Service Bulletin No: 27-021 Date: Jan 20/15

Rev. No. Date: Page 1 of 12 Service Bulletin No: 27-021 Ref No: 331 Modification No: EC-14-0549, EC-14-0714 ATA Chapter: 27 SERVICE BULLETIN

PILATUS AIRCRAFT LTD, STANS, SWITZERLAND

FLIGHT CONTROLS - AILERON CONTROL SYSTEM AILERON TAB COUNTER BALANCE WEIGHT INCREASE 1. Planning Information A. Effectivity PC-12/47 aircraft MSN 684 thru MSN 888 and PC-12/47 E aircraft MSN 545, 1001 thru 1520. Aileron trim tab assemblies P/N 527.15.12.037 or 52 7.15.12.038 held as spare. Aileron assemblies P/N 557.05.12.015 / 016 / 017 / 018 held as spare. This modification will be embodied on PC-12/47E aircraft MSN 1521 and up at production. B. Concurrent Requirements None. C. Reason During a continued airworthiness review, Pilatus Ai rcraft Ltd. has identified a potentially unsafe condition that could result from a disconnected ail eron trim tab occurring above an altitude of 10,000 feet. While there has been no case of a disconnected tab nor any other in-flight control disconnection on record for the entire PC-12 fleet, all owners and operators should implement this modification to provide improved stability and damping qualities by increasing the weight of the aileron tab counter balance. D. Description This Service Bulletin gives the data and instructio ns necessary to replace the aileron tab counter balance weight. The old counter balance weight has a diameter of 1.25 in. (31,75 mm) and a thickness of 0.34 in. (8,70 mm). The new counter ba lance weight has a diameter of 1.46 in. (37,20 mm) and a thickness of 0.39 in. (10,00 mm). E. Compliance Mandatory. Required at next Annual Inspection, but no later th an 29 February 2016.Service Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 2 of 12 SERVICE BULLETIN

F. 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 ma y affect the embodiment of this Service Bulletin. G. Copyright © Pilatus Aircraft Ltd. This document contains prop rietary 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 wri tten consent of Pilatus Aircraft Ltd. H. Manpower

NOTE: Man-hours do not include drying time for paints. I. Weight and Balance Weight Change +0,060 kg Moment Change +0,392 kg m J. Electrical load Data No change. K. Software No change. L. References NOTE: Throughout this Service Bulletin, references are gi ven without the model prefix.

For PC-12, PC-12/45 and PC-12/47 aircraft, prefix references with 12-A. For PC-12/47E aircraft, prefix references with 12-B

. Aircraft Maintenance Manual (AMM) Task Man-hours Part A Manhours Part B Preparation 1.0 - Modification 1.0 1.0 Installation 0.5 1.0 Close-Up 3.0 - TOTAL MAN-HOURS 5.5 2.0

20-31-00-00A-070A-A 24-00-00-00A-901A-A 57-60-02-00A -920A-AService Bulletin No: 27-021 Date: Jan 20/15

Rev No. Date: Page 3 of 12 SERVICE BULLETIN

Structural Repair Manual (SRM)

M. Publications Affected IPC, SRM. N. Interchangeability of Parts Not interchangeable. 51-60-01-00A-276A-AService Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 4 of 12 SERVICE BULLETIN

2. Material Information A. Material - Price and Availability Customers are advised that the standard lead time f or parts may be up to two months. 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 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. Part numbers of items delivered with the Modification Kit are co rrect when the kit is dispatched. This could lead to differences between those part numbers quoted in this Service Bulletin and the Modification Kit if parts are superseded. O perators are requested to check the IPC for delivered parts which differ from those lis ted in the Service Bulletin Materials Kit List. 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: 27-021 Date: Jan 20/15

Rev No. Date: Page 5 of 12 SERVICE BULLETIN

(1) Parts to be ordered from Pilatus for Part A

(2) Parts to be ordered from Pilatus for Part B

D. Operator Supplied Materials (Ref. AMM, 20-31-00-0 0A-070A-A)

E. Tooling - Cost and Availability None. New Part No. Description Old Part No. Qty Disp. Code Fig Item
527.15.12.105 COUNTER BALANCE

WEIGHT 527.15.12.102 2 D Disposition Codes: D - Discard / N - New / R - Retu rn to Pilatus

New Part No. Description Old Part No. Qty Disp. Code Fig Item
527.15.12.105 COUNTER BALANCE

WEIGHT 527.15.12.102 1 D Disposition Codes: D - Discard / N - New / R - Retu rn to Pilatus

Material No. Description Qty Remarks 940.17.02.502 COTTER PIN 2 P02-008 LOCKWIRE A/R 939.27.81.018 RIVET NAS1097AD4 A/R Grip length to suit P07-007 EPOXY PRIMER A/R P08-073 SEALANT A/R P08-073 for EU. P08-020 is an alternative product and available for USAService Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 6 of 12 SERVICE BULLETIN

3. Accomplishment Instructions - Part A On-Aircraft A. Preparation (1) Energize the aircraft electrical system, refer t o AMM 24-00-00-00A-901A-A. (2) Extend the flaps to 40°. (3) De-energize the aircraft electrical system, refe r to AMM 24-00-00-00A-901A-A. (4) Put a warning sign in the cockpit to warn “DO NO T MOVE FLYING CONTROLS”. (5) Remove the left and right aileron, AMM 57-60-02- 00A-920A-A. B. Modification (1) If installed, remove the trim tab from the aileron, refer to Figure 1: (a) Remove and discard the cotter pin (4). (b) Remove the nut (5) and washer (6) from the control rod bolt (9). (c) Remove the control rod bolt (9) from the trim ta b brackets. (d) Disconnect the bonding lead (8) from the bolt (9 ). (e) Disconnect the control rod eye end (7) from the trim tab (1). (f) Remove and discard the lockwire from the trim ta b hinge pin (3) and the lockwire tab (2) on the trim tab. (g) Hold the trim tab (1) then remove and keep the h inge pin (3). (h) Remove the trim tab from the aileron. Refer to Figure 2. (2) Carefully remove the two rivets (12) that hold t he counter balance weight (10) to the aileron trim tab rib (1). (3) Remove the existing counter balance weight (10) from the trim tab. NOTE: The counter balance weight may have sealant on the mating surface with the

trim tab rib. (4) Make sure that the surface finish on the trim ta b rib (1) is clean and undamaged. Reprotect the rib as necessary. (5) Use sealant (Mat. No. P08-073) to wet assemble. Put the new counter balance weight (11) (P/N 527.15.12.105) in position on the trim tab rib (1). (6) Use sealant (Mat. No. P08-073) to wet assemble. Install two new rivets (12) (P/N 939.27.81.018) to hold the counter balance weight ( 11). Make sure that the countersunk rivet heads are in the trim tab rib.Service Bulletin No: 27-021 Date: Jan 20/15

Rev No. Date: Page 7 of 12 SERVICE BULLETIN

(7) Apply epoxy primer (Mat. No. P07-007) to the newcounter balance weight and rivet heads. (8) Let the epoxy primer dry. (9) Apply the applicable surface finish as needed an d let the paint dry. (10) Part mark the modified item(s) with a permanentmarker as follows:

C. Installation Refer to Figure 1. (1) Install the aileron trim tab on the aileron: (a) Align the trim tab hinge with the hinge half on the aileron. (b) Install the trim tab hinge pin (3). (c) Safety the trim tab hinge pin (3) with lockwire (Mat. No. P02-008) to the lockwire tab (2) on the trim tab. (d) Put the control rod eye end (7) in the trim tab brackets. (e) Install the bonding lead (8) on the control rod bolt (9). (f) Install the control rod bolt (9) through the tri m tab brackets and the control rod eye end (7). (g) Install the washer (6) and the nut (5) on the bo lt (9). (h) Safety the nut (5) with a new cotter pin (P/N 94 0.17.02.502) (4). D. Close Up (1) Do the procedure to balance the ailerons, SRM 51 -60-01-00A-276A-A. (2) Install the left and right aileron, AMM 57-60-02 -00A-920A-A. (3) Make sure that the work area is clean and clear of tools and other items. E. Documentation (1) Record in the aircraft logbook that this Service Bulletin has been accomplished.

Description New P/N Old P/N Trim Tab LH 527.15.12.043 527.15.12.037 Trim Tab RH 527.15.12.044 527.15.12.038Service Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 8 of 12 SERVICE BULLETIN

4. Accomplishment Instructions - Part B Spares A. Modification (1) If installed, remove the trim tab from the aileron, refer to Figure 1: (a) Remove and discard the cotter pin (4). (b) Remove the nut (5) and washer (6) from the control rod bolt (9). (c) Remove the control rod bolt (9) from the trim ta b brackets. (d) Disconnect the bonding lead (8) from the bolt (9 ). (e) Disconnect the control rod eye end (7) from the trim tab (1). (f) Remove and discard the lockwire from the trim ta b hinge pin (3) and the lockwire tab (2) on the trim tab. (g) Hold the trim tab (1) then remove and keep the h inge pin (3). (h) Remove the trim tab from the aileron. Refer to Figure 2. (2) Carefully remove the two rivets (12) that hold t he counter balance weight (10) to the aileron trim tab rib (1). (3) Remove the existing counter balance weight (10) from the trim tab. NOTE: The counter balance weight may have sealant on the mating surface with the

trim tab rib. (4) Make sure that the surface finish on the trim ta b rib (1) is clean and undamaged. Reprotect the rib as necessary. (5) Use sealant (Mat. No. P08-073) to wet assemble. Put the new counter balance weight (11) (P/N 527.15.12.105) in position on the trim tab rib (1). (6) Use sealant (Mat. No. P08-073) to wet assemble. Install two new rivets (12) (P/N 939.27.81.018) to hold the counter balance weight ( 11). Make sure that the countersunk rivet heads are in the trim tab rib. (7) Apply epoxy primer (Mat No. P07-007) to the new counter balance weight and rivet heads. (8) Let the epoxy primer dry. (9) Apply the applicable surface finish as needed an d let the paint dry. (10) Part mark the modified item with a permanent ma rker as follows:

Description New P/N Old P/N Trim Tab LH 527.15.12.043 527.15.12.037Service Bulletin No: 27-021 Date: Jan 20/15

Rev No. Date: Page 9 of 12 SERVICE BULLETIN

B. Installation Refer to Figure 1. (1) If needed, install the aileron trim tab on the a ileron: (a) Align the trim tab hinge with the hinge half on the aileron. (b) Install the trim tab hinge pin (3). (c) Safety the trim tab hinge pin (3) with lockwire (Mat. No. P02-008) to the lockwire tab (2) on the trim tab. (d) Put the control rod eye end (7) in the trim tab brackets. (e) Install the bonding lead (8) on the control rod bolt (9). (f) Install the control rod bolt (9) through the tri m tab brackets and the control rod eye end (7). (g) Install the washer (6) and the nut (5) on the bo lt (9). (h) Safety the nut (5) with a new cotter pin (P/N 94 0.17.02.502) (4). C. Close Up (1) Do the procedure to balance the aileron, SRM 51- 60-01-00A-276A-A.

Trim Tab RH 527.15.12.044 527.15.12.038 Description New P/N Old P/NService Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 10 of 12 SERVICE BULLETIN

Aileron Trim Tab - Removal/Installation

Figure 1 7
4

8 

# A 3 6 

# A

LH SHOWN RH OPPOSITE

1 2

5

9 

# BSB2546Service Bulletin No: 27-021 Date: Jan 20/15

Rev No. Date: Page 11 of 12 SERVICE BULLETIN

Aileron Trim Tab Mass Balance Weight - Removal/Inst allation Figure 2SB2547 

# B 1 10

11

12Service Bulletin No: 27-021 Date: Jan 20/15 Rev No. Date: Page 12 of 12 SERVICE BULLETIN

INTENTIONALLY BLANK