Leonardo ASB 109SP-148: No revision named

N ° 109SP-148 D ATE: October 26, 2021 REV. : / - September 28, 2018 P age 1 of 7 TITLE ATA 67 – FIXED FLIGHT CONTROL CHAIN INSPECTION

REVISION LOG First Issue An appropriate entry should be made in the aircraft log book upon accomplishment.

If ownership of aircraft has changed, please, forward to new owner.

Leonardo S.p.A.

Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595 ALERT

SERVICE BULLETIN

S.B. N°109SP-148 ALERT DATE: October 26, 2021 Page 2 of 7 REVISION: /

1. PLANNING INFORMATION A. EFFECTIVITY AW109SP helicopters S/N 22407, 22408, 22409, 22412, from 22414 thru 22427, 22429.

B. COMPLIANCE Within and not later than 50 FH flight hours or 3 months whichever occurs first after the issue of this Service Bulletin.

C. CONCURRENT REQUIREMENTS N.A.

D. REASON This Service Bulletin is issued in order to provide the necessary instructions on how to perform the inspection of some of the control rods and levers of the rotors flight controls located in the areas of LH and RH FWD struts, under the cockpit floor and in the tail boom of the helicopter.

E. DESCRIPTION During inspection, a protective nomex sheath was found installed around the fixed flight control rod P/N 109-0032-03-1. The protection should have been removed during the helicopter final assembly. For this reason, in order to prevent potential hazards, Leonardo Helicopters decided to issue this SB to perform an inspection of the potentially affected control rods and levers and to remove any foreign object that may have not been removed.

F. APPROVAL The technical content of this Service Bulletin is approved under the authority of DOA nr. EASA.21.J.005. For helicopters registered under other Aviation Authorities, before applying the Service Bulletin, applicable Aviation Authority approval must be checked within Leonardo Helicopters customer portal.

EASA states mandatory compliance with inspections, modifications or technical directives and related time of compliance by means of relevant Airworthiness Directives.

If an aircraft listed in the effectivity embodies a modification 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

S.B. N°109SP-148 ALERT DATE: October 26, 2021 REVISION: / Page 3 of 7 the aircraft, for any adaptation necessary before incorporation of the present Service Bulletin.

G. MANPOWER To comply with this Service Bulletin 4 (four) MMH are deemed necessary.

MMH are based on hands-on time and can change with personnel and facilities available.

H. WEIGHT AND BALANCE N.A.

I. REFERENCES

1) PUBLICATIONS Following Data Modules refer to AMP:

DATA MODULE DESCRIPTION PART DM01 0B-A-00-20-00-00A-120A-A Helicopter safety – Pre-operation - DM02 0B-A-06-41-00-00A-010A-A Access doors and panels - General data -

2) ACRONYMS & ABBREVIATIONS AMP Aircraft Maintenance Publication DM Data Module DOA Design Organization Approval EASA European Aviation Safety Agency LHD Leonardo Helicopters MMH Maintenance Man Hours P/N Part Number S/N Serial Number

3) ANNEX N.A.

J. PUBLICATIONS AFFECTED N.A.

K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

S.B. N°109SP-148 ALERT DATE: October 26, 2021 Page 4 of 7 REVISION: /

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS N.A.

2) CONSUMABLES N.A.

3) LOGISTIC MATRIX N.A.

B. SPECIAL TOOLS The following special tools, or equivalent, are necessary to accomplish this Service Bulletin:

# P/N DESCRIPTION Q.TY NOTE PART 1 Commercial Borescope (B1) -

Refer also to ITEP for the special tools required to comply with the AMP DM referenced in the accomplishment instructions.

SPECIAL TOOLS NOTE Tool to be procured as local supply.

C. INDUSTRY SUPPORT INFORMATION N.A.

S.B. N°109SP-148 ALERT DATE: October 26, 2021 REVISION: / Page 5 of 7

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.

b) Exposed thread surface and nut must be protected using a layer of tectyl according to MIL-C-16173 grade I.

1. In accordance with AMP DM 0B-A-00-20-00-00A-120A- A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, all electrical power sources and/or the external power supply.

2. In accordance with AMP DM 0B-A-06-41-00-00A-010A-A, open the access doors D8 and D9 and remove the access panels P1, P12, P70 and P71 from the helicopter.

NOTE It is alternatively possible to perform step 3 or 4.

3. Gain access to the inspection door P/N 109-0316-2 1-137. Remove the panel and the relevant attaching elements. Retain the parts for later reuse.

4. In accordance with AMP DM 0B-A-06-41-00-00A-010A-A, remove the access panel P35.

5. With reference to the steps below, using a borescope where needed, perform the inspection of the following control rods and levers:

5.1 Through the access obtained removing the panel P1, inspect the following parts:

 Bellcrank C2-C3 P/N 109-0010-03-105;

 Bellcrank Y6-Y7 P/N 109-0040-29-1;

 LH side of the Control Tube Y7 P/N 109-0032-14-105;

5.2 Through the access obtained removing the panel P12, inspect the following parts:

 Bellcrank F4-F5 P/N 109-0020-69-9;

 Bellcrank L3-L4 P/N 109-0020-55-9;

5.3 Through the access between the two halves of the co-pilot collective control lever boot, inspect the following parts:

 Copilot Collective Lever Fitting P/N 109-0012-22-101;

 Torque Tube Y5 P/N 109-0040-26-1.

S.B. N°109SP-148 ALERT DATE: October 26, 2021 Page 6 of 7 REVISION: / NOTE It is possible to perform the inspection as per step 5.4 through the access obtained removing the inspection door P/N 109-0316-21-137 or the access panel P35.

5.4 Through the access obtained removing the inspect ion door P/N 109-0316-21-137 or the panel P35, inspect the following parts:

 Bellcrank F3-F4 P/N 109-0030-95-101 or 109G6712A04-101;

 Bellcrank L2-L3 P/N 109-0030-96-101 or 109G6712A03-101;

 Control Tube F3 P/N 109-0032-03-1;

 Control Tube L2 P/N 109-0032-02-1;

 Bellcrank L1-L2 P/N 109-0020-17-105.

5.5 Through the access between the two halves of the pilot collective control lever boot, inspect the following parts:

 Control Tube Y3 P/N 109-0032-02-17;

 Bellcrank Y3-Y4-Y10 P/N 109-0040-33-1;

 Control Tube Y10 P/N 109-0032-01-61;

 Collective Torque Tube C1 P/N 109-0010-82-101.

5.6 Through the access obtained moving slightly from its position the bellows installed on the Control Tube Y1 P/N 109-0032-07-113, inspect the following part:

 Bellcrank Y1-Y2-Y3 P/N 109-0040-36-9 or 109-0040-36-115 or 109-0040-36-113.

5.7 Through the access obtained opening the door D9, inspect the following parts:

 RH side of the Control Tube Y7 P/N 109-0032-14-105;

 Bellcrank Y7-Y8 P/N 109-0040-35-1;

5.8 Through the access obtained removing the access panels P70 and P71, inspect the following part:

 Actuator Lever P/N 109-0040-91-101.

6. If during the inspection performed at step 5 no FOs have been detected, proceed to step 8, otherwise go to step 7.

NOTE If necessary, to perform step 7, remove the affected parts from the helicopter and reinstall them according to the relevant applicable AMP DMs.

7. If during the inspection performed at step 5 one or more parts have been detected with FOs, gain access to the affected parts and remove FOs detected.

8. In accordance with AMP DM 0B-A-06-41-00-00A-010A-A reinstall the access panels P1,

S.B. N°109SP-148 ALERT DATE: October 26, 2021 REVISION: / Page 7 of 7 P12, P70 and P71 previously removed and close the access doors D8 and D9.

NOTE Perform step 9 if the inspection door P/N 109-0316-21-137 has been removed, otherwise perform step 10.

9. Reinstall the inspection door P/N 109-0316-21-137 and all parts previously removed at step 3.

10. In accordance with AMP DM 0B-A-06-41-00-00A-010A-A reinstall the access panel P35.

11. Return the helicopter to flight configuration and record for compliance with this Service Bulletin on the helicopter logbook.

12. Send the attached compliance form to the following mail box:

engineering.support.lhd@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”. 

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.