutschland GmbH (Airbus Helicopters)
Model MBB–BK 117 C–2 and Model
MBB–BK 117 D–2 helicopters. This
action revises the notice of proposed
rulemaking (NPRM) by changing one of
the required actions. The FAA is
proposing this airworthiness directive
(AD) to address the unsafe condition on
these products. Since these actions
impose an additional burden over that
proposed in the NPRM, the FAA is
reopening the comment period to allow
the public the chance to comment on
these proposed changes.
DATES: The comment period for the
NPRM published in the Federal
Register on December 5, 2017 (82 FR
57390), is reopened. The FAA must
receive comments on this SNPRM by
April 27, 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:
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Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1123; 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 proposed
AD, the European 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/technicalsupport.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: 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:
Comments Invited
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views. The FAA also
invites comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
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
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this proposal in light of the comments
received.
Discussion
The FAA issued an NPRM to amend
14 CFR part 39 to remove AD 2017–02–
07, Amendment 39–18786 (82 FR
10267, February 10, 2017) (‘‘AD 2017–
02–07’’) and add a new AD. AD 2017–
02–07 applies to Airbus Helicopters
Model MBB–BK 117 C–2 helicopters,
serial numbers up to and including
9750, and Model MBB–BK 117 D–2
helicopters, serial numbers up to and
including 20110, with a hydraulic
module plate assembly part number
B291M0003103 with a single locking
attachment point installed. AD 2017–
02–07 requires a repetitive inspection
and a one-time torque of the hydraulic
module plate assembly attachment
points (attachment points). The actions
in AD 2017–02–07 are intended to
prevent failure of an attachment point,
loss of the hydraulic module plate, and
subsequent loss of control of the
helicopter.
The NPRM published in the Federal
Register on December 5, 2017 (82 FR
57390). The NPRM proposed to retain
the initial inspection and torque
requirements of AD 2017–02–07 and
require replacing the single locking
attachment mechanisms with double
locking attachment mechanisms. The
NPRM was prompted by EASA AD No.
2017–0047, dated March 13, 2017,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition on Airbus Helicopters
Deutschland GmbH (formerly
Eurocopter Deutschland GmbH) Model
MBB–BK117 C–2, MBB–BK117 C–2e,
MBB–BK117 D–2 and MBB–BK117 D–
2m helicopters. EASA advises that the
hydraulic plate assembly on certain
MBB–BK117 models has four
attachment points on the fuselage
secured by a single locking mechanism.
According to EASA, a design
reassessment revealed stiffness of the
hydraulic plate may be insufficient to
withstand the in-service loads in the
event one of the four single locking
attachment points fails. The EASA AD
requires a repetitive inspection and onetime torque tightening of the attachment
points until replacement of the single
locking attachment hardware with
double locking attachment hardware.
Actions Since the NPRM Was Issued
Since the NPRM was issued, Airbus
Helicopters revised its service
information by adding a requirement to
reposition the aft grounding straps and
inspect the clamping effect of the aft
attachment points when the double
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locking attachment hardware is
installed. The revised service
information also has an alternative
clamp effect inspection for helicopters
that have previously installed the
double locking attachment hardware.
These additional actions address the
unsafe condition by ensuring the correct
torque is applied and the bolts do not
loosen. The FAA is proposing this
SNPRM to include these additional
actions.
Further, the FAA has corrected an
error in the NPRM proposing to apply
a torque of 9 to 10 Nm to the left-hand
and right-hand nuts of each attachment
point. This torque adjustment is only
necessary for each forward (not aft)
attachment point.
Lastly, the website address for Airbus
Helicopters has also changed. This
website address has been updated
throughout this SNPRM.
Comments
The FAA gave the public the
opportunity to comment on the original
NPRM (82 FR 57390, December 5, 2017).
The FAA received no comments on that
NPRM or on the determination of the
cost to the public.
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
SNPRM after evaluating all information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs. Certain
changes described above expand the
scope of the original NPRM. As a result,
the FAA has determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Alert Service Bulletin (ASB) No. ASB
MBB–BK117 C–2–29A–003 for Model
MBB–BK 117 C–2 helicopters and ASB
No. ASB MBB–BK117 D–2–29A–001 for
Model MBB–BK 117 D–2 helicopters,
both Revision 3 and dated December 19,
2017. Until the attachment points are
modified with double locking
attachment mechanisms, this service
information specifies a repetitive visual
inspection for condition and correct
installation of the attachment points and
replacing the affected parts if there is a
crack. This service information also
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specifies a tightening torque check of
the forward attachment points after the
initial inspection and replacing the
affected parts if torque cannot be
applied. This service information
specifies procedures to replace the
single locking attachment hardware
with double locking attachment
hardware.
For certain helicopters with a
hydraulic module plate assembly with
the double locking attachment hardware
installed, this revision of the service
information contains procedures to
inspect the clamping effect of the aft
attachment points and torque tightening
the screw joints (bolts). If a bolt can be
turned while applying this torque, the
service information specifies
instructions to replace the split pin,
washer, and self-locking castellated nut,
check the bolt for wear and replace it if
necessary, change the position of the aft
grounding strap, check the electrical
bonding, and apply PU-Lacquer to the
grounding connection.
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.
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Other Related Service Information
The FAA also reviewed Airbus
Helicopters ASB No. ASB MBB–BK117
C–2–29A–003 for Model MBB–BK 117
C–2 helicopters and ASB No. ASB
MBB–BK117 D–2–29A–001 for Model
MBB–BK 117 D–2 helicopters, both
Revision 1 and dated October 14, 2016,
and both Revision 2 and dated February
1, 2017. Revisions 1 and 2 of this service
information contain the same visual
inspection and torque tightening check
procedures as Revision 3. Revision 2 of
this service information adds the
procedures to replace the single locking
attachment hardware with double
locking attachment hardware and
contains the same forward locking
attachment hardware replacement
procedures as Revision 3.
Proposed Requirements of the SNPRM
For helicopters with a hydraulic
module plate assembly with the single
locking attachment hardware installed,
this proposed AD would require, within
100 hours time-in-service (TIS),
performing a visual inspection of each
attachment point of the hydraulic
module plate assembly for a crack and
proper installation, and applying torque
to the nuts of each forward attachment
point. Within 300 hours TIS, this
proposed AD would require replacing
each single locking attachment point
mechanism with a double locking
attachment point mechanism.
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For helicopters with a hydraulic
module plate assembly with double
locking attachment hardware installed
in accordance with Airbus Helicopters
ASB No. ASB MBB–BK117 C–2–29A–
003 or ASB No. ASB MBB–BK117 D–2–
29A–001, both Revision 2 and dated
February 1, 2017, this proposed AD
would require, within 300 hours TIS,
inspecting the clamping effect of the aft
joints and torque tightening the bolts. If
a bolt can be turned while applying
torque, this proposed AD would require
removing the split pin and self-locking
castellated nut from service, inspecting
the bolt for wear and replacing it if
necessary, repositioning the aft
grounding strap to the opposite side of
the attachment point, replacing the
washer, installing a new self-locking
castellated nut, inspecting the electrical
bonding, installing a new split pin, and
applying lacquer to the grounding
connection.
Differences Between This SNPRM and
the EASA AD
The EASA AD specifies performing
the visual inspection of each attachment
point at intervals not exceeding 400
flight hours. This proposed AD would
not require a repetitive inspection. This
proposed AD would require the
replacement of each single locking
attachment point mechanism with a
double locking attachment point
mechanism within 300 hours TIS
instead, which would make subsequent
inspections unnecessary. Since EASA
has not revised or superseded its AD to
incorporate Revision 3 of the service
information, the EASA AD does not
require inspecting the clamping effect of
the aft joints, torque tightening the bolts,
and corrective action if necessary for
helicopters with a hydraulic module
plate assembly with double locking
attachment hardware installed in
accordance with Airbus Helicopters
ASB No. ASB MBB–BK117 C–2–29A–
003 or ASB No. ASB MBB–BK117 D–2–
29A–001, both Revision 2 and dated
February 1, 2017.
Costs of Compliance
The FAA estimates that this proposed
AD affects 167 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this AD. The
FAA estimates the cost of labor at $85
per work-hour.
Visually inspecting the four
attachment points would take about
0.75 work-hour for an estimated cost of
$64 per helicopter and $10,688 for the
U.S. fleet. Inspecting the torque of the
four attachment points would take about
0.25 work-hour for an estimated cost of
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11317
$21 per helicopter and $3,507 for the
U.S. fleet. Replacing any of the
attachment point parts would take a
minimal amount of time and parts
would cost about $48 per attachment
point. Installing four double locking
attachment point mechanisms would
take a minimal amount of time and parts
would cost about $400 per helicopter
and $66,800 for the U.S. fleet.
For certain double locking attachment
hardware aft joints, inspecting the
clamping effect and applying torque
would take about 1 work-hour for an
estimated cost of $85 per helicopter. If
required, inspecting and replacing parts,
repositioning the aft grounding strap,
inspecting the electrical bonding, and
applying lacquer to the grounding
connection would take about 0.5 workhour and parts would cost about $15 for
an estimated cost of $58 per helicopter.
According to Airbus Helicopters’
service information, some of the costs of
this proposed AD may be covered under
warranty, thereby reducing the cost
impact on affected individuals. The
FAA does not control warranty coverage
by Airbus Helicopters. Accordingly, the
FAA has included all costs in this cost
estimate.
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.
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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
removing airworthiness directive (AD)
2017–02–07, Amendment 39–18786 (82
FR 10267, February 10, 2017), and
adding the following new AD:
■
Airbus Helicopters Deutschland GmbH:
Docket No. FAA–2017–1123; Product
Identifier 2017–SW–013–AD.
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(a) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 C–
2 helicopters, serial numbers up to and
including 9750, and Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 D–
2 helicopters, serial numbers up to and
including 20110, certificated in any category,
with a hydraulic module plate assembly part
number B291M0003103 with a single locking
attachment point installed or with a double
locking attachment point installed before the
effective date of this AD in accordance with
Airbus Helicopters Alert Service Bulletin
(ASB) No. ASB MBB–BK117 C–2–29A–003
(ASB MBB–BK117 C–2–29A–003 Rev 2) or
ASB No. ASB MBB–BK117 D–2–29A–001
(ASB MBB–BK117 D–2–29A–001 Rev 2),
both Revision 2 and dated February 1, 2017,
as applicable to your model helicopter.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a hydraulic module plate assembly
attachment point (attachment point). This
condition could result in loss of the
hydraulic module plate and subsequent loss
of control of the helicopter.
(c) Affected ADs
This AD replaces 2017–02–07, Amendment
39–18786 (82 FR 10267, February 10, 2017).
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(d) Comments Due Date
The FAA must receive comments by April
27, 2020.
(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
Comply with either paragraphs (f)(1) and
(2) of this AD, or paragraph (f)(3) of this AD,
as applicable to your helicopter.
(1) For helicopters with a hydraulic
module plate assembly with a single locking
attachment hardware installed, within 100
hours time-in-service (TIS):
(i) Visually inspect the split pins,
castellated nuts, plugs, nuts, and hexagon
bolts of each attachment point for a crack and
for proper installation by following the
Accomplishment Instructions, paragraphs
3.B.1.3.a. through 3.B.1.3.d., of Airbus
Helicopters ASB No. ASB MBB–BK117 C–2–
29A–003 (ASB MBB–BK117 C–2–29A–003
Rev 3) or Airbus Helicopters ASB No. ASB
MBB–BK117 D–2–29A–001 (ASB MBB–
BK117 D–2–29A–001 Rev 3), both Revision 3
and dated December 19, 2017, as applicable
to your model helicopter. Replace any part
that has a crack before further flight. If the
split pins, castellated nuts, or hexagon bolts
are not as depicted in Figures 1 and 2 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, before
further flight, properly install them.
(ii) Apply a torque of 9 to 10 Nm to the
left-hand (LH) and right-hand (RH) nuts of
each forward attachment point. If a torque of
9 to 10 Nm cannot be applied, replace the
affected nut before further flight.
(2) For helicopters with a hydraulic
module plate assembly with a single locking
attachment hardware installed, within 300
hours TIS:
(i) Replace each forward single locking
attachment hardware with double locking
attachment hardware by following the
Accomplishment Instructions, paragraphs
3.B.3.3. through 3.B.3.6. on page 11 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, as
applicable to your model helicopter, except
you are not required to discard old parts.
(ii) Replace each aft single locking
attachment hardware with double locking
attachment hardware and reposition the LH
and RH aft grounding straps by following the
Accomplishment Instructions, paragraphs
3.B.3.1. through 3.B.3.7. on page 13 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, as
applicable to your model helicopter, except
you are not required to discard old parts.
(3) If you have replaced the attachment
hardware with double locking attachment
hardware before the effective date of this AD
in accordance with ASB MBB–BK117 C–2–
29A–003 Rev 2 or ASB MBB–BK117 D–2–
29A–001 Rev 2, as applicable to your model
helicopter: Within 300 hours TIS, inspect the
clamping effect of the LH and RH aft screw
joints (bolts) of the hydraulic module plate
by following the Accomplishment
Instructions, paragraph 3.B.5., of ASB MBB–
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BK117 C–2–29A–003 Rev 3 or ASB MBB–
BK117 D–2–29A–001 Rev 3, as applicable to
your model helicopter, except you are not
required to discard old parts.
Note 1 to paragraph (f)(3) of this AD:
Airbus Helicopters refers to bolts as ‘‘screw
joints.’’
(g) Credit for Previous Actions
Actions accomplished before the effective
date of this AD in accordance with the
procedures specified in the following are
considered acceptable for compliance with
the corresponding actions in paragraph (f)(1)
of this AD:
(1) AD 2017–02–07, Amendment 39–18786
(82 FR 10267, February 10, 2017).
(2) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003, Revision 1, dated
October 14, 2016.
(3) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003, Revision 2, dated
February 1, 2017.
(4) Airbus Helicopters ASB No. ASB MBB–
BK117 D–2–29A–001, Revision 1, dated
October 14, 2016.
(5) Airbus Helicopters ASB No. ASB MBB–
BK117 D–2–29A–001, Revision 2, dated
February 1, 2017.
(h) 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-ASW-FTWAMOC-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.
(i) Additional Information
(1) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003 and ASB No. ASB
MBB–BK117 D–2–29A–001, both Revision 1
and dated October 14, 2016, and both
Revision 2 and dated February 1, 2017,
which are not incorporated by reference,
contain 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 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
European Aviation Safety Agency (EASA) AD
No. 2017–0047, dated March 13, 2017. You
may view the EASA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2017–1123.
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Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 2900, Hydraulic Power System.
Issued in Fort Worth, Texas, on February
14, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–03932 Filed 2–26–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0103; Product
Identifier 2019–NM–149–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2012–21–08, which applies to certain
The Boeing Company Model 737–600,
–700, –700C, –800, and –900 series
airplanes. AD 2012–21–08 requires
inspecting for part numbers of the
operational program software (OPS) of
the flight control computers (FCCs) and
installing and testing an updated
version of the FCC OPS. Since the FAA
issued AD 2012–21–08, the FAA has
determined that there is a new unsafe
condition which must be addressed by
an updated version of the FCC OPS.
This proposed AD would retain the
requirement to inspect for part numbers
of the OPS of the FCCs, and add a new
requirement to update the version of the
FCC OPS if necessary. This proposed
AD would also expand the applicability
to include The Boeing Company Model
737–900ER series airplanes. The FAA is
proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments
on this proposed AD by April 13, 2020.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
lotter on DSKBCFDHB2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:50 Feb 26, 2020
Jkt 250001
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0103.
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–
0103; 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 NPRM, the
regulatory evaluation, 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 FURTHER INFORMATION CONTACT:
David Sumner, Aerospace Engineer,
Systems and Equipment Section, FAA,
Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and
fax: 206–231–3538; email:
david.sumner@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under the ADDRESSES section. Include
‘‘Docket No. FAA–2020–0103; Product
Identifier 2019–NM–149–AD’’ at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments,
without change, to https://
www.regulations.gov, including any
personal information you provide. The
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
11319
FAA will also post a report
summarizing each substantive verbal
contact the agency receives about this
proposed AD.
Discussion
The FAA issued AD 2012–21–08,
Amendment 39–17224 (77 FR 64711,
October 23, 2012) (‘‘AD 2012–21–08’’),
for certain The Boeing Company Model
737–600, –700, –700C, –800, and –900
series airplanes. AD 2012–21–08
requires inspecting for part numbers of
the OPS of the FCCs and installing and
testing an updated version of the FCC
OPS. AD 2012–21–08 resulted from
reports of undetected erroneous output
from a single radio altimeter channel,
which resulted in premature
autothrottle retard during approach. The
FAA issued AD 2012–21–08 to address
this condition, which, if not detected
and corrected, could result in the loss of
automatic speed control, and
consequent loss of control of the
airplane.
Actions Since AD 2012–21–08 Was
Issued
Since the FAA issued AD 2012–21–
08, the FAA has received reports that
during autopilot coupled Instrument
Landing System (ILS) approaches, the
airplane did not capture or track the
glideslope correctly. This caused
airplanes to continue descending below
the glideslope without any fault
indication from the autopilot system.
The problems were reported with the
autopilot engaged while attempting to
capture the glideslope from above, with
a high descent rate greater than 2,000
feet per minute and late arming of
approach mode. The high descent rate is
maintained by the autopilot and can
result in the airplane descending below
the glideslope beam, which requires the
flight crew to correct the problem
manually. Boeing has developed an
upgrade to the FCC OPS for certain
affected airplanes equipped with
Rockwell Collins FCCs that corrects the
glideslope capture problem. The FAA is
proposing this AD to address this
condition, which can result in
controlled flight into terrain on
airplanes that do not have the upgraded
FCC OPS installed.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 737–22A1322
RB, dated November 21, 2018. The
service information describes
procedures for installing and testing an
updated version of the FCC OPS.
This proposed AD would also require
Boeing Alert Service Bulletin 737–
E:\FR\FM\27FEP1.SGM
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]]>Agencies
[Federal Register Volume 85, Number 39 (Thursday, February 27, 2020)]
[Proposed Rules]
[Pages 11315-11319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-03932]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising an earlier proposal for Airbus Helicopters
Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and Model
MBB-BK 117 D-2 helicopters. This action revises the notice of proposed
rulemaking (NPRM) by changing one of the required actions. The FAA is
proposing this airworthiness directive (AD) to address the unsafe
condition on these products. Since these actions impose an additional
burden over that proposed in the NPRM, the FAA is reopening the comment
period to allow the public the chance to comment on these proposed
changes.
DATES: The comment period for the NPRM published in the Federal
Register on December 5, 2017 (82 FR 57390), is reopened. The FAA must
receive comments on this SNPRM by April 27, 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.
[[Page 11316]]
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1123; 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 proposed AD, the European 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: 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
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.
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.
Discussion
The FAA issued an NPRM to amend 14 CFR part 39 to remove AD 2017-
02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017) (``AD 2017-
02-07'') and add a new AD. AD 2017-02-07 applies to Airbus Helicopters
Model MBB-BK 117 C-2 helicopters, serial numbers up to and including
9750, and Model MBB-BK 117 D-2 helicopters, serial numbers up to and
including 20110, with a hydraulic module plate assembly part number
B291M0003103 with a single locking attachment point installed. AD 2017-
02-07 requires a repetitive inspection and a one-time torque of the
hydraulic module plate assembly attachment points (attachment points).
The actions in AD 2017-02-07 are intended to prevent failure of an
attachment point, loss of the hydraulic module plate, and subsequent
loss of control of the helicopter.
The NPRM published in the Federal Register on December 5, 2017 (82
FR 57390). The NPRM proposed to retain the initial inspection and
torque requirements of AD 2017-02-07 and require replacing the single
locking attachment mechanisms with double locking attachment
mechanisms. The NPRM was prompted by EASA AD No. 2017-0047, dated March
13, 2017, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition on Airbus
Helicopters Deutschland GmbH (formerly Eurocopter Deutschland GmbH)
Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2 and MBB-BK117 D-2m
helicopters. EASA advises that the hydraulic plate assembly on certain
MBB-BK117 models has four attachment points on the fuselage secured by
a single locking mechanism. According to EASA, a design reassessment
revealed stiffness of the hydraulic plate may be insufficient to
withstand the in-service loads in the event one of the four single
locking attachment points fails. The EASA AD requires a repetitive
inspection and one-time torque tightening of the attachment points
until replacement of the single locking attachment hardware with double
locking attachment hardware.
Actions Since the NPRM Was Issued
Since the NPRM was issued, Airbus Helicopters revised its service
information by adding a requirement to reposition the aft grounding
straps and inspect the clamping effect of the aft attachment points
when the double locking attachment hardware is installed. The revised
service information also has an alternative clamp effect inspection for
helicopters that have previously installed the double locking
attachment hardware. These additional actions address the unsafe
condition by ensuring the correct torque is applied and the bolts do
not loosen. The FAA is proposing this SNPRM to include these additional
actions.
Further, the FAA has corrected an error in the NPRM proposing to
apply a torque of 9 to 10 Nm to the left-hand and right-hand nuts of
each attachment point. This torque adjustment is only necessary for
each forward (not aft) attachment point.
Lastly, the website address for Airbus Helicopters has also
changed. This website address has been updated throughout this SNPRM.
Comments
The FAA gave the public the opportunity to comment on the original
NPRM (82 FR 57390, December 5, 2017). The FAA received no comments on
that NPRM or on the determination of the cost to the public.
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 SNPRM
after evaluating all information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs. Certain changes described above
expand the scope of the original NPRM. As a result, the FAA has
determined that it is necessary to reopen the comment period to provide
additional opportunity for the public to comment on this SNPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. ASB MBB-BK117 C-2-29A-003 for Model MBB-BK 117 C-2 helicopters and
ASB No. ASB MBB-BK117 D-2-29A-001 for Model MBB-BK 117 D-2 helicopters,
both Revision 3 and dated December 19, 2017. Until the attachment
points are modified with double locking attachment mechanisms, this
service information specifies a repetitive visual inspection for
condition and correct installation of the attachment points and
replacing the affected parts if there is a crack. This service
information also
[[Page 11317]]
specifies a tightening torque check of the forward attachment points
after the initial inspection and replacing the affected parts if torque
cannot be applied. This service information specifies procedures to
replace the single locking attachment hardware with double locking
attachment hardware.
For certain helicopters with a hydraulic module plate assembly with
the double locking attachment hardware installed, this revision of the
service information contains procedures to inspect the clamping effect
of the aft attachment points and torque tightening the screw joints
(bolts). If a bolt can be turned while applying this torque, the
service information specifies instructions to replace the split pin,
washer, and self-locking castellated nut, check the bolt for wear and
replace it if necessary, change the position of the aft grounding
strap, check the electrical bonding, and apply PU-Lacquer to the
grounding connection.
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 Airbus Helicopters ASB No. ASB MBB-BK117 C-2-
29A-003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117
D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 1 and
dated October 14, 2016, and both Revision 2 and dated February 1, 2017.
Revisions 1 and 2 of this service information contain the same visual
inspection and torque tightening check procedures as Revision 3.
Revision 2 of this service information adds the procedures to replace
the single locking attachment hardware with double locking attachment
hardware and contains the same forward locking attachment hardware
replacement procedures as Revision 3.
Proposed Requirements of the SNPRM
For helicopters with a hydraulic module plate assembly with the
single locking attachment hardware installed, this proposed AD would
require, within 100 hours time-in-service (TIS), performing a visual
inspection of each attachment point of the hydraulic module plate
assembly for a crack and proper installation, and applying torque to
the nuts of each forward attachment point. Within 300 hours TIS, this
proposed AD would require replacing each single locking attachment
point mechanism with a double locking attachment point mechanism.
For helicopters with a hydraulic module plate assembly with double
locking attachment hardware installed in accordance with Airbus
Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 or ASB No. ASB MBB-BK117
D-2-29A-001, both Revision 2 and dated February 1, 2017, this proposed
AD would require, within 300 hours TIS, inspecting the clamping effect
of the aft joints and torque tightening the bolts. If a bolt can be
turned while applying torque, this proposed AD would require removing
the split pin and self-locking castellated nut from service, inspecting
the bolt for wear and replacing it if necessary, repositioning the aft
grounding strap to the opposite side of the attachment point, replacing
the washer, installing a new self-locking castellated nut, inspecting
the electrical bonding, installing a new split pin, and applying
lacquer to the grounding connection.
Differences Between This SNPRM and the EASA AD
The EASA AD specifies performing the visual inspection of each
attachment point at intervals not exceeding 400 flight hours. This
proposed AD would not require a repetitive inspection. This proposed AD
would require the replacement of each single locking attachment point
mechanism with a double locking attachment point mechanism within 300
hours TIS instead, which would make subsequent inspections unnecessary.
Since EASA has not revised or superseded its AD to incorporate Revision
3 of the service information, the EASA AD does not require inspecting
the clamping effect of the aft joints, torque tightening the bolts, and
corrective action if necessary for helicopters with a hydraulic module
plate assembly with double locking attachment hardware installed in
accordance with Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 or
ASB No. ASB MBB-BK117 D-2-29A-001, both Revision 2 and dated February
1, 2017.
Costs of Compliance
The FAA estimates that this proposed AD affects 167 helicopters of
U.S. Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. The FAA estimates the cost of
labor at $85 per work-hour.
Visually inspecting the four attachment points would take about
0.75 work-hour for an estimated cost of $64 per helicopter and $10,688
for the U.S. fleet. Inspecting the torque of the four attachment points
would take about 0.25 work-hour for an estimated cost of $21 per
helicopter and $3,507 for the U.S. fleet. Replacing any of the
attachment point parts would take a minimal amount of time and parts
would cost about $48 per attachment point. Installing four double
locking attachment point mechanisms would take a minimal amount of time
and parts would cost about $400 per helicopter and $66,800 for the U.S.
fleet.
For certain double locking attachment hardware aft joints,
inspecting the clamping effect and applying torque would take about 1
work-hour for an estimated cost of $85 per helicopter. If required,
inspecting and replacing parts, repositioning the aft grounding strap,
inspecting the electrical bonding, and applying lacquer to the
grounding connection would take about 0.5 work-hour and parts would
cost about $15 for an estimated cost of $58 per helicopter.
According to Airbus Helicopters' service information, some of the
costs of this proposed AD may be covered under warranty, thereby
reducing the cost impact on affected individuals. The FAA does not
control warranty coverage by Airbus Helicopters. Accordingly, the FAA
has included all costs in this cost estimate.
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.
[[Page 11318]]
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 removing airworthiness directive (AD)
2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017), and
adding the following new AD:
Airbus Helicopters Deutschland GmbH: Docket No. FAA-2017-1123;
Product Identifier 2017-SW-013-AD.
(a) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model
MBB-BK 117 C-2 helicopters, serial numbers up to and including 9750,
and Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-2
helicopters, serial numbers up to and including 20110, certificated
in any category, with a hydraulic module plate assembly part number
B291M0003103 with a single locking attachment point installed or
with a double locking attachment point installed before the
effective date of this AD in accordance with Airbus Helicopters
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-
BK117 C-2-29A-003 Rev 2) or ASB No. ASB MBB-BK117 D-2-29A-001 (ASB
MBB-BK117 D-2-29A-001 Rev 2), both Revision 2 and dated February 1,
2017, as applicable to your model helicopter.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a hydraulic
module plate assembly attachment point (attachment point). This
condition could result in loss of the hydraulic module plate and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD replaces 2017-02-07, Amendment 39-18786 (82 FR 10267,
February 10, 2017).
(d) Comments Due Date
The FAA must receive comments by April 27, 2020.
(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
Comply with either paragraphs (f)(1) and (2) of this AD, or
paragraph (f)(3) of this AD, as applicable to your helicopter.
(1) For helicopters with a hydraulic module plate assembly with
a single locking attachment hardware installed, within 100 hours
time-in-service (TIS):
(i) Visually inspect the split pins, castellated nuts, plugs,
nuts, and hexagon bolts of each attachment point for a crack and for
proper installation by following the Accomplishment Instructions,
paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB
No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-BK117 C-2-29A-003 Rev 3) or
Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 (ASB MBB-BK117
D-2-29A-001 Rev 3), both Revision 3 and dated December 19, 2017, as
applicable to your model helicopter. Replace any part that has a
crack before further flight. If the split pins, castellated nuts, or
hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB-
BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, before
further flight, properly install them.
(ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and
right-hand (RH) nuts of each forward attachment point. If a torque
of 9 to 10 Nm cannot be applied, replace the affected nut before
further flight.
(2) For helicopters with a hydraulic module plate assembly with
a single locking attachment hardware installed, within 300 hours
TIS:
(i) Replace each forward single locking attachment hardware with
double locking attachment hardware by following the Accomplishment
Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB
MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as
applicable to your model helicopter, except you are not required to
discard old parts.
(ii) Replace each aft single locking attachment hardware with
double locking attachment hardware and reposition the LH and RH aft
grounding straps by following the Accomplishment Instructions,
paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB-BK117 C-
2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to
your model helicopter, except you are not required to discard old
parts.
(3) If you have replaced the attachment hardware with double
locking attachment hardware before the effective date of this AD in
accordance with ASB MBB-BK117 C-2-29A-003 Rev 2 or ASB MBB-BK117 D-
2-29A-001 Rev 2, as applicable to your model helicopter: Within 300
hours TIS, inspect the clamping effect of the LH and RH aft screw
joints (bolts) of the hydraulic module plate by following the
Accomplishment Instructions, paragraph 3.B.5., of ASB MBB-BK117 C-2-
29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to
your model helicopter, except you are not required to discard old
parts.
Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters refers
to bolts as ``screw joints.''
(g) Credit for Previous Actions
Actions accomplished before the effective date of this AD in
accordance with the procedures specified in the following are
considered acceptable for compliance with the corresponding actions
in paragraph (f)(1) of this AD:
(1) AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10,
2017).
(2) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003,
Revision 1, dated October 14, 2016.
(3) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003,
Revision 2, dated February 1, 2017.
(4) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001,
Revision 1, dated October 14, 2016.
(5) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001,
Revision 2, dated February 1, 2017.
(h) 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, 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.
(i) Additional Information
(1) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 and ASB
No. ASB MBB-BK117 D-2-29A-001, both Revision 1 and dated October 14,
2016, and both Revision 2 and dated February 1, 2017, which are not
incorporated by reference, contain 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 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 European Aviation
Safety Agency (EASA) AD No. 2017-0047, dated March 13, 2017. You may
view the EASA AD on the internet at https://www.regulations.gov in
Docket No. FAA-2017-1123.
[[Page 11319]]
(j) Subject
Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic
Power System.
Issued in Fort Worth, Texas, on February 14, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-03932 Filed 2-26-20; 8:45 am]
BILLING CODE 4910-13-P
