Airworthiness Directives; Airbus Helicopters, 80689-80693 [2020-27416]
Download as PDF
<![CDATA[
Note 1 to paragraph (g)(1): In ‘‘TA/RA’’
mode, the TA stands for traffic advisory and
RA stands for resolution advisory.
(2) In addition to the provisions of 14 CFR
43.3 and 43.7, the actions required by
paragraphs (g)(1)(i) through (iii) of this AD
may be performed by the owner/operator
(pilot) holding at least a private pilot
certificate and must be entered into the
aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9(a)(1)
through (4) and 14 CFR 91.417(a)(2)(v). The
record must be maintained as required by 14
CFR 91.417. This authority is not applicable
to aircraft being operated under 14 CFR part
119.
(3) Within 12 months after the effective
date of this AD, upgrade the FDSA–6500
field loadable software for your airplane as
listed in the table in Section C and by
following the instructions in Section F of
Rockwell Collins Service Information Letter
FDSA–6500–19–1, Revision No. 2, dated June
12, 2019.
(4) The airplane flight manual revision and
placards required by paragraph (g)(1) of this
AD may be removed after completing the
software upgrade required by paragraph (g)(3)
of this AD.
(5) As of the effective date of this AD, do
not install a Rockwell Collins Flight Display
System Application FDSA–6500 P/N 810–
0234–1H0001, 810–0234–1H0002, 810–
0234–1H0003, 810–0234–2H0001, 810–
0234–2C0001, 810–0234–2C0002, or 810–
0234–4B0001 on any airplane.
VerDate Sep<11>2014
20:48 Dec 11, 2020
Jkt 253001
80689
(h) Alternative Methods of Compliance
(AMOCs)
the availability of this material at the FAA,
call (816) 329–4148.
(1) The Manager, Wichita ACO 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 manager of the
certification office, send it to the attention of
the person identified in Related Information.
(2) 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.
Issued on December 8, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(i) Related Information
(1) For more information about this AD,
contact Nhien Hoang, Aviation Safety
Engineer, Wichita ACO Branch, FAA, 1801
Airport Road, Room 100, Wichita, Kansas
67209; phone: (316) 946–4157; fax: (316)
946–4107; email: nhien.hoang@faa.gov or
Wichita-COS@faa.gov.
(2) For service information identified in
this AD, contact Rockwell Collins, Inc. at
Collins Aviation Services, 400 Collins Road
NE, M/S 164–100, Cedar Rapids, IA 52498–
0001; phone: (319) 295–9258; fax: (319) 295–
4351; email: techmanuals@
rockwellcollins.com; website: https://
www.rockwellcollins.com/Services_and_
Support/Publications.aspx. You may view
this referenced service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
[FR Doc. 2020–27281 Filed 12–11–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1123; Project
Identifier MCAI–2020–01294–R]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2016–23–05, which applies to certain
Airbus Helicopters Model SA–365N1,
AS–365N2, AS 365 N3, SA–366G1, EC
155B, and EC155B1 helicopters. AD
2016–23–05 requires repetitive checks
of the oil level of the tail rotor gearbox
and, if necessary, filling the oil to the
SUMMARY:
E:\FR\FM\14DEP1.SGM
14DEP1
EP14DE20.087</GPH>
jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules
80690
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules
maximum level; and replacement of a
certain control rod double bearing
(bearing) with a new bearing. Since
issuing AD 2016–23–05, the FAA has
determined additional inspections,
replacements, and modifications are
necessary to address the unsafe
condition. This proposed AD would
retain the requirements of AD 2016–23–
05 and would add helicopters to the
applicability. This proposed AD would
also require modifying the helicopter by
replacing the tail gearbox (TGB) control
shaft guide bushes; repetitive
inspections of the TGB magnetic plug
and corrective actions if necessary;
repetitive replacements of the bearing;
and modifying the helicopter by
replacing the TGB; as specified in a
European Union Aviation Safety Agency
(EASA) AD, which will be incorporated
by reference. 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 January 28,
2021.
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
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 material incorporated by reference
(IBR) in this AD, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call 817–222–5110. It is also available in
the AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
1123.
jbell on DSKJLSW7X2PROD with PROPOSALS
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
VerDate Sep<11>2014
20:48 Dec 11, 2020
Jkt 253001
and locating Docket No. FAA–2020–
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 NPRM, 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:
Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section,
International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA
98198; telephone and fax 206–231–
3218; email kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views about this
proposal. 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 submit only one
copy of the comments. Send your
comments to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA 20_2020–1123; Project Identifier
MCAI–2020–01294–R’’ at the beginning
of your comments.
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 post all comments
received, without change, 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 by
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 NPRM because of those comments.
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
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
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 Kathleen Arrigotti,
Aviation Safety Engineer, Large Aircraft
Section, International Validation
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax
206–231–3218; email
kathleen.arrigotti@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Discussion
The FAA issued AD 2016–23–05,
Amendment 39–18712 (81 FR 85126,
November 25, 2016) (‘‘AD 2016–23–
05’’), which applies to certain Airbus
Helicopters Model SA–365N1, AS–
365N2, AS 365 N3, SA–366G1, EC 155B,
and EC155B1 helicopters. AD 2016–23–
05 requires repetitive checks of the oil
level of the tail rotor gearbox and, if
necessary, filling the oil to the
maximum level; and replacement of a
certain bearing with a new partnumbered bearing. The FAA issued AD
2016–23–05 to address damage to the
bearing, which could result in end play,
loss of tail rotor pitch control, and
subsequent loss of control of the
helicopter.
Actions Since AD 2016–23–05 Was
Issued
Since the FAA issued AD 2016–23–
05, the FAA has determined additional
repetitive inspections of the TGB
magnetic plug for the presence of
particles (and corrective actions if
necessary), repetitive replacements of
the bearing, and modifications
(replacing TGB control shaft guide
bushes and replacing the TGB) are
necessary to address the unsafe
condition.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2017–0125, dated July 21, 2017 (‘‘EASA
AD 2017–0125’’) (also referred to as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Helicopters Model SA 365 N1, AS 365
N2, AS 365 N3, SA 366 G1, EC 155 B,
and EC 155 B1 helicopters. EASA AD
2017–0125 supersedes EASA AD 2017–
0007, dated January 13, 2017, which
superseded EASA AD 2016–0097R1,
dated May 25, 2016 (which corresponds
to FAA AD 2016–23–05). EASA AD
2017–0125 adds helicopters to the
E:\FR\FM\14DEP1.SGM
14DEP1
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules
applicability, adds repetitive
inspections of the magnetic plug after
bearing replacement, requires the use of
the revised Airbus Helicopters Alert
Service Bulletin (ASB) instructions, and
requires replacement of the TGB with a
modified unit, which terminates the
repetitive inspections.
This proposed AD was prompted by
a determination that additional
inspections, replacements, and
modifications are necessary to address
the unsafe condition. The FAA is
proposing this AD to address damage to
the bearing, which could result in end
play, loss of tail rotor pitch control, and
subsequent loss of control of the
helicopter. See the MCAI for additional
background information.
Comments on AD 2016–23–05
The FAA gave the public the
opportunity to comment on AD 2016–
23–05. The following presents the
comments received on AD 2016–23–05
and the FAA’s response to each
comment.
jbell on DSKJLSW7X2PROD with PROPOSALS
Request To Revise the Applicability To
Exclude Certain TGBs
A commenter requested that the FAA
revise the applicability of AD 2016–23–
05 to exclude TGBs that are post-Airbus
Helicopters mod 07 65B63 having part
number (P/N) 365A33–6005–09. The
commenter stated that the referenced
service information clarifies that only
TGBs that are pre-Airbus Helicopters
mod 07 65B63 are affected.
The FAA disagrees. In developing AD
2016–23–05, the FAA differed with
EASA AD 2016–0097R1, dated May 25,
2016, and the referenced service
information. The FAA determined that
TGBs that are post-Airbus Helicopters
mod 07 65B63 having P/N 365A33–
6005–09 should not be excluded from
the requirements of that AD. However,
the FAA notes that the new MCAI
addresses TGBs that are pre-Airbus
Helicopters mod 07 65B63 and TGBs
that are post-Airbus Helicopters mod 07
65B63 separately, as does this proposed
AD.
Request To Revise the Applicability To
Include All TGBs
A commenter requested that the FAA
revise the applicability of AD 2016–23–
05 to include all TGBs. The commenter
stated the applicability for AD 2016–23–
05 should be the same as AD 2007–25–
08, Amendment 39–15290 (72 FR
69604, December 10, 2007), which
VerDate Sep<11>2014
20:48 Dec 11, 2020
Jkt 253001
included all bearings, regardless of the
part number of the TGB.
The FAA disagrees. In developing AD
2016–23–05, the FAA determined the
requirement to check the oil level is
only necessary for helicopters with a
TGB bearing having P/N 704A33–651–
093 or P/N 704A33–651–104. However,
the FAA notes that the new MCAI
requires the oil level check for all TGBs,
as does this proposed AD.
Related Service Information Under 1
CFR Part 51
EASA AD 2017–0125 describes
procedures for modifying the helicopter
by replacing TGB control shaft guide
bushes, repetitive inspections (checks)
of the oil level of the tail rotor gearbox
and, if necessary, filling the oil to the
maximum level, repetitive inspections
of the TGB magnetic plug for the
presence of particles and corrective
actions if necessary (corrective actions
include removing the TGB, complying
with certain work cards to address
particles and other conditions such as
abrasions, scales, flakes, and splinters,
and replacing the bearing), repetitive
replacements of the bearing; and
modifying the helicopter by replacing
the TGB.
This material 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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to the
bilateral agreement with the State of
Design Authority, the FAA has been
notified of the unsafe condition
described in the MCAI referenced
above. The FAA is proposing this AD
because the FAA evaluated all the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
in other products of the same type
design.
Proposed AD Requirements
This proposed AD would retain the
actions required by AD 2016–23–05 and
would require accomplishing the
actions specified in EASA AD 2017–
0125 described previously, as
incorporated by reference, except for
any differences identified as exceptions
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
80691
in the regulatory text of this AD and
except as discussed under ‘‘Differences
Between this Proposed AD and the
MCAI.’’
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA initially worked with
Airbus and EASA to develop a process
to use certain EASA ADs as the primary
source of information for compliance
with requirements for corresponding
FAA ADs. The FAA has since
coordinated with other manufacturers
and civil aviation authorities (CAAs) to
use this process. As a result, EASA AD
2017–0125 will be incorporated by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2017–0125
in its entirety, through that
incorporation, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
Using common terms that are the same
as the heading of a particular section in
the EASA AD does not mean that
operators need comply only with that
section. For example, where the AD
requirement refers to ‘‘all required
actions and compliance times,’’
compliance with this AD requirement is
not limited to the section titled
‘‘Required Action(s) and Compliance
Time(s)’’ in the EASA AD. Service
information specified in EASA AD
2017–0125 that is required for
compliance with EASA AD 2017–0125
will be available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–1123 after the FAA final
rule is published.
Explanation of Retained Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2016–23–05, this proposed AD would
retain certain requirements of AD 2016–
23–05. Those requirements are
referenced in paragraphs (2) and (5) of
EASA AD 2017–0125, which, in turn, is
referenced in paragraph (g) of this
proposed AD.
Costs of Compliance
The FAA estimates that this proposed
AD affects 52 helicopters of U.S.
registry. The FAA estimates the
following costs to comply with this
proposed AD:
E:\FR\FM\14DEP1.SGM
14DEP1
80692
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Retained actions from AD 2016–23–05 .........
New proposed actions ....................................
17 work-hours × $85 per hour = $1,445 ........
63 work-hours × 85 per hour = 5,355 ............
$1,125
1,395
Cost per
product
$2,570
6,750
Cost on U.S.
operators
$133,640
351,000
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Parts cost
Cost per
product
8 work-hours × $85 per hour = $680 ......................................................................................................................
$0
$680
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for the oncondition actions specified in this
proposed AD.
According to the manufacturer, some
or all of the costs of this proposed AD
may be covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known 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.
jbell on DSKJLSW7X2PROD with PROPOSALS
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 above, I
certify this proposed regulation:
VerDate Sep<11>2014
20:48 Dec 11, 2020
Jkt 253001
(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)
2016–23–05, Amendment 39–18712 (81
FR 85126, November 25, 2016), and
adding the following new AD:
■
Airbus Helicopters: Docket No. FAA–2020–
1123; Project Identifier MCAI–2020–
01294–R.
(a) Comments Due Date
The FAA must receive comments by
January 28, 2021.
(b) Affected Airworthiness Directives (ADs)
This AD replaces AD 2016–23–05,
Amendment 39–18712 (81 FR 85126,
November 25, 2016) (‘‘AD 2016–23–05’’).
(c) Applicability
This AD applies to Airbus Helicopters
Model SA–365N1, AS–365N2, AS 365 N3,
SA–366G1, EC 155B, and EC155B1
helicopters, certificated in any category, all
serial numbers.
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
(d) Subject
Joint Aircraft System Component (JASC)
Code 65, Tail Rotor.
(e) Reason
This AD was prompted by reports of
occurrences of loss of yaw control due to
failure of the tail gearbox (TGB) control rod
double bearing (bearing). This AD was also
prompted by the determination that
additional inspections, replacements, and
modifications are necessary to address the
unsafe condition. The FAA is issuing this AD
to address damage to the bearing, which
could result in end play, loss of tail rotor
pitch control, and subsequent loss of control
of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(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 Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD 2017–0125, dated
July 21, 2017 (‘‘EASA AD 2017–0125’’).
(h) Exceptions to EASA AD 2017–0125
(1) Where EASA AD 2017–0125 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2017–0125 refers to
June 4, 2011 (the effective date of EASA AD
2011–0105), this AD requires using the
effective date of this AD.
(3) Where EASA AD 2017–0125 refers to
May 25, 2016 (the effective date of EASA AD
2016–0197R1), this AD requires using the
effective date of this AD.
(4) The ‘‘Remarks’’ section of EASA AD
2017–0125 does not apply to this AD.
(5) Where paragraph (2) of EASA AD 2017–
0125 requires inspections (checks) to be done
‘‘in accordance with the instructions of
Paragraph 3.B.1 of the applicable inspection
ASB,’’ for this AD, those instructions are for
reference only and are not required for the
actions in paragraph (2) of EASA AD 2017–
0125. The inspections (checks) required by
paragraph (2) of EASA AD 2017–0125 may be
performed by the owner/operator (pilot)
holding at least a private pilot certificate and
must be entered into the aircraft records
showing compliance with this AD in
E:\FR\FM\14DEP1.SGM
14DEP1
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules
jbell on DSKJLSW7X2PROD with PROPOSALS
accordance with 14 CFR 43.9 (a)(1) through
(4) and 14 CFR 91.417(a)(2)(v). The record
must be maintained as required by 14 CFR
91.417, 121.380, or 135.439.
(6) Where paragraph (5) of EASA AD 2017–
0125 specifies to ‘‘accomplish the applicable
corrective action(s) in accordance with the
instructions of Paragraph 3.B.1 of the
applicable inspection ASB,’’ for this AD, a
qualified mechanic must add oil to the TGB
to the ‘‘max’’ level if the oil level is not at
maximum. The instructions are for reference
only and are not required for the actions in
paragraph (5) of EASA AD 2017–0125.
(7) Where EASA AD 2017–0125 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(8) Where EASA AD 2017–0125 requires
action after the last flight of the day or
‘‘ALF,’’ this AD requires those actions before
the first flight of the day.
(9) Where the service information referred
to in EASA AD 2017–0125 specifies to
perform a metallurgical analysis and contact
the manufacturer if collected particles are not
clearly characterized, this AD does not
require contacting the manufacturer to
determine the characterization of the
particles collected.
(10) Although service information
referenced in EASA AD 2017–0125 specifies
to scrap parts, this AD does not include that
requirement.
(11) Although service information
referenced in EASA AD 2017–0125 specifies
reporting information to Airbus Helicopters
and filling in a ‘‘particle dectection’’ followup sheet, this AD does not include those
requirements.
(12) Although service information
referenced in EASA AD 2017–0125 specifies
returning certain parts to an approved
workshop, this AD does not include that
requirement.
(13) Where paragraph (6) of EASA AD
2017–0125 refers to ‘‘any discrepancy,’’ for
this AD, discrepancies include the presence
of particles and other conditions such as
abrasions, scales, flakes, and splinters.
(i) Alternative Methods of Compliance
(AMOCs):
The Manager, 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 International Validation Branch, send
it to the attention of the person identified in
paragraph (j)(2) of this AD. Information may
be emailed to: 9-AVS-AIR-730-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.
(j) Related Information
(1) For information about EASA AD 2017–
0125, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 8999 000; email ADs@
easa.europa.eu; internet
VerDate Sep<11>2014
20:48 Dec 11, 2020
Jkt 253001
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, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX 76177.
For information on the availability of this
material at the FAA, call 817–222–5110. 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–2020–1123.
(2) For more information about this AD,
contact Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@faa.gov.
Issued on December 8, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–27416 Filed 12–11–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0819; Project
Identifier 2019–CE–027–AD]
RIN 2120–AA64
Airworthiness Directives; Textron
Aviation Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
97–06–10, which applies to certain
Raytheon Aircraft Company (type
certificate now held by Textron
Aviation Inc. (Textron)) Model 76
airplanes. AD 97–06–10 requires
repetitively inspecting the main landing
gear (MLG) ‘‘A’’ frame assemblies for
cracks and replacing any cracked
assembly. Since the FAA issued AD 97–
06–10, the replacement parts have also
experienced failure due to cracking.
This proposed AD would require
magnetic particle inspections of the
MLG ‘‘A’’ frame assemblies for cracks
and replacement of the affected parts if
necessary. 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 January 28,
2021.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
SUMMARY:
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
80693
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
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 Textron Aviation
Customer Service, P.O. Box 7706,
Wichita, Kansas 67277; phone: (316)
517–5800; email: customercare@
txtav.com; website: https://txtav.com.
You may view this service information
at the FAA, Airworthiness Products
Section, Operational Safety Branch, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0819; 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, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Brian Adamson, Aviation Safety
Engineer, Wichita ACO Branch, FAA,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; phone: (316) 946–4193;
fax: (316) 946–4107; email:
brian.adamson@faa.gov or WichitaCOS@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–2020–0819; Project
Identifier 2019–CE–027–AD’’ at the
beginning of your comments. The most
helpful comments reference a specific
portion of the final rule, explain the
reason for any recommended change,
and include supporting data. The FAA
will consider all comments received by
the closing date and may amend this
proposal because of those comments.
Except for Confidential Business
Information (CBI) as described in the
E:\FR\FM\14DEP1.SGM
14DEP1
]]>Agencies
[Federal Register Volume 85, Number 240 (Monday, December 14, 2020)]
[Proposed Rules]
[Pages 80689-80693]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27416]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1123; Project Identifier MCAI-2020-01294-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2016-23-05, which applies to certain Airbus Helicopters Model SA-365N1,
AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD
2016-23-05 requires repetitive checks of the oil level of the tail
rotor gearbox and, if necessary, filling the oil to the
[[Page 80690]]
maximum level; and replacement of a certain control rod double bearing
(bearing) with a new bearing. Since issuing AD 2016-23-05, the FAA has
determined additional inspections, replacements, and modifications are
necessary to address the unsafe condition. This proposed AD would
retain the requirements of AD 2016-23-05 and would add helicopters to
the applicability. This proposed AD would also require modifying the
helicopter by replacing the tail gearbox (TGB) control shaft guide
bushes; repetitive inspections of the TGB magnetic plug and corrective
actions if necessary; repetitive replacements of the bearing; and
modifying the helicopter by replacing the TGB; as specified in a
European Union Aviation Safety Agency (EASA) AD, which will be
incorporated by reference. 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 January 28,
2021.
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 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 material incorporated by reference (IBR) in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49
221 8999 000; email [email protected]; internet www.easa.europa.eu.
You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of this
material at the FAA, call 817-222-5110. It is also available in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2020-1123.
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-
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 NPRM, 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: Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section, International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-
3218; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views about this proposal. 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 submit only one copy of the comments. Send your comments to an
address listed under the ADDRESSES section. Include ``Docket No. FAA
20_2020-1123; Project Identifier MCAI-2020-01294-R'' at the beginning
of your comments.
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 post all comments received, without change, 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 by 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 NPRM because of those
comments.
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
Kathleen Arrigotti, Aviation Safety Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200 South 216th St., Des Moines,
WA 98198; telephone and fax 206-231-3218; email
[email protected]. Any commentary that the FAA receives which
is not specifically designated as CBI will be placed in the public
docket for this rulemaking.
Discussion
The FAA issued AD 2016-23-05, Amendment 39-18712 (81 FR 85126,
November 25, 2016) (``AD 2016-23-05''), which applies to certain Airbus
Helicopters Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and
EC155B1 helicopters. AD 2016-23-05 requires repetitive checks of the
oil level of the tail rotor gearbox and, if necessary, filling the oil
to the maximum level; and replacement of a certain bearing with a new
part-numbered bearing. The FAA issued AD 2016-23-05 to address damage
to the bearing, which could result in end play, loss of tail rotor
pitch control, and subsequent loss of control of the helicopter.
Actions Since AD 2016-23-05 Was Issued
Since the FAA issued AD 2016-23-05, the FAA has determined
additional repetitive inspections of the TGB magnetic plug for the
presence of particles (and corrective actions if necessary), repetitive
replacements of the bearing, and modifications (replacing TGB control
shaft guide bushes and replacing the TGB) are necessary to address the
unsafe condition.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2017-0125, dated July 21, 2017
(``EASA AD 2017-0125'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus Helicopters Model SA 365 N1, AS 365 N2, AS 365
N3, SA 366 G1, EC 155 B, and EC 155 B1 helicopters. EASA AD 2017-0125
supersedes EASA AD 2017-0007, dated January 13, 2017, which superseded
EASA AD 2016-0097R1, dated May 25, 2016 (which corresponds to FAA AD
2016-23-05). EASA AD 2017-0125 adds helicopters to the
[[Page 80691]]
applicability, adds repetitive inspections of the magnetic plug after
bearing replacement, requires the use of the revised Airbus Helicopters
Alert Service Bulletin (ASB) instructions, and requires replacement of
the TGB with a modified unit, which terminates the repetitive
inspections.
This proposed AD was prompted by a determination that additional
inspections, replacements, and modifications are necessary to address
the unsafe condition. The FAA is proposing this AD to address damage to
the bearing, which could result in end play, loss of tail rotor pitch
control, and subsequent loss of control of the helicopter. See the MCAI
for additional background information.
Comments on AD 2016-23-05
The FAA gave the public the opportunity to comment on AD 2016-23-
05. The following presents the comments received on AD 2016-23-05 and
the FAA's response to each comment.
Request To Revise the Applicability To Exclude Certain TGBs
A commenter requested that the FAA revise the applicability of AD
2016-23-05 to exclude TGBs that are post-Airbus Helicopters mod 07
65B63 having part number (P/N) 365A33-6005-09. The commenter stated
that the referenced service information clarifies that only TGBs that
are pre-Airbus Helicopters mod 07 65B63 are affected.
The FAA disagrees. In developing AD 2016-23-05, the FAA differed
with EASA AD 2016-0097R1, dated May 25, 2016, and the referenced
service information. The FAA determined that TGBs that are post-Airbus
Helicopters mod 07 65B63 having P/N 365A33-6005-09 should not be
excluded from the requirements of that AD. However, the FAA notes that
the new MCAI addresses TGBs that are pre-Airbus Helicopters mod 07
65B63 and TGBs that are post-Airbus Helicopters mod 07 65B63
separately, as does this proposed AD.
Request To Revise the Applicability To Include All TGBs
A commenter requested that the FAA revise the applicability of AD
2016-23-05 to include all TGBs. The commenter stated the applicability
for AD 2016-23-05 should be the same as AD 2007-25-08, Amendment 39-
15290 (72 FR 69604, December 10, 2007), which included all bearings,
regardless of the part number of the TGB.
The FAA disagrees. In developing AD 2016-23-05, the FAA determined
the requirement to check the oil level is only necessary for
helicopters with a TGB bearing having P/N 704A33-651-093 or P/N 704A33-
651-104. However, the FAA notes that the new MCAI requires the oil
level check for all TGBs, as does this proposed AD.
Related Service Information Under 1 CFR Part 51
EASA AD 2017-0125 describes procedures for modifying the helicopter
by replacing TGB control shaft guide bushes, repetitive inspections
(checks) of the oil level of the tail rotor gearbox and, if necessary,
filling the oil to the maximum level, repetitive inspections of the TGB
magnetic plug for the presence of particles and corrective actions if
necessary (corrective actions include removing the TGB, complying with
certain work cards to address particles and other conditions such as
abrasions, scales, flakes, and splinters, and replacing the bearing),
repetitive replacements of the bearing; and modifying the helicopter by
replacing the TGB.
This material 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the bilateral agreement with the State of Design Authority, the FAA
has been notified of the unsafe condition described in the MCAI
referenced above. The FAA is proposing this AD because the FAA
evaluated all the relevant information and determined the unsafe
condition described previously is likely to exist or develop in other
products of the same type design.
Proposed AD Requirements
This proposed AD would retain the actions required by AD 2016-23-05
and would require accomplishing the actions specified in EASA AD 2017-
0125 described previously, as incorporated by reference, except for any
differences identified as exceptions in the regulatory text of this AD
and except as discussed under ``Differences Between this Proposed AD
and the MCAI.''
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA initially worked with Airbus and EASA to develop a
process to use certain EASA ADs as the primary source of information
for compliance with requirements for corresponding FAA ADs. The FAA has
since coordinated with other manufacturers and civil aviation
authorities (CAAs) to use this process. As a result, EASA AD 2017-0125
will be incorporated by reference in the FAA final rule. This proposed
AD would, therefore, require compliance with EASA AD 2017-0125 in its
entirety, through that incorporation, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Using common terms that are the same as the heading of a particular
section in the EASA AD does not mean that operators need comply only
with that section. For example, where the AD requirement refers to
``all required actions and compliance times,'' compliance with this AD
requirement is not limited to the section titled ``Required Action(s)
and Compliance Time(s)'' in the EASA AD. Service information specified
in EASA AD 2017-0125 that is required for compliance with EASA AD 2017-
0125 will be available on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2020-1123 after the FAA
final rule is published.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2016-23-05, this proposed AD would retain certain
requirements of AD 2016-23-05. Those requirements are referenced in
paragraphs (2) and (5) of EASA AD 2017-0125, which, in turn, is
referenced in paragraph (g) of this proposed AD.
Costs of Compliance
The FAA estimates that this proposed AD affects 52 helicopters of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
[[Page 80692]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2016-23-05... 17 work-hours x $85 per $1,125 $2,570 $133,640
hour = $1,445.
New proposed actions.................. 63 work-hours x 85 per 1,395 6,750 351,000
hour = 5,355.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
8 work-hours x $85 per hour = $680............................................ $0 $680
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this proposed AD.
According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators. The FAA does not control warranty
coverage for affected operators. As a result, the FAA has included all
known 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.
For the reasons discussed above, 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)
2016-23-05, Amendment 39-18712 (81 FR 85126, November 25, 2016), and
adding the following new AD:
Airbus Helicopters: Docket No. FAA-2020-1123; Project Identifier
MCAI-2020-01294-R.
(a) Comments Due Date
The FAA must receive comments by January 28, 2021.
(b) Affected Airworthiness Directives (ADs)
This AD replaces AD 2016-23-05, Amendment 39-18712 (81 FR 85126,
November 25, 2016) (``AD 2016-23-05'').
(c) Applicability
This AD applies to Airbus Helicopters Model SA-365N1, AS-365N2,
AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters, certificated
in any category, all serial numbers.
(d) Subject
Joint Aircraft System Component (JASC) Code 65, Tail Rotor.
(e) Reason
This AD was prompted by reports of occurrences of loss of yaw
control due to failure of the tail gearbox (TGB) control rod double
bearing (bearing). This AD was also prompted by the determination
that additional inspections, replacements, and modifications are
necessary to address the unsafe condition. The FAA is issuing this
AD to address damage to the bearing, which could result in end play,
loss of tail rotor pitch control, and subsequent loss of control of
the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(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 Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2017-0125, dated July 21, 2017
(``EASA AD 2017-0125'').
(h) Exceptions to EASA AD 2017-0125
(1) Where EASA AD 2017-0125 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2017-0125 refers to June 4, 2011 (the
effective date of EASA AD 2011-0105), this AD requires using the
effective date of this AD.
(3) Where EASA AD 2017-0125 refers to May 25, 2016 (the
effective date of EASA AD 2016-0197R1), this AD requires using the
effective date of this AD.
(4) The ``Remarks'' section of EASA AD 2017-0125 does not apply
to this AD.
(5) Where paragraph (2) of EASA AD 2017-0125 requires
inspections (checks) to be done ``in accordance with the
instructions of Paragraph 3.B.1 of the applicable inspection ASB,''
for this AD, those instructions are for reference only and are not
required for the actions in paragraph (2) of EASA AD 2017-0125. The
inspections (checks) required by paragraph (2) of EASA AD 2017-0125
may be performed by the owner/operator (pilot) holding at least a
private pilot certificate and must be entered into the aircraft
records showing compliance with this AD in
[[Page 80693]]
accordance with 14 CFR 43.9 (a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be maintained as required by 14 CFR
91.417, 121.380, or 135.439.
(6) Where paragraph (5) of EASA AD 2017-0125 specifies to
``accomplish the applicable corrective action(s) in accordance with
the instructions of Paragraph 3.B.1 of the applicable inspection
ASB,'' for this AD, a qualified mechanic must add oil to the TGB to
the ``max'' level if the oil level is not at maximum. The
instructions are for reference only and are not required for the
actions in paragraph (5) of EASA AD 2017-0125.
(7) Where EASA AD 2017-0125 refers to flight hours (FH), this AD
requires using hours time-in-service.
(8) Where EASA AD 2017-0125 requires action after the last
flight of the day or ``ALF,'' this AD requires those actions before
the first flight of the day.
(9) Where the service information referred to in EASA AD 2017-
0125 specifies to perform a metallurgical analysis and contact the
manufacturer if collected particles are not clearly characterized,
this AD does not require contacting the manufacturer to determine
the characterization of the particles collected.
(10) Although service information referenced in EASA AD 2017-
0125 specifies to scrap parts, this AD does not include that
requirement.
(11) Although service information referenced in EASA AD 2017-
0125 specifies reporting information to Airbus Helicopters and
filling in a ``particle dectection'' follow-up sheet, this AD does
not include those requirements.
(12) Although service information referenced in EASA AD 2017-
0125 specifies returning certain parts to an approved workshop, this
AD does not include that requirement.
(13) Where paragraph (6) of EASA AD 2017-0125 refers to ``any
discrepancy,'' for this AD, discrepancies include the presence of
particles and other conditions such as abrasions, scales, flakes,
and splinters.
(i) Alternative Methods of Compliance (AMOCs):
The Manager, 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 International Validation Branch, send it to the
attention of the person identified in paragraph (j)(2) of this AD.
Information may be emailed to: [email protected]. 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.
(j) Related Information
(1) For information about EASA AD 2017-0125, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email [email protected]; 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, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call 817-222-5110. 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-
2020-1123.
(2) For more information about this AD, contact Kathleen
Arrigotti, Aviation Safety Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206-231-3218; email
[email protected].
Issued on December 8, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-27416 Filed 12-11-20; 8:45 am]
BILLING CODE 4910-13-P
