Airworthiness directives › 2020-07-22
AD 2020-07-22 Airworthiness Directives; PZL Swidnik S.A. Helicopters
Applicability*9
This AD becomes effective May 5, 2020.
Compliance
(1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email 9-ASW-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.
Required actions
The subject of this AD is addressed in European Union Aviation Safety Agency (previously European Aviation Safety Agency) (EASA) AD No. 2018-0238, dated November 6, 2018. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2020-0390.
Unsafe condition
(1) Within 25 hours time-in-service (TIS), inspect each bolt to determine if it is properly locked with the washer by following Chapter II, Inspection Procedure, paragraphs 3.1.a) and 3.1.b) of WYTWÓRNIA SPRZĘTU KOMUNIKACYJNEGO “PZL-Świdnik” Spólka Akcyjna Mandatory Bulletin No. BO-37-18-289, dated October 23, 2018 (MB BO-37-18-289). If any bolt is not properly locked, before further flight: (i) Remove the engine to visually inspect the bolt head for any sign of rubbing and deformation. (ii) If there is no sign of rubbing or deformation, loosen the bolt and tighten to the correct torque value of 2.5-3.0 Nm. Lock the bolt by folding tabs of the washer up to the side surfaces of the bolt head. Photo 4 of MB BO-37-18-289 shows an example of a properly locked bolt. (iii) If there is any sign of rubbing or deformation; (A) Remove from service the bolt. (B) Remove the left-hand (LH) and right-hand (RH) input drive quill seals by following paragraphs 1.1. through 1.6., Procedure—Case B. Attachment 1 to MB BO-37-18-289. (C) Visually inspect each graphite seal assembly of the LH and RH input drive quill seals for any crack, damage, and surface deformation in the surface area identified as “D” of Sketch 3. Radial Seal, Attachment 1 to MB BO-37-18-289, and any crack, damage, surface deformation, cracked graphite segments and seizing of grooves in the surface area identified as “E” of Sketch 3. Radial Seal, Attachment 1 to MB BO-37-18-289. For purposes of this inspection, damage to the graphite seal assembly may be indicated by spalling, chipping, scratches, or dents. Also visually inspect for unsmooth freedom of radial motion of each graphite ring in the surface area identified as “E” of Sketch 3. Radial Seal, Attachment 1 to MB BO-37-18-289, any scratch and dent in the surface areas identified as “A” and “B” of Sketch 3. Radial Seal, Attachment 1 to MB BO-37-18-289, and seizing on the surface area identified as “C” of Sketch 3. Radial Seal, Attachment 1 to MB BO-37-18-289. ( 1 ) If there is any crack, damage, or surface deformation in surface area “E” greater than an area of 1.5 mm 2 or a depth of 1mm, before further flight, remove from service the graphite seal assembly. ( 2 ) If there is any spalling or chipping in surface area “E” that is equal to or less than an area of 1.5 mm 2 and a depth of 1 mm, or any scratch or dent in surface areas “A” or “B” or seizing in surface area “C” that is acceptable after blending material flashes, before further flight, replace the graphite seal assembly. ( 3 ) If there is any crack, damage, or surface deformation on surface “D”, cracked graphite segments or seizing of grooves on surface “E”, any scratch or dent in surface areas “A” or “B” or seizing in surface area “C” that is not acceptable after blending material flashes, or radial motion of graphite rings is difficult and not smooth, before further flight, remove from service the graphite seal assembly. (2) After the effective date of this AD, do not install a WR-3 MGB with an S/N up to 316463007M inclusive and with a bolt P/N 89.00.0049 and washer P/N 89.06.0387 on any PZL Model PZL W-3A helicopter, unless it has been inspected in accordance with the requirements of this AD.
Affected ADs
This AD defines the unsafe condition as improper locking of the bolts which secure the input quill cover and graphite seal assembly of the WR-3 MGB. This condition could result in disconnection of an engine to the MGB mechanical link and subsequent loss of control of the helicopter.
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