[Federal Register Volume 85, Number 196 (Thursday, October 8, 2020)]
[Rules and Regulations]
[Pages 63431-63434]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22259]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0856; Product Identifier 2019-SW-071-AD; Amendment 
39-21270; AD 2020-20-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 
N3, EC 155B, EC155B1, AS350B3, AS355F, AS355F1, AS355F2, AS355N, 
AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting 
the main rotor (M/R) servo actuators, and depending on the inspection 
results, replacing the affected part, applying a slippage mark, and 
reporting information. This AD was prompted by an incident of a sudden, 
strong nose-up attitude followed by intensive vibrations and increased 
loads on the flight controls during a cruise flight. The actions of 
this AD are intended to address an unsafe condition on these products.

DATES: This AD becomes effective October 23, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of October 23, 
2020.
    The FAA must receive comments on this AD by November 23, 2020.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0856; 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 AD, the European Union Aviation Safety Agency (EASA) AD, any 
service information that is incorporated by reference, any comments 
received, and other information. The street address for Docket 
Operations is listed above. Comments will be available in the AD docket 
shortly after receipt.
    For service information identified in this final rule, contact 
Airbus Helicopters, 2701 N 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 the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0856.

FOR FURTHER INFORMATION CONTACT: Matthew L. Thompson, Aerospace 
Engineer, DSCO Branch, Compliance & Airworthiness Division, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5251; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and the FAA did not provide you with notice and an opportunity 
to provide your comments prior to it becoming effective. However, the 
FAA invites you to participate in this rulemaking by submitting written 
comments, data, or views. The most helpful comments reference a 
specific portion of the AD, explain the reason for any recommended 
change, and include supporting data. To ensure the docket does not 
contain duplicate comments, commenters should send only one copy of 
written comments, or if comments are filed electronically, commenters 
should submit them only one time.
    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 file in the docket all comments received, as well 
as a report summarizing each substantive public contact with FAA 
personnel concerning this rulemaking during the comment period. The FAA 
will consider all the comments received and may conduct additional 
rulemaking based on those comments.

Confidential Business Information

    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 final rule 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 final rule, it is important that 
you clearly designate the

[[Page 63432]]

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 final rule. Submissions containing CBI 
should be sent to Matthew L. Thompson, Aerospace Engineer, DSCO Branch, 
Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone 817-222-5251; email 
[email protected]. Any comments that the FAA receives which 
are not specifically designated as CBI will be placed in the public 
docket for this rulemaking.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2019-0184, dated July 29, 2019, 
to correct an unsafe condition for Airbus Helicopters (AH), formerly 
Eurocopter, Eurocopter France, Aerospatiale, Sud Aviation, Model SA 365 
N, SA 365 N1, AS 365 N2, AS 365 N3, EC155 B and EC155 B1 helicopters, 
AS 350 B3 helicopters if equipped with dual hydraulic system (OP 3346 
or OP 3082), EC 130 B4 and EC 130 T2 helicopters, and AS355 F, AS355 
F1, AS355 F2, AS355 N and AS355 NP helicopters. EASA advises that a 
Model AS 365 N3 helicopter experienced a sudden, strong nose-up 
attitude followed by intense vibrations and increased loads on the 
flight controls during a cruise flight. Following an emergency landing, 
the post-flight visual inspection of the front left-hand M/R servo 
actuator showed that the threaded-shouldered bushing holding the lower 
end-fitting was uncoupled from the actuator body. EASA further advises 
that other helicopter models are affected due design similarity of the 
installed M/R servo actuators. EASA also advises that this condition, 
if not detected and corrected, could lead to loss of control of the 
helicopter.
    Accordingly, the EASA AD requires a one-time inspection of each M/R 
servo actuator for correct installation and, depending on the findings, 
replacing the affected part or applying a slippage mark. The EASA AD 
also requires inspecting the slippage mark for misalignment and, 
depending on the findings replacing the affected part. EASA considers 
its AD an interim action and states that further AD action may follow.

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 of the 
unsafe condition described in its AD. The FAA is issuing this AD after 
evaluating all of the information provided by EASA and determining the 
unsafe condition exists and 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 one document that co-publishes eight Airbus 
Helicopters Emergency Alert Service Bulletin (EASB) identification 
numbers: No. 67.00.17 for Model AS365 N, N1, N2, and N3 helicopters and 
non FAA-type certificated military Model AS365 F, Fs, Fi, K, and K2 
helicopters; No. 67.00.10 for non FAA-type certificated military Model 
AS565 MA, MB, MBe, SA, SB, and UB helicopters; No. 67.11 for non FAA-
type certificated military Model SA366 GA helicopters; No. 67A016 for 
Model EC155 B and B1 helicopters; No. 67.00.77 for Model AS350 B3 
helicopters; No. 67.00.48 for Model AS355 F, F1, F2, N, and NP 
helicopters; No. 67.00.33 for non FAA-type certificated military Model 
AS555 AF, AN, AP, SN, UF, and UN helicopters; and No. 67A021 for Model 
EC130 B4 and T2 helicopters, each Revision 0 and dated July 25, 2019. 
EASB Nos. 67.00.17, 67A016, 67.00.77, 67.00.48, and 67A021 are 
incorporated by reference in this AD. EASB Nos. 67.00.10, 67.11, and 
67.00.33 are not incorporated by reference in this AD.
    This service information specifies procedures for inspecting the 
links between the lower ball end fitting and the M/R actuator rods. 
This service information also specifies procedures for applying a 
slippage mark (red mark) and inspecting the slippage mark.
    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.

AD Requirements

    This AD requires, within 30 hours time-in-service (TIS), with any 
sealing compound on the lower ball end fitting link removed, inspecting 
each M/R servo actuator for correct installation by inspecting the link 
between the lower ball end fitting and the actuator rod for visible 
threads and play between the actuator rod and the punched lockwasher, 
inspecting for protrusion of the threaded shouldered bushing from the 
punched lockwasher, and inspecting the alignment between the punching 
of the punched lockwasher and the stud of the lower ball end fitting. 
Depending on the inspection results, this AD requires replacing the M/R 
servo actuator and reporting the inspection results to Airbus 
Helicopters if there is any visible thread or play between the actuator 
rod and the punched lockwasher, protrusion of the threaded shouldered 
bushing, or misalignment between the punching of the punched lockwasher 
and the stud of the lower ball end fitting. This AD also requires 
applying a slippage mark from the actuator rod (excluding the chamfered 
part of the rod) to the nut, including the punched lockwasher and the 
lockwasher.

Differences Between This AD and the EASA AD

    The EASA AD is applicable to affected M/R servo actuators that were 
supplied by Airbus Helicopters before August 12, 2019, whereas this AD 
applies to affected M/R servo actuators that were manufactured before 
July 25, 2019 or with an unknown date of manufacture, instead. The EASA 
AD requires the one-time inspection within 55 flight hours, whereas 
this AD requires the one-time inspection within 30 hours TIS instead. 
The EASA AD requires a longer-term inspection of the slippage mark for 
misalignment for affected M/R servo actuators regardless of when they 
were originally supplied, whereas this AD does not. The FAA plans to 
publish a notice of proposed rulemaking to give the public an 
opportunity to comment on this longer-term requirement.

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.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 1,270 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this AD.
    Inspecting the M/R servo actuators takes about one work-hour for an 
estimated cost of $85 per helicopter and

[[Page 63433]]

$107,950 for the U.S. fleet. Applying a slippage mark takes a minimal 
amount of time at a nominal cost.
    If required, reporting information takes about 1 hour for an 
estimated cost of $85.
    Replacing an M/R actuator takes about 2 work-hours and parts cost 
up to $53,315 for an estimated cost of up to $53,485 per replacement.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

FAA's Justification and Determination of the Effective Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (5 U.S.C.) 
authorizes agencies to dispense with notice and comment procedures for 
rules when the agency, for ``good cause'' finds that those procedures 
are ``impracticable, unnecessary, or contrary to the public interest.'' 
Under this section, an agency, upon finding good cause, may issue a 
final rule without seeking comment prior to the rulemaking.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because the required corrective action must be completed within 30 
hours TIS, a time period of up to one month based on the average 
flight-hour utilization rate of these helicopters. Therefore, the FAA 
finds good cause that notice and opportunity for prior public comment 
are impracticable. In addition, for the reason(s) stated above, the FAA 
finds that good cause exists for making this amendment effective in 
less than 30 days.

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 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, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866, and
    2. Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of 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 (AD):

2020-20-14 Airbus Helicopters: Amendment 39-21270; Docket No. FAA-
2020-0856; Product Identifier 2019-SW-071-AD.

(a) Applicability

    This AD applies to the following Airbus Helicopters model 
helicopters, certificated in any category:
    (1) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, and 
EC155B1 helicopters with a main rotor (M/R) servo actuator part 
number (P/N) 704A44831074 (manufacturer part number (MP/N) SC8031), 
P/N 704A44831117 (MP/N SC8031-1), P/N 704A44831144 (MP/N SC8031-2), 
P/N 704A44831106 (MP/N SC8031A), P/N 704A44831097 (MP/N SC8032), P/N 
704A44831118 (MP/N SC8032-1), P/N 704A44831145 (MP/N SC8032-2), P/N 
704A44831127 (MP/N SC8033-1), P/N 704A44831146 (MP/N SC8033-2), P/N 
704A44831128 (MP/N SC8034-1), P/N 704A44831147 (MP/N SC8034-2), P/N 
704A44831149 (MP/N SC8037), or P/N 704A44831155 (MP/N SC8037-1) 
manufactured before July 25, 2019 or with an unknown date of 
manufacture, installed.
    (2) Model AS350B3, AS355F, AS355F1, AS355F2, AS355N, AS355NP, 
EC130B4, and EC130T2 helicopters with an M/R servo actuator P/N 
704A44831102 (MP/N SC8042) or P/N 704A44831103 (MP/N SC8043) 
manufactured before July 25, 2019 or with an unknown date of 
manufacture, installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as an uncoupled M/R servo 
actuator rod. This condition could result in excessive vibrations, 
increased loads on the flight controls, failure of the M/R servo 
actuator, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective October 23, 2020.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 30 hours time-in-service, with any sealing compound 
on the lower ball end fitting link removed, determine if each M/R 
servo actuator is correctly installed by:
    (i) Inspecting the link between the lower ball end fitting (f) 
and the actuator rod (a) for visible threads and play between the 
actuator rod (a) and the punched lockwasher (b) as depicted in 
Figures 1 and 2 of Airbus Helicopters Emergency Alert Service 
Bulletin (EASB) Nos. 67.00.17, 67A016, 67.00.77, 67.00.48, or 
67A021, each Revision 0 and dated July 25, 2019 (EASB 67.00.17, 
67A016, 67.00.77, 67.00.48, or 67A021), as applicable to your 
helicopter. If there is a visible thread

[[Page 63434]]

or play, before further flight, replace the M/R servo actuator.
    (ii) Inspecting for protrusion of the threaded shouldered 
bushing (c) from the punched lockwasher (b) as depicted in Figure 3 
of EASB 67.00.17, 67A016, 67.00.77, 67.00.48, or 67A021, as 
applicable to your helicopter. If there is a protrusion, before 
further flight, replace the M/R servo actuator.
    (iii) Inspecting the alignment between the punching of the 
punched lockwasher (b) and the stud of the lower ball end fitting 
(f) as depicted in Figure 4 of EASB 67.00.17, 67A016, 67.00.77, 
67.00.48, or 67A021, as applicable to your helicopter. If there is 
misalignment, before further flight, replace the M/R servo actuator.
    (2) After accomplishing paragraph (e)(1) of this AD, before 
further flight, apply a slippage mark from the actuator rod (a) 
(excluding the chamfered part of the rod) to the nut (e), including 
the punched lockwasher (b) and the lockwasher (d) as depicted in 
Figure 5 of EASB 67.00.17, 67A016, 67.00.77, 67.00.48, or 67A021, as 
applicable to your helicopter.
    (3) If any parts were required to be replaced as a result of the 
inspections required by paragraph (e)(1) of this AD, within 10 days 
after completing the inspection, report the information in Appendix 
1 to this AD by email to [email protected].
    (4) For Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, 
and EC155B1 helicopters, as of the effective date of this AD, do not 
install an M/R servo actuator identified in paragraph (a)(1) of this 
AD on any helicopter, unless the actions required by paragraphs 
(e)(1) and (2) of this AD have been accomplished.
    (5) For Model AS350B3, AS355F, AS355F1, AS355F2, AS355N, 
AS355NP, EC130B4, and EC130T2 helicopters, as of the effective date 
of this AD, do not install an M/R servo actuator identified in 
paragraph (a)(2) of this AD on any helicopter, unless the actions 
required by paragraphs (e)(1) and (2) of this AD have been 
accomplished.

(f) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a currently valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, searching existing data sources, 
gathering and maintaining the data needed, and completing and 
reviewing the collection of information. All responses to this 
collection of information are mandatory. Send comments regarding 
this burden estimate or any other aspect of this collection of 
information, including suggestions for reducing this burden to: 
Information Collection Clearance Officer, Federal Aviation 
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matthew L. Thompson, 
Aerospace Engineer, DSCO Branch, Compliance & Airworthiness 
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 
817-222-5251; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
that you notify your principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or certificate holding district office, before operating any 
aircraft complying with this AD through an AMOC.

(h) Additional Information

    (1) Airbus Helicopters EASB Nos. 67.00.10, 67.11, and 67.00.33, 
each Revision 0 and dated July 25, 2019, which are not incorporated 
by reference, contain additional information about the subject of 
this AD. For service information identified in this AD, contact 
Airbus Helicopters, 2701 N 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 a copy of the service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD No. 2019-0184, dated July 29, 2019. 
You may view the EASA AD on the internet at https://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2020-0856.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft 
Servo System.

(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 Emergency Alert Service Bulletin (EASB) 
No. 67.00.17, Revision 0, dated July 25, 2019.
    (ii) Airbus Helicopters EASB No. 67A016, Revision 0, dated July 
25, 2019.
    (iii) Airbus Helicopters EASB No. 67.00.77, Revision 0, dated 
July 25, 2019.
    (iv) Airbus Helicopters EASB No. 67.00.48, Revision 0, dated 
July 25, 2019.
    (v) Airbus Helicopters EASB No. 67A021, Revision 0, dated July 
25, 2019.


    Note 1 to paragraph (j)(2):  Airbus Helicopters EASB Nos. 
67.00.17, 67A016, 67.00.77, 67.00.48, and 67A021, each Revision 0 
and dated July 25, 2019 are co-published as one document along with 
Airbus Helicopters EASB Nos. 67.00.10, 67.11, and 67.00.33, each 
Revision 0 and dated July 25, 2019, which are not incorporated by 
reference in this AD.


    (3) For service information identified in this AD, contact 
Airbus Helicopters, 2701 N 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.
    (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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Appendix 1 to AD 2020-20-14

    Report the following information by email to [email protected]. (Airbus Helicopters Emergency Alert 
Service Bulletin Nos. 67.00.17, 67A016, 67.00.77, 67.00.48, and 
67A021, each Revision 0 and dated July 25, 2019.)
    (1) Date of Inspection:
    (2) Helicopter Model and Serial Number:
    (3) Total hours time-in-service (TIS) on the aircraft:
    (4) Date of manufacture of the main rotor (M/R) servo actuator:
    (5) Total hours TIS on M/R servo actuator:
    (6) Total hours TIS since last service of the M/R servo actuator 
and description of service:
    (7) Describe in detail any information and findings and, if 
possible, provide photos.

    Issued on September 24, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-22259 Filed 10-7-20; 8:45 am]
BILLING CODE 4910-13-P