Rule2022-01864
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
January 31, 2022
Effective
March 7, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters; AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters; and Model SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted a report of increased vibration during flight. This AD requires the application of alignment markings on, and repetitive inspections of, the main rotor (MR) pitch rod upper links and, depending on findings, the accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 20 (Monday, January 31, 2022)</title>
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[Federal Register Volume 87, Number 20 (Monday, January 31, 2022)]
[Rules and Regulations]
[Pages 4800-4803]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-01864]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0947; Project Identifier MCAI-2021-00195-R;
Amendment 39-21889; AD 2022-01-01]
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 all
Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3,
AS350D, EC130B4, and EC130T2 helicopters; AS355E, AS355F, AS355F1,
AS355F2, AS355N, and AS355NP helicopters; and Model SA-365C1, SA-365C2,
SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was
prompted a report of increased vibration during flight. This AD
requires the application of alignment markings on, and repetitive
inspections of, the main rotor (MR) pitch rod upper links and,
depending on findings, the accomplishment of applicable corrective
actions, as specified in a European Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective March 7, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 7,
2022.
ADDRESSES: For EASA material incorporated by reference (IBR) in this
AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email <a href="/cdn-cgi/l/email-protection#df9e9bac9fbabeacbef1baaaadb0afbef1baaa"><span class="__cf_email__" data-cfemail="2c6d685f6c494d5f4d0249595e435c4d024959">[email protected]</span></a>; internet
www.easa.europa.eu. You may find this material on the EASA website at
<a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>. 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. It is also available
in the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and
locating Docket No. FAA-2021-0947.
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-2021-0947; 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
EASA AD, any comments received, and other information. The 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: 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 <a href="/cdn-cgi/l/email-protection#accdc2c8dec9cd82c6c5c1c9c2c9d6eccacdcd82cbc3da"><span class="__cf_email__" data-cfemail="7a1b141e081f1b541013171f141f003a1c1b1b541d150c">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0048, dated February 16, 2021
(EASA AD 2021-0048), to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France,
A[eacute]rospatiale) Model AS 350 B, AS 350 BA, AS 350 BB, AS 350 B1,
AS 350 B2, AS 350 B3, AS 350 D, EC 130 B4, and EC 130 T2 helicopters;
Model AS 355 E, AS 355 F, AS 355 F1, AS 355 F2, AS 355 N, and AS 355 NP
helicopters; and Model SA 365 C1, SA 365 C2, SA 365 C3, SA 365 N, SA
365 N1, AS 365 N2, and AS 365 N3 helicopters; all serial numbers. Model
AS 350 BB and SA 365 C3 helicopters are not certificated by the FAA and
are not included on the U.S. type certificate data sheet; this AD
therefore does not include those helicopters in the applicability.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus Helicopters
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and
EC130T2 helicopters; Model AS355E, AS355F, AS355F1, AS355F2, AS355N,
and AS355NP helicopters; and Model SA-365C1, SA-365C2, SA-365N, SA-
365N1, AS-365N2, and AS 365 N3 helicopters. The NPRM published in the
Federal Register on October 29, 2021 (86 FR 59892). The NPRM was
prompted by a report of increased vibration during flight. The NPRM
proposed to require the application of alignment markings on, and
repetitive inspections of, the MR pitch rod upper links and, depending
on findings, the accomplishment of applicable corrective actions, as
specified in EASA AD 2021-0048.
The FAA is issuing this AD to address loss of tightening torque of
the screws connecting the MR pitch rods to the horns of the upper
links. This condition, if not addressed, could result in loss of one or
more MR pitch rod upper links, possibly resulting in loss of control of
the helicopter. See EASA AD 2021-0048 for additional background
information.
[[Page 4801]]
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
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 reviewed the relevant
data and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these helicopters. Except for minor editorial changes,
this AD is adopted as proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0048 requires the application of alignment markings on
the screw, washer, nut, and horn on both sides of each MR pitch rod
upper link, and repetitive visual inspections of the two alignment
markings to determine if the markings are aligned on both sides. If,
during any inspection the markings on one or both sides of an MR pitch
rod upper link are found misaligned, the additional actions and
corrective actions include the following.
<bullet> Measuring the tightening torque value of the nut of the
pitch rod upper link and adjusting the nut if it does not meet the
specified criteria.
<bullet> Inspecting the pitch rod upper link to determine the
condition of the bush (bushing) and spherical bearing and to determine
if the cups are tight (paint mark in place), and measuring the play. If
there is seizing, carbide chips, or the cups are loose (paint mark not
in place), the corrective actions include replacing the spherical
bearing. If the play measurement is greater than the specified
measurement the corrective action is replacing the rod end fitting.
Additional actions include checking the bonding and condition of the
retaining ring and inspecting the pitch rod bodies for evidence of any
impact, scratch, strike, or corrosion.
<bullet> Inspecting the pitch rods for chipped finish paint,
scratches, impacts, and cracking, and measuring the play. If paint is
chipped the corrective action is repair (sanding the affected area and
applying touch-up primer and paint). If there is any scratch, an impact
with a depth equal to or greater than the specified measurement, or any
crack, the corrective action is replacing the pitch rod. If the play
measurement is greater than 0.25 mm or there is cracking, the
corrective action is replacing the spherical bearing. An additional
action, if a helicopter was involved in an incident, is inspecting the
straightness of the rod body ``R'' and replacing the pitch rod if the
straightness of the rod body is greater than 0.5 mm.
<bullet> Inspecting the pitch horn for any evidence of impact,
scratch, corrosion, chipped paint, cracking, and any elongated
attachment hole; and inspecting the bonding of the retaining ring and
measuring dimension ``X'' of the retaining ring. If there is any
evidence of impact, scratch, or corrosion, and the depth meets the
specified criteria, the corrective actions include touching up the
affected area with an abrasive cloth and applying a protective coating
and a coat of primer. If there is any cracking, elongated attachment
hole, or the impact, scratch, or corrosion depth exceeds the specified
criteria, the corrective action is replacing the pitch horn. If paint
is chipped the corrective actions include sanding the affected area and
applying touch-up primer and paint. If the retaining ring has debonded
the corrective action is to rebond the retaining ring. If dimension
``X'' of the retaining ring exceeds the specified criteria, the
corrective action is replacing the retaining ring.
<bullet> Measuring the geometry of ``G'' of the pitch horn and
replacing the pitch horn if the dimension is not within the specified
range.
<bullet> Installing new split pins, nuts, washers, and a screw on
the pitch rod upper link.
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.
Costs of Compliance
The FAA estimates that this AD affects 1,266 helicopters of U.S.
Registry. The FAA estimates the following costs to comply with this AD.
Estimated Costs *
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection................. 0.50 work-hour x $85 $0 $42.50 per inspection $53,805 per
per hour = $42.50 cycle.. inspection cycle.
per inspection
cycle..
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* The FAA has determined that application of alignment markings would take a minimal amount of time at a nominal
cost.
The FAA estimates the following costs to do any necessary actions
that would be required based on the results of the inspection. The
agency has no way of determining the number of aircraft that might need
these actions:
On-Condition Costs *
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Cost per
Action Labor cost Parts cost product
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Screw, Washer, Nut, and Split Pin 1 work-hour x $85 per hour = $85... $40 $125
Replacement.
Spherical Bearing Replacement.............. 4 work hours x $85 per hour = $340. 500 840
Pitch Rod Replacement...................... 4 work hours x $85 per hour = $340. 3,000 3,340
Pitch Horn Replacement..................... 16 work hours x $85 per hour = 4,000 5,360
$1360.
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* The FAA has determined that ``repair'' of chipped paint would take a minimal amount of time at a nominal cost.
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.
[[Page 4802]]
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
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:
2022-01-01 Airbus Helicopters: Amendment 39-21889; Docket No. FAA-
2021-0947; Project Identifier MCAI-2021-00195-R.
(a) Effective Date
This airworthiness directive (AD) is effective March 7, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus Helicopters helicopters,
certificated in any category, identified in paragraphs (c)(1)
through (3) of this AD, all serial numbers.
(1) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D,
EC130B4, and EC130T2 helicopters.
(2) Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP
helicopters.
(3) Model SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, and
AS 365 N3 helicopters.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
(e) Unsafe Condition
This AD was prompted by a report of increased vibration during
flight on an Airbus Helicopters Model AS 365 helicopter. Subsequent
investigation found a total loss of tightening torque of one screw
connecting the main rotor (MR) pitch rod to the horn of its upper
link, which led to abnormal wear of the screw and consequently
increased the vibrations coming from the MR control chain to the
pilot's flight controls. The FAA is issuing this AD to address loss
of tightening torque of the screws connecting the MR pitch rods to
the horns of the upper links. The unsafe condition, if not
addressed, could result in loss of one or more MR pitch rod upper
links, possibly resulting in 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 Union Aviation Safety Agency (EASA) AD
2021-0048, dated February 16, 2021 (EASA AD 2021-0048).
(h) Exceptions to EASA AD 2021-0048
(1) Where EASA AD 2021-0048 requires compliance in terms of
flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2021-0048 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where the service information referenced in EASA AD 2021-
0048 specifies discarding parts, this AD requires removing those
parts from service.
(4) This AD does not mandate compliance with the ``Remarks''
section of EASA AD 2021-0048.
(5) Where a work card in the service information referenced in
EASA AD 2021-0048 specifies returning a part to the manufacturer,
this AD does not include that requirement.
(6) For Model AS350 helicopters: For the visual inspection of
the pitch rod upper link, where a work card in the service
information referenced in EASA AD 2021-0048 specifies to do an
inspection of a pitch rod body for any dent, impact, scratch, or
corrosion, and any dent, impact, scratch, or corrosion is found,
this AD requires replacing the pitch rod before further flight.
(7) For Model AS355 helicopters: For the visual inspection of
the pitch rod upper link, where a work card in the service
information referenced in EASA AD 2021-0048 specifies to do an
inspection of a pitch rod body for any impact, scratch, strike, or
corrosion, and any impact, scratch, strike, or corrosion is found,
this AD requires replacing the pitch rod before further flight.
(8) For Model SA365 helicopters: For the visual inspection of
the pitch rod upper link, where a work card in the service
information referenced in EASA AD 2021-0048 specifies to ``check
bonding and state retaining ring on the pitch rods,'' and any
discrepancy (e.g., disbonding) is found and no corrective action is
specified, before further flight, contact the Manager, General
Aviation & Rotorcraft Section, International Validation Branch FAA;
or EASA; or Airbus Helicopters' EASA Design Organization Approval
(DOA); for approved corrective actions, and accomplish those actions
before further flight. If approved by the DOA, the approval must
include the DOA-authorized signature.
(9) For Model SA365 helicopters: For the visual inspection of
the pitch horn, if any discrepancy (corrosion, scratch, impact,
crack, or debonded retaining ring) is found during the inspection of
the pitch horn and there is no corrective action specified in the
work card in the service information referenced in EASA AD 2021-
0048, before further flight, contact the Manager, General Aviation &
Rotorcraft Section, International Validation Branch, FAA; or EASA;
or Airbus Helicopters' EASA DOA; for approved corrective actions,
and accomplish those actions before further flight. If approved by
the DOA, the approval must include the DOA-authorized signature.
(10) For Model AS365 helicopters: For the visual inspection of
the pitch horn, where a work card in the service information
referenced in EASA AD 2021-0048 specifies to do a dye penetrant
inspection ``if in doubt,'' this AD requires doing a dye penetrant
inspection.
(11) For Model AS350 and EC130 helicopters: Where a work card in
the service information referenced in EASA AD 2021-0048 refers to
``the pitch change lever,'' for this AD, that term is equivalent to
``pitch horn.''
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2021-0048
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(j) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are prohibited.
(k) 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
[[Page 4803]]
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 (l) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#784155392e2b5539312a554f4b48553935373b381e1919561f170e"><span class="__cf_email__" data-cfemail="b38a9ef2e5e09ef2fae19e8480839ef2fefcf0f3d5d2d29dd4dcc5">[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.
(l) Related Information
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 <a href="/cdn-cgi/l/email-protection#65040b011700044b0f0c08000b001f250304044b020a13"><span class="__cf_email__" data-cfemail="f1909f95839490df9b989c949f948bb1979090df969e87">[email protected]</span></a>.
(m) 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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2021-0048,
dated February 16, 2021.
(ii) [Reserved]
(3) For EASA AD 2021-0048, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#16575265567377657738736364796677387363"><span class="__cf_email__" data-cfemail="afeeebdcefcacedcce81cadaddc0dfce81cada">[email protected]</span></a>; internet www.easa.europa.eu. You may find the
EASA material on the EASA website at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</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. This material may be
found in the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching
for and locating Docket No. FAA-2021-0947.
(5) You may view this material 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#e58397cb8c8b96958086918c8a8ba58b849784cb828a93"><span class="__cf_email__" data-cfemail="b8deca96d1d6cbc8dddbccd1d7d6f8d6d9cad996dfd7ce">[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 December 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01864 Filed 1-28-22; 8:45 am]
BILLING CODE 4910-13-P
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