[Federal Register Volume 85, Number 144 (Monday, July 27, 2020)]
[Rules and Regulations]
[Pages 45073-45075]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-16129]
[[Page 45073]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0675; Product Identifier 2018-SW-027-AD; Amendment
39-21174; AD 2020-15-11]
RIN 2120-AA64
Airworthiness Directives; PZL Swidnik S.A. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PZL
Swidnik S.A. Model PZL W-3A helicopters. This AD requires repetitively
inspecting the main rotor (M/R) vibration absorber star and depending
on the inspection outcome, performing more in-depth inspections and
repairing, replacing, or removing the vibration absorber star from
service. This AD was prompted by a report of corrosion detected on an
M/R vibration absorber star. The actions of this AD are intended to
address an unsafe condition on these products.
DATES: This AD becomes effective August 11, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as August 11, 2020.
The FAA must receive comments on this AD by September 25, 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-
0675; 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 Aviation Safety Agency (now 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.
For service information identified in this final rule, contact WSK
``PZL- [Sacute]widnik'' S.A., Al. Lotnik[oacute]w Polskich 1, 21-045
[Sacute]widnik, Poland, telephone +48 664 424 798, or at
www.pzl.swidnik.pl. 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-2020-0675.
FOR FURTHER INFORMATION CONTACT: Kristi Bradley, Aerospace Engineer,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817-222-5110; 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 NPRM contain commercial or financial information that is
customarily treated as private, that you actually treat as private, and
that is relevant or responsive to this NPRM, it is important that you
clearly designate the submitted comments as CBI. Please mark each page
of your submission containing CBI as ``PROPIN.'' The FAA will treat
such marked submissions as confidential under the FOIA, and they will
not be placed in the public docket of this NPRM. Submissions containing
CBI should be sent to Kristi Bradley, Aerospace Engineer, Rotorcraft
Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817-222-5110; email [email protected]. Any commentary
that the FAA receives which is not specifically designated as CBI will
be placed in the public docket for this rulemaking.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD No. 2018-0070, dated March 27, 2018,
to correct an unsafe condition for Wytw[oacute]rnia Sprz[eogon]tu
Komunikacyjnego ``PZL-[Sacute]widnik'' Sp[oacute][lstrok]ka Akcyjna
(WSK, ``PZL-[Sacute]WIDNIK'' S.A.) Model PZL W-3A and PZL W-3AS
helicopters with M/R vibration absorber star part number (P/N)
30.23.005.01.04 installed. EASA advises that corrosion was found on the
M/R vibration absorber star during routine maintenance. EASA advises
subsequent investigation could not identify the root cause of the
corrosion. EASA states this condition, if not detected and corrected,
could lead to structural failure of the M/R vibration absorber star,
possibly resulting in damage to the main or tail rotor and subsequent
loss of control of the helicopter.
Accordingly, the EASA AD requires repetitive inspections of the M/R
vibration absorber star, and depending on the outcome of the
inspections, repair or replacement. The EASA AD also requires
inspecting an M/R vibration absorber star before installation on a
helicopter.
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 information
[[Page 45074]]
provided by EASA and determining the unsafe condition exists and is
likely to exist or develop on other helicopters of the same type
design.
Related Service Information Under 1 CFR Part 51
WYTWORNIA SPRZ[Eogon]TU KOMUNIKACYJNEGO ``PZL-[Sacute]widnik''
Spolka Akcyjna has issued Mandatory Bulletin No. BO-37-18-291, dated
March 13, 2018, which specifies repetitively inspecting the M/R
vibration absorber star for paint coating damage and for signs of
corrosion. Depending on the inspection results, this service
information specifies inspecting for corrosion under the bolt heads
that secure the M/R vibration absorber star to the bracket and
mechanically removing the paint coating on the M/R vibration absorber
star to inspect further for corrosion. This service information also
specifies removing corrosion and repairing mechanical damage that is
within allowable limits. Additionally, this service information
specifies emailing sketches showing the polishing depth in repaired M/R
vibration absorber star surfaces to PZL [Sacute]widnik S.A. Finally,
this service information specifies contacting PZL [Sacute]widnik S.A.
for any corrosion or mechanical damage that reaches the maximum total
polishing depth or for corrosion under a bolt head.
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 visually inspecting certain areas of the M/R
vibration absorber star within an initial compliance time based on the
helicopter serial number, and thereafter, repeating the inspections at
intervals not to exceed 300 hours time-in-service (TIS) or 12 months,
whichever occurs first. This AD requires inspecting the M/R vibration
absorber star for paint coating delamination, blistering, and
discoloration, and missing paint coating, a scratch, a dent, a nick,
and corrosion. If there is any paint coating delamination, blistering,
or discoloration, or missing paint, a scratch, a dent, a nick, or
corrosion, this AD requires mechanically removing any remaining paint
coating. If there is no scratch, dent, nick, or corrosion, this AD
requires repairing the paint coating. If there is a scratch, a dent, a
nick, or corrosion less than the accumulated maximum total polishing
depth of 0.5 mm, this AD requires repairing the surface. If there is a
scratch, a dent, a nick, or corrosion that exceeds the accumulated
maximum total polishing depth of 0.5 mm, this AD requires removing the
M/R vibration absorber star from service. This AD also requires
inspecting under each bolt head P/N 30.23.000.08.04 for corrosion.
Lastly, this AD requires inspecting an M/R vibration absorber star
before being installed on any helicopter.
Differences Between This AD and the EASA AD
The EASA AD applies to Model PZL W-3AS helicopters, whereas this AD
does not because that model is not FAA type-certificated. The EASA AD
requires reporting certain information to PZL [Sacute]widnik S.A.,
whereas this AD does not. The EASA AD requires contacting PZL
[Sacute]widnik S.A., if the accumulated maximum total polishing depth
exceeds 0.5 mm or if there is corrosion under the bolt head, whereas
this AD requires repairing or replacing the affected part in accordance
with FAA approved repair procedures or removing the affected part from
service.
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
There are no costs of compliance associated with this AD because
there are no helicopters of this type certificate on the U.S. Registry.
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.
There are no helicopters with this type certificate on the U.S.
Registry. Therefore, notice and opportunity for prior public comment
are unnecessary pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the
reasons stated above, the FAA finds that good cause exists pursuant to
5 U.S.C. 553(d) 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
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):
[[Page 45075]]
2020-15-11 PZL Swidnik S.A.: Amendment 39-21174; Docket No. FAA-
2020-0675; Product Identifier 2018-SW-027-AD.
(a) Applicability
This AD applies to PZL Swidnik S.A. (PZL) Model PZL W-3A
helicopters, certificated in any category, with a main rotor (M/R)
vibration absorber star part number (P/N) 30.23.005.01.04 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as corrosion pits in the M/
R vibration absorber star. This condition could result in structural
failure of the M/R vibration absorber star, damage to the main and
tail rotor, and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective August 11, 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
For helicopters with a serial number (S/N) up to 37.10.12
inclusive, within 25 hours time-in-service (TIS) or 15 days,
whichever occurs first; and for helicopters with an S/N above
37.10.12, within 300 hours TIS or 12 months after the date of
manufacture, whichever occurs first:
(1) Access the M/R vibration absorber by following Attachment 1,
Procedure--Removal, Inspection, Repair, and Installation of
Vibration Absorber Star, section II., of WYTWORNIA SPRZ[Eogon]TU
KOMUNIKACYJNEGO ``PZL-Swidnik'' Spolka Akcyjna Mandatory Bulletin
No. BO-37-18-291, dated March 13, 2018 (MB BO-37-18-291 Attachment
1).
(i) Clean the M/R vibration absorber star surface. Visually
inspect the M/R vibration absorber star for paint coating
delamination, blistering, discoloration, and missing paint coating,
a scratch, a dent, a nick, and corrosion.
(ii) If there is any paint coating delamination, blistering, or
discoloration, or missing paint, any scratch, any dent, any nick, or
corrosion, before further flight, mechanically remove any remaining
paint coating and inspect the M/R vibration absorber star for a
scratch, a dent, a nick, and corrosion. Additionally, inspect the
heads of each bolt P/N 30.23.000.08.04 that secures the vibration
absorber star to the bracket for corrosion under the bolt heads.
Note 1 to paragraph (e)(1)(ii) of this AD: the anodic coating
may become damaged while removing the paint coating.
(A) If there is no scratch, dent, nick, or corrosion on the M/R
vibration absorber star, before further flight, repair the paint
coating.
(B) If there is a scratch, a dent, a nick, or corrosion on the
M/R vibration absorber star not exceeding the accumulated maximum
total polishing depth of 0.5 mm, using 80-100 grit abrasive paper or
an equivalent grit file or scraper, polish out any scratch, dent,
nick, and corrosion and do the following:
(1) Using 150-180 grit abrasive paper, blend the repaired
surface and make a smooth chamfer as shown in Sketch 2. Blending
Method, MB BO-37-18-291 Attachment 1. The blending width ``S'' must
be at least 10 times greater than blending depth ``h.'' The radii
``R1'' and ``R2'' must be at least 5 times greater than depth ``h.''
(2) Using 600-900 grit abrasive paper, polish the repaired
surface and repair the paint coating.
(C) If there is a scratch, a dent, a nick, or corrosion on the
M/R vibration absorber star that meets or exceeds the accumulated
maximum total polishing depth of 0.5 mm, before further flight,
remove from service the M/R vibration absorber star.
(D) If there is corrosion on the head of any bolt P/N
30.23.000.08.04 that secures the vibration absorber star to the
bracket, before further flight, repair or replace the M/R vibration
absorber star in accordance with FAA approved procedures.
(2) Thereafter, at intervals not to exceed 300 hours TIS or 1
year, whichever occurs first, perform the actions required by
paragraph (e)(1) of this AD.
(3) After the effective date of this AD, do not install an M/R
vibration absorber star on any helicopter unless the requirements of
paragraph (e)(1) of this AD have been accomplished.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: Kristi Bradley, Aerospace
Engineer, Safety Management Section, Rotorcraft Standards Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-
5110; 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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (now European Union Aviation Safety Agency) (EASA) AD No.
2018-0070, dated March 27, 2018. You may view the EASA AD on the
internet at https://www.regulations.gov in Docket No. FAA-2020-0675.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor
Drive System.
(i) 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) WYTWORNIA SPRZ[Eogon]TU KOMUNIKACYJNEGO ``PZL-Swidnik''
Spolka Akcyjna Mandatory Bulletin No. BO-37-18-291, dated March 13,
2018.
(ii) [Reserved]
(3) For service information identified in this AD, contact PZL-
[Sacute]widnik S.A., A1. Lotnik[oacute]w Polskich 1, 21-045
[Sacute]widnik, Poland; telephone +48 81 468 09 01, 751 20 71; fax
+48 81 468 09 19, 751 21 73; or at www.pzl.swidnik.pl.
(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.
Issued on July 14, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-16129 Filed 7-24-20; 8:45 am]
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