[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 [www.gpo.gov]
[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 [email protected]; internet 
www.easa.europa.eu. You may find this material on the EASA website at 
https://ad.easa.europa.eu. You may view this material at the FAA, 
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 
Room 6N-321, Fort Worth, TX 76177. For information on the availability 
of this material at the FAA, call (817) 222-5110. It is also available 
in the AD docket at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0947.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov 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 [email protected].

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.
     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.
     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.
     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.
     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.
     Measuring the geometry of ``G'' of the pitch horn and 
replacing the pitch horn if the dimension is not within the specified 
range.
     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 *
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
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: [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.

(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 [email protected].

(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 
[email protected]; internet www.easa.europa.eu. You may find the 
EASA material on the EASA website at https://ad.easa.europa.eu.
    (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 https://www.regulations.gov 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 
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    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


