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Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations end and body end for a crack in the areas depicted in Figure 2 of Finmeccanica Bollettino Tecnico No. 189080, Revision A, dated July 15, 2016 BT 189080.
i If there is a crack on the body end, before further flight, replace the MR damper.
ii If there is a crack on the rod end, before further flight, replace the rod end and, within 300 hours TIS, dye penetrant or eddy current inspect the rod end for a crack as described in paragraph e3 of this AD.
iii If there are no cracks, before further flight, mark the rod end and body end with a dot of black polyurethane paint as shown in Figure 13 of BT 189080.
iv Thereafter, before the first flight of each day, using a mirror and a magnifying glass visually inspect each rod end and body end for a crack in the areas shown in Figure 14 of BT 189080. If there is a crack in the rod end, before further flight, replace the rod end. If there is a crack on the body end, before further flight, replace the MR damper.
4 Within the compliance times listed in paragraphs e4i and ii of this AD, inspect each rod end bearing and body end for bearing rotation in the damper seat. An example of rotation misaligned slippage marks is shown in Figure 4 of BT 189080.
If there is any bearing rotation in the rod end, before further flight, replace the rod end. If there is any bearing rotation in the body end, before further flight, replace the MR damper.
i For MR dampers that have accumulated less than 300 hours TIS since new or since the last overhaul, within 30 hours TIS and thereafter at intervals not to exceed 10 hours TIS.
ii For MR dampers that have accumulated 300 or more hours TIS since new or since the last overhaul, within 5 hours TIS and thereafter before the first flight of each day.
5 For helicopters with an MR damper with a serial number S/N MCR0001 through MCR0154 and MCR0174 through MCR0195, within 30 hours TIS and thereafter at intervals not to exceed 20 hours TIS until the MR damper has accumulated 600 hours TIS, visually inspect each MR damper broached ring nut for broken teeth, proper engagement, and alignment as depicted in Figure 5 and shown in Figures 6, 7, and 8 of BT 189080.
If there is a broken tooth, improper engagement, or misalignment of the broached ring nut, before further flight, remove from service the rod end and broached ring nut.
6 Within 50 hours TIS and thereafter at intervals not to exceed 100 hours TIS:
i Rotate the body end around the damper axis to put it near the middle position and determine the bearing friction torque value of the body end, using as a reference Figure 11
of BT 189080.
Note 1 to Paragraph e6i: Applying too much force while rotating the body end around the damper axis may cause damage.
A If the torque value of the body end is more than 30.0 Nm 265.5 in lb, before further flight, replace the MR damper.
B If the torque value of the body end is 30.0 Nm 265.5 in lb or less, determine the bearing friction torque value of each rod end, using as a reference Figure 11 of BT 189080.
If the torque value of the rod end is more than 30.0 Nm 265.5 in lb, before further flight, replace the rod end.

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ii Inspect each MR damper anti-rotation block for wear by following paragraphs 4.3
through 4.3.6 of the Compliance Instructions, Part VI, of BT 189080. If there is wear, before further flight, replace the MR damper anti-rotation block.
7 Within 50 hours TIS:
i On each MR damper, replace special washer P/N 3G6220A05051 with special washer P/N 3G6220A05052.
ii For helicopters with an MR damper with a S/N MCR0001 through MCR0041, MCR0043, MCR0045 through MCR0151, MCR0153 through MCR0157, MCR0159
through MCR 0179, and MCR0185 through MCR0370; and for MR dampers with a rod end P/N M00601H004045 or P/N M006
01H004053 installed, do the following:
A Inspect each broached ring for wear, bent teeth, missing teeth, and stripped threads. Pay particular attention to the four pins that engage the piston grooves. If there is any wear or damage to the broached ring, before further flight, remove from service the broached ring. An example of an acceptable broached ring is shown in Figure 4, Annex A, of BT 189080.
B Align each rod end and broached ring by applying a torque of 60 Nm 531 in lb to 80 Nm 708 in lb. If the rod end and broached ring cannot be aligned, before further flight, replace the broached ring.
8 Except for MR dampers with a S/N
MCR0042, MCR0044, MCR0152, MCR0158, and MCR0180 through MCR0184, do not install an MR damper P/N 4F6220V00251 on any helicopter unless the MR damper has passed the requirements in paragraph e7ii of this AD.
f Credit For Previous Actions 1 Actions accomplished before the effective date of this AD in accordance with the Compliance Instructions, Part II, of Finmeccanica Bollettino Tecnico No. 189
069, dated February 12, 2016 BT 189069, are considered acceptable for compliance with the corresponding actions in paragraph e7i of this AD.
2 Actions accomplished before the effective date of this AD in accordance with the Compliance Instructions, Part III, of BT
189069, are considered acceptable for compliance with the corresponding actions in paragraph e7ii of this AD.
g Alternative Methods of Compliance AMOCs 1 The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, AD
Program Manager, Operational Safety Branch, Airworthiness Products Section, General Aviation & Rotorcraft Unit, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 8172225110; email 9-ASW-FTWAMOC-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.

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h Additional Information 1 Finmeccanica Bollettino Tecnico No.
189069, dated February 12, 2016, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate Va Italy; telephone +390331
225074; fax +390331229046; or at https
www.leonardocompany.com/en/home. You may view the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX 76177.
2 The subject of this AD is addressed in European Aviation Safety Agency now European Union Aviation Safety Agency EASA No. 20160145R1, dated January 17, 2018. You may view the EASA AD on the internet at https www.regulations.gov in Docket No. FAA20200503.
i Subject Joint Aircraft Service Component JASC
Code: 6200, Main Rotor System.
j 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. 552a 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 Finmeccanica Bollettino Tecnico No.
189080, Revision A, dated July 15, 2016.
ii Leonardo Helicopters Alert Service Bulletin No. 189102, Revision A, dated December 21, 2017.
3 For service information identified in this AD, contact Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G. Agusta 520, 21017 C. Costa di Samarate Va Italy; telephone +390331
225074; fax +390331229046; or at https
www.leonardocompany.com/en/home.
4 You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 8172225110.
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.
Issued on January 6, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202103658 Filed 22421; 8:45 am BILLING CODE 491013P

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