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Federal Register / Vol. 86, No. 184 / Monday, September 27, 2021 / Rules and Regulations
prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required.

PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.

Costs of Compliance There are no costs of compliance with this AD because there are no helicopters with this type certificate on the U.S.
Registry.
Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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.

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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:

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16:20 Sep 24, 2021

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39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

20211812 PZL Swidnik S.A.:
Amendment 3921713; Docket No.
FAA20210721; Project Identifier MCAI202000616R.
a Effective Date This airworthiness directive AD is effective October 12, 2021.
b Affected ADs None.
c Applicability This AD applies to PZL Swidnik S.A.
Model PZL W3A helicopters, certificated in any category, with hoist type 76378 or hoist carrying assembly bracket bracket part number P/N 39.30.205.03.01 or 39.30.213.00.00 installed.
d Subject Joint Aircraft Service Component JASC
Code: 2500, Cabin Equipment/Furnishings.
e Unsafe Condition This AD was prompted by a report of fractured bracket bolts. The FAA is issuing this AD to prevent detachment of the bracket resulting in movement of the hoist carrying assembly around the axis of the remaining two lower brackets. The unsafe condition, if not addressed, could result in damage to the helicopter and loss of hoisted load or persons.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 For helicopters with a hoist type 76378
installed, before further flight after the effective date of this AD:
i Clean the area where bracket P/N
39.30.205.03.01 or 39.30.213.00.00 is installed to the fuselage structure using extraction or aliphatic naphtha. Using a flashlight and a magnifying glass with a minimum x5 magnification, inspect around the bracket edge and near each nut for cracked sealing compound. Refer to Figure 1
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of WYTWO
KOMUNIKACYJNEGO PZL-Swidnik Spo5ka Akcyjna Mandatory Bulletin No. BO
3719296, dated July 30, 2019 MB BO37
19296, for an example of cracked sealing compound.
A If there is any cracked sealing compound, before further flight, remove the hoist from service. Reinstallation of a hoist type 76378 that has not been removed from service is allowed, provided that, before installation, the helicopter is modified in
PO 00000

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Fmt 4700

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accordance with a method approved by the Manager, General Aviation and Rotorcraft Section, International Validation Branch, FAA; or EASA; or PZL Swidnik S.A.s EASA
Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
Following modification, all repetitive inspections, replacements, and applicable corrective actions must be done as specified in this AD.
B If there are no cracks in the sealing compound, before further flight, replace each bracket bolt one-by-one by following Chapter II, paragraphs A.4.b. through i., of MB BO
3719296, except where it states to use extraction naphtha, you may substitute aliphatic naphtha. Remove each previouslyinstalled bracket bolt, nut, washer, and cotter pin from service.
C As an option to the actions required by paragraph g1iB of this AD, deactivate the hoist by following Chapter II, paragraph 3.2.2., of MB BO3719296; and thereafter, before each flight, inspect the sealing compound by accomplishing the actions required by paragraph g1i of this AD.
ii If there are no cracks in the sealing compound, within 25 hours time-in-service TIS after the replacement required by paragraph g1iB of this AD, and thereafter at intervals not to exceed 25 hours TIS, accomplish the actions required by paragraph g1i of this AD.
iii Within 800 hoist cycles after the replacement required by paragraph g1iB of this AD, and thereafter at intervals not to exceed 800 hoist cycles, replace each bracket bolt by accomplishing the actions required by paragraph g1iB
of this AD. For the purposes of this AD, a cycle is counted anytime the cable is extended and then retracted during flight or on the ground, for any cable length extended and retracted and with or without load.
2 For helicopters with a bracket P/N
39.30.205.03.01 or 39.30.213.00.00 installed, but no hoist installed, as of the effective date of this AD, do not install a hoist type 76378
unless the actions required by paragraph g1 of this AD have been accomplished.
3 As of the effective date of this AD, do not install bracket P/N 39.30.205.03.01 or 39.30.213.00.00 and hoist type 76378 on any helicopter unless the actions required by paragraph g1 of this AD have been accomplished.
h 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 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 i1 of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager
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