AD 2021-18-12 Airworthiness Directives; PZL Swidnik S.A. Helicopters

Models named: PZL W-3A. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to PZL Swidnik S.A. Model PZL W-3A 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.

Comply with this AD within the compliance times specified, unless already done.

(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 of WYTWÓRNIA SPRZĘTU KOMUNIKACYJNEGO “PZL-Świdnik” Spółka Akcyjna Mandatory Bulletin No. BO-37-19-296, dated July 30, 2019 (MB BO-37-19-296), 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 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-37-19-296, except where it states to use extraction naphtha, you may substitute aliphatic naphtha. Remove each previously-installed bracket bolt, nut, washer, and cotter pin from service. (C) As an option to the actions required by paragraph (g)(1)(i)(B) of this AD, deactivate the hoist by following Chapter II, paragraph 3.2.2., of MB BO-37-19-296; and thereafter, before each flight, inspect the sealing compound by accomplishing the actions required by paragraph (g)(1)(i) 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 (g)(1)(i)(B) of this AD, and thereafter at intervals not to exceed 25 hours TIS, accomplish the actions required by paragraph (g)(1)(i) of this AD. (iii) Within 800 hoist cycles after the replacement required by paragraph (g)(1)(i)(B) of this AD, and thereafter at intervals not to exceed 800 hoist cycles, replace each bracket bolt by accomplishing the actions required by paragraph (g)(1)(i)(B) 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 (g)(1) 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 (g)(1) of this AD have been accomplished.

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 person(s).

None.