Leonardo ASB 109SP-131: No revision named

N° 109SP-131 DA TE: June 28, 2019 REV. : / - March 15, 2017 Pa ge 1 of 19 TITLE ATA 32 - INSPECTION OF LH/RH ENHANCED MAIN LANDING GEAR STRUT ASSY P /N 109-0503-45

REVISION LOG New 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-131 ALERT DATE: June 28, 2019 Page 2 of 19 REVISION: /

1. PLANNING INFORMATION A. EFFECTIVITY NOTE Refer to Figure 1 for LH/RH Wheel Axle P/N and S/N identification.

All the Leonardo S.p.A. AW109SP helicopters equipped with LH/RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102 which install the LH/RH Wheel Axle with P/N listed in Table 1 and S/N listed in Table 2.

LH/RH Enhanced MLG Strut. Assy P/N LH/RH Wheel Axle P/N 109-0503-45-101 M019-01H003-101 109-0503-45-102 M019-01H003-102 Table 1

LH Wheel Axle P/N M019-01H003-101 RH Wheel Axle P/N M019-01H003-102 from S/N 1 to S/N 146 from S/N 1 to S/N 147 from S/N 152 to S/N 172 from S/N 153 to S/N 173 Table 2 NOTE If a LH/RH Wheel Axle with P/N listed in Table 1 and S/N listed in Table 2 is installed on a MLG strut. assy in stock, attach a copy of this Service Bulletin to its box for future compliance before the MLG strut. assy installation on the helicopter.

B. COMPLIANCE Within and not later than 50 flight hours or 200 landings or 6 months, whichever occurs first, after the issue of this Service Bulletin and subsequently every 12 months.

C. CONCURRENT REQUIREMENTS N.A.

D. REASON This Service Bulletin is issued in order to introduce a periodical inspection of the LH/RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102.

S.B. N°109SP-131 ALERT DATE: June 28, 2019 REVISION: / Page 3 of 19 E. DESCRIPTION On two A109E helicopter in service, a failure of the RH Main Landing Gear Wheel Assy was reported. Further investigation revealed that the cause of the failure was caused by stress corrosion cracking, enhanced by local presence of hydrogen embrittlement, on the threaded end of the RH Enhanced Main Landing Gear Strut.

Assy P/N 109-0503-45-102, where lack of cadmium plating was observed.

This Service Bulletin is issued with the purpose to provide the necessary instruction to perform a periodical liquid penetrant inspection to verify the presence of cracks on the threaded end of the LH and RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102 and to apply a corrosion protective compound at wheel re-installation. An alternative inspection method with magnetic particles is provided, too.

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 the aircraft, for any adaptation necessary before incorporation of the present Service Bulletin.

G. MANPOWER To comply with this Service Bulletin 2 (two) 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.

S.B. N°109SP-131 ALERT DATE: June 28, 2019 Page 4 of 19 REVISION: / I. REFERENCES

1) PUBLICATIONS

DATA MODULE DESCRIPTION PART DM01 0B-A-00-20-00-00A-120A-A Helicopter safety - Make the helicopter safe for maintenance.

- DM02 0B-A-07-11-00-00A-028A-A Helicopter - Lift on jacks - General - DM03 0B-A-32-41-02-00A-520A-A Left main wheel - Remove procedures - DM04 0B-A-32-41-03-00A-520A-A Right main wheel - Remove procedures - DM05 0B-A-32-11-01-00A-520A-A Left main landing gear strut - Remove procedures - DM06 0B-B-32-11-01-00A-520A-A Left main landing gear strut - Remove procedures - DM07 0B-A-32-11-01-00A-720A-A Left main landing gear strut - Install procedures - DM08 0B-B-32-11-01-00A-720A-A Left main landing gear strut - Install procedures - DM09 0B-A-32-11-02-00A-520A-A Right main landing gear strut - Remove procedures - DM10 0B-B-32-11-02-00A-520A-A Right main landing gear strut - Remove procedures - DM11 0B-A-32-11-02-00A-720A-A Right main landing gear strut - Install procedures - DM12 0B-B-32-11-02-00A-720A-A Right main landing gear strut - Install procedures - DM13 0B-A-32-41-02-00A-720A-A Left main wheel - Install procedures - DM14 0B-A-32-41-03-00A-720A-A Right main wheel - Install procedures - DM15 CMM 32-11-19 4 th issue Main Landing Gear - Component Maintenance Manual (only for authorized service station) -

2) ACRONYMS AMP Aircraft Maintenance Publication AR As Required CMM Component Maintenance Manual DM Data Module DOA Design Organization Approval EASA European Aviation Safety Agency IPD Illustrated Part Data LH Left LHD Leonardo Helicopters

S.B. N°109SP-131 ALERT DATE: June 28, 2019 REVISION: / Page 5 of 19 LS Local Supply MLG Main Landing Gear MMH Maintenance Man Hours N.A. Not Applicable RH Right P/N Part Number SB Service Bulletin S/N Serial Number

3) ANNEX Annex A AW109SP MLG Liquid Penetrant Inspection.

Annex B AW109SP MLG Magnetic Particle Inspection.

J. PUBLICATIONS AFFECTED 0B-B-AMPI-00-P AW109SP Maintenance Planning Information 0B-C-AMPI-00-P AW109SP REGA Maintenance Planning Information K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

S.B. N°109SP-131 ALERT DATE: June 28, 2019 Page 6 of 19 REVISION: /

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS # P/N ALTERNATIVE P/N DESCRIPTION Q.TY LVL NOTE LOG P/N 1 MS24665-374 MS24665-372 Cotter pin 2 . - Refer also to IPD for the spares materials required to 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 2 MIL-PRF-16173, Cl I & II, Grade 1 (LHD cod. 999999999000000191) Tectyl 891D (C509) AR (1) - 3 MIL-PRF-16173, Cl I, Grade 4 (LHD cod. 999999999000000190) Tectyl 846 (C532) AR (1) - 4 SAE-AMS-2644 TY I, Method C, Level 3 Dye Penetrant AR (1)(2) - 5 SAE-AMS-2644, Form D Developer AR (1)(2) - 6 SAE-AMS-2644 Cl II Solvent (C290) AR (1)(2) - 7 ASTM F945 Ardrox 6333 (C292) AR (1) - 8 Commercial Alkaline Steel Cleaner AR (1) - Refer also to AMDI for the consumable materials required to comply with the AMP DMs referenced in the accomplishment instructions.

3) LOGISTIC MATRIX N.A.

NOTE

(1) Local supply.

(2) This material shall be certified in accordance with AMS2644, obtained from a supplier listed in QPL-AMS2644 and supplied in aerosol cans packaging.

B. SPECIAL TOOLS Refer also 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 will be eligible to receive

S.B. N°109SP-131 ALERT DATE: June 28, 2019 REVISION: / Page 7 of 19 REQUIRED MATERIALS on free of charge basis, except for Consumable Materials and Special Tools.

NOTE: Customers who fail to comply with the instructions 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. Accompanied by INSPECTION REPORT and PICTURE of the affected area.

NOTE: The INSPECTION REPORT and PICTURE are mandatory; in case the MMIR is not accompanied by these documents, it will be rejected.

NOTE: WRM will include RETURN MATERIAL AUTHORIZATION (RMA) number; the unit removed from the aircraft has to be returned to LHD as per instructions defined into LHD Information Letter GEN-15-047.

S.B. N°109SP-131 ALERT DATE: June 28, 2019 Page 8 of 19 REVISION: /

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 the instructions given in 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 the instructions given in AMP DM 0B-A-07-11-00-00A-028A-A, lift the helicopter on jacks.

3. In accordance with the instructions given in AMP DMs 0B-A-32-41-02-00A-520A-A and 0B-A-32-41-03-00A-520A-A remove the LH and RH MLG wheel assy.

NOTE Magnetic Inspection in Annex B is a valid alternative to the liquid penetrant inspection. The two methods are equivalent.

4. In accordance with the instruction given in the A nnex A, perform the liquid penetrant inspection on the threaded end of the LH and RH enhanced MLG strut. assy P/N 109-0503-45-101/-102. Cracks are not allowed.

5. In case of no findings, proceed to step 7.

NOTE In case of finding contact Product Support Engineering (aw109.mbx.aw@leonardocompany.com).

6. In case of findings, perform the replacement of t he damaged leg as described in the following procedure:

NOTE The following steps are applicable both on LH and RH MLG strut. assy.

6.1 In accordance with the instructions given in AMP DM 0B-A-32-11-01-00A-520A-A

S.B. N°109SP-131 ALERT DATE: June 28, 2019 REVISION: / Page 9 of 19 or 0B-B-32-11-01-00A-520A-A, depending by the MLG configuration (DM 0B-A-32-11-02-00A-520A-A or 0B-B-32-11-02-00A-520A-A for RH side), remove and return to LHD the LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

6.2 In accordance with the instructions given in AMP DM 0B-A-32-11-01-00A-720A-A or 0B-B-32-11-01-00A-720A-A, depending by the MLG configuration (DM 0B-A-32-11-02-00A-720A-A or 0B-B-32-11-02-00A-720A-A for RH side), install the new LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

7. In accordance with the instructions given in AMP DMs 0B-A-32-41-02-00A-720A-A and 0B-A-32-41-03-00A-720A-A, reinstall the LH and RH MLG wheel assy.

8. Apply corrosion preventive compound MIL-PRF-16173 Grade 1 (Tectyl 891D) or Grade 4 (Tectyl 846) on the exposed surface of the threaded end and on inner surface of the end lightening hole of the LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

9. Record for compliance with this Service Bulletin on the component log card.

10. Return the helicopter to a ready to flight condition and record for compliance with this Service Bulletin on the helicopter logbook.

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

aw109.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 segnalibro Non cancellare mai interruzione sezione 

* LEONARDO HELICOPTERS MG19-G1H003-102 REV. N S/N 7 LN MO18-014003-042 S/N 29 ASSY REV M

ARE ASSY 67 N

- 10TS 201-620H15•810W (FOR REFERENCE ONLY) Figure 1 S.B. N°109SP-131 ALERT DATE: June 28, 2019 Page 10 of 19 REVISION: /

ANNEX A S.B. N°109SP-131 ALERT DATE: June 28, 2019 REVISION: / Page 11 of 19

ANNEX A AW109SP MAIN LANDING GEAR

LIQUID PENETRANT INSPECTION

ANNEX A S.B. N°109SP-131 ALERT DATE: June 28, 2019 Page 12 of 19 REVISION: / 1 PURPOSE AND APPLICABILITY This procedure details the requirements for the Liquid Penetrant Inspection (PT) on the following P/Ns:

MAG P/N DESCRIPTION M019-01H003-101 Wheel Axle LH M019-01H003-102 Wheel Axle RH Purpose of this inspection is the detection of any possible crack starting from the root of the bottom of the thread of the hub; the inspection of this procedure shall be performed on all the thread of the hub after the removal of the wheel.

2 REFERENCES The following documents in their last revision are considered part of this procedure:

ASTM E1417 Standard Practice for Liquid Penetrant Testing;

ASTM E3022 Standard Practice for Measurement of Emission Characteristics and Requirements for LED UV-A Lamps Used in Fluorescent Penetrant and Magnetic Particle Testing;

EN4179/NAS410 Qualification and approval of personnel for non-destructive testing;

QPL AMS2644 Qualified Product List of Inspection Materials, Penetrant;

SAE AMS2644 Inspection Materials, Penetrant.

3 EQUIPMENT AND MATERIALS The following materials, equipment and tools are requested.

3.1 MATERIALS

a) Dye Penetrant SAE-AMS-2644 TY I, Method C, Level 3;

b) Developer SAE-AMS-2644 Form D;

c) Solvent SAE-AMS-2644 Class 2.

All the above materials shall be certified in accordance with AMS2644, obtained from a supplier listed in QPL-AMS2644 and supplied in aerosol cans packaging.

3.2 EQUIPMENT/TOOLS

a) A booth suitable for darkening the area of inspection up to an illuminance of 20 lux maximum;

b) a Luxmeter for checking the illuminance (20 lux maximum on the part during the inspection and the 1,000 lux minimum for the assessment of indications);