Service Bulletin No: 27-022 Date: Mar 17/15

Rev. No. Date: Page 1 of 10 Service Bulletin No: 27-022 Ref No: 334 Modification No: - ATA Chapter: 27 SERVICE BULLETIN

PILATUS AIRCRAFT LTD, STANS, SWITZERLAND

FLIGHT CONTROLS - AILERON CONTROL SYSTEM REPLACEMENT OF THE UNIVERSAL JOINTS IN THE FLIGHT C ONTROLS
1. Planning Information A. Effectivity PC-12/47E aircraft MSN 1447 thru 1450, 1461, 1462, 1466 thru 1514, 1516 thru 1520 and 1523. PC-12 Series aircraft where the universal joints (P/N 944.61.73.012 or 527.10.12.195), purchased from March 2014 to, and including, Februa ry 2015 were installed as replacement parts. PC-12 Series aircraft modified with the inspection kit (P/N 500.50.12.314) for the aileron control system, purchased from March 2014 to, and including , February 2015. Universal joints (P/N 944.61.73.012 or 527.10.12.19 5) held as spares purchased from March 2014 to, and including, February 2015. Inspection kits (P/N 500.50.12.314) held as spares purchased from March 2014 to, and including, February 2015. NOTE: The inspection kit (P/N 500.50.12.314) is used for:

• SB 04-009 (Airworthiness Limitations - Life Extens ion to 25,000 flying hours or 30,000 landings) • SSID Task 27-10/394 (Aileron Control System – Exam ine). This task is performed initially at 32,500 flying h ours or 42,000 landings, whichever comes first, and every 12,500 flying hours or 15,00 0 landings or 6 years whichever comes first. B. Concurrent Requirements None. C. Reason A universal joint installed between the control tub e assembly and the control column malfunctioned. D. Solution Replace the universal joints, as defined in 1. A., with new parts ordered from Pilatus.Service Bulletin No: 27-022 Date: Mar 17/15 Rev No. Date: Page 2 of 10 SERVICE BULLETIN

E. Description This Service Bulletin gives the data and instructio ns necessary to replace the universal joints (P/N 527.10.12.195): • Part A is for on-aircraft • Part B is for parts held as spare. F. Compliance Mandatory. For aircraft with less than 200 flights since new o r less than 200 flights since the installation of a spare part as defined in 1. A.: • No more than 10 flights or • 3 months from the issue date of this Service Bulle tin. For aircraft with more than 200 flights since new o r more than 200 flights since the installation of a spare part as defined in 1. A.: • No later than 1 year after the issue date of this Service Bulletin. This Service Bulletin can be performed at annual inspection. G. Approval The technical content of this document is approved under the authority of DOA No. EASA. 21J. 357. PILATUS advises operators/owners to check with thei r designated Airworthiness Authority for any changes, local regulations or sanctions that may affect the embodiment of this Service Bulletin. H. Copyright © Pilatus Aircraft Ltd. This document contains prop rietary information that is protected by copyright. All rights are reserved. No part of thisdocument may be copied, reproduced or translated to other languages without the prior wri tten consent of Pilatus Aircraft Ltd. I. Manpower

J. Weight and Balance No change. Task Man-hours Man-hours At Annual Inspection Preparation 1.0 0.0 Modification 1.0 1.0 Close-Up 1.0 0.0 TOTAL MAN-HOURS 3.0 1.0Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 3 of 10 SERVICE BULLETIN

K. Electrical load Data No change. L. Software No change. M. References Aircraft Maintenance Manual (AMM)

N. Publications Affected No change. O. Interchangeability of Parts Not interchangeable. 12-B-07-10-00-00A-901A-A 12-B-20-20-01-00A-040A-A 12- B-20-31-00-00A-070A-A 12-B-24-00-00-00A-901A-A 12-B-25-10-01-00A-920A-A 12 -B-27-10-00-00A-903A-A 12-B-27-30-00-00A-903A-AService Bulletin No: 27-022 Date: Mar 17/15 Rev No. Date: Page 4 of 10 SERVICE BULLETIN

2. Material Information A. Material - Price and Availability If you require more information about this modification, please contact us as follows:

Operators are requested to advise Pilatus Aircraft Ltd, of the Manufacturer’s Serial Number (MSN) and the flying hours of aircraft which are affected by this Service Bulletin. B. Warranty Credit will be issued for parts and labour for all affected aircraft on approval of a warranty claim, provided the work is accomplished by an authorised Service Center within 12 months of the issue date of this Service Bulletin. C. Material Necessary for one Aircraft NOTE: Part Numbers given in this Service Bulletin are cor rect at the time of approval. Pilatus

Aircraft Ltd. reserves the right to change the partnumbers as necessary. Operators are requested to check the IPC for delivered parts whic h differ from those listed in the Service Bulletin. PILATUS AIRCRAFT LTD CUSTOMER SUPPORT MANAGER CH-6371 STANS SWITZERLAND General Aviation: Tel: + 41 41 619 3333 Fax: + 41 41 619 7311 eMail: SupportPC12@pilatus-aircraft.com

PILATUS BUSINESS AIRCRAFT LTD PRODUCT SUPPORT DEPARTMENT 11755 AIRPORT WAY BROOMFIELD, CO 80021 UNITED STATES OF AMERICA Tel: +1 303 465 9099 Fax: +1 303 465 6040 eMail: supportPC12@PilBal.com

PILATUS AUSTRALIA PTY LTD 17 JAMES SCHOFIELD DRIVE ADELAIDE AIRPORT SA 5950 AUSTRALIA Tel: +61 8 8238 1600 Fax: +61 8 8234 4499 Free Call: +61 1800 PILATUS (745 2887) eMail: supportpc12@pilatus.com.auService Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 5 of 10 SERVICE BULLETIN

(1) Parts to be ordered from Pilatus

D. Operator Supplied Materials (Ref. AMM 12-B-20-31- 00-00A-070A-A)

E. Tooling - Cost and Availability None. New Part No. Description Old Part No. Qty Disp. Code Fig Item
527.10.12.195 Universal joint

(New parts are marked with a placard) 527.10.12.195 2 R 1 1,16

932.19.60.814 BOLT, HEX 932.19.60.814 2 D 1 6, 12 938.77.11.115 WASHER, FLAT 938.77.11.115 2 D 1 10, 14 938.07.68.505 NUT, HEX 938.07.68.505 2 D 1 11, 15 932.35.14.016 BOLT, HEX 932.35.14.016 1 D 1 20 932.35.14.012 BOLT, HEX 932.35.14.012 1 D 1 2 938.77.11.112 WASHER, FLAT 938.77.11.112 2 D 1 3, 17 938.07.68.304 NUT, HEX 938.07.68.304 2 D 1 4, 18 Disposition Codes: D - Discard / N - New / R - Retu rn to Pilatus

Material No. Description Qty Remarks P04-039 Corrosion preventive ARService Bulletin No: 27-022 Date: Mar 17/15 Rev No. Date: Page 6 of 10 SERVICE BULLETIN

3. Part A: Accomplishment Instructions - On Aircraft A. Preparation (1) Raise the aircraft on jacks, refer to AMM 12-B-0 7-10-00-00A-901A-A. (2) De-energize the aircraft electrical system, refe r to AMM 12-B-24-00-00-00A-901A-A. (3) Open and install a safety clip (Circuit breaker hold open) (P/N 110.88.07.065) on the circuit breaker: A/P SERVO (AVIONICS BUS). (4) Put a warning sign in the cockpit: DO NOT MOVE F LYING CONTROLS. (5) Remove the crew seats, refer to AMM 12-B-25-10-0 1-00A-920A-A. B. Removal - Pilot Side Refer to Figure 1. CAUTION: BE CAREFUL NOT TO DAMAGE THE ADJACENT WIRING LOOM. (1) Remove the nut (22) and the bolt (23). (2) Remove and discard the nut (15), washer (14) and the bolt (12). (3) Remove and discard the nut (18), washer (17) and the bolt (20). (4) Move back the control wheel and remove the unive rsal joint (16) (P/N 527.10.12.195) from the control tube assembly (13) and the control colu mn (21). (5) Remove the stop block (19) from the universal jo int. C. Installation - Pilot Side Refer to Figure 1. (1) Apply corrosion preventive (Material No. P04-039 ) to the internal surface of the stop block (19). (2) Apply corrosion preventive (Material No. P04-039 ) to the mating surfaces of the control tube assembly (13) the control column (21) and the new universal joint (16) (P/N 527.10.12.195). (3) Put the stop block (19) on the universal joint ( 16) (P/N 527.10.12.195) and align the holes. (4) Install the new universal joint (16) (P/N 527.10 .12.195) to the control column (21). (5) Install the control tube assembly (13) to the un iversal joint (16) (P/N 527.10.12.195) and align the holes. (6) Install the new bolt (20) (P/N 932.35.14.016), w asher (17) (P/N 938.77.11.112) and the nut (18) (P/N 938.07.68.304).Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 7 of 10 SERVICE BULLETIN

(7) Install the new bolt (12) (P/N 932.19.60.814), w asher (14) (P/N 938.77.11.115) and the nut (15) (P/N 938.07.68.505). (8) Install the bolt (23) and the nut (22). (9) Torque the nuts to the standard torque values, refer to AMM 12-B-20-20-01-00A-040A-A. D. Removal - Co-pilot Side Refer to Figure 1. CAUTION: BE CAREFUL NOT TO DAMAGE THE ADJACENT WIRING LOOM. (1) Remove the nut (8) and the bolt (9). (2) Remove and discard the nut (11), washer (10) and the bolt (6). (3) Remove and discard the nut (4), washer (3) and t he bolt (2). (4) Move back the control wheel and remove the unive rsal joint (1) (P/N 527.10.12.195) from the control tube assembly (7) and the control colum n (5). E. Installation - Co-pilot Side Refer to Figure 1. (1) Apply corrosion preventive (Material No. P04-039 ) to the mating surfaces of the control tube assembly (7) the control column assembly (5) a nd the new universal joint (1) (P/N 527.10.12.195). (2) Install the new universal joint (1) (P/N 527.10. 12.195) to the control column (5). (3) Install the control tube assembly (7) to the uni versal joint (1) (P/N 527.10.12.195) and align the holes. (4) Install the new bolt (2) (P/N 932.35.14.012), wa sher (3) (P/N 938.77.11.112) and the nut (4) (P/N 938.07.68.304). (5) Install the new bolt (6) (P/N 932.19.60.814), wa sher (10) (P/N 938.77.11.115) and the nut (11) (P/N 938.07.68.505). (6) Install the bolt (9) and the nut (8). (7) Torque the nuts to the standard torque values, refer to AMM 12-B-20-20-01-00A-040A-A. F. Close Up (1) Do an functional test of the aileron control system, refer to AMM 12-B-27-10-00-00A903A-A. (2) Do an functional test of the elevator control sy stem, refer to AMM 12-B-27-30-00-00A903A-A. (3) Make sure that the work area is clean and clear of tools and other items. (4) Install the crew seats, refer to AMM 12-B-25-10- 01-00A-920A-A.Service Bulletin No: 27-022 Date: Mar 17/15 Rev No. Date: Page 8 of 10 SERVICE BULLETIN

(5) Remove the safety clip and close the circuit bre aker:

A/P SERVO (AVIONICS BUS). (6) Remove the warning sign from the cockpit. (7) Lower the aircraft to the ground and remove the jacks, refer to AMM 12-B-07-10-00-00A901A-A. G. Documentation (1) Record in the aircraft logbook that this ServiceBulletin has been accomplished. (2) Mark the removed universal joints “unserviceable ” and return to Pilatus at the applicable address below:
PILATUS AIRCRAFT LTD WARRANTY COORDINATOR ENNETBÜRGENSTRASSE 101 CH-6371 STANS SWITZERLAND Attn: Mr Stefan Brun Tel: + 41 41 619 3333

PILATUS BUSINESS AIRCRAFT LTD PARTS SALES AND SERVICES 11755 AIRPORT WAY BROOMFIELD, CO 80021 UNITED STATES OF AMERICA Attn: Mr Jerry Frank Tel: +1 303 465 9099Service Bulletin No: 27-022 Date: Mar 17/15

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4. Part B: Accomplishment Instructions - Spares A. Instruction Parts held as spares must be marked “unserviceable”and return to Pilatus at the applicable address below:
PILATUS AIRCRAFT LTD WARRANTY COORDINATOR ENNETBÜRGENSTRASSE 101 CH-6371 STANS SWITZERLAND Attn: Mr Stefan Brun Tel: + 41 41 619 3333

PILATUS BUSINESS AIRCRAFT LTD PARTS SALES AND SERVICES 11755 AIRPORT WAY BROOMFIELD, CO 80021 UNITED STATES OF AMERICA Attn: Mr Jerry Frank Tel: +1 303 465 9099Service Bulletin No: 27-022 Date: Mar 17/15 Rev No. Date: Page 10 of 10 SERVICE BULLETIN

Universal Joint - Removal/Installation

Figure 1 

# A A 1

2

3 5 6

8 9

10 11

12 FRAME 12

4 

# B



# B 7

13

14 15
16

17 18 20 22 23

21SB2603 19