Piaggio SB 80-0492: Revision 3

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 1 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 The EASA states mandatory compliance with inspections, modifications or technical directives and related time compliance by means of relevant Airworthiness Directives.

SERVICE BULLETIN (MANDATORY) N.: 80-0492 REV. 3 ATA CHAPTER: 55-30 MODIFICATION N.: Not applicable TITLE: VERTICAL STABILIZER ASSEMBLY – HORIZONTAL TAIL TRIM ACTUATOR (HTTA) FITTING ASSEMBLY – INSPECTION

REVISION STATUS OF THE BULLETIN This MANDATORY Service Bulletin (MSB) is at Revision 3 status and consists of 17 pages, plus Confirmation Slip (1 page).

This Service Bulletin is revised to:

(i) add minor clarifications for the Compliance (§ 1.E.);

(ii) update the References (§ 1.M.) with the addition of new Temporary Revision (TR) to SRM and NDTM.

This Revision supersedes the previous issue of this Service Bulletin.

Operators that have already accomplished to the original issue or Revision 1 of this Service Bulletin are required to verify the compliance (§ 1.E.) and § 2. B. Part B, as applicable, of this Revision.

No further action is required to operators that have already accomplished to Revision 2 of this SB.

The parts which are affected by this revision are shown by a black bar in the right margin of the page.

1. PLANNING INFORMATION A. EFFECTIVITY Piaggio Aero Industries (PAI) P180 A vanti Manufacturer’s Serial Number (MSN): 1004 thru 1033, provided that the concurrent requirements (§1.B.) are met.

Piaggio Aero Industries (PAI) P180 Avanti Manufacturer’s Serial Number (MSN): 1034 thru 1052 and 1054 thru 1104.

Piaggio Aero Industries (PAI) P180 Avanti II Manufacturer’s Serial Number (MSN): 1002, 1053, 1105 thru 1234, 3001 thru 3014, 3016 and 3018.

B. CONCURRENT REQUIREMENTS This MSB applies on P180 Avanti aircraft MSN 1004 thru 1033 on which PAI SB no. 80- 0142 has been embodied.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 2 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 C. REASON During a scheduled maintenance of a P180 Avanti airplane, an occurrence was reported of finding stress corrosion crackings on the fitting assembly of the Horizontal T ail Trim Actuator (HTTA). This type of problem, being mainly due to corrosion, is more likely to occur on older aircraft, usually parked outdoors, based and operated in environments of high humidity and/or frequent heavy precipitations and/or near the seaside and therefore exposed to a salty environment, when it is not properly preserved.

This condition, if not properly addressed, could result in the inability of the structural element to sustain the limit load which could consequently reduce the control of the airplane.

This MSB gives the instructions for an NDT inspection to be performed on the f itting assembly to verify its good condition in terms of absence of corrosion and/or damage and for reporting to PAI the check outcome. The SB also provides instruction about the management of the airplanes where the presence of corrosion/damage is determined.

Aviation Authority action is expected.

Revision history:

► Revision 1 (dated December 20th, 2022) was issued to complete the compliance with Avanti II aircraft to be delivered/certified and add clarifications in the accomplishment instructions and material information.

► Revision 2 (dated May 15 th, 2023) was issued to update the Effectivity; update the compliance with the addition of a terminating action; detail the Manpower; update the References with the addition of the new Temporary Revisions to SRM and NDTM;

add a minor clarification in the Accomplishment Ins tructions for the use of a flexible probe for Eddy Current inspection; update the Accomplishment Instructions with the addition of repetitive inspections, corrective actions and other minor clarifications and make minor changes in the document.

D. DESCRIPTION General This MSB consists of the following:

PART A

(i) access to the inspection areas including, but not limited to, removal of the Horizontal Tail Trim Actuator (HTTA);

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 3 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4

(ii) NDT inspection (Eddy Current) of the HTTA fitting assembly for absence of corrosion/damage and, if this is not the case, report to PAI and follow-up actions in accordance with Part B;

(iii) aircraft close-up and return to service.

PART B

(iv) follow up actions based on the inspection results.

E. COMPLIANCE This MSB shall be accomplished:

Part A: (i) for airplanes having less than 3000 FH and less than 10Y, within 220 FH or 13M, whichever occurs first, from the original issue date of this SB;

(ii) for all other airplanes within 100 FH or 7M, whichever occurs first, from the original issue date of this SB.

Part B: following the results of the inspection as required by Part A, the accomplishment of different actions is necessary as specified in § 2.B. Part B of this SB.

Inspections accomplished in accordance with § 2.B. Part A of this SB at original issue or Revision 1 or Revision 2 are acceptable to comply with this Revision as long as the follow-up actions are undertaken as per § 2.B. Part B of this Revision.

Terminating action : replacement of all the parts of the HTTA fitting assembly in accordance with a PAI Repair Design Approval Sheet (RDAS) or a procedure of SRM (report no. 180-MAN-0250-01106 Rev. D0 or later, including new relevant or previously approved Temporary Revision as indicated in § 1.M. iii) constitutes terminating action for the repetitive insp ections as required by § 2.B. Part B of this SB. Following the replacement of the fitting assembly, inspections shall be performed in accordance with the scheduled maintenance as per AMM instructions.

In compliance with this Service Bulletin, please comple te the attached Confirmation Slip and send it back to Piaggio Aero Industries S.p.A. – Product Support Department.

F. APPROVAL The technical content of this document is approved under the Authority of the DOA ref.

EASA.21J.220.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 4 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 G. MANPOWER This MSB may be accomplished in approximately:

A. Preparation: 12 man-hours (MH).

B. Procedure/Modification: 14 MH (including the removal of the upper rib as per §

2.B.(11) ).

C. Test & D. Close-up: 42 MH (including the installation of the upper rib as per §

2.D.(20) ).

NOTE: estimated man-hours do not include the time to prepare and plan the work, procure parts and tools and contact local providers (if any).

H. TECHNICAL INFORMATION For questions concerning the technical content of this Service Bulletin, please contact:

Piaggio Aero Industries – P180 Customer Support via Pionieri e Aviatori d’Italia, snc - 16154 Genoa, Italy technicalsupport@piaggioaerospace.it : (+39) 331 679 74 93 I. MATERIAL – COST AND AVAILABILITY For pricing, availability and scheduling, please contact:

spareparts@piaggioaerospace.it comm-civ@piaggioaerospace.it (+39) 335 810 59 20 J. TOOLING – COST AND AVAILABILITY When required, refer to § 1.I..

K. WEIGHT AND BALANCE Unchanged.

L. ELECTRICAL LOAD DATA No effect.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 5 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 M. REFERENCES Document Title Document Number Chapter/Section i Airplane Maintenance Manual (AMM) 9066 1 180-MAN-0200-01105 2 180-MAN-0200-01105(E) 3 06-00-00 12-00-00 20-00-01 24-00-00 27-40-00 33-42-00 51-00-00 51-25-00 51-40-00 51-43-00 55-30-00 ii Illustrated Parts Catalog (IPC) 9065 1 180-MAN-0100-01103 2 180-MAN-0100-01103(E) 3 55-30-00 iii Structural Repair Manual (SRM) 180-MAN-0250-01106 51-20-20 51-30-30 51-10-50 51-70-70 (TR no. 031) 4,5 iv Non-Destructive Test Manual (NDTM) 180-MAN-0300-01107 51-00-04 (TR no. 008) 4 51-01-00 v PAI Service Letter (SL) 80-0097 6,7 - vi PAI Service Bulletin (SB) 80-0142 6,8 - Note: 1 P180 Avanti. 2 P180 Avanti II. 3 P180 Avanti II EVO.

4 The use of later approved new TR or new Revision of the manual is acceptable as reference for the purpose of this SB, as applicable.

5 Previously approved TR no. 030 refer enced in Revision 2 of this SB is valid as terminating action as per § 1.E. of this SB.

6 Current revision. 7 “Warranty Claim & Failure Report procedure”.

8 Information - “Replacement of the composite material tail-cone/vertical fin assembly, with the metal construction assembly, in the event of not repairable damages”.

N. PUBLICATIONS AFFECTED Not applicable.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 6 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4

2. ACCOMPLISHMENT INSTRUCTIONS Procedure NOTE 1: refer to AMM c hap. 20-00-01 for the Standard Practices Airframe, taking care to the health and safety precautions.

NOTE 2: obey all of the warnings and cautions given in the specified manual sections.

NOTE 3: for aircraft stations, zoning and location of access/inspection panels, refer to AMM chap. 06-00-00.

NOTE 4: refer to AMM chap. 51-00-00 for Standard Practices and Structures and/or to SRM.

NOTE 5: all work, in particular that which is not explicitly described in this SB, must be performed in accordance with the approved manuals.

NOTE 6 if it is necessary to remove more parts for access, y ou can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts.

NOTE 7: incomplete review of all the information in the following paragraphs can cause errors. Read the entire pr ocedure as well as material and tool(s) necessities before beginning work to make sure you have a complete understanding of the requirements.

A. PREPARATION

(1) Configure the aircraft for standard maintenance (in accordance with AMM chap. 12-00- 00, TASK 12-00-00-860-801).

(2) De-energize the aircraft electrical system ( in accordance with AMM chap. 24 -00-00, TASK 24-00-00-000-801).

(3) In the flight compartment put a warning notice to tell persons not to restore/apply the electrical power and operate the flight controls.

(4) Make sure that the following circuit breaker(s) is(are) open, safetied and tagged:

CB PANEL DESIGNATION NO.

PILOT A/P SERVO AIL/RUD 2,3 CB 5043 PILOT PRI PITCH TRIM CB 90 PILOT SEC PITCH TRIM CB 89 MJB PRI PITCH TRIM PWR 1,2 CB 120 PILOT A/P SERVO ELEV CB 5044 CO-PILOT A/P SERVOS 1 CB 619 CO-PILOT REC LT CB 110 1,2 / CB 6110 3 1 P180 Avanti 2 P180 Avanti II 3 P180 Avanti II EVO

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 7 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4

(5) Put an access platform in position at the vertical stabilizer assembly.

(6) Remove the vertical stabilizer front fairing in a ccordance with AMM chap. 55 -30-00, TASK 55-30-00-000-801.

(7) Remove the horizontal tail trim actuator (HTTA) in accordance with AMM chap. 27-40- 00, TASK 27 -40-00-000-802. Make sure to properly cap, coil and stow the wires/harnesses in a suitable and safe area, as applicable.

(8) Remove the recognition light in accordance with AMM chap. 33-42-00, TASK 33-42-00- 000-812 (for P180 Avanti and Avanti II). Make sure to properly cap, coil and stow the wires/harnesses in a suitable and safe area, as applicable.

(9) If require d, remove the power supply unit in accordance with AMM chap. 33 -42-00, TASK 33-42-00-000-808 (for P180 Avanti and Avanti II). Make sure to properly cap, coil and stow the wires/harnesses in a suitable and safe area, as applicable.

B. PROCEDURE/MODIFICATION PART A

(10) Find the HTTA fitting assembly P/N 80-363283-401 (1, Figure 1).

(11) In order to ease the NDT inspection , removal of the upper closure rib P/N 80 -363263- 401 or P/N 80-363263-403 (2, Figure 1) is required, unless a flexible/orientable probe is available and the conditions listed under NOTE 8 are satisfied . For fasteners removal, refer to AMM chap. 51-43-00.

NOTE 8: the use of a flexible/orientable probe for E ddy Current inspection on the forward end of the fitting is allowed, provided the NDT inspector is able to ensure the same level of reliability and accuracy of the check with respect to a standard probe. The proper contact of the probe over all the areas to be inspected shall be guaranteed (simultaneous use of a bor escope is suggested), and the probe calibration shall be performed under the same conditions of the actual check.

(12) Make sure that the inspection areas of the fitting assembly are clean and free from paint and runs and used sealant. If necessary, clean the inspection areas and make sure they are dry before you continue.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 8 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 NOTE 9: operators may contact local NDT providers for tooling availability and inspection accomplishment. Eddy current is to be performed by a technician certified by either SNT−TC−1A or NAS-410 in eddy current and active in eddy current inspection within the last 12 months. Additionally, it is highly recommended that the NDT provider knows the instrument and material specification and parameters setup as per PAI NDTM, when applicable.

(13) Do a High Frequency Eddy Current (HFCE) inspection for corrosion and/or damage at the following areas (refer also to Figure 3):

(13a) around the 14 attaching fastener heads (1, Figure 2);

(13b) around the bu shing P/N 80 -363259-001 on both sides of the lug (2 and 3 , Figure 2 and 4, Figure 3);

(13c) around the sleeve bushing P/N MS14238C10P028 on both sides of the lug (4 and 5, Figure 2 and 5, Figure 3);

(13d) the fillet radii (6a and 6d, Figure 2) of the supports P/N 80 -363285-001 ( 7, Figure 2 and 2, Figure 3) and P/N 80-363285-002 (8, Figure 2 and 3, Figure 3) and the fillet radii (6b and 6c, Figure 2) of the support P/N 80-363284-001 (9, Figure 2 and 1, Figure 3).

(14) Acceptable corrosion (hereinafter referred to as “light corrosion”) limits are: depth 0.15 mm and extension 1 in2 (645.2 mm2) maximum. Clean the affected area, carefully polish out light surface corrosion and make sure that all the corrosion is removed (refer to SRM chap. 51-10-50). Restore the protective treatment and the topcoat in accordance with SRM chap. 51-20-20 and chap. 51-20-30 as applicable.

(15) Proceed with Part B for further actions based on inspection findings.

PART B

(16) Following the inspection defined in step (1 3) and the acceptable findings as per step

(14), if any corrosion 1 and/or damage/crack is detected, fill out the Failure Report form (in accordance with PAI SL no. 80 -0097) including the location and a preliminary corrosion/damage assessment and report to Piaggio Aerospace - Product Support Department (refer to §1.H.).

[ 1 light corrosion reporting is required in any case ]

(17) On the basis of the inspection findings, the following actions shall be undertaken:

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 9 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 Case 1

(a) Finding: Absence of corrosion or presence of light corrosion without any other damage.

(b) Action: Aircraft can continue safe flight without any replacement and in case of light corrosion, repair as per SRM chap. 51-10-50.

(c) Compliance Time: Not applicable or before next flight in case of repair of light corrosion is required.

(d) Repetitive Inspection: Following the initial inspection , repeat the inspection as per § 2. PART A of this MSB within 6 60 FH or 2 6 M, whichever occurs first, unless the terminating action is accomplished (refer to § 1.E.).

Case 2

(a) Finding: Corrosion1 and/or damage/crack detected around one attaching fastener in Zone I (see VIEW A, Figure 3) and/or in Zone II (see VIEW A, Figure 3).

Corrosion1 and/or damage/crack detected around the bushing and/or the sleeve bushing, not on the same fitting assembly lug, as also shown below (red color indicates corrosion/damage):

Corrosion1 and/or damage/crack detected on one or more fillet radii (6a, 6b, 6c, 6d, Figure 2) not on the same fitting assembly lug (9 and/or 10, Figure 3).

[ 1 other than light corrosion. In case of evidence of light corrosion only, action, compliance time and repetitive inspection(s) are in accordance with Case 1 ]

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 10 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4

(b) Action: Aircraft can continue safe flight provided that the fitting assembly is replaced2 as per Compliance Time. Replace in accordance with SRM chap. 51-70-70 (ref. § 1.M.).

[ 2 contact PAI P180 Customer Support (§ 1.H.) for technical and logistic support, if required]

(c) Compliance Time: Within 150 FH or 7M, whichever occurs first, after the embodiment of Part A of this MSB.

(d) Corrective action: the replacement3 of all the parts of the HTTA fitting assembly (SECTION A-A, Figure 3) constitutes the terminating action for the repetitive inspection as per § 1.E. . Following inspection/maintenance shall be performed in accordance with the AMM instructions.

[ 3 as per SRM instructions (ref. § 1.M.) including, but not limited to, wet assembly of the parts and final protective coating ] Case 3

(a) Finding: Corrosion1 and/or damage/crack detected around two or more attaching fasteners in Zone I (see VIEW A, Figure 3) and/or in Zone II (see VIEW A, Figure 3).

Corrosion1 and/or damage/crack detected around the bushing /sleeve bushing on both sides of the same fitting assembly lug (2,3 and/or 4,5, Figure 2 and 7 and/or 8, Figure 3) , as also shown below (red color indicates corrosion/damage):

Corrosion 1 and/or damage/crack detected on both fillet radii of the same fitting assembly lug (6a, 6b and/or 6c, 6d, Figure 2 and 9 and/or 10, Figure 3).

[ 1 other than light corrosion. In case of evidence of light corrosion only , action, compliance time and repetitive inspection are in accordance with Case 1 ]

(b) Action: The fitting assembly shall be replaced 2 as per Compliance Time .

Replace in accordance with SRM chap. 51-70-70 (ref. § 1.M.).

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 11 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 [ 2 contact PAI P180 Customer Support (§ 1.H.) for technical and logistic support, if required]

(c) Compliance Time: Before next flight.

(d) Corrective action: the replacement3 of all the parts of the HTTA fitting assembly (SECTION A-A, Figure 3) constitutes the terminating action for the repetitive inspection as per § 1.E.. Following inspection/maintenance shall be performed in accordance with the AMM instructions.

[ 3 as per SRM instructions (ref. § 1.M.) including, but not limited to, wet assembly of the parts and final protective coating ] C. TEST

(18) When required, adjustment/rigging procedures and/or functional/operational test are specified in the AMM installation tasks during close-up operations (refer to § 2. D.).

D. CLOSE-UP

(19) Make sure that the work area is clean and clear of tool(s) and other items.

(20) Install the upper closure rib P/N 80-363263-401 or P/N 80-363263-403 (2, Figure 1). For fasteners installation, refer to AMM chap. 51 -40-00. Paint touch-up may be required:

refer to AMM chap. 51-25-00.

(21) Install the recognition light in accordance with AMM chap. 33 -42-00, TASK 33 -42-00- 400-812 (for P180 Avanti and Avanti II).

(22) Install the power supply unit in accordance with AMM chap. 33-42-00, TASK 33-42-00- 400-808 (for P180 Avanti and Avanti II).

(23) Install the horizontal tail trim actuator (HTTA) in accordance with AMM chap. 27-40-00, TASK 27-40-00-400-802.

(24) Install the vertical stabilizer front fairing in accordance with AMM chap. 55-30-00, TASK 55-30-00-400-801.

(25) Remove the access platform.

(26) Remove the warning notice from the flight compartment.

(27) Restore the systems and the aircraft to normal operating conditions.

PIAGGIO AERO INDUSTRIES S.p.A. in A.S.

Via Pionieri e Aviatori d’Italia - 16154 Genoa, Italy Product Support Department Original Issue: November 30th, 2022

Service Bulletin: 80-0492 Rev. N. 3 Date: June 12th, 2023 Page: 12 of 17 EXPORT CONTROL COMPLIANCE: This document might contain controlled technology subject to national and international Export Control Restrictions; retransfer is prohibited unless previously authorized by Piaggio Aero Industries S.p.A. in A.S.

Mod. D007_ed_4 E. DOCUMENTATION

(28) Complete the attached Confirmation Slip and send it back to Piaggio Aero Industries S.p.A. – Product Support Department.

(29) Make an appropriate entry in the airplane logbook to show compliance with this Service Bulletin.