# Pilatus Service Bulletin 25-059: No revision named - Rights: © Pilatus Aircraft Ltd. Filed by the FAA in regulations.gov docket FAA-2026-0018, the docket of AD 2026-15-12. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Pilatus Service Bulletin 25-059](https://openairdocs.org/service-documents/pilatus/sb-25-059.md) - Title as filed: Pilatus PC-12 SB 25-059 Original - Pages: 14 - PDF: https://openairdocs.org/files/sha256/0f/d4/0fd4cff2a1a61ad29708b7ba33e7ea85ae9ea78fb29932207af5efd803108ce4 - Page: https://openairdocs.org/service-documents/pilatus/sb-25-059/file/0fd4cff2a1a6 ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 1 of 14 Service Bulletin No: 25-059 Ref No: 469 Modification No: EC-25-0067 ATA Chapter: 25 SERVICE BULLETIN Pilatus Aircraft Ltd, Pilatusstrasse 1, 6371 Stans, Switzerland EQUIPMENT AND FURNISHINGS - PASSENGER COMPARTMENT IMPROVEMENT TO THE PSU TRIM PANEL INSTALLATION ABOVE THE EMERGENCY EXIT 1. Planning Information A. Effectivity PC-12/47E series aircraft MSN 2001 thru MSN 2999. NOTE: Some aircraft were fitted with the modification proposed in this SB during production by the aircraft OEM. This SB does not need to be implemented if visual inspection confirms that the aircraft is already equipped with the dual locks. Refer to Figure 1. B. Concurrent requirements None. C. Reason (1) Problem During an inspection it was identified that it is possible for the PSU trim panel (installed above the emergency exit door) to block the opening of the emergency exit. This is possible if the PSU trim panel is positioned too far inboard due to incorrect installation, which can cause interference with the emergency exit door panel. (2) Solution A modification is necessary to improve the installation of the interior trim panels in the area of the emergency exit. D. Description This Service Bulletin gives the data and instructions necessary to: • Part 1 - Determine if the dual lock fasten ers are installed on the PSU trim panel • Part 2 - If necessary, introduce additional fa steners on the interior trim panels in the area of the emergency exit. E. Compliance Mandatory. To be accomplished at the next scheduled annual inspection after the issue of this Service Bulletin. ### Page 2 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 2 of 14 SERVICE BULLETIN The technical content of this document is approved under the authority of the DOA ref. EASA.21J.357. Pilatus advises Operators/Owners to check with their designated Airworthiness Authority for any changes, local regulations or sanctions that may affect the embodiment of this Service Bulletin. F. Approval © Pilatus Aircraft Ltd. This document contains proprietary information that is protected by copyright. All rights are reserved. No part of this document may be copied, reproduced or translated to other languages without the prior written consent of Pilatus Aircraft Ltd. In connection with the use of this document, Pilatus does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. This document contains trade secrets, confidential and/or proprietary information of Pilatus and technical data subject to export control laws and regulations, including the U.S. Export Administration Regulations (EAR). Disclosure or distribution of this document contrary to the EAR, and other laws and regulations, is strictly forbidden. The above restrictions may apply to data on all pages of this document. G. Copyright and legal statement H. Manpower NOTE: The man-hours do not include the time necessary to cure sealants, paints and adhesives. I. Weight and balance Not changed. J. Electrical load change data Not changed. K. Software Not changed. Description Man-Hours Part 1 Part 1 and Part 2 Preparation 0.5 Part 1 - Examination for installation of dual lock fasteners 0.25 1.25 Part 2 - Modification to install the dual lock fasteners -1 . 0 Requirements after job completion 0.5 TOTAL MAN-HOURS 1.25 2.25 ### Page 3 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 3 of 14 L. References AMM references are given without the model prefix: For PC-12/47E Series aircraft use the prefix 12-B, and/or 12-C as applicable for MSN 2001 thru MSN 2999. Aircraft Maintenance Manual (AMM) M. Publications affected Aircraft Maintenance Manual (AMM). Illustrated Parts Data (IPD). N. Interchangeability of parts One-way interchangeable. 20-31-00-00A-070A-A 25-21-03-00A-920A-A 52-20-00-00A-920A-A ### Page 4 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 4 of 14 SERVICE BULLETIN 2. Material Information A. Material - Price and availability Operators that require additional information and/or Service Bulletin material can contact their authorized Pilatus Service Center, or Pilatus Customer Support on: https://www.pilatus-aircraft.com  contact us. NOTE: Part numbers given in this Service Bulletin are correct at the time of approval. Pilatus Aircraft Ltd reserves the right to change the part numbers as necessary. Part numbers of items delivered are correct when dispatched. This could lead to differences between those part numbers quoted in this Service Bulletin and the delivered parts, if parts are superseded. Operators are requested to check the Illustrated Parts Data (IPD) for delivered parts that differ from those listed in the Service Bulletin Materials List. Operators are requested to advise Pilatus Aircraft Ltd of the Manufacturer’s Serial Number (MSN), the flying hours and landings of aircraft that are allocated for this Service Bulletin. B. Warranty Credit will be issued for labour for all affected aircraft on approval of a warranty claim, provided the work is accomplished by an authorized Service Center within the compliance time given in Section 1.E on Page 1 of this Service Bulletin. C. Material necessary for each aircraft NOTE: Referenced AMM procedures may contain additional materials to be procured. (1) Material to or der from Pilatus None (2) Material to procure locally New Part No. Description Old Part No. Qty Disp. Code Fig. Item 917.47.28.046 Fastener self-adhesive, Dual-lock (SUPPLIER P/N SJ3552CF) -A R N 1 4 917.47.28.045 Fastener self-adhesive, Dual-lock (SUPPLIER P/N SJ3551CF) -A R N 1 6 Disposition Codes: D - Discard / N - New / R - Return to Pilatus / E - Exchange Part ### Page 5 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 5 of 14 D. Locally supplied consumables NOTE: Referenced AMM procedures may contain additional consumables to be used. To identify the materials used in this procedure, look in the Consumable materials list. Refer to AMM 12-B-20-31-00-00A-070A-A. E. Material necessary for each spare Not applicable. F. Re-identified parts Not applicable. G. Tools and equipment NOTE: Referenced AMM procedures may contain additional tools to be used. Material No. Description Qty Remarks P01-033 Wipes, presaturated solvent AR - P08-080 Adhesive AR Scotch-Weld 10 Tools and equipment Recommended Pilatus part Tool kit, mechanic Local supply ### Page 6 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 6 of 14 SERVICE BULLETIN 3. Accomplishment Instructions WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE MANUFACTURER´S HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE LOCAL INSTRUCTIONS. CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL AND / OR DAMAGE TO EQUIPMENT. NOTE: Refer to the manufacturer’s instructions for the necessary time for consumable materials to cure/dry. A. Preparation (1) Move the aircraft into a hangar. (2) Open the passenger or cargo door to get access to the modification area. (3) Remove the emergency exit door. Refer to AMM 12-B-52-20-00-00A-920A-A. ### Page 7 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 7 of 14 B. Part 1 - Examination for installation of dual lock fasteners Refer to Figure 1 (1) Remove and keep the PSU, trim panel RH (1) from over the emergency exit door in the passenger compartment. Refer to AMM 12-C-25-21-03-00A-920A-A. (2) Do a visual inspection for the installation of the dual-lock fastener tapes (4) and (6) on the panels that follow: Refer to views C, E, G, and J. • FWD, Upper, RH (3) • AFT, Upper, RH (2) • PSU, trim panel RH (1). (a) If the dual-lock fastener tapes (4) and (6) are installed, install the PSU, trim panel RH (1) that you kept. Refer to AMM 12-C-25-21-03-00A-920A-A. 1 Make sure that the PSU, trim panel RH (1) is installed correctly and the dual- lock fastener tape (4) and (6) are engaged. 2 Continue with the ‘Requirements after job completion’ and ‘Documentation’ sections of this Service Bulletin. (b) If the dual-lock fastener tapes (4) and (6) are not installed go to Part 2 of this Service Bulletin, refer to Para 3.C. ### Page 8 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 8 of 14 SERVICE BULLETIN C. Part 2 - Modification to install the dual lock fasteners (1) Cut two pieces of the dual-lock fastener tape (4) (P/N 917.47.28.046) to 20 x 25 mm (0.79 x 0.98 in). (2) Cut two pieces of the dual-lock fastener tape (6) (P/N 917.47.28.045) to 13 x 13 mm (0.51 x 0.51 in). (3) If necessary, remove the panel cover material (leather/vinyl) in the installation area of the dual-lock fastener tape (6). Refer to views G and J. NOTE: The dual-lock fastener tape is to be bonded to the structure of the composite panels. (4) Use wipes, presaturated solvent (Material No. P01-033) to clean the installation positions of the dual-lock fastener tapes (4) and (6) on the panels that follow: Refer to views C, E, G, and J. • FWD, Upper, RH (3) • AFT, Upper, RH (2) • PSU, trim panel RH (1). (5) Let the solvent dry. (6) Apply a thin layer of adhesive (Material No. P08-080) to the mating surfaces of the dual- lock fastener tapes (4) and (6) and the panels that follow: Refer to views C, E, G, and J. • FWD, Upper, RH (3) • AFT, Upper, RH (2) • PSU, trim panel RH (1). (7) Let the adhesive cure as per the manufacturers instructions. (8) Install the dual-lock fastener tape (4) and (6) on the mating surfaces of the panels that follow: Refer to views C, E, G, and J. • FWD, Upper, RH (3) • AFT, Upper, RH (2) • PSU, trim panel RH (1). (a) Make sure that the dual-lock fastener tape (4) on the PSU, trim panel RH (1) is aligned with the locator pins (5). Refer to views E and C. (b) Make sure that the dual-lock fastener tape (6) is aligned with the edge of the panels (2) and (3) and 30mm (1.18 in) above the emergency exit. Refer to views G and J. (c) Make sure that the dual-lock fastener tape (4) and (6) is securely fastened to the panels. ### Page 9 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 9 of 14 (9) Install the PSU, trim panel RH (1) over the emergency exit door in the RH side of the passenger compartment. Refer to AMM 12-C-25-21-03-00A-920A-A. (10) Make sure that the PSU, trim panel RH (1) is installed correctly and the dual-lock fastener tape (4) and (6) are engaged. ### Page 10 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 10 of 14 SERVICE BULLETIN D. Requirements after job completion (1) Install the emergency exit door. Refer to AMM 12-B-52-20-00-00A-920A-A. (2) Make sure that the PSU, trim panel RH (1 ) has sufficient clearance with the emergency exit door. Refer to Figure 1. (3) Remove all tools and materials. Make sure that the work areas are clean. E. Documentation (1) Make an entry in the Aircraft Log book to record the accomplishment of Part 1 only or Part 1 and Part 2 of this Service Bulletin. (2) Make sure that the Aircraft Logbook shows any new Pilatus Part Number(s) and/or Serial Number(s), as applicable. (3) Make an entry in the PC-12/47E Pilot’s Operating Handbook, Document No. 02406, to record the incorporation of this Service Bulletin. (4) Make sure that all applicable Ai rcraft Documentation is updated. (5) Inform CAMP of the incorporation of this Service Bulletin and any new Pilatus Part Number(s) and/or Serial Number(s), as applicable. Send the completed CAMP feedback sheet to: fax@campsystems.com ### Page 11 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 11 of 14 Installation of dual-lock fastener tape Figure 1 (Sheet 1 of 2) SB 5050 CE A B C E B F A NOTE: ALIGNED WITH FORWARD EDGE OF PIN1 ALIGNED WITH AFT EDGE OF PIN2 1 2 D D SECTION D-D 1 3 1 2 1 1 4 4 4 1 5 5 5 ### Page 12 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 12 of 14 SERVICE BULLETIN Installation of dual-lock fastener tape Figure 1 (Sheet 2 of 2) SECTION H-H F G J J G SB 5051 H H 3 2 6 6 1 3 2 6 30 mm 30 mm ### Page 13 SERVICE BULLETIN Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 13 of 14 Feedback Sheet for the Accomplishment of SB 25-059 The purpose of this feedback sheet is to provide CAMP with the current information on each individual PC-12 aircraft. Please complete the grey cells as appropriate using black ink and block letters. Print out and send the completed feedback sheet to: fax@campsystems.com SB Accomplishment Information CAMP Feedback Sheet Aircraft MSN Aircraft Registration Total Airframe Hours Service Center Total Landings We have embodied/accomplished this SB Fully Partially Part 1 only Part 1 and Part 2 The undersigned confirms the accomplishment of this Service Bulletin Date of accomplishment Name Signature Comments (procedure, kit quality, suggested improvements etc.) ### Page 14 Service Bulletin No: 25-059 Date: May 02/25 Rev. No. - Date: - Page 14 of 14 SERVICE BULLETIN INTENTIONALLY BLANK --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.