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Page 1 of 14 N° 119-156 DATE: July 1, 2025 REV. : / - January 21, 2025 TITLE ATA 67 – CYCLIC CONTROL SYSTEM PITCH AND ROLL ACTUATORS ATTACHING
BOLTS 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°119-156 ALERT DATE: July 1, 2025 Page 2 of 14 REVISION: /
1. PLANNING INFORMATION A. EFFECTIVITY All A119 helicopters.
All AW119MKII helicopters from S/N 14701 to S/N 14999, from S/N 15001 to S/N 15035, from S/N 15521 to S/N 15535 and from S/N 15801 to S/N 15927 (except S/N 15809 and S/N 15810).
B. COMPLIANCE Within and not later than 25 flight hours after the issue of this Service Bulletin.
C. CONCURRENT REQUIREMENTS N.A.
D. REASON This Service Bulletin is consequence of an in-service event, related to human factor, concerning the incorrect installation direction of the bolt that connects the roll (lateral) actuator assy to the related bellcrank assy of the cyclic control system in the upper deck area.
Leonardo Helicopters issued this Service Bulletin in order to prescribe a visual inspection of the installation direction of the bolts that connect the pitch (longitudinal) and roll (lateral) actuator assemblies to the related bellcrank assemblies and to prescribe, if necessary, the required corrective actions.
To avoid future potential issues, Leonardo Helicopters updated the following AMP DMs with the AMP issue 009 dated on February 19, 2025:
19-A-67-10-00-00A-271A-A – Rotor control – Adjust;
19-A-67-12-07-00A-520A-A - Roll linear actuator - Remove procedure;
19-A-67-12-07-00A-720A-A - Roll linear actuator - Install procedure;
19-A-67-12-10-00A-520A-A - Pitch linear actuator - Remove procedure;
19-A-67-12-10-00A-720A-A - Pitch linear actuator - Install procedure;
and the IPD DM 19-A-67-12-00-010-941A-A - Cyclic pitch control installation – Illustrated Parts Data with the IPD issue 008 dated on February 19, 2025 (refer to IETP issue 32, update of March 31, 2025).
The previous revisions of the above DMs are no longer considered applicable.
S.B. N°119-156 ALERT DATE: July 1, 2025 REVISION: / Page 3 of 14 E. DESCRIPTION This Service Bulletin provides the necessary instructions to perform a visual inspection of the two bolts that connect the bellcrank assemblies to the pitch and roll actuator assy of the longitudinal and lateral cyclic control lines in the upper deck area, to verify their installation direction. Based on the inspection findings, it is prescribed to perform the installation correction and the adjust procedure of the cyclic control lines or to contact the PSE of Leonardo Helicopters in order to receive further instructions.
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 Aviation Authorities other than those of EASA Member States, the applicable Aviation Authority’s approval must be verified with the Local Aviation Authority prior to applying the Service Bulletin.
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 Leonardo Helicopters 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, the following MMH are deemed necessary:
approximately one (1), to perform the bolt inspection;
approximately thirty-nine (39), to perform the rigging procedure (ONLY in case of findings).
MMH are based on hands-on time and can change with helicopter configuration, personnel and facilities available. MMH are not comprehensive of the overall hours necessary to get access to work areas and to remove all the equipment that interferes with the application of the prescribed instructions.
H. WEIGHT AND BALANCE N.A.
S.B. N°119-156 ALERT DATE: July 1, 2025 Page 4 of 14 REVISION: / I. REFERENCES I.1 PUBLICATIONS Following Data Modules refer to AMP:
DATA MODULE DESCRIPTION PART DM01 19-A-00-20-00-00A-120A-A Helicopter safety – Preoperation (make helicopter safe for maintenance) - DM02 19-A-06-40-00-00A-018A-A Access provisions – Introduction - DM03 19-A-12-40-02-00A-730A-A External hydraulic power – Connect procedure - DM04 19-A-12-40-02-00A-510A-A External hydraulic power – Disconnect procedure - DM05 19-A-67-10-00-00A-271A-A Rotor control – Adjust -
I.2 ACRONYMS & ABBREVIATIONS AMDI Aircraft Material Data Information AMP Aircraft Maintenance Publication AR As Required DM Data Module DOA Design Organization Approval EASA European Union Aviation Safety Agency IPD Illustrated Parts Data publication ITEP Illustrated Tools and Equipment Publication MMH Maintenance Man Hours N.A. Not Applicable P/N Part Number PSE Product Support Engineer SB Service Bulletin S/N Serial Number I.3 ANNEX N.A.
J. PUBLICATIONS AFFECTED 19-A-AMP-00-X – Aircraft Maintenance Publication (AMP) 19-A-IPD-00-X – Illustrated Parts Data publication (IPD)
S.B. N°119-156 ALERT DATE: July 1, 2025 REVISION: / Page 5 of 14 K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.
S.B. N°119-156 ALERT DATE: July 1, 2025 Page 6 of 14 REVISION: /
2. MATERIAL INFORMATION A. REQUIRED MATERIALS A.1 PARTS # P/N ALTERNATIVE P/N DESCRIPTION Q.TY LVL NOTE LOG P/N 1 AN174-13 Bolt AR . (1) (2) (3) - 2 MS17825-4 Nut AR . (1) (2) - 3 MS24665-151 Cotter pin AR . (1) (2) (3) -
Refer also to IPD for the spares materials required to comply with the AMP DMs referenced in the accomplishment instructions.
A.2 CONSUMABLES Refer to AMDI for the consumable materials required to comply with the AMP DMs referenced in the accomplishment instructions.
A.3 LOGISTIC MATRIX N.A.
NOTES
(1) This item is necessary in maximum q.ty 2 per helicopter, based on the result of the inspection.
(2) Item to be procured as local supply.
(3) If requested to Leonardo Helicopters, please check the relevant MSQ with your Order Administrator based on your fleet. Maximum q.ty 1 bag for Customer’s fleet could be provided.
B. SPECIAL TOOLS The following special tools, or equivalent, are necessary to accomplish this Service Bulletin:
# P/N DESCRIPTION Q.TY NOTE PART 4 Commercial Source light 1 (B1) - 5 Commercial Mirror 1 (B1) -
Refer also to ITEP for the special tools required to comply with the AMP DMs referenced in the accomplishment instructions.
SPECIAL TOOLS NOTES Item to be procured as local supply.
S.B. N°119-156 ALERT DATE: July 1, 2025 REVISION: / Page 7 of 14 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 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. including the Inspection Report Form in Figure 4, completed of pictures, signed and stamped.
If the required documentation is not provided, the relevant MMIR will be rejected.
S.B. N°119-156 ALERT DATE: July 1, 2025 Page 8 of 14 REVISION: /
3. ACCOMPLISHMENT INSTRUCTIONS
GENERAL NOTES
a) Place an identification tag on all components that are re-usable, including the attaching hardware that have 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.
c) All lengths are expressed in mm.
1. In accordance with AMP DM 19-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 19-A-06-40-00-00A-018A-A and with reference to Figures 1 thru 3, remove all external panels required to gain access to the area affected by the cyclic control assy bolts inspection and perform the following procedure:
2.1 With reference to Figure 3, perform a visual inspection to verify the installation position of the bolts that attach the pitch (longitudinal) actuator assy P/N 109-0020-86-3 and the roll (lateral) actuator assy P/N 109-0020-86-1, respectively to the pitch (longitudinal) bellcrank assy P/N 109-0020-69-9 (or P/N 109-0020-69-113) and the roll (lateral) bellcrank assy P/N 109-0020-55-9 (or P/N 109-0020-55-113):
If the bolts are not installed correctly, as shown in the Figure 3, proceed with the following step 2.2.
If the bolts are installed in the correct position, as shown in the Figure 3, proceed with the step 3.
2.2 In accordance with AMP DM 19-A-12-40-02-00A-730A-A, connect the helicopter to the external hydraulic power supply and set it to 103.42 bar (1500 psi).
S.B. N°119-156 ALERT DATE: July 1, 2025 REVISION: / Page 9 of 14
2.3 Move the cyclic control stick through its full travel and with reference to Figure 3, using a source light and a mirror, as necessary, perform a visual inspection in the area between the incorrectly installed bolt and the support assy P/N 109-0020-70-105 to verify the presence of interferences and/or any type of damage:
If no interferences and/or damages are detected during the inspection, proceed with the following step 2.4 In case of any interference and/or damage findings, contact the PSE to receive further instructions.
NOTE “XXXXX” in the subject line below is the helicopter S/N.
2.4 Compile the Inspection Report Form in Figure 4 a nd send it with Subject line “SB 119-156 – S/N XXXXX Inspection Report Form” to the following mail box:
engineering.support.lhd@leonardo.com and (for North, Central and South America) also to:
AWPC.Engineering.Support@leonardocompany.us
2.5 With reference to Figure 2, remove and retain the fixing hardware listed below that attaches the pitch (longitudinal) actuator assy P/N 109-0020-86-3 or the roll (lateral) actuator assy P/N 109-0020-86-1, respectively to the pitch (longitudinal) bellcrank assy P/N 109-0020-69-9 (or P/N 109-0020-69-113) or the roll (lateral) bellcrank assy P/N 109-0020-55-9 (or P/N 109-0020-55-113), as applicable:
the bolt P/N AN174-13;
the washer P/N A160A0432K;
n°2 washers P/N NAS1149D0432K;
the nut P/N MS17825-4 (discard);
the cotter pin P/N MS24665-151 (discard).
2.6 With reference to Figure 2, perform a visual inspection on the bolt previously removed to verify the presence of any type of damage:
In case of damage, replace it with a new serviceable one;
If no damage is detected during the inspection, retain the current bolt.
S.B. N°119-156 ALERT DATE: July 1, 2025 Page 10 of 14 REVISION: /
2.7 With reference to Figure 2, fix the pitch (longitudinal) actuator assy P/N 109-0020-86-3 or the roll (lateral) actuator assy P/N 109-0020-86-1, respectively to the pitch (longitudinal) bellcrank assy P/N 109-0020-69-9 (or P/N 109-0020-69-113) or the roll (lateral) bellcrank assy P/N 109-0020-55-9 (or P/N 109-0020-55-113), as applicable, by means of the previously removed fixing hardware listed below, ensuring it is installed in the correct orientation:
the bolt P/N AN174-13;
the washer P/N A160A0432K;
n°2 washers P/N NAS1149D0432K;
the new nut P/N MS17825-4;
the new cotter pin P/N MS24665-151.
2.8 With reference to Figure 2, torque the bolt to 2.82 – 3.95 Nm.
2.9 In accordance with AMP DM 19-A-67-10-00-00A-271A-A, perform the cyclic control system rods adjustment procedure and the mixing control stop screw rigging procedure (refer to step 2 and step 4 of DM).
2.10 In accordance with AMP DM 19-A-12-40-02-00A-510A-A, disconnect the helicopter from the external hydraulic power supply.
3. In accordance with AMP DM 19-A-06-40-00-00A-018A-A, re-install all external panels previously removed.
4. Return the helicopter to flight configuration and record for compliance with this Service Bulletin on the helicopter logbook.
5. Gain access to My Communications section on Leonardo Customer Portal and compile the “Service - Technical Bulletin Application”.
As an alternative, send the attached compliance form to the following mail box:
engineering.support.lhd@leonardo.com and (for North, Central and South America) also to:
AWPC.Engineering.Support@leonardocompany.us
Non cancellare mai questo segnalibro Non cancellare mai interruzione sezione
Figure 1 S.B. N°119-156 ALERT DATE: July 1, 2025 REVISION: / Page 11 of 14
FRONT VIEW
STRUCTURE AND SYSTEMS ARE P ARTIALLY OMITTED FOR BETTER CLARITY PURPOSE 109-0020-69-9 (OR 109-0020-69-1 13)
PITCH LONGITUDINAL BELLCRANK ASSY (REF) 109-0020-55-9 (OR 109-0020-55-113) R
OLL BELLCRANK ASSYLATERAL (REF) 109-0020-86-1 R
OLL LA TERAL ACTUATOR ASSY (REF) WL 1550.0 REF WL 1400.0 REF BL
9.0 52 RH REF A (SEE FIGURE ) 2 109-0020-86-3
PITCH LONGITUDINAL ACTUATOR ASSY (REF) C (SEE FIGURE 3) 109-0020-70-105 SUPPORT ASSY (REF)
Figure 2 S.B. N°119-156 ALERT DATE: July 1, 2025 Page 12 of 14 REVISION: /
TO PERFORM ONLY IF THE BOL T IS INSTALLED IN THE DIRECTION INCORRECT 1
DETAIL B ROTA TED 90° CW
STRUCTURE AND SYSTEMS ARE PARTIALL Y OMITTED FOR BETTER CLARITY PURPOSE VIEW A
TOP VIEW
STRUCTURE AND SYSTEMS ARE PARTIALLY OMITTED FOR BETTER CLARITY PURPOSE (REFER TO FIGURE 1) REMOVE/RE-INSTALL:
AN174-13 BOLT (DISCARD, IF NECESSARY) A160A0432K WASHER (UNDER BOLT HEAD) NAS1149D0432K WASHER (QTY 2) (UNDER A160A0432K WASHER AND UNDER NUT) MS17825-4 NUT (DISCARD) COTTER PIN (DISCARD)MS24665-151 INSTALL:
MS17825-4 NUT (NEW ITEM) COTTER PIN (NEW ITEM)MS24665-151 TORQUE TO:
2.82 – 3.95 Nm 1 109-0020-86-3