Airworthiness Directives; Airbus Helicopters, 56220-56225 [2021-21955]
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(h) Definitions
DEPARTMENT OF TRANSPORTATION
For the purpose of this AD:
(1) An ‘‘engine shop visit’’ is the induction
of an engine into the shop for maintenance
involving the separation of pairs of major
mating engine flanges, except that the
separation of engine flanges solely for the
purposes of transportation without
subsequent engine maintenance does not
constitute an engine shop visit.
(2) A ‘‘part eligible for installation’’ is an
HPT rotor stage 1 disk that is not listed in
Figure 1 or Figure 2 to paragraph (c) of this
AD or an HPT rotor stage 1 disk that has been
repaired using an FAA-approved repair.
Note 1 to paragraph (h)(2): Guidance for
repairing the HPT rotor stage 1 disk can be
found in GE Repair Document RD # 150–
1811–P1, dated March 17, 2020.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 paragraph (j)(1) of this AD.
Information may be emailed to: ANE-ADAMOC@faa.gov.
(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.
(j) Related Information
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(1) For more information about this AD,
contact Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7132; fax: (781) 238–7759; email:
Scott.M.Stevenson@faa.gov.
(2) For service information identified in
this AD, contact General Electric Company,
1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552–3272; email:
aviation.fleetsupport@ae.ge.com; website:
https://www.ge.com. You may view this
referenced service information at the FAA,
Airworthiness Products Section, 1200
District Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (781) 238–7759.
Issued on September 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–21905 Filed 10–7–21; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0872; Project
Identifier MCAI–2021–00312–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)
2020–11–05, which applies to all Airbus
Helicopters Model EC120B helicopters.
AD 2020–11–05 requires repetitive
inspections of the tail rotor (TR) hub
body for cracks and applicable
corrective actions if necessary, and
repetitive replacement of the attachment
bolts, washers, and nuts of the TR hub
body. This proposed AD would retain
certain requirements of AD 2020–11–05,
add repetitive inspections, require
additional corrective actions, and
update applicable service information.
The FAA is proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
The FAA must receive comments
on this proposed AD by November 22,
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 service information identified in
this NPRM, contact Airbus Helicopters,
2701 North 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 this service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
DATES:
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availability of this material at the FAA,
call (817) 222–5110.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0872; 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 European Union Aviation
Safety Agency (EASA) AD, any
comments received, and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance
& Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228–7330; email
andrea.jimenez@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 ADDRESSES. Include ‘‘Docket No.
FAA–2021–0872; Project Identifier
MCAI–2021–00312–R’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, 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
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
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
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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 Andrea Jimenez,
Aerospace Engineer, COS Program
Management Section, Operational
Safety Branch, Compliance &
Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228–7330; email
andrea.jimenez@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.
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Background
The FAA issued AD 2020–11–05,
Amendment 39–21130 (85 FR 31042,
May 22, 2020) (AD 2020–11–05), for
Airbus Helicopters Model EC120B
helicopters, all serial numbers. AD
2020–11–05 requires repetitive
inspections of the TR hub body for
cracks and applicable corrective actions
if necessary, and repetitive replacement
of the attachment bolts, washers, and
nuts of the TR hub body. AD 2020–11–
05 was prompted by EASA AD 2019–
0272R1, dated November 18, 2019
(EASA AD 2019–0272R1), issued by
EASA, which is the Technical Agent for
the Member States of the European
Union, to correct an unsafe condition
for Airbus Helicopters, formerly
Eurocopter, Eurocopter France, Model
EC120 B helicopters. EASA advised that
an inspection of the TR hub body
revealed a recurring loss of tightening
torque on several attachment bolts. This
condition, if not addressed, could result
in cracking and potential loss of the TR
drive and consequent loss of yaw
control of the helicopter.
Accordingly, EASA AD 2019–0272R1
required repetitive inspections of the TR
hub body for cracks and applicable
corrective actions if necessary, as well
as repetitive replacement of the
associated attachment bolts, washers,
and nuts.
Actions Since AD 2020–11–05 Was
Issued
Since the FAA issued AD 2020–11–
05, EASA issued AD 2021–0069, dated
March 11, 2021 (EASA AD 2021–0069),
which supersedes EASA AD 2019–
0272R1. EASA advises that further
detailed analysis showed that a loss of
tightening torque in the interface
between the TR hub body and splined
flange creates the risk of crack initiation
from a fretting area located on the TR
hub body and splined flange or on the
TR hub body and flange bolts.
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Accordingly, EASA AD 2021–0069
retains the requirements of EASA AD
2019–0272R1 and requires additional
repetitive detailed inspections of the
interface between the TR hub body part
number (P/N) C642A0100103 and the
splined flange. Depending on the
inspection results, EASA AD 2021–0069
requires accomplishment of applicable
corrective actions.
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 about the unsafe condition
described in its AD. The FAA is
proposing this AD after evaluating all
known relevant information and
determining that the unsafe condition
described previously is likely to exist or
develop on other helicopters of the same
type designs.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Emergency Alert Service Bulletin
05A020, Revision 2, dated February 8,
2021 (ASB 05A020 Rev 2). This service
information specifies procedures for
repetitive inspections of the TR hub
body for cracks and the TR spline flange
for cracks and fretting and the
appropriate corrective actions.
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.
Proposed AD Requirements in This
NPRM
This proposed AD would retain some
of the requirements of AD 2020–11–05,
and would require, within 15 hours
time-in-service (TIS) or 7 days,
whichever occurs first, performing
repetitive inspections of the TR hub
body for a crack and depending on the
inspection results, removing the affected
parts from service. This proposed AD
would also require inspecting the TR
spline flange for corrosion, impacts,
fretting, wear, and a crack and
depending on the inspection results,
removing the TR splined flange from
service. For helicopters with 9,000 or
more total hours TIS or with unknown
total hours TIS, this proposed AD would
require, within 15 hours TIS or 7 days,
whichever occurs first, and thereafter at
intervals not to exceed 1,000 hours TIS,
removing from service any bolt, washer,
and nut installed on the TR hub body,
replacing them with airworthy parts,
inspecting the TR splined flange, and
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depending on the inspection results,
removing the TR splined flange from
service. This proposed AD would also
require, for helicopters with less than
9,000 total hours TIS, within 1,000
hours TIS or before accumulating 9,000
total hours TIS, whichever occurs first,
and thereafter at intervals not to exceed
1,000 hours TIS, removing from service
any bolt, washer, and nut installed on
the TR hub body replacing them with
airworthy parts, inspecting the TR
splined flange, and depending on the
inspection results, removing the TR
splined flange from service. This
proposed AD would also prohibit the
installation of a certain part-numbered
TR hub body unless certain actions have
been accomplished.
Differences Between This Proposed AD
and EASA AD 2021–0069
EASA AD 2021–0069 uses flight
hours (FH) for certain compliance times,
whereas this proposed AD uses hours
TIS. EASA AD 2021–0069 retains the
compliance time of November 1, 2019
for certain actions, which is the effective
date of EASA AD 2019–0272R1,
whereas this proposed AD would
require compliance as of the effective
date of the proposed AD.
Where Note 1 of EASA AD 2021–0069
allows a non-cumulative tolerance of
100 hours TIS to be applied to the
compliance times for the initial
replacement of bolts, washers, and nuts
(Table 1 of EASA AD 2021–0069) to
allow for synchronization of the
required inspections with other
maintenance tasks, this proposed AD
would not allow a non-cumulative
tolerance of 100 hours TIS to be applied
to the compliance times.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 89
helicopters of U.S. Registry. Labor rates
are estimated at $85 per work-hour.
Based on these numbers, the FAA
estimates the following costs to comply
with this proposed AD.
Visually inspecting each TR hub body
for a crack would take about 0.25 workhour for an estimated cost of $22 per
inspection and $1,958 for the U.S. fleet.
Visually inspecting each TR spline
flange for corrosion, impacts, fretting,
wear, and a crack would take about 0.25
work-hour for an estimated cost of $22
per inspection and $1,958 for the U.S.
fleet.
Replacing a TR hub body would take
about 2 work-hours and parts would
cost about $16,417 for an estimated cost
of $16,587 per TR hub body
replacement.
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(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
This AD was prompted by a report of
recurrent loss of tightening torque on several
attachment bolts on the tail rotor (TR) hub
body. The FAA is issuing this AD to detect
cracking and fretting, which if not addressed,
could result in potential loss of the TR drive
and consequent loss of yaw control of the
helicopter.
The Proposed Amendment
(f) Compliance
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Comply with this AD within the
compliance times specified, unless already
done.
PART 39—AIRWORTHINESS
DIRECTIVES
(1) Within 15 hours time-in-service (TIS) or
7 days, whichever occurs first after the
effective date of this AD, and thereafter at
intervals not to exceed 15 hours TIS, using
a light source and mirror, visually inspect TR
hub body part number (P/N) C642A0100103
for a crack in the entire inspection area
depicted in Figure 1 of Airbus Helicopters
Emergency Alert Service Bulletin 05A020
Revision 2, dated February 8, 2021 (ASB
05A020 Rev 2). If there is a crack, before
further flight, perform the actions in
paragraphs (g)(1)(i) and (ii) of this AD.
(i) Remove the TR hub body and each bolt,
washer, and nut installed on the TR hub
body from service and replace with airworthy
parts.
(ii) Inspect the TR splined flange for
corrosion, impacts, fretting, wear, and a crack
in the areas identified in Figure 2 of this AD.
If the condition of the part (including
corrosion, impacts, fretting, wear, or cracks)
exceeds the criteria as specified in Figure 1
of this AD, before further flight, remove the
splined flange from service and replace with
an airworthy part.
Note 1 to paragraph (g)(1)(ii): You may
refer to ‘‘Detailed Check—Splined Flange,’’
Task 64–21–00, 6–5, Airbus Aircraft
Maintenance Manual (AMM), dated October
15, 2020 which pertains to the TR splined
flange inspection.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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(d) Subject
Replacing a TR spline flange would
take about 0.5 work-hour and parts
would cost about $2,950 for an
estimated cost of $2,993 per TR spline
flange replacement.
Replacing a bolt, washer, and nut
would take about 0.5 work-hour and
parts would cost about $68 for an
estimated cost of $111 per replacement.
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List of Subjects in 14 CFR Part 39
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:
a. Removing Airworthiness Directive
2020–11–05, Amendment 39–21130 (85
FR 31042, May 22, 2020); and
■ b. Adding the following new
airworthiness directive:
■
■
Airbus Helicopters: Docket No. FAA–2021–
0872; Project Identifier MCAI–2021–
00312–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by
November 22, 2021.
(b) Affected ADs
This AD replaces AD 2020–11–05,
Amendment 39–21130 (85 FR 31042, May 22,
2020) (AD 2020–11–05).
(c) Applicability
This AD applies to Airbus Helicopters
Model EC120B helicopters, certificated in
any category, all serial numbers.
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Joint Aircraft Service Component (JASC)
Code: 6400, Tail rotor system.
(e) Unsafe Condition
(g) Required Actions
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(2) For helicopters with 9,000 or more total
hours TIS, or with unknown total hours TIS,
within 15 hours TIS or 7 days, whichever
occurs first after the effective date of this AD,
and thereafter at intervals not to exceed 1,000
hours TIS, remove each bolt, washer, and nut
installed on the TR hub body from service
and replace with airworthy parts and perform
the actions in paragraph (g)(1)(ii) of this AD.
(3) For helicopters with less than 9,000
total hours TIS, within 1,000 hours TIS or
before accumulating 9,000 total hours TIS,
whichever occurs first after the effective date
of this AD, and thereafter at intervals not to
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exceed 1,000 hours TIS, remove each bolt,
washer, and nut installed on the TR hub
body from service and replace with airworthy
parts and perform the actions in paragraph
(g)(1)(ii) of this AD.
(4) As of the effective date of this AD, do
not install TR hub body P/N C642A0100103
on any helicopter, unless the actions of
paragraph (g)(1) of this AD have been
accomplished.
(h) Special Flight Permits
A special flight permit may be permitted
provided that there are no passengers
onboard.
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(i) Alternative Methods of Compliance
(AMOCs)
(1) 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 manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (j)(1) of this AD.
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Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(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.
(j) Related Information
(1) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart
Ave., Suite 410, Westbury, NY 11590;
telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
(2) For service information identified in
this AD, contact Airbus Helicopters, 2701
North 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 this
referenced service information 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.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2021–0069, dated March 11,
2021. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–0872.
Issued on October 1, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–21955 Filed 10–7–21; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0842; Project
Identifier 2019–CE–032–AD]
RIN 2120–AA64
Airworthiness Directives; Stemme AG
Gliders
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Stemme AG Model Stemme S 12
gliders. This proposed AD was
prompted by mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as the incorrect installation of
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SUMMARY:
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an axle connecting the main landing
gear (MLG) to the center steel frame.
This proposed AD would require
inspecting the MLG installation. 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 November 22,
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 service information identified in
this NPRM, contact STEMME AG,
Flugplatzstrasse F2, Nr. 6–7, D–15344
Strausberg, Germany; phone: + 49 (0)
3341 3612–0, fax: + 49 (0) 3341 3612–
30; email: airworthiness@stemme.de;
website: https://www.stemme.com. You
may view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, MO 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–2021–0842; 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 MCAI, any comments
received, and other information. The
street address for Docket Operations is
listed above.
FOR FURTHER INFORMATION CONTACT: Jim
Rutherford, Aviation Safety Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA,
901 Locust, Room 301, Kansas City, MO
64106; phone: (816) 329–4165; fax: (816)
329–4090; email: jim.rutherford@
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 ADDRESSES. Include ‘‘Docket No.
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FAA–2021–0842; Project Identifier
2019–CE–032–AD’’ at the beginning of
your comments. The most helpful
comments reference a specific portion of
the proposal, 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
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
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 Jim Rutherford,
Aviation Safety Engineer, General
Aviation & Rotorcraft Section,
International Validation Branch, FAA,
901 Locust, Room 301, Kansas City, MO
64106. Any commentary that the FAA
receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
Background
The European Union Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0130–E, dated June 7, 2019
(referred to after this as ‘‘the MCAI’’), to
address an unsafe condition on Stemme
AG Model Stemme S 12 gliders. The
MCAI states:
Following a production acceptance flight,
the pilot noticed that the aeroplane was in a
banked position on the ground. Further
examination determined that an axle,
connecting the main landing gear (MLG) leg
to the centre steel frame of the aeroplane, had
E:\FR\FM\08OCP1.SGM
08OCP1
]]>Agencies
[Federal Register Volume 86, Number 193 (Friday, October 8, 2021)]
[Proposed Rules]
[Pages 56220-56225]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-21955]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0872; Project Identifier MCAI-2021-00312-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)
2020-11-05, which applies to all Airbus Helicopters Model EC120B
helicopters. AD 2020-11-05 requires repetitive inspections of the tail
rotor (TR) hub body for cracks and applicable corrective actions if
necessary, and repetitive replacement of the attachment bolts, washers,
and nuts of the TR hub body. This proposed AD would retain certain
requirements of AD 2020-11-05, add repetitive inspections, require
additional corrective actions, and update applicable service
information. 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 November
22, 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 service information identified in this NPRM, contact Airbus
Helicopters, 2701 North 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 this service information 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.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0872; 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 European
Union Aviation Safety Agency (EASA) AD, any comments received, and
other information. The street address for Docket Operations is listed
above.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email [email protected].
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 ADDRESSES. Include ``Docket No. FAA-2021-0872; Project Identifier
MCAI-2021-00312-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, 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 following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
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 56221]]
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 Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; 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.
Background
The FAA issued AD 2020-11-05, Amendment 39-21130 (85 FR 31042, May
22, 2020) (AD 2020-11-05), for Airbus Helicopters Model EC120B
helicopters, all serial numbers. AD 2020-11-05 requires repetitive
inspections of the TR hub body for cracks and applicable corrective
actions if necessary, and repetitive replacement of the attachment
bolts, washers, and nuts of the TR hub body. AD 2020-11-05 was prompted
by EASA AD 2019-0272R1, dated November 18, 2019 (EASA AD 2019-0272R1),
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters, formerly Eurocopter, Eurocopter France, Model EC120 B
helicopters. EASA advised that an inspection of the TR hub body
revealed a recurring loss of tightening torque on several attachment
bolts. This condition, if not addressed, could result in cracking and
potential loss of the TR drive and consequent loss of yaw control of
the helicopter.
Accordingly, EASA AD 2019-0272R1 required repetitive inspections of
the TR hub body for cracks and applicable corrective actions if
necessary, as well as repetitive replacement of the associated
attachment bolts, washers, and nuts.
Actions Since AD 2020-11-05 Was Issued
Since the FAA issued AD 2020-11-05, EASA issued AD 2021-0069, dated
March 11, 2021 (EASA AD 2021-0069), which supersedes EASA AD 2019-
0272R1. EASA advises that further detailed analysis showed that a loss
of tightening torque in the interface between the TR hub body and
splined flange creates the risk of crack initiation from a fretting
area located on the TR hub body and splined flange or on the TR hub
body and flange bolts. Accordingly, EASA AD 2021-0069 retains the
requirements of EASA AD 2019-0272R1 and requires additional repetitive
detailed inspections of the interface between the TR hub body part
number (P/N) C642A0100103 and the splined flange. Depending on the
inspection results, EASA AD 2021-0069 requires accomplishment of
applicable corrective actions.
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 about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that
the unsafe condition described previously is likely to exist or develop
on other helicopters of the same type designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin 05A020, Revision 2, dated February 8, 2021 (ASB 05A020 Rev 2).
This service information specifies procedures for repetitive
inspections of the TR hub body for cracks and the TR spline flange for
cracks and fretting and the appropriate corrective actions.
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.
Proposed AD Requirements in This NPRM
This proposed AD would retain some of the requirements of AD 2020-
11-05, and would require, within 15 hours time-in-service (TIS) or 7
days, whichever occurs first, performing repetitive inspections of the
TR hub body for a crack and depending on the inspection results,
removing the affected parts from service. This proposed AD would also
require inspecting the TR spline flange for corrosion, impacts,
fretting, wear, and a crack and depending on the inspection results,
removing the TR splined flange from service. For helicopters with 9,000
or more total hours TIS or with unknown total hours TIS, this proposed
AD would require, within 15 hours TIS or 7 days, whichever occurs
first, and thereafter at intervals not to exceed 1,000 hours TIS,
removing from service any bolt, washer, and nut installed on the TR hub
body, replacing them with airworthy parts, inspecting the TR splined
flange, and depending on the inspection results, removing the TR
splined flange from service. This proposed AD would also require, for
helicopters with less than 9,000 total hours TIS, within 1,000 hours
TIS or before accumulating 9,000 total hours TIS, whichever occurs
first, and thereafter at intervals not to exceed 1,000 hours TIS,
removing from service any bolt, washer, and nut installed on the TR hub
body replacing them with airworthy parts, inspecting the TR splined
flange, and depending on the inspection results, removing the TR
splined flange from service. This proposed AD would also prohibit the
installation of a certain part-numbered TR hub body unless certain
actions have been accomplished.
Differences Between This Proposed AD and EASA AD 2021-0069
EASA AD 2021-0069 uses flight hours (FH) for certain compliance
times, whereas this proposed AD uses hours TIS. EASA AD 2021-0069
retains the compliance time of November 1, 2019 for certain actions,
which is the effective date of EASA AD 2019-0272R1, whereas this
proposed AD would require compliance as of the effective date of the
proposed AD.
Where Note 1 of EASA AD 2021-0069 allows a non-cumulative tolerance
of 100 hours TIS to be applied to the compliance times for the initial
replacement of bolts, washers, and nuts (Table 1 of EASA AD 2021-0069)
to allow for synchronization of the required inspections with other
maintenance tasks, this proposed AD would not allow a non-cumulative
tolerance of 100 hours TIS to be applied to the compliance times.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 89 helicopters of U.S. Registry. Labor rates are estimated at
$85 per work-hour. Based on these numbers, the FAA estimates the
following costs to comply with this proposed AD.
Visually inspecting each TR hub body for a crack would take about
0.25 work-hour for an estimated cost of $22 per inspection and $1,958
for the U.S. fleet.
Visually inspecting each TR spline flange for corrosion, impacts,
fretting, wear, and a crack would take about 0.25 work-hour for an
estimated cost of $22 per inspection and $1,958 for the U.S. fleet.
Replacing a TR hub body would take about 2 work-hours and parts
would cost about $16,417 for an estimated cost of $16,587 per TR hub
body replacement.
[[Page 56222]]
Replacing a TR spline flange would take about 0.5 work-hour and
parts would cost about $2,950 for an estimated cost of $2,993 per TR
spline flange replacement.
Replacing a bolt, washer, and nut would take about 0.5 work-hour
and parts would cost about $68 for an estimated cost of $111 per
replacement.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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:
0
a. Removing Airworthiness Directive 2020-11-05, Amendment 39-21130 (85
FR 31042, May 22, 2020); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters: Docket No. FAA-2021-0872; Project Identifier
MCAI-2021-00312-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by November 22, 2021.
(b) Affected ADs
This AD replaces AD 2020-11-05, Amendment 39-21130 (85 FR 31042,
May 22, 2020) (AD 2020-11-05).
(c) Applicability
This AD applies to Airbus Helicopters Model EC120B helicopters,
certificated in any category, all serial numbers.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6400, Tail rotor
system.
(e) Unsafe Condition
This AD was prompted by a report of recurrent loss of tightening
torque on several attachment bolts on the tail rotor (TR) hub body.
The FAA is issuing this AD to detect cracking and fretting, which if
not addressed, could result in potential loss of the TR drive and
consequent loss of yaw control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 15 hours time-in-service (TIS) or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 15 hours TIS, using a light source and
mirror, visually inspect TR hub body part number (P/N) C642A0100103
for a crack in the entire inspection area depicted in Figure 1 of
Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision
2, dated February 8, 2021 (ASB 05A020 Rev 2). If there is a crack,
before further flight, perform the actions in paragraphs (g)(1)(i)
and (ii) of this AD.
(i) Remove the TR hub body and each bolt, washer, and nut
installed on the TR hub body from service and replace with airworthy
parts.
(ii) Inspect the TR splined flange for corrosion, impacts,
fretting, wear, and a crack in the areas identified in Figure 2 of
this AD. If the condition of the part (including corrosion, impacts,
fretting, wear, or cracks) exceeds the criteria as specified in
Figure 1 of this AD, before further flight, remove the splined
flange from service and replace with an airworthy part.
Note 1 to paragraph (g)(1)(ii): You may refer to ``Detailed
Check--Splined Flange,'' Task 64-21-00, 6-5, Airbus Aircraft
Maintenance Manual (AMM), dated October 15, 2020 which pertains to
the TR splined flange inspection.
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(2) For helicopters with 9,000 or more total hours TIS, or with
unknown total hours TIS, within 15 hours TIS or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 1,000 hours TIS, remove each bolt, washer,
and nut installed on the TR hub body from service and replace with
airworthy parts and perform the actions in paragraph (g)(1)(ii) of
this AD.
(3) For helicopters with less than 9,000 total hours TIS, within
1,000 hours TIS or before accumulating 9,000 total hours TIS,
whichever occurs first after the effective date of this AD, and
thereafter at intervals not to exceed 1,000 hours TIS, remove each
bolt, washer, and nut installed on the TR hub body from service and
replace with airworthy parts and perform the actions in paragraph
(g)(1)(ii) of this AD.
(4) As of the effective date of this AD, do not install TR hub
body P/N C642A0100103 on any helicopter, unless the actions of
paragraph (g)(1) of this AD have been accomplished.
(h) Special Flight Permits
A special flight permit may be permitted provided that there are
no passengers onboard.
(i) Alternative Methods of Compliance (AMOCs)
(1) 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 manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (j)(1) of
this AD.
[[Page 56225]]
Information may be emailed to: [email protected].
(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.
(j) Related Information
(1) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, COS Program Management Section, Operational
Safety Branch, Compliance & Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
(2) For service information identified in this AD, contact
Airbus Helicopters, 2701 North 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 this referenced service information 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.
(3) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2021-0069, dated March 11, 2021.
You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2021-0872.
Issued on October 1, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-21955 Filed 10-7-21; 8:45 am]
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