# Leonardo Alert Service Bulletin 189-237: Revision A - Rights: © Leonardo S.p.A. Filed by the FAA in regulations.gov docket FAA-2021-0612, the docket of AD 2021-20-17. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Leonardo Alert Service Bulletin 189-237](https://openairdocs.org/service-documents/leonardo/sb-189-237.md) - Title as filed: Leonardo Helicopters Emergency ASB No. 189-237 Rev A - Pages: 49 - PDF: https://openairdocs.org/files/sha256/57/5d/575ddf496db2e2819c2043651ee4ed5f1b730aee61f1abe16754e1ef0341500e - Page: https://openairdocs.org/service-documents/leonardo/sb-189-237/file/575ddf496db2 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 N° 189-237 DATE: May 29, 2019 REV. : A - September 5, 2019 Page 1 of 48 TITLE ATA 64 - TAIL ROTOR FLIGHT CONTROL IMPROVED PERIODICAL INSPECTION REVISION LOG Revision A of this Service Bulletin cancels and supersedes the previous Revision /. Revision A is issued in order to introduce the following changes: • Update the “Compliance” section clarifying the note relevant to accomplishment of Part VI. • Provide instruction to remove the castellated nut in pl ace of loosen it while performing the replacement of the TR duplex bearing. • Add closure action in case of findings after accomplishment with Part VI step 3. • Add cleaning instruction of the TR duplex bearing area in Part V before installation of the spider plug. • Add details to cleaning procedure of spacer control rod surface with aliphatic naphtha. • Add use of a borescope as alternative mean to perform i nspection of Part I, in such case the removal of the access panels 495A and 496A is not required. • In case of no-findings after the inspections, it is not required anymore to send feedback to LHD. • Add HUMS data download in case TRA HUMS accelerometer h as been already installed to helicopter. • Update the reference to Annex A - UTC Microtecnica Service Bulletin 67-0006 Issue 1. Leonardo S.p.A. Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595 An appropriate entry should be made in the aircraft log book upon accomplishment. If ownership of aircraft has changed, please, forward to new owner. EMERGENCY ALERT SERVICE BULLETIN ### Page 2 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 2 of 48 REVISION: A - September 5, 2019 Revision bars in the margins identify changes. ### Page 3 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 3 of 48 1. PLANNING INFORMATION A. EFFECTIVITY Part I: All AW189 helicopters. Part II: All AW189 helicopters. Part III: All AW189 helicopters. Part IV: All AW189 helicopters. Part V: All AW189 helicopters. Part VI: All AW189 helicopters. B. COMPLIANCE Part I: Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH. NOTE Every time it is required to perform Part II, accomplishment of Part I, Part IV and Part V on the same maintenance downtime, must be performed as a prerequisite. If Part III is required in the same maintenance downtime, it shall be performed last. Part II: Within 50 FH from last application of Part II of SB 1 89-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 50 FH. Part III: Within 20 FH from last application of Part III of SB 189-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the installation every 20 FH. Part IV: Within 10 FH from last application of Part IV of SB 1 89-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH. NOTE Perform as a prerequisite Part I and Part IV. If Part III is required in the same maintenance downtime, it shall be performed lastly. ### Page 4 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 4 of 48 REVISION: A - September 5, 2019 Part V: Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH. NOTE • After the first accomplishment of Part VI repeat Part VI phased with Part II, not exceeding 200FH from the first application of the Part VI. Then repeat every 200FH. • Perform in sequence Part I, Part IV, Part V as a prerequisite. • If Part II is required in the same maintenance downtime, it shall be performed after Part V and before Part VI. • If Part III is required in the same maintenance downtime, it shall be performed after Part VI. Part VI: Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 200 FH. C. CONCURRENT REQUIREMENTS This SB supersedes and replaces the SB 189-224. D. REASON This Service Bulletin is issued in order to require the periodical inspection of the slippage marking of the back-end castellated nut of th e TR servo-actuator and the periodical detailed inspection of the TR duplex bearing. E. DESCRIPTION Following additional tests and the completion of the i nitial phase of the in service monitoring carried out on the AW169 and AW189 fleet, it has been confirmed that the introduction of a temperature monitoring represents a n effective independent measure to confirm the health of the TR bearing. In addition a refinement of the current inspection schedule is required with this SB along with the introduction of an additional instruction for duplex bearing roughness check. This Service Bulletin provides the instructions for the above together with the transition to the new inspection regime. ### Page 5 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 5 of 48 In details Part I of this Service Bulletin provides th e periodical detailed inspection of the slippage marking of the castellated nut installed on the back end of the TRA. Part II partly retains the requirement of the Part I I of the SB 189-224 defining the required detailed inspection requirement of TR duplex bearing. Part III provides the instructions to install a dedicated thermal strip in the area of the TR duplex bearing. Part IV provides the instructions to recursively check the thermal strip. Part V requires the verification of metallic particle presence in the grease that could be found on the visible part of the duplex bearing. Thi s check was already present in the Part II of the SB 189-224 and it is now confirmed with a tighter compliance. Part VI prescribe an additional roughness check of the duplex bearing to be performed after removal of the spider assembly. Incorrect installation of the TR servo-actuator back-end nut or seizure of the TR duplex bearing may lead to loss of Tail Rotor control which, depending on the flight condition, could lead to loss of control of the aircraft. Feedback on the compliance to this Service Bulletin is required. Revision A of this Service Bulletin allows the simplif ication of Part I inspection and reduce the amount of feedback required after “no-findings” inspections. F. APPROVAL The technical content of this Service Bulletin is approve d under the authority of DOA nr. EASA.21.J.005. For helicopters registered under oth er Aviation Authorities, before applying the Service Bulletin, applicable Aviation Auth ority approval must be checked within Leonardo Helicopters customer portal. E.A.S.A. states mandatory compliance with inspections, mod ifications or technical directives and related time of compliance by means of rel evant Airworthiness Directives. If an aircraft listed in the effectivity embodies a m odification or repair not LHD certified and affecting the content of this Service Bulletin, it is responsibility of the Owner/Operator to obtain a formal approval by Aviation Authority having jurisdiction on the aircraft, for any adaptation necessary before incor poration of the present Service Bulletin. G. MANPOWER To comply with this Service Bulletin the following MMH are deemed necessary: Part I: approximately one (0.5); Part II: approximately three (3); ### Page 6 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 6 of 48 REVISION: A - September 5, 2019 Part III: approximately half (0.5); Part IV: approximately one (1). Part V: approximately one (0.5); Part VI: approximately three (3); MMH are based on hands-on time and can change with per sonnel and facilities available. H. WEIGHT AND BALANCE N.A. I. REFERENCES 1) PUBLICATIONS DATA MODULE DESCRIPTION PART DM01 89-A-00-20-00-00A-120A-A Helicopter on ground f or a safe maintenance. I, II; III, IV, V, VI DM02 89-A-06-41-00-00A-010A-A Access door provision I, II DM03 89-A-64-31-01-00A-520A-A Pitch link - Remove pro cedure II DM04 89-A-64-31-01-00A-720A-A Pitch link - Install pr ocedure II, IV, V, VI DM05 89-A-64-31-03-00A-520A-A Spider plug - Remove procedure II, III, IV,V DM06 89-A-64-31-03-00A-720A-A Spider plug - Install procedure II, III, IV, V DM07 89-A-64-31-02-00A-520A-A Scissors group – Remove procedure II DM08 89-A-64-31-04-00A-520A-A Spider and slider assemb ly - Remove procedure II, VI DM09 89-A-64-31-04-00A-720A-A Spider and slider assemb ly - Install procedure II, VI DM10 89-A-64-31-05-00A-520A-B Duplex bearing - Remo ve procedure II, IV, V, VI DM11 89-A-64-31-05-00A-720A-B Duplex bearing - Insta ll procedure II, IV, V, VI 2) ACRONYMS SB Service Bulletin DM Data Module DOA Design Organization Approval EASA European Aviation Safety Agency LHD Leonardo Spa Helicopters ### Page 7 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 7 of 48 MMH Maintenance Man Hours SB Service Bulletin FH Flight Hours TR Tail Rotor TRA Tail Rotor Actuator 3) ANNEX Annex A UTC AEROSPACE SYSTEMS SB 67-0006 Issue 1. J. PUBLICATIONS AFFECTED N.A. K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A. ### Page 8 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 8 of 48 REVISION: A - September 5, 2019 2. MATERIAL INFORMATION A. REQUIRED MATERIALS 1) PARTS Refer to AW189 IPD for the spares materials required t o comply with the AMP DMs referenced in the accomplishment instructions. 2) CONSUMABLES The following consumable materials, or equivalent, are necessary to accomplish this Service Bulletin: # Spec./LHD code number DESCRIPTION Q.TY NOTE PART 1 Thermax 8 Level strip indicator code No.26805 Thermal strip AR (1)(2)(3) III,IV 2 TT-N-95-B / Code No. 531055030 Aliphatic Naphtha (C059) AR (1) III,IV Refer to AW189 AMDI for the consumables required to com ply with the AMP DMs referenced in the accomplishment instructions. 3) LOGISTIC MATRIX N.A. NOTE (1) Item to be furnished as local supply. (2) Thermal strip Thermax 5 Level clock style indicat or code No.26004 may be used as a valid alternative. (3) The use of further alternative strip is allowed pr ovided that it complies with the following requirements: • Irreversible temperature indication. • Self-Adhesive. • Temperature Range shall be included within 100°C – 1 60°C provided that it shows a discrete level at 121±2°C. • Overall measurement accuracy: ±2°C. • The maximum allowed length to prevent overlap is 80 mm. In case any clarification is needed, contact the Product S upport Engineering (pse_aw189.mbx.aw@leonardocompany.com). ### Page 9 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 9 of 48 B. SPECIAL TOOLS Refer to ITEP for the special tools required to comply with the AMP DMs referenced in the accomplishment instructions. C. INDUSTRY SUPPORT INFORMATION Owners/Operators who comply with the instructions of this Service Bulletin no later than the applicable date in the “Compliance” section wi ll be eligible to receive REQUIRED MATERIALS on free of charge basis, except for Consumable Materials and Special Tools. NOTE: Customers who fail to comply with the instruction s in this Service Bulletin before the compliance date are not eligible for the aforementioned special policy. Please Issue relevant MMIR form to your Warranty Administration Dpt. NOTE: WRM will include RETURN MATERIAL AUTHORIZATION (RMA) number; the unit disembarked from the aircraft has to be returned to LHD within thirty (30) calendar days after the shipment of the replacement part. In case of missing return within thirty (30) calendar days, Customer will be invoiced for the price of the replacement part. ### Page 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 10 of 48 REVISION: A - September 5, 2019 3. ACCOMPLISHMENT INSTRUCTIONS GENERAL NOTES a) Place an identification tag on all components that are re-usable, including the attaching hardware that has been removed to gain access to the modification area and adequately protect them until their later re-use. PART I 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. NOTE Removal of access panels 496A and 495A can be avoided if visual access to the inspection area is available by other means. A suitable boroscope can be inserted in the grid of access panel 496A as shown on Figure 3. 2. In accordance with AMP DM 89-A-06-41-00-00A-010A-A, remove the access panels 496A and 495A. 3. Take a picture of the back-end area of the TRA clear ly showing the slippage mark, and keep a record in a local archive to be made available if required. 4. With reference to Figure 3, check the slippage mark o n the castellated nut for absence of evidence of rotation between the parts. Record the result on Table I (refer to Figure 7). 5. If any evidence of rotation is found, contact the Pr oduct Support Engineering (pse_aw189.mbx.aw@leonardocompany.com), wait for further instructions before to perform the following checks: 5.1 Perform Part II of this SB; 5.2 Perform Part V of this SB; 5.3 Send the picture taken at step 3 to Product Suppo rt Engineering (pse_aw189.mbx.aw@leonardocompany.com). 5.4 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. ### Page 11 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 11 of 48 6. If no evidence of rotation is found in step 4, ret urn the helicopter to a ready to flight condition and record for compliance with Part I of this Service Bulletin on the helicopter logbook. 7. Send the attached compliance form and the compiled T able I to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. ### Page 12 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 12 of 48 REVISION: A - September 5, 2019 PART II 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. 2. In accordance with AMP DM 89-A-64-31-03-00A-520A-A, remove the spider plug. 3. In accordance with AMP DM 89-A-64-31-01-00A-520A-A, remove all the pitch links from the TR. 4. In accordance with applicable steps of AMP DM 89-A-64- 31-02-00A-520A-A, disconnect the upper half scissors from the spider. 5. Remove and discard the strap that attach the boot to the spider and slider assembly. Disconnect and lower the boot from the spider. 6. Perform the inspection of the TR duplex bearing in accordance with the following procedure: 6.1 Inspect the visible part of the TR duplex bearing (including the seals) for absence of wear, damages and security of attachment. Record the results on Table II (refer to Figure 8). 6.2 Check for absence of axial play when trying to move t he spider along the control rod axis. Record the result on Table II (refer to Figure 8). NOTE With reference to Figure 1 and Figure 2 Details B and C, apply a 35 ± 2.5 N upward force on the squared ro d end by means of a dynamometer while performing the instructions reported in steps from 6.3 to 6.7. It is allowed to apply the force either pushing or pulling the rod end with the dynamometer. 6.3 Perform at least three (3) complete and continuous revolutions of the spider both in clockwise and in counterclockwise directions and verify that the spider has a free and easy rotation. Record the result on Table II (refer to Figure 8). 6.4 Put one arm of the spider along the vertical posit ion; locate a dynamometer gauge on the spider arm hole (pitch link upper bolt l ocation). Hold the gauge perpendicular to the spider arm surface. Gently push ri ghtward the device until a slight rotation of the spider occurs (see Figure 2 for fu rther details and dynamometer positioning). Record the force measured on Table II (refer to Figure 8). 6.5 Repeat step 6.4 for the opposite spider rotation o n the same arm, pushing leftward the dynamometer gauge from the vertical posi tion of the spider arm. ### Page 13 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 13 of 48 Record the force measured on Table II (refer to Figure 8). 6.6 Repeat steps 6.4 and 6.5 for all the other three spider arms. 6.7 The force detected by dynamometer on steps 6.4 thru 6.6 shall be measured within 2 N and 10 N. 7. If none of the checks performed in step 6 fails procee d as follows, otherwise skip to step 8. NOTE Removal of access panel 496A can be avoided if visual access to the inspection area is available by other means. A suitable boroscope can be inserted in the grid of access panel 496A as shown on Figure 3. 7.1 In accordance with AMP DM 89-A-06-41-00-00A-010A -A, remove the access panels 496A and 495A. 7.2 With reference to Figure 3, check the slippage mar k on the castellated nut for absence of evidence of rotation between the parts by me ans of the borescope. If any evidence of rotation is found, immediately contact the PSE (pse_aw189.mbx.aw@leonardocompany.com) and wait for further instructions. 7.3 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. 7.4 Skip to step 12. 8. If one of the checks performed from step 6.1 to 6.2 fails skip to step 10, otherwise proceed with the following step 9. 9. If one of the checks performed from step 6.3 to step 6.7 fails proceed as follows: 9.1 Perform the cleaning procedure of the sliding contr ol assy in accordance with the following procedure: 9.1.1 In accordance with AMP DM 89-A-06-41-00-00A-010A -A remove the access panels 496A and 495A. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 9.1.2 In accordance with the applicable steps of UTC SB 6 7-0006, remove and discard the cotter pin and the lockwire from the ca stellated nut of the TRA back-end and remove the nut. 9.1.3 In accordance with applicable steps of AMP DM 89-A- 64-31-04-00A- 520A-A, remove the spider and slider assembly. ### Page 14 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 14 of 48 REVISION: A - September 5, 2019 9.1.4 Clean the external surface of the spider and slid er assembly by means of soft lint-free cloth. 9.1.5 Clean the accessible internal surface of the slider bushing by means of soft lint-free cloth. 9.1.6 In accordance with applicable steps of AMP DM 89-A- 64-31-04-00A- 720A-A, reinstall the spider and slider assembly. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end 9.1.7 In accordance with the applicable steps of UTC SB 6 7-0006, reinstall castellated nut of the TRA back-end and cotter pin P/N EN2367-29020 and lockwire P/N MS20995C20. 9.1.8 With reference to Figure 3, restore the slippag e marking on the castellated nut from the hinge bracket element to the rod. 9.2 Repeat steps from 6.2 to 6.7 to verify the absence of axial play of TR duplex bearing and to perform again the roughness and breaka way force checks of TR duplex bearing. 9.3 If any of the checks performed in step 9.2 fails pr oceed with the following step 10, otherwise skip to step 12. 10. Contact immediately the Product Support Engineeri ng (pse_aw189.mbx.aw@leonardocompany.com) to receive further instruction before performing the replacement of the TR duplex bearing in accordance with the following procedure: 10.1 If the helicopter is already compliant with the S B 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 10.2 In accordance with the applicable steps of UTC SB 67 -0006, remove and discard the cotter pin and the lockwire from the castellated n ut of the TRA back-end and remove the nut. ### Page 15 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 15 of 48 NOTE Before removal of the TR duplex bearing, take note of its installation orientation marking “OUT” on the outboard visible face. After removal mark “IN” on the inboard opposite face of the TR duplex bearing. Use an indelible pen. 10.3 In accordance with AMP DM 89-A-64-31-05-00A-520A- B, remove the TR duplex bearing. 10.4 Collect the grease leaked from the TR duplex beari ng “IN” marked side in a container different from the one used before. 10.5 Take a picture of both faces of the removed TR du plex bearing and send them to PSE (pse_aw189.mbx.aw@leonardocompany.com) before returning the bearing. 10.6 Clean by means of a soft lint-free cloth the housi ng of the TR duplex bearing, the rod visible part and the internal side of the spider plug. 10.7 In accordance with AMP DM 89-A-64-31-05-00A-720A- B, install a new TR duplex bearing. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 10.8 In accordance with the applicable steps of UTC SB 67 -0006, reinstall castellated nut of the TRA back-end and cotter pin P/N EN2367-290 20 and lockwire P/N MS20995C20. 10.9 With reference to Figure 3, restore the slippage marking on the castellated nut from the hinge bracket element to the rod. 11. In case replacement of the TR duplex bearing is req uired, please return immediately (within 2 days) the removed TR duplex bearing and th e collecting containers of the grease to Leonardo Helicopters. Contact the Product Su pport Engineering (pse_aw189.mbx.aw@leonardocompany.com) to receive the proper instructions to return the removed component. 12. In accordance with AMP DM 89-A-64-31-01-00A-720A-A , while performing installation of TR pitch links, it is possible to re-protect TR pitch l inks and the scissors using the following procedure. 12.1 Clean the bolts by means of cleaning solvent. ### Page 16 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 16 of 48 REVISION: A - September 5, 2019 12.2 Check the bolts looking for corrosion. Contact the P roduct Support Engineering (pse_aw189.mbx.aw@leonardocompany.com) in case of any findings. 12.3 Protect the parts using Tectyl Grade I or Thixof lex Black as a valid alternative. 13. In accordance with AMP DM 89-A-64-31-03-00A-720A-A , install the spider plug. NOTE In case of any findings, report within 2 days the inspection results along with the available records of the previous checks. 14. Send the attached compliance form and the compiled Table II to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. 15. Return the helicopter to a ready to flight condit ion and record for compliance with Part II of this Service Bulletin on the helicopter logbook. ### Page 17 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 17 of 48 PART III 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. 2. In accordance with AMP DM 89-A-64-31-03-00A-520A-A, remove the spider plug. 3. With reference to Figure 4, perform the installati on of thermal strip Thermax 8 level strip No.26805 or equivalent as follows: 3.1 Clean the spacer control rod P/N 4F6430A02551 surfa ce with a soft lint-free cloth soaked with a small quantity of aliphatic naphtha. The n dry the surface with a clean cloth. 3.2 With reference to Figure 5, if the selected therma l strip exceeds the height of 16 mm it shall be cut taking care not to remove the Celsius scale and not to damage the sensitive elements of the strip. CAUTION When installing the thermal strip pay attention to: • avoid contact with bearing gaskets; • ensure a good adhesion with the spacer control rod P/N 4F6430A02551; • all temperature indicators of the thermal strip shall be visible. CAUTION If thermal strip trimming is required, confirm that the cut did not cause debonding of strip layers. 3.3 With reference to Figure 4, with the help of a n on metallic spatula, perform the installation of the thermal strip on the surface of the spacer control rod P/N 4F6430A02551. 4. In accordance with AMP DM 89-A-64-31-03-00A-720A-A, install the spider plug. 5. Return the helicopter to a ready to flight conditi on and record for compliance with Part III of this Service Bulletin on the helicopter logbook. 6. Send the attached compliance form to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. ### Page 18 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 18 of 48 REVISION: A - September 5, 2019 PART IV 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. 2. In accordance with AMP DM 89-A-64-31-03-00A-520A-A, remove the spider plug. 3. With reference to Figure 4, check the thermal strip for good adhesion and readability and proceed as follows: 3.1 If the thermal strip is properly installed proceed with step 4; 3.2 If the strip is detached, partially detached or unr eadable perform the spider and slider inspection in accordance with accomplishment instructio ns from step 3 to step 14 of Part II of this SB; 3.3 Replace the thermal strip in accordance with step 3 of Part III of this SB; 3.4 Skip to step 6. CAUTION In case the selected thermal strip does not provide a discrete value equal to 121°C, select the lowest value comprised within the range 121±2°C. 4. With reference to Figure 4, check the temperature r eached by the thermal strip installed on spacer control rod P/N 4F6430A02551. Make sure that the temperature has not reached a value equal to or above 121°C. Record the ch eck result on Table III (refer to Figure 9). 5. If temperature has exceeded a value equal to or ab ove 121°C, contact immediately the Product Support Engineering ( pse_aw189.mbx.aw@leonardocompany.com) and perform the following procedure. Otherwise, skip to Step 6: 5.1 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. 5.2 Contact immediately the Product Support Engineer ing (pse_aw189.mbx.aw@leonardocompany.com) to receive further instruction before thermal strip and duplex bearing removal and replacement. 5.3 Perform from step 3 to step 14 of Part II of this SB. 5.4 Perform from step 3 to step 10 of Part V of this S B. 5.5 Remove the spacer control rod P/N 4F6430A02551, w ithout removing the thermal strip. 5.6 Take a picture of the thermal strip, installed on the removed spacer control rod P/N 4F6430A02551 and send it to Product Support Engin eering (pse_aw189.mbx.aw@leonardocompany.com). ### Page 19 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 19 of 48 CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 5.7 In accordance with the applicable steps of UTC SB 67- 0006, remove and discard the cotter pin and the lockwire from the castellated n ut of the TRA back-end and remove the nut. NOTE Before removal of the TR duplex bearing, take note of its installation orientation marking “OUT” on the outboard visible face. After removal mark “IN” on the inboard opposite face of the TR duplex bearing. Use an indelible pen. 5.8 In accordance with AMP DM 89-A-64-31-05-00A-520A-B , remove the TR duplex bearing. 5.9 Collect the grease leaked from the TR duplex bearin g “IN” marked side in a container different from the one used before. 5.10 Take a picture of both faces of the removed TR du plex bearing and send them to PSE (pse_aw189.mbx.aw@leonardocompany.com) before returning the bearing. 5.11 Clean by means of a soft lint-free cloth the housi ng of the TR duplex bearing, the rod visible part and the internal side of the spider plug. 5.12 In accordance with AMP DM 89-A-64-31-05-00A-720A- B, install a new TR duplex bearing. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 5.13 In accordance with the applicable steps of UTC SB 67 -0006, reinstall castellated nut of the TRA back-end and cotter pin P/N EN2367-290 20 and lockwire P/N MS20995C20. 5.14 With reference to Figure 3, restore the slippage marking on the castellated nut from the hinge bracket element to the rod. 5.15 In case replacement of the TR duplex bearing is re quired, please return immediately (within 2 days) the removed TR duplex be aring, the collecting containers of the grease and the thermal strip to Leona rdo Helicopters. Contact ### Page 20 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 20 of 48 REVISION: A - September 5, 2019 the Product Support Engineering ( pse_aw189.mbx.aw@leonardocompany.com) to receive the proper instructions to return the removed component. 5.16 In accordance with AMP DM 89-A-64-31-01-00A-720A- A, while performing installation of TR pitch links, it is possible to re-pro tect TR pitch links and the scissors using the following procedure 5.16.1 Clean the bolts by means of cleaning solvent. 5.16.2 Check the bolts looking for corrosion. Contact th e Product Support Engineering ( pse_aw189.mbx.aw@leonardocompany.com) in case of any findings. 5.16.3 Protect the parts using Tectyl Grade I or Thix oflex Black as a valid alternative. 5.17 Go to step 6. 6. In accordance with AMP DM 89-A-64-31-03-00A-720A-A, install the spider plug. 7. Return the helicopter to a ready to flight conditi on and record for compliance with Part IV of this Service Bulletin on the helicopter logbook. NOTE In case of any findings, report within 2 days the inspection results along with the available records of the previous checks. 8. Send the attached compliance form and the compiled T able III to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. ### Page 21 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 21 of 48 PART V 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. 2. In accordance with AMP DM 89-A-64-31-03-00A-520A-A, remove the spider plug. 3. Perform a detailed inspection of TR duplex bearing in accordance with the following procedure: 3.1 Check the visible part of the TR duplex bearing fo r particles absence. CAUTION Pay attention not to damage the thermal strip durin g the grease sampling from the bearing housing. 3.2 Check the visible part of the TR duplex bearing a nd/or the spider plug for grease leakage and confirm absence of any particles by finger touch. 3.3 Put a small quantity of grease using a small spatul a in a transparent container and add a solvent (aliphatic naphtha). Then by using a magnet on the bottom out side of the container check for presence of metallic particles. 3.4 Record the result on Table IV (refer to Figure 1 0) and collect the grease leaked from the visible surface in a proper container. 4. If magnetic metallic and/or any other particles are found during accomplishment of step 3 proceed with the following step 5, otherwise skip to step 9. 5. Perform from step 3 to step 14 of Part II of this S B. 6. Contact immediately the Product Support Engineerin g (pse_aw189.mbx.aw@leonardocompany.com) to receive further instruction before performing the replacement of the TR duplex bearing in accordance with the following procedure: 6.1 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 6.2 In accordance with the applicable steps of UTC SB 67- 0006, remove and discard the cotter pin and the lockwire from the castellated n ut of the TRA back-end and remove the nut. ### Page 22 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 22 of 48 REVISION: A - September 5, 2019 NOTE Before removal of the TR duplex bearing, take note of its installation orientation marking “OUT” on the outboard visible face. After removal mark “IN” on the inboard opposite face of the TR duplex bearing. Use an indelible pen. 6.3 In accordance with AMP DM 89-A-64-31-05-00A-520A-B , remove the TR duplex bearing. 6.4 Collect the grease leaked from the TR duplex bearin g “IN” marked side in a container different from the one used before. 6.5 Take a picture of both faces of the removed TR dup lex bearing and send them to PSE (pse_aw189.mbx.aw@leonardocompany.com) before returning the bearing. 6.6 Clean by means of a soft lint-free cloth the housin g of the TR duplex bearing, the rod visible part and the internal side of the spider plug. 6.7 In accordance with AMP DM 89-A-64-31-05-00A-720A-B , install a new TR duplex bearing. CAUTION Pay attention to prevent rod rotation, when screwing / un-screwing the castellated nut, holding the rod square end. 6.8 In accordance with the applicable steps of UTC SB 67- 0006, reinstall castellated nut of the TRA back-end and cotter pin P/N EN2367-290 20 and lockwire P/N MS20995C20. 6.9 With reference to Figure 3, restore the slippage m arking on the castellated nut from the hinge bracket element to the rod. 7. In case replacement of the TR duplex bearing is requ ired, please return immediately (within 2 days) the removed TR duplex bearing and th e collecting containers of the grease to Leonardo Helicopters. Contact the Product Su pport Engineering (pse_aw189.mbx.aw@leonardocompany.com) to receive the proper instructions to return the removed component. 8. In accordance with AMP DM 89-A-64-31-01-00A-720A-A, while performing installation of TR pitch links, it is possible to re-protect TR pitch l inks and the scissors using the following procedure 8.1 Clean the bolts by means of cleaning solvent. 8.2 Check the bolts looking for corrosion. Contact the Pr oduct Support Engineering ### Page 23 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 23 of 48 (pse_aw189.mbx.aw@leonardocompany.com) in case of any findings. 8.3 Protect the parts using Tectyl Grade I or Thixofl ex Black as a valid alternative. 9. Clean the visible surface of the TR duplex bearing by means of soft lint-free cloth. 10. In accordance with AMP DM 89-A-64-31-03-00A-720A-A , install the spider plug. 11. Return the helicopter to a ready to flight condit ion and record for compliance with Part V of this Service Bulletin on the helicopter logbook. NOTE In case of any findings, report within 2 days the inspection results along with the available records of the previous checks. 12. Send the attached compliance form and the compiled Table IV to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. ### Page 24 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 24 of 48 REVISION: A - September 5, 2019 PART VI 1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply. 2. In accordance with applicable steps of AMP DM 89-A-64- 31-04-00A-520A-A, remove the spider and slider assembly. 3. Inspect the visible part of the inboard side of the TR duplex bearing (including the seals) for absence of wear, damages and absence of particles by l ooking inside the slider cylinder. Record the results on Table V (refer to Figure 11). 4. With reference to Figure 6 lock the slider of the sliding control assembly in a bench vice with padded jaws. 5. Examine the duplex bearing to find roughness in accordance with the following procedure: NOTE • To initiate rotation of the duplex bearing, a break-out force could be necessary. The break- out force is not an indication of roughness. • Relative axial movement between the inner races is acceptable and shall not be considered as a finding. 5.1 Use your fingers to push down on the upper face of the inner race of the duplex bearing. NOTE Do not release pressure, continue to apply pressure with your fingers during the subsequent step. 5.2 With reference to Figure 6 section A-A Step 1, push the top inner race down and at the same time turn it to feel if there is roughness. 5.3 Put your finger into the duplex bearing until y ou can pull up the lower face of the inner race. NOTE Do not release pressure, continue to apply pressure with your finger during the subsequent step. 5.4 With reference to Figure 6 section A-A Step 2, pul l the bottom inner race in the up direction and at the same time turn it to feel if there is roughness. 5.5 Repeat the Step 5.1 thru Step 5.4 at least one t ime to confirm the results. 5.6 Record the results of the previous steps on Table V (refer to Figure 11). ### Page 25 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 25 of 48 6. If any of the checks performed in the steps 3 and 5 fails proceed with the following step, otherwise skip to step 10. 7. Contact immediately the Product Support Engineerin g (pse_aw189.mbx.aw@leonardocompany.com) to receive further instruction before performing the replacement of the TR duplex bearing in accordance with the following procedure: 7.1 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise. NOTE Before removal of the TR duplex bearing, take note of its installation orientation marking “OUT” on the outboard visible face. After removal mark “IN” on the inboard opposite face of the TR duplex bearing. Use an indelible pen. 7.2 In accordance with AMP DM 89-A-64-31-05-00A-520A-B , remove the TR duplex bearing. 7.3 Collect the grease leaked from the TR duplex bearin g “IN” marked side in a container different from the one used before. 7.4 Take a picture of both faces of the removed TR dup lex bearing and send them to PSE (pse_aw189.mbx.aw@leonardocompany.com) before returning the bearing. 7.5 Clean by means of a soft lint-free cloth the housin g of the TR duplex bearing, the rod visible part and the internal side of the spider plug. 7.6 In accordance with AMP DM 89-A-64-31-05-00A-720A-B , install a new TR duplex bearing. 7.7 In accordance with the applicable steps of UTC SB 67- 0006, reinstall castellated nut of the TRA back-end and cotter pin P/N EN2367-290 20 and lockwire P/N MS20995C20. 7.8 With reference to Figure 3, restore the slippage m arking on the castellated nut from the hinge bracket element to the rod. 8. In case replacement of the TR duplex bearing is requ ired, please return immediately (within 2 days) the removed TR duplex bearing and th e collecting containers of the grease to Leonardo Helicopters. Contact the Product Su pport Engineering (pse_aw189.mbx.aw@leonardocompany.com) to receive the proper instructions to return the removed component. ### Page 26 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 26 of 48 REVISION: A - September 5, 2019 9. In accordance with AMP DM 89-A-64-31-01-00A-720A-A, while performing installation of TR pitch links, it is possible to re-protect TR pitch l inks and the scissors using the following procedure 9.1 Clean the bolts by means of cleaning solvent. 9.2 Check the bolts looking for corrosion. Contact the Pr oduct Support Engineering (pse_aw189.mbx.aw@leonardocompany.com) in case of any findings. 9.3 Protect the parts using Tectyl Grade I or Thixofl ex Black as a valid alternative. 10. In accordance with applicable steps of AMP DM 89-A-64 -31-04-00A-520A-A, reinstall the spider and slider assembly. 11. Return the helicopter to a ready to flight condit ion and record for compliance with Part VI of this Service Bulletin on the helicopter logbook. NOTE In case of any findings, report within 2 days the inspection results along with the available records of the previous checks. 12. Send the attached compliance form and the compiled Table V to the following mail box: pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”.  Non cancellare mai questo segnalibroNon cancellare mai interruzione sezione ### Page 27 Figure 1 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 27 of 48 ### Page 28 (OCR) K LEONARDO HELICOPTERS DETAIL C DYNAMOMETER 1 ALTERNATIVE APPLICATION DYNAMOMETER 2 SPIDER DETAIL D DYNAMOMETER 2 ORTHOGONAL TO SPIDER DYNAMOMETER 1 DYNAMOMETER 1 (VERTICAL POSITION) DETAIL B TRA SQUARED ROD END SPIDER DYNAMOMETER 2 Figure 2 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 ### Page 29 Figure 3 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 29 of 48 ### Page 30 Figure 4 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 30 of 48 REVISION: A - September 5, 2019 ### Page 31 (OCR) LEONARDO HELICOPTERS Cutting line. Pay attention to not cut the degree Celsius scale. 16mm Limit cutting at the minimum required to obtain 16mm of height. Pay attention to not damage or to expose to the environment the sensitive elements. NOTE Do not use a thermal strip if after having trimmed it, its sensitive element is exposed to air. See below an example of a badly cut strip. THERM 10 Thermal strip layers delamination. NOT acceptable. Figure 5 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 31 of 48 ### Page 32 Figure 6 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 32 of 48 REVISION: A - September 5, 2019 ### Page 33 Figure 7 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 33 of 48 TABLE I AIRCRAFT S/N SB COMPLIANCE DATE: P/N 6F6730V00331 TRA S/N A/C FH at SB COMPLIANCE DATE: TRA FH at SB COMPLIANCE DATE A/C LANDINGS at SB COMPLIANCE DATE: ACTION Required Obtained PART I CASTELLATED NUT paint mark check NO ROTATION BETWEEN PARTS ### Page 34 Figure 8 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 34 of 48 REVISION: A - September 5, 2019 TABLE II AIRCRAFT S/N SB COMPLIANCE DATE: P/N 4F6430V00551 TR DUPLEX BEARING S/N A/C FH at SB COMPLIANCE DATE: TR DUPLEX BEARING FH at SB COMPLIANCE DATE A/C LANDINGS at SB COMPLIANCE DATE: ACTION Required Obtained PART II TR DUPLEX BEARING wear and damages check NO FINDINGS TR SPIDER axial play check ABSENCE of AXIAL PLAY TR DUPLEX BEARING roughness check FREE AND EASY ROTATION TR DUPLEX BEARING breakaway torque check – Arm blue, clockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm yellow, clockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm red, clockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm white, clockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm blue, counterclockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm yellow, counterclockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm red, counterclockwise direction 2 N thru 10 N TR DUPLEX BEARING breakaway torque check – Arm white, counterclockwise direction 2 N thru 10 N ### Page 35 Figure 9 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 35 of 48 TABLE III AIRCRAFT S/N SB COMPLIANCE DATE: P/N 4F6430V00551 TR DUPLEX BEARING S/N A/C FH at SB COMPLIANCE DATE: TR DUPLEX BEARING FH at SB COMPLIANCE DATE A/C LANDINGS at SB COMPLIANCE DATE: ACTION Required Obtained PART IV THERMAL STRIP Temperature check TEMPERATURE SHALL NOT REACH A VALUE EQUAL TO OR ABOVE 121°C. ### Page 36 Figure 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 36 of 48 REVISION: A - September 5, 2019 TABLE IV AIRCRAFT S/N SB COMPLIANCE DATE: P/N 4F6430V00551 TR DUPLEX BEARING S/N A/C FH at SB COMPLIANCE DATE: TR DUPLEX BEARING FH at SB COMPLIANCE DATE A/C LANDINGS at SB COMPLIANCE DATE: ACTION Required Obtained PART V TR DUPLEX BEARING Particles check ABSENCE of ANY PARTICLES TR DUPLEX BEARING Grease leakage check ABSENCE of METALLIC PARTICLES ### Page 37 Figure 11 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 37 of 48 TABLE V AIRCRAFT S/N SB COMPLIANCE DATE: P/N 4F6430V00551 TR DUPLEX BEARING S/N A/C FH at SB COMPLIANCE DATE: TR DUPLEX BEARING FH at SB COMPLIANCE DATE A/C LANDINGS at SB COMPLIANCE DATE: ACTION Required Obtained PART VI TR DUPLEX BEARING Roughness check by fingers FREE AND EASY ROTATION TR DUPLEX BEARING wear, damages and particles check on the inboard side of the bearing NO FINDINGS ### Page 38 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 38 of 48 REVISION: A - September 5, 2019 ANNEX A UTC MICROTECNICA SERVICE BULLETIN 67-0006 ISSUE 1 ### Page 39 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY PROPRIETARY Copyright © UTC Aerospace Systems. This document and the information contained herein are the property of Microtecnica Srl. Recipient agrees to hold all such information in confidence and agrees it shall be used only for recipient's equipment or as may otherwise be permitted in an applicable agreement between recipient and Microtecnica Srl. This document and the information contained herein shall not be used for any other purpose, including the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, design, or configuration changes, or to obtain FAA or any other government or regulatory approval for same. Recipient agrees not to disclose such information to any third party, except as may otherwise be provided for in an applicable agreement between recipient and Microtecnica Srl. Copying or disclosure of this document and the information contained herein by anyone without Microtecnica Sri. prior written permission is not authorized and may result in criminal and/or civil liability. Microtecnica S.r.l. assumes no liability whatsoever, whether contractual, warranty, tort or otherwise, for unauthorized alteration or alterations not performed in accordance with Microtecnica S.r.l. approved procedures. This document does not contain export controlled technology or export controlled technical data. IT Export Classification: NSR Copyright (c) 2018, UTC Aerospace Systems TAIL ROTOR ACTUATOR (TRA) PN C161223-1 TORQUE CHECK AND RE-APPLICATION ON CASTELLATED NUT OF ROD Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 1 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 39 of 48 ### Page 40 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY 1. PLANNING INFORMATION A. Effectivity All Microtecnica TAIL ROTOR ACTUATOR (TRA) reported in Table 1 (all S/N's). Table 1 - Components Affected Nomenclature Part Number (MT) Manufacturer Type Certificate Holder Part Number (LH) Manufacturer Cage Code Tail Rotor Actuator C161223-1 6F6730V00331 A0076 B. Concurrent Requirements None. C. Reason To check and re-apply the torque of the castellated nut (60) connecting the rod (150) to the input lever (110) of the Tail Rotor Actuator (see Fig. 1a and 1b). Figure 1a Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 2 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 40 of 48 REVISION: A - September 5, 2019 ### Page 41 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY - 40 ,110 80 100 130 160 60 130 100 Figure 1b Table 1.1 - List of Items Item N. (ref. Fig. 1) Item Description 50 cotter pin 60 castellated nut 90 hinge bracket element 110 input lever 150 rod D. Description & Solution This Service Bulletin gives the instruction to check and re-apply the Torque of the castellated nut (60). E. Compliance It is recommended to introduce this Service Bulletin in accordance with Leonardo Helicopters Service Bulletin. F. Approval Government or other regulatory agency approval of this service bulletin is the responsibility of Leonardo Helicopters. G. Manpower The Manpower for the accomplishment of these operations is 1 hour. H. Weight and Balance Not Affected. I. Electrical Load Data Not Applicable. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 3 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 41 of 48 ### Page 42 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY J. Software Accomplishment Summary Not Applicable. K. References Not applicable. L. Other Publications Affected Not applicable. M. Interchangeability or Intermixability of Parts Not applicable. 2. MATERIAL INFORMATION A. Material Price and Availability The material is composed of the parts listed in the Table below. Table 2.1 - List of parts MT Code Standard Part Number Qty Keyword 083321 EN2367-29020 (Alternative 3.2x20-DIN94 - Stainless Steel) 1 (Fig. 1 Item 50) Cotter Pin Note: all the above parts as per Table 2.1 can be locally procured or requested to Leonardo Helicopters. All consumable materials are listed in Table 3.3. of para. 3.H. B. Industry Support Information This modification will be introduced in accordance with one of the options noted below: - by organizational authorized helicopter maintenance personnel. - by Microtecnica maintenance personnel C. Material Necessary For Each Unit Locking Wire MS20995C20 in accordance with NASM 33540. D. Material Necessary For Each Spare Locking Wire MS20995C20 in accordance with NASM 33540. E. Reidentified Parts Not applicable. F. Tooling - Price and Availability Standard tools have to be used for the activities required by this Service Bulletin. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 4 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 42 of 48 REVISION: A - September 5, 2019 ### Page 43 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY 3. ACCOMPLISHMENT INSTRUCTIONS A. General All the values to be recorded as indicated in the following points have to be reported on the registration form in the last page of this Service Bulletin. All the pictures taken as indicated in the following points have to be provided together with the registration form to Leonardo Helicopters within the completion time required by Leonardo Helicopters Service Bulletin. The Service Bulletin can be carried out with the actuator removed from the helicopter provided that it is installed in a suitable vice locking the flange of the actuator. B. Cleaning procedure When necessary, cold solvent and a natural bristle brush or a cloth that does not contain any lint should be used to clean the external surfaces of the TAIL ROTOR ACTUATOR (TRA). C. Record the Torque on the castellated nut (60) 1. Take a picture of the castellated nut (60) area of the Tail Rotor Actuator seen from the input lever (110) side (see Fig. 2 below for reference): Figure 2 Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 5 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 43 of 48 ### Page 44 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY 2. Check the paint mark for absence of evidence of rotation between the parts. Record the result of the check in the template provided at the end of this Service Bulletin. 3. Cut and remove the locking wire. 4. Bend the cotter pin (50) end in order to re-align it with the hole in the rod (150). If cotter pin (50) is distorted by castellated nut (60) rotation, then rotate castellated nut (60) to allow cotter pin (50) removal. 5. Carefully remove the cotter pin (50) from its housing and scrap it. 6. Manual check if the castellated nut (60) is loose. Record the result. If castellated nut (60) is loose then contact Leonardo Helicopters for further instructions. 7. Hold the squared end of the rod (150) (input lever side) using the proper socket or a standard wrench (8mm size). Set the calibrated torque wrench to 10 Nm and slowly tighten the castellated nut (60). Verify for relative rotation between the castellated nut (60) and the hinge bracket element (90). If no relative rotation is detected, then increase the setting of the torque wrench by 5 Nm at a time and repeat slowly tightening until the castellated nut (60) relatively rotates with respect to the hinge bracket element (90). Record the value of the torque to have relative rotation. If no relative rotation is detected with a maximum tightening torque of 49 Nm, then stop the tightening procedure and record "torque greater than 49 Nm". D. Apply the Torque on the castellated nut (60) 1. Remove the paint mark (as per Point 3.B) from the castellated nut (60), the rod end (150) and the hinge bracket element (90) using scotch brite and/or solvent (MEK or equivalent), see Fig. 1 for reference. Caution: in all the operation below, do not move the input lever (110), do not disconnect the input lever (110) from the rod (150). 2. Apply tie rap on the input lever (110) as per Fig. 3. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 6 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 44 of 48 REVISION: A - September 5, 2019 ### Page 45 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY Figure 3 3. Hold the squared end of the rod (150) (input lever side) using the proper socket or a standard wrench (8mm size) and unscrew the castellated nut (60). 4. Carefully remove completely the castellated nut (60) from the rod (150) without disconnecting the hinge bracket element (90) from the rod (150). 5. Polish the castellated nut (60) surface of contact and clean it by means of abrasive paper (grit 600). Clean the hinge bracket element (90) contact area with lint free cloth. Sliding marks in the contact area of castellated nut (60) and hinge bracket element (90) are 6. Clean the rod (150) thread with lint free cloth without using solvent. Note - the thread area may present a different colour because of molybdenum disulphate. 7. Apply a thin layer of grease as per MIL-PRF-81322 on the castellated nut (60) contact face. 8. Hold the squared end of the rod (150) (input lever side) using the proper socket or a standard wrench (8mm size) and slowly tighten the castellated nut (60) by means of calibrated torque wrench set to 40 Nm up to the contact with the hinge bracket element (90). 9. Check that the hole on the rod (150) is aligned with one of the available slots in the castellated nut (60). If the hole is not aligned, increase the torque wrench setting by 1 Nm per step and verify the alignment. The maximum applicable torque is 49 Nm. If the alignment is not achieved yet, unscrew the castellated nut (60) and repeat the torque application starting from 40 Nm. Record the applied torque. 10. Insert the new cotter pin (50) into the hole in the rod (150). Bend the cotter pin (50) end (the preferred configuration is shown in Fig. 2) in order to minimize axial or rotational cotter pin (50) movement. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 7 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 45 of 48 ### Page 46 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY 11. Install the Locking Wire MS20995C20 in accordance with NASM 33540 as per Fig. 2 in order to avoid castellated nut (60) unscrewing. 12. Cut and remove the tie rap from the input lever (110). 13. Apply a coloured paint mark on the castellated nut (60) from the hinge bracket element (90) to the rod (150) using a narrow brush as per Fig. 4. Figure 4 14. Mark "SB 67-0006" on the input lever (110) with permanent ink pen as per Fig. 5. SB67-0006 Figure 5 15. Take at least two pictures showing cotter pin (50), locking wire installation and coloured paint mark application. 16. Record compliance with this Service Bulletin SB 67-0006 on the relevant component log card. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 8 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 46 of 48 REVISION: A - September 5, 2019 ### Page 47 (OCR) UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY E. Re-identification Refer to Point C.19 of paragraph 3. F. Functional tests Not applicable. G. SPARES Not applicable H. CONSUMABLE MATERIALS Table 3.3 List of consumables Material Locking wire MS20995C20 Paint Abrasive Paper (grit 600) Grease MIL-PRF-81322 Solvent MEK Note: all the parts as per Table 3.3 above can be locally procured. 1. Requirement after job completion After the accomplishment of the procedure as per para. 3, complete the registration form situated at the bottom of this Service Bulletin and return it to Leonardo Helicopters within the completion time required by Leonardo Helicopters Service Bulletin. Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 9 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 47 of 48 ### Page 48 (OCR) & UTC Aerospace Systems SERVICE BULLETIN CIRCULATE PROMPTLY AW169 - AW189 TAIL ROTOR ACTUATOR (TRA) PN C161223-1 (LH P/N 6F6730V00331) Torque check and re-application on the Castellated Nut of the Rod Customer Name Helicopter Serial Number: Tail Rotor Actuator Serial Number: C.2. Paint Mark rotation (Yes/No): C.6. Castellated Nut loose (Yes/No): C.7. Value of the torque to have relative rotation between the Castellated Nut and the Hinge Bracket Element: D.9. Value of the torque re-applied to the Castellated Nut of the Rod: Visual checks after the torque re-applied: • D. 11. The locking wire is properly installed:. • D. 13. The parts are marked with paint: ..... • D. 14. "SB 67-0006" is marked on the Input Lever:.. Torque check and re-application to the Castellated Nut of the Rod accomplished by (Operator Name): . Execution date: . Issue 1 - Nov. 29/18 Subject to the restriction on the title or cover page. SB 67 -0006 IT Export Classification: NSR Page 10 of 10 S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 48 of 48 REVISION: A - September 5, 2019 ### Page 49 Remarks: Information:฀ SERVICE฀BULLETIN฀COMPLIANCE฀ ฀ ฀FORM Date: Number: Revision: Please฀send฀to฀the฀following฀address:฀ Telephone: Fax: ฀B.T.฀Compliance฀Date: ฀Customer฀Name฀and฀Address: ฀Helicopter฀Model S/N Total฀Number Total฀Hours฀ T.S.O. LEONARDO S.p.A. CUSTOMER SUPPORT & SERVICES - ITALY PRODUCT SUPPORT ENGINEERING & LICENSES DEPT. Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) - ITALY Tel.: +39 0331 225036 Fax: +39 0331 225988 We request your cooperation in filling this form, in order to keep out statistical data relevant to aircraft configuration up-to-date. The form should be filled in all its parts and sent to the above address or you can communicate the application also via Technical Bulletin Application Communication Section placed in Leonardo AW Customer Portal - MyCommunications Area. We thank you beforehand for the information given. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.