Airworthiness Directives; PZL Swidnik S.A. Helicopters, 45073-45075 [2020-16129]

Download as PDF Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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. SUMMARY: jbell on DSKJLSW7X2PROD with RULES 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 VerDate Sep<11>2014 16:16 Jul 24, 2020 Jkt 250001 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 ‘‘PZLS´widnik’’ S.A., Al. Lotniko´w Polskich 1, 21–045 S´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 kristin.bradley@faa.gov. 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 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 45073 (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 kristin.bradley@faa.gov. 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 Wytwo´rnia Sprze˛tu Komunikacyjnego ‘‘PZLS´widnik’’ Spo´5ka Akcyjna (WSK, ‘‘PZLS´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 E:\FR\FM\27JYR1.SGM 27JYR1 45074 Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of the same type design. jbell on DSKJLSW7X2PROD with RULES Related Service Information Under 1 CFR Part 51 WYTWORNIA SPRZE˛TU KOMUNIKACYJNEGO ‘‘PZL-S´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 S´widnik S.A. Finally, this service information specifies contacting PZL S´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 VerDate Sep<11>2014 16:16 Jul 24, 2020 Jkt 250001 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 S´widnik S.A., whereas this AD does not. The EASA AD requires contacting PZL S´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 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ E:\FR\FM\27JYR1.SGM 27JYR1 Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations 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. jbell on DSKJLSW7X2PROD with RULES (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 SPRZE˛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: VerDate Sep<11>2014 16:16 Jul 24, 2020 Jkt 250001 45075 (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. 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-S´widnik S.A., A1. Lotniko´w Polskich 1, 21–045 S´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 fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (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 9ASW-FTW-AMOC-Requests@faa.gov. (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. DEPARTMENT OF TRANSPORTATION (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 SPRZE˛TU KOMUNIKACYJNEGO ‘‘PZL-Swidnik’’ PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 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] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0136; Project Identifier MCAI–2019–00114–E; Amendment 39–21168; AD 2020–15–05] RIN 2120–AA64 Airworthiness Directives; Austro Engine GmbH Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2018–18– 02 for certain Austro Engine GmbH model E4 engines and all Austro Engine GmbH model E4P engines. AD 2018– 18–02 required replacement of the timing chain and amending certain airplane flight manuals (AFMs) to limit the use of windmill restarts. This AD requires amendment of certain existing AFMs to limit the use of windmill restarts and removes the timing chain replacement requirement in AD 2018– 18–02. This AD was prompted by reports of considerable wear of the timing chain on the affected engines. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 31, 2020. The Director of the Federal Register approved the incorporation by reference SUMMARY: E:\FR\FM\27JYR1.SGM 27JYR1

Agencies

[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.

-----------------------------------------------------------------------

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]
BILLING CODE 4910-13-P

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