EASA AD No.: 2015-0071

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0071

Date: 30 April 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption].


### Design Approval Holder’s Name: PIAGGIO AERO INDUSTRIES S.p.A. Type/Model designation(s): P.180 Avanti aeroplanes

TCDS Number: EASA.A.059

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2010-0146 d ated 22 July 2010.



### ATA 53 Fuselage – Forward Pressurized Bulkhead – Inspectio n /

Reinforcement / Modification

Manufacturer(s): Piaggio Aero Industries S.p.A (PAI )

Applicability: Piaggio Aero Industries P.180 Avanti aeroplanes, manufacturer serial numbers (S/N) 1004 through 1033 inclusive.

Reason: In 1997, Piaggio Aero Industries S.p.A (PAI ) developed a modification of the forward pressurized bulkhead, published through PAI Service Bulletin (SB) 80-0081, aiming to restore the safe fatigue life of the bulkhead structure. Consequently, ENAC Italy (formerly RAI) issued Pres crizione di Aeronavigabilita (PA) 97-148 to require compliance with this SB.
After RAI PA 97-148 was issued, PAI issued SB 80-00 81 Revision 2 to provide improved instructions for specific serial numbers. Prompted by this development, EASA issued AD 2010-0146 superseding P A 97-148 and requiring accomplishment of instruction of PAI issu ed SB 80-0081 Revision 2.
After that AD was issued, PAI issued SB 80-0081 Rev ision 3 to make the instructions for inspection (and, depending on find ings, rework/reinforcement) applicable to all aeroplanes.
For the reasons described above, this AD retains th e requirements of EASA AD 2010-0146, which is superseded, requires inspect ion and, depending on findings, reinforcement of the pressurized bulkhead structure on extended population of aeroplanes. This AD also specifies th at certain aeroplanes modified in accordance with SB 80-0081 up to Revisi on 2 need to be inspected and, depending on findings, reinforced as required by this AD.EASA AD No.: 2015-0071

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 14 May 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) Within the compliance time as defined in Table 1 of this AD, depending on aeroplane S/N, inspect (visually or using a stan dard Endoscope Equipment) the forward pressurized bulkhead to veri fy presence of bulkhead reinforcement in accordance with Part A1 o f the Accomplishment Instructions of PAI SB 80-0081 Revis ion 3. Table 1 – Inspection
Aeroplane S/N Compliance Time

1004, 1015 and 1017 Within 1 500 FH after 15 July 1997 [the

effective date of ENAC PA 97-148], or before exceeding 6 000 FH since aeroplane first flight, whichever occurs first

1005 through 1014 inclusive, 1016, and 1018 through 1033 inclusive (whichever occurs later, A or B )
A : Within 1 500 FH after the effective date of this AD, or before exceeding 6 000 FH since aeroplane first flight, whichever occurs first;

or B : Within 200 FH or 6 months, whichever occurs first after the effective date of this AD
(2) If, during the inspection as required by paragr aph (1) of this AD, it is determined that no bulkhead reinforcement is instal led, within the compliance time as defined in Table 1 of this AD, a s applicable, or for aeroplanes, which on the effective date of this AD accumulated equal to or more than 6 000 FH since aeroplane first flight, within 200 FH after accomplishment of the inspection, as required by pa ragraph (1) of this AD, reinforce the forward pressurized bulkhead in a ccordance with Part A2 of the Accomplishment Instructions of PAI SB 80- 0081 Revision 3. (3) Before exceeding 6 000 FH since aeroplane first flight, modify the forward pressurized bulkhead in accordance with Part C of t he Accomplishment Instructions of PAI SB 80-0081 Revision 3. (4) Inspection (Part A1 of the SB), reinforcement ( Part A2 of the SB) and modification (Part C of the SB) of an aeroplane, ac complished before the effective date of this AD in accordance with the in structions of PAI SB 80-0081 original issue, Revision 1 or Revision 2, i s acceptable to comply with the requirements of this AD for that aeroplane

. (5) For aeroplanes with S/N 1006 through 1033 (excl uding S/N 1015 and 1017): Modification of an aeroplane in accordance w ith Part C of PAI SB 80-0081 original issue, Revision 1 or Revision 2 do es not constitute compliance with the requirements of paragraphs (1) and (2) of this AD.

Ref. Publications: Piaggio Aero Industries SB 80-00 81, original issue dated 28 April 1997, or Revision 1 dated 11 May 2010, or Revision 2 dated 1 9 July 2010, or Revision 3, dated 20 January 2015. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 31 March 2015 as PAD 15-03 0 for consultation until 28 April 2015. The Comment Response Document can be found at http://ad.easa.europa.eu

.EASA AD No.: 2015-0071

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Piaggio Aero Industries S.p.A – Airworthiness Offic e Viale Generale Disegna, 1 – 17038 Villanova d’Alben ga (SV) – Italy E-mail: airworthiness@piaggioaerospace.it