Rule2021-25703
Airworthiness Directives; Airbus Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
November 26, 2021
Effective
January 3, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was prompted by the failure of a main gearbox (MGB) second stage planet gear. This AD requires replacing the MGB, or as an alternative, replacing the epicyclic reduction gear module for certain serial numbered planet gear assemblies installed on the MGB. This AD also requires inspecting the MGB magnetic plugs and MGB filter for particles, and for certain serial-numbered planet gear assemblies, inspecting the oil sump for particles. Depending on the outcome of these inspections, this AD requires further inspections and replacing certain parts. This AD also prohibits installing certain parts. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 86 Issue 225 (Friday, November 26, 2021)</title>
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[Federal Register Volume 86, Number 225 (Friday, November 26, 2021)]
[Rules and Regulations]
[Pages 67303-67307]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-25703]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0197; Project Identifier 2018-SW-107-AD; Amendment
39-21789; AD 2021-22-16]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was
prompted by the failure of a main gearbox (MGB) second stage planet
gear. This AD requires replacing the MGB, or as an alternative,
replacing the epicyclic reduction gear module for certain serial
numbered planet gear assemblies installed on the MGB. This AD also
requires inspecting the MGB magnetic plugs and MGB filter for
particles, and for certain serial-numbered planet gear assemblies,
inspecting the oil sump for particles. Depending on the outcome of
these inspections, this AD requires further inspections and replacing
certain parts. This AD also prohibits installing certain parts. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 3, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of January 3, 2022.
ADDRESSES: For service information identified in this final rule,
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 <a href="https://www.airbus.com/helicopters/services/technical-support.html">https://www.airbus.com/helicopters/services/technical-support.html</a>. You may view the referenced service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the
availability of this material at the FAA, call (817) 222-5110. Service
information
[[Page 67304]]
that is incorporated by reference is also available at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2021-
0197.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-0197; 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 final rule, the
European Aviation Safety Agency (now European Union Aviation Safety
Agency) (EASA) AD, any comments received, and other information. The
street address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer,
Dynamic Systems Section, Technical Innovation Policy Branch, Policy &
Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#0476656b2a616071747163656a706d446265652a636b72"><span class="__cf_email__" data-cfemail="cebcafa1e0abaabbbebba9afa0baa78ea8afafe0a9a1b8">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model EC 155B and EC155B1 helicopters. The NPRM published in the
Federal Register on July 22, 2021 (86 FR 38608). In the NPRM, the FAA
proposed to require for helicopters with at least one Type Y planet
gear assembly with a certain serial number (S/N) installed, or at least
one Type Z planet gear assembly with a certain S/N installed, within 10
hours time-in-service (TIS) after the effective date of the AD and
thereafter at intervals not to exceed 10 hours TIS, inspecting the MGB
magnetic plugs for particles. If there are particles, the NPRM proposed
to require further inspections and analyses and replacing the MGB,
depending on the type and the size of the particles.
The NPRM also proposed to require for helicopters with a Type Y
planet gear assembly with a certain S/N installed, within 25 hours TIS
after the effective date of the AD, inspecting the MGB filter for
particles. If there are particles, the NPRM proposed to require further
inspections and analyses and replacing the MGB, depending on the type
and the size of the particles. The NPRM proposed to require for
helicopters with at least one Type Y planet gear assembly with a
certain S/N installed, within 50 hours TIS after the effective date of
the AD, replacing the MGB. As an alternative to replacing the MGB, the
NPRM would allow replacing the epicyclic reduction gear in the affected
MGB.
Additionally, the NPRM proposed to require, for helicopters without
any Type Y planet gear assembly but at least one Type Z planet gear
assembly with a certain S/N installed, replacing the MGB within 50
hours TIS after the effective date of the AD or before any planet gear
assembly accumulates 1,800 total hours TIS, whichever occurs later. As
an alternative to replacing the MGB, the NPRM would allow replacing the
epicyclic reduction gear in the affected MGB.
The NPRM also proposed to require, for helicopters with at least
one Type Z planet gear with a certain S/N installed, within certain
compliance times specified in the figures in this AD, inspecting the
MGB filter and inspecting the oil sump for particles. If there are
particles, the NPRM proposed to require further inspections and
analyses, and replacing the MGB, depending on the type and the size of
the particles.
The NPRM also proposed to prohibit installing an MGB with a certain
serial numbered Type Y planet gear assembly and proposed to prohibit
installing a Type Y planet gear assembly with a certain S/N on any
helicopter.
Additionally, the NPRM proposed to prohibit installing certain
serial numbered Type Z planet gear assemblies that have accumulated
1,800 or more total hours TIS and prohibit installing an MGB with
certain serial numbered Type Z planet gear assemblies that have
accumulated 1,800 or more total hours TIS.
Finally, the NPRM proposed to prohibit installing an MGB if the
type of the planet gear assembly cannot be determined and also prohibit
installing any planet gear assembly if the type cannot be determined.
The NPRM was prompted by EASA AD 2018-0263, dated December 7, 2018
(EASA AD 2018-0263), issued by EASA, which is the Technical Agent for
the Member States of the European Union, to correct an unsafe condition
for Airbus Helicopters Model EC 155 B and EC 155 B1 helicopters. EASA
advises that after an accident on a Model EC225 helicopter, an
investigation revealed the failure of an MGB second stage planet gear.
EASA states that one of the two types of planet gear used in the MGB
epicyclic module is subject to higher outer race contact pressures and
therefore is more susceptible to spalling and cracking. This condition,
if not addressed, could result in failure of a MGB planet gear
assembly, failure of the MGB, and subsequent loss of helicopter
control.
Accordingly, EASA AD 2018-0263 requires repetitive inspections of
the MGB magnetic plugs, the MGB filer, and the oil sump for particles,
and depending on the results of those inspections, removing or
replacing certain parts. EASA AD 2018-0263 also requires reducing the
life limit of Type Z planet gear assemblies. EASA AD 2018-0263 also
requires, if certain gear assemblies are installed, either replacing
the MGB or replacing the epicyclic reduction gear. Finally, EASA AD
2018-0263 prohibits installing a Type Y planet gear assembly or an MGB
with a Type Y planet gear assembly on any helicopter.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter. The following
presents the comments received on the NPRM and the FAA's response.
Request to Revise the Required Actions Section of the NPRM
Airbus Helicopters Inc., requested that the FAA revise the Required
Actions section of this AD dealing with the 25 hours TIS inspection for
the oil sump (also referred to as inspecting the bottom housing of the
MGB) by removing that repetitive inspection and explained that some of
the proposed actions are unclear and not in line with the original
equipment manufacturer's (OEM) service information. The commenter also
provided an example of a similar AD, AD 2021-12-06, Amendment 39-21593
(86 FR 31612, June 15, 2021) (AD 2021-12-06), stating that AD 2021-12-
06 is clear in explaining both the required repetitive actions and the
limits provided by the OEM for the MGB oil filter inspection after
finding particle(s) on the chip detector. The commenter stated that, as
written, the proposed actions would create extra work, which could lead
to an unwanted condition exposing the dynamic component to possible
contamination and possibly foreign object debris.
The FAA agrees that the repetitive 25 hours TIS oil sump inspection
for Type Y planet gears is not necessary and has revised paragraph
(g)(1) of the Required Actions section in this final rule by deleting
this inspection.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and
[[Page 67305]]
determined that air safety and the public interest require adopting
this AD as proposed, except for the change described previously,
updating the service information for the optional replacement of the
epicyclic reduction gear module in paragraphs (g)(3) and (4) of this
AD, and for clarity, deleting the corrective actions when there are no
16NCD13 particles. The FAA has determined that these changes will not
increase the economic burden on any operator or increase the scope of
this final rule.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB No.
EC155-05A034, Revision 5, dated December 4, 2018 (ASB EC155-05A34 Rev
5) for Model EC 155 helicopters, which specifies periodic inspections
of the MGB magnetic plugs, the MGB filter, and the oil sump for
particles. ASB EC155-05A34 Rev 5 also specifies identifying the type of
gear assembly installed in the MGB and replacing any Type Y planet gear
assembly within 50 hours TIS. For Type Z gear assemblies that have
logged less than 1,800 hours TIS since new, this service information
specifies replacing the gear assembly before exceeding 1,800 total
hours TIS, and for Type Z gear assemblies that have logged 1,800 or
more total hours TIS, replacing the gear assembly within 600 hours TIS.
The FAA also reviewed Airbus Helicopters Service Bulletin SB No.
EC155-63-016, Revision 5, dated March 6, 2019, for Model EC 155
helicopters. This service information specifies procedures for
replacing the MGB epicyclic reduction gear without removing the MGB.
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.
Interim Action
The FAA considers this AD to be an interim action. If final action
is later identified, the FAA might consider further rulemaking then.
Differences Between This AD and EASA AD 2018-0263
EASA AD 2018-0263 specifies compliance times based on flight hours
and calendar dates. This AD sets compliance times based on hours TIS or
before further flight. EASA AD 2018-0263 allows a pilot to inspect the
MGB magnetic plugs for particles, while this AD does not. For
helicopters with at least one affected Type Z planet gear assembly that
has accumulated 1,800 or more total hours TIS installed, EASA AD 2018-
0263 requires replacing the MGB or epicyclic reduction gear within 600
flight hours after March 16, 2018, whereas this AD requires either of
those replacements within 50 hours TIS after the effective date of this
AD instead. If 16NCD13 particles are present, EASA AD 2018-0263
requires taking a 1 liter sample of oil and returning it to Airbus
Helicopters and removing the MGB for depot-level inspection, whereas
this AD requires replacing the MGB instead.
Costs of Compliance
The FAA estimates that this AD affects 14 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 AD.
Inspecting the magnetic plugs for particle deposits takes about 1
work-hour for an estimated cost of $85 per helicopter per inspection
cycle.
Inspecting the MGB filter or oil sump for particle deposits takes
about 1 work-hour for an estimated cost of $85 per helicopter per
inspection cycle.
Replacing an MGB takes about 42 work-hours, and parts cost about
$295,000 (overhauled) for an estimated total cost of $298,570 per
helicopter.
Replacing the epicyclic reduction gear takes about 56 work-hours
and parts cost about $11,404 for an estimated total cost of $16,164 per
helicopter.
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 helicopters identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-22-16 Airbus Helicopters: Amendment 39-21789; Docket No. FAA-
2021-0197; Project Identifier 2018-SW-107-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 3, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Model EC 155B and EC155B1
helicopters, certificated in any category.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor
Drive System.
(e) Unsafe Condition
This AD was prompted by the failure of a main gearbox (MGB)
second stage planet gear. The FAA is issuing this AD to prevent
failure of an MGB planet gear assembly. The unsafe condition, if not
addressed, could result in failure of the MGB and subsequent loss of
helicopter control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 67306]]
(g) Required Actions
(1) For helicopters with at least one Type Y planet gear
assembly with a serial number (S/N) listed in Appendix 4.A. of
Airbus Helicopters Alert Service Bulletin ASB No. EC155-05A034,
Revision 5, dated December 4, 2018 (ASB EC155-05A034 Rev 5) or with
at least one Type Z planet gear assembly with an S/N listed in
Appendix 4.B. of ASB EC155-05A034 Rev 5 installed, within 10 hours
time-in-service (TIS) after the effective date of this AD, and
thereafter at intervals not to exceed 10 hours TIS, inspect the MGB
magnetic plugs for particles. If there are any particles that
consist of any scale, flake, splinter, or other particle other than
cotter pin fragments, pieces of lock wire, swarf, abrasion, or
miscellaneous non-metallic waste, and any of the planet gears have
accumulated less than 50 total hours TIS, before further flight,
inspect the MGB filter for particles. Thereafter, for 25 hours TIS,
continue to inspect the MGB plugs for particles before each flight,
inspect the MGB filter for particles at intervals not to exceed 25
hours TIS, and inspect the cumulative surface area of the particles
collected from the magnetic plugs, the MGB filter, since last MGB
overhaul, or since new if no overhaul has been performed.
Note 1 to the introductory text of paragraph (g)(1): Airbus
Helicopters service information refers to an MGB filter as an oil
filter.
(i) If the total surface area of the particles is less than 3
mm\2\, examine the particles with the largest surface area (S),
greatest length (L), and greatest thickness (e).
(A) If any (S) of all of the particles is less than or equal to
1 mm\2\, the (L) is less than or equal to 1.5 mm, and the (e) is
less than or equal to 0.2 mm, inspect the MGB plugs for particles
before further flight, and inspect the MGB filter for particles
within 25 hours TIS. Thereafter:
(1) For 25 hours TIS, continue to inspect the MGB plugs for
particles before each flight and perform the actions required by
paragraphs (g)(1)(i) and (ii) of this AD.
(2) Inspect the MGB filter for particles at intervals not to
exceed 25 hours TIS and perform the actions required by paragraphs
(g)(1)(i) and (ii) of this AD.
(B) If any (S) is greater than 1 mm\2\, (L) is greater than 1.5
mm, or (e) is greater than 0.2 mm, perform a metallurgical analysis
for any 16NCD13 particles, using a method in accordance with FAA-
approved procedures.
(C) If there are any 16NCD13 particles, before further flight,
replace the MGB with an airworthy MGB.
(ii) If the total surface area of collected particles is greater
than or equal to 3 mm\2\, before further flight, perform a
metallurgical analysis for any 16NCD13 particles using a method in
accordance with FAA-approved procedures. If there are any 16NCD13
particles, before further flight, replace the MGB with an airworthy
MGB.
(2) For helicopters with at least one Type Y planet gear
assembly with an S/N listed in Appendix 4.A. of ASB EC155-05A034 Rev
5 installed, within 25 hours TIS after the effective date of this
AD, inspect the MGB filter for particles. If there are any particles
that consist of any scale, flake, splinter, or particle other than
cotter pin fragments, pieces of lock wire, swarf, abrasion, or
miscellaneous non-metallic waste, and any of the planet gears have
accumulated more than 50 total hours TIS, before further flight,
perform the actions required by paragraphs (g)(1)(i) and (ii) of
this AD.
(3) For helicopters with at least one Type Y planet gear
assembly with an S/N listed in Appendix 4.A. of ASB EC155-05A034 Rev
5 installed, within 50 hours TIS after the effective date of this
AD, replace the MGB or as an alternative to replacing an affected
MGB, replace the epicyclic reduction gear module in the affected MGB
in accordance with paragraph 3.B.2. of the Accomplishment
Instructions of Airbus Helicopters Service Bulletin SB No. EC155-63-
016, Revision 5, dated March 6, 2019 (SB EC155-63-016 Rev 5), except
you are not required to contact Airbus Helicopters.
(4) For helicopters without any Type Y planet gear assembly
installed but with at least one Type Z planet gear assembly with an
S/N listed in Appendix 4.B. of ASB EC155-05A034 Rev 5 installed,
within 50 hours TIS after the effective date of this AD, or before
any gear accumulates 1,800 total hours TIS, whichever occurs later,
replace the MGB or as an alternative to replacing an affected MGB,
replace the epicyclic reduction gear module in the affected MGB in
accordance with paragraph 3.B.2. of the Accomplishment Instructions
of SB EC155-63-016 Rev 5, except you are not required to contact
Airbus Helicopters.
(5) For helicopters with at least one Type Z planet gear
assembly with an S/N listed in Appendix 4.B. of ASB EC155-05A034 Rev
5 installed, inspect the MGB filter for particles within the
compliance times specified in Figure 1 to paragraph (g)(5) of this
AD and inspect the oil sump for particles within the compliance
times specified in Figure 2 to paragraph (g)(5) of this AD, based on
the total hours TIS accumulated by the Type Z planet gear with the
most total hours TIS accumulated since first installation in an MGB.
If there are particles, before further flight, perform the actions
required by paragraphs (g)(1)(i) and (ii) of this AD.
Figure 1 to Paragraph (g)(5)
------------------------------------------------------------------------
Compliance time Compliance time
Total hours TIS accumulated for initial for repetitive
inspection inspections
------------------------------------------------------------------------
Less than 400 total hours TIS... Within 55 hours Within 55 hours
TIS after the TIS.
effective date of
this AD.
400 or more total hours TIS..... Within 25 hours Within 25 hours
TIS after the TIS.
effective date of
this AD.
------------------------------------------------------------------------
Figure 2 to Paragraph (g)(5)
------------------------------------------------------------------------
Compliance time Compliance time
Total hours TIS accumulated for initial for repetitive
inspection inspections
------------------------------------------------------------------------
Less than 400 total hours TIS... Before exceeding Within 55 hours
400 hours TIS TIS.
after the
effective date of
this AD.
400 or more total hours TIS..... Within 55 hours Within 55 hours
TIS after the TIS.
effective date of
this AD.
------------------------------------------------------------------------
(6) As of the effective date of this AD, do not install a type Y
planet gear assembly with an S/N listed in Appendix 4.A. of ASB
EC155-05A034 Rev 5 on any helicopter, and do not install an MGB with
a Type Y planet gear assembly with an S/N listed in Appendix 4.A. of
ASB EC155-05A034 Rev 5 on any helicopter.
(7) As of the effective date of this AD, do not install a Type Z
planet gear assembly with an S/N listed in Appendix 4.B. of ASB
EC155-05A034 Rev 5 that has accumulated 1,800 or more total hours
TIS on any helicopter, and do not install an MGB with at least one
Type Z planet gear assembly with an S/N listed in Appendix 4.B. of
ASB EC155-05A034 Rev 5 that has accumulated 1,800 or more total
hours TIS on any helicopter.
(8) As of the effective date of this AD, do not install any
planet gear on any helicopter if the planet gear assembly type
cannot be determined, and do not install any MGB on any helicopter
if any of the planet gear assembly types cannot be determined.
[[Page 67307]]
(h) 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 (i)(1) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#9da4b0dccbceb0dcd4cfb0aaaeadb0dcd0d2deddfbfcfcb3faf2eb"><span class="__cf_email__" data-cfemail="eed7c3afb8bdc3afa7bcc3d9dddec3afa3a1adae888f8fc0898198">[email protected]</span></a>.
(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.
(i) Related Information
(1) For more information about this AD, contact Rao Edupuganti,
Aerospace Engineer, Dynamic Systems Section, Technical Innovation
Policy Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#285a4947064d4c5d585d4f49465c41684e4949064f475e"><span class="__cf_email__" data-cfemail="76041719581312030603111718021f3610171758111900">[email protected]</span></a>.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
2018-0263, dated December 7, 2018. You may view the EASA AD at
<a href="https://www.regulations.gov">https://www.regulations.gov</a> in Docket No. FAA-2021-0197.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service Bulletin ASB No. EC155-
05A034, Revision 5, dated December 4, 2018.
(ii) Airbus Helicopters Service Bulletin SB No. EC155-63-016,
Revision 5, dated March 6, 2019.
(3) 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 <a href="https://www.airbus.com/helicopters/services/technical-support.html">https://www.airbus.com/helicopters/services/technical-support.html</a>.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: <a href="/cdn-cgi/l/email-protection#cdabbfe3a4a3bebda8aeb9a4a2a38da3acbface3aaa2bb"><span class="__cf_email__" data-cfemail="87e1f5a9eee9f4f7e2e4f3eee8e9c7e9e6f5e6a9e0e8f1">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on October 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-25703 Filed 11-24-21; 8:45 am]
BILLING CODE 4910-13-P
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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.