Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 1 of 18 Service Bulletin No: 34-038 Ref No: 305 Modification No: EC-13-0125 ATA Chapter: 34 SERVICE BULLETIN

PILATUS AIRCRAFT LTD, STANS, SWITZERLAND

NAVIGATION - ATTITUDE AND DIRECTION MODIFICATION TO THE ELECTR ONIC STANDBY INSTRUMENT-SYST EM (ESIS) POWER RETURN WIRES 1. Planning Information A. Effectivity PC-12/47E Series aircraft MSN 545, 1001 thru 1450. MSN 1451 and up will have this modification incorporated during production. NOTE: Throughout this Service Bulleti n, Config. 1 aircraft are MSN 545 and MSN 1001 thru MSN 1270. Config. 2 aircraft are MSN 1271 thru MSN 1450. B. Concurrent Requirements None. C. Reason In order to minimize any possibilit y that the Apex displays can be affected together with the ESIS, the ESIS ground connection is relocated, improv ing isolation and separation from the main displays. D. Description This Service Bulletin gives the data and instructio ns necessary to do a modification to change the ground connection for the ESIS

. E. Compliance Mandatory. Accomplishment required not later than May 31/2013.Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 2 of 18 SERVICE BULLETIN

F. Approval The technical content of this document is appr oved under the authorit y of DOA No. EASA. 21J. 357. PILATUS advises Operators/Owners to check wit h their designated Airworthiness Authority for any changes, local regulations or sanctions th at may affect the embodiment of this Service Bulletin. G. Copyright © 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. H. Manpower

I. Weight and Balance (1) Weight change: None. (2) Moment change: None. J. Electrical load Data Not changed. K. Software Not changed. L. References Aircraft Maintenance Manual (AMM): 12-B-20-20-01-00A-040A-A, 12-B-20-31-00-00A-070A-A, 12-B-25-10-03-00A-920A-A, 12-B-34-26-40-00A-903A-A or 12-B-34-26-40-00A-903B-A, 12-B-46-30-00-00A-903A-A,12-B-46-30-01-00A-920A-A, 12-B-46-30-03-00A-920A-A. M. Publications Affected Wiring Diagram Manual (WDM).

Task Man-hours (With Ground Point Ready) Man-hours (Without Ground Point Ready) Preparation 0.50 0.50 Modification 2.50 2.75 Close-Up 1.25 1.25 TOTAL MAN-HOURS 4.25 4.50Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 3 of 18 SERVICE BULLETIN

N. Interchangeability of Parts One way interchangeable. Pre Service Bulletin pa rts must not be installed on Post Service Bulletin aircraft.Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 4 of 18 SERVICE BULLETIN

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

PILATUS AUSTRALIA (PTY.) LTD, 17 JAMES SCHOFIELD DRIVE, ADELAIDE AIRPORT SA 5950, AUSTRALIA Tel: +61 (8) 8234 4433 Fax: +61 (8) 8234 4499 eMail: supportpc12@pilatus.com.au

Operators are requested to advise Pilatus Aircra f t Ltd, of the Manufacturer’s Serial Number (MSN) and the flying hours of aircraft which are affected by this Service Bulletin.

500.51.12.030 Contact address above Contact address above B. Warranty Pilatus agrees to cover the costs for parts and labor of affected aircraft provided the work is a ccomplished by an Authorized Service Center wit hin 6 months from the issue date of this Service Bulletin. Modification Kit Number Price AvailabilityService Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 5 of 18 SERVICE BULLETIN

C. Material Necessary for one Aircraft Modification Kit No. 500.51.12.030 has these parts:

New Part No. Description Old Part No. Qty Disp. Code Fig Item

591.30.12.031 GROUND STUD 12

- 1

- 1 1 511.36.12.986 PLACARD (GS125)

- 1

- 1 8 971.31.18.830 TERMINAL LUG

- 2

- 1 2 938.07.68.304 NUT

- 2

- 1 4 10 938.77.11.112 WASHER

- 2

- 1 3 9 971.32.18.105 RETAINING CLIP

- 3

- 1 6 919.79.41.302 WIRE, (F4H22N) 1500 MM AWG22 - 1 3

-
971.42.31.535 PIN MODULE

- 1 3

-

NOTE: Config 1 aircraf t requires new wire (P/N 919.79.41.302) and pin module (P/N 971.42.31.535 ). NOTE: Co nfig 2 aircraft only require one terminal lug (P/N 971.31.18.830)

. NOTE: Par t 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 the part is dispatched. Disposition Codes: N - New / D - Discard / R - Return to PilatusService Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 6 of 18 SERVICE BULLETIN

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

MATERIAL NO. DESCRIPTION QTY REMARKS P01-010 SOLVENT A/R Or equivalent P02-031 ABSORBENT PAPER A/R Or equivalent P07-021 ALODINE 1132 TOUCH-NPREP PEN A/R Or equivalent

P08-076

Alternative P07-007 MASKING VARNISH

EPOXY PRIMER A/R

A/R Glyptal G7526F (P/N 9 08.18.12.095) AKZO NOBEL (P/N 9 10.02.05.031) P09-005 CABLE TIE A/R Or equivalent P09-008 CABLE TIE A/R Or equivalent P09-014 CABLE TIE A/R Or equivalent P09-026 MASKING TAPE A/R Or equivalent

- RED PROTECTIVE TAPE A/R Pilatus P/N 917.40.60.311

- BONDING TESTER 1 Local supply E. Tooling - Cost and Availability None.Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 7 of 18 SERVICE BULLETIN

3. Accomplishment Instructions A. Preparation (1) Remove the left bottom sidewall (Ref. AMM, 12-B-25-10-03-00A-920A-A). (2) Remove the pilot’s PFD (Ref. AMM, 12-B-46-30-01-00A-920A-A). (3) Remove the upper MFD (Ref. AMM, 12-B-46-30-03-00A-920A-A). B. Modification (1) Disconnect the wires from the ground point (Ref. Fig. 6 - Hook-Up Chart): (a) Get access to the grounding block GB109 installed on the aft face of FR10. Do this through the location for the pilot’s PFD. (b) For Config. 1 aircraft (Ref. Fig. 2):
1 Locate the wire F6A20N. 2 Disconnect the wire from position 4 of the grounding block GB109 (Ref. Line 1 of the Hook-Up Chart). 3 Remove the terminal pin from the wire.
4 Locate the wire F4H22N.
5 Disconnect the wire from position 1 of the grounding block GB109 (Ref. Line 2 of the Hook-Up Chart). 6 Remove the terminal pin from the wire. (c) For Config. 2 aircraft (Ref. Fig. 4):
1 Locate the wire F81A22N. 2 Disconnect the wire from position 4 of the grounding block GB109 (Ref. Line 5 of the Hook-Up Chart). 3 Remove the terminal pin from the wire. (2) Install the ground stud GS125 (Ref. Fig. 1): (a) Find the hole for the ground stud GS125 (1) (P/N 591.30.12.031 ) in FR12, LH. (b) Remove the protective tape, if installed. (c) If the hole has bare metal surrounding it for 14 mm (0.55 in.) diameter on the forward and the aft face, continue this Service Bulletin from Step 3.B.(2)(j). (d) If the hole does not have bare metal surrounding it for 14 mm (0.55 in.) diameter on the forward and the aft face, cont inue with this Service Bulletin. (e) Make a mark to show a circle of approximately 14 mm (0.55 in.) diameter on the forward face of FR12 with the same center as that of the hole.Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 8 of 18 SERVICE BULLETIN

(f) Make another mark to show a circle of approximately 14 mm (0.55 in.) diameter on the aft face of FR12 with the same center as that of the hole. (g) Put the masking tape (Material No. P09- 026) on the edges of the marked circles on the forward and aft faces of FR12. (h) Remove the surface finish from the area inside the masking tape (Material No. P09- 026) circles. (i) Remove the masking tape (Material No. P09-026). (j) Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) to clean: • The area on the forward face of FR12 • The area on the aft face of FR12. (k) Apply a layer of Alodine (Material No. P07-021) to: • The bare area on the forward face of FR12 • The bare area on the aft face of FR12. (l) Wait approximately 10 minutes. (m) Put the ground stud GS125 (1) (P/N 591.30.12.031 ) in position with the stud to the front of the aircraft. (n) Install the washer (9) (P/N 938.77.11.112) and the nut (10) (P/N 938.07.68.304 ). (o) Hold the ground stud GS125 (1) (P/N 591.30.12.031 ) and torque the nut (10) (P/N 938.07.68.304 ) to between 2,3 and 2,9 Nm (20 and 25 lb in.). NOTE: Do not forget to add the run down torque to the value given above (Ref. AMM, 12-B-20-20-01-00A-040A-A). (p) Do an electrical continuity test betwee n the ground stud GS125 and the aircraft structure (pilots seat rail or similar). The resistance must be less than 5 m Ω

. (3) Connect the wires to the ground stud GS125 (Ref. Fig. 6 - Hook-Up Chart): (a) For Config. 1 aircraft (Ref. Fig. 1 and 3):
1 For the wire F6A20N.

a Make a note of the position of the cable ties that attach this wire to other wires in the aircraft. b Cut the cable ties, if necessary, to remove this wire from the other wires in the aircraft.

c Route the wire to the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031) (Ref. Fig. 3). d Cut the wire to length and install a terminal lug (2) (P/N 971.31.18.830) (Ref. Line 3 of the Hook-Up Chart, Fig. 6).Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 9 of 18 SERVICE BULLETIN

e Use the cable ties (Material No. P09-005, Material No. P09-008 or Material No. P09-014) to attach the cables you released in Step 3.B.(3)(a)1 b

. 2 For the wire F4H22N.

a Make a note of the position of the cable ties that attach this wire to other wires in the aircraft. b Cut the cable ties, if necessary, and remove this wire from the aircraft.

c Install pin module (P/N 971.42.31.535) to the wire (P/N 919.79.41.302) and connect to TB109-01 terminal X (Ref. Fig. 3). d Route the wire from TB109-01 terminal X to the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031) (Ref. Fig. 3).

e Cut the wire to length and install a terminal lug (2, Fig. 1) (P/N 971.31.18.830) (Ref. Line 4 of the Hook-Up Chart, Fig. 6). f Use the cable ties (Material No. P09-005, Material No. P09-008 or Material No. P09-014) to attach the cables you released in Step 3.B.(3)(a)2 b

. 3 Put the two terminal lugs (2) (P/N 971.31.18.830 ) (complete with the wires F6A20N and F4H22N) on the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031 ).
4 Install the washer (3) (P/N 938.77.11.112) and the nut (4, Fig. 1) (P/N 938.07.68.304 ).
5 Apply a layer of the masking varnish (Material No. P08-076) to both sides of the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031). 6 Put the three retaining clips (6) (P/N 971.32.18.105 ) in position equally spaced along the wires F6A20N and F4H22N between FR11 and FR12, LH.
7 At these positions, wrap a piece of the protective tape (7) (P/N 917.40.60.311) around the wire F6A20N and the wire F4H22N. 8 Put the three retaining clips (6, Fig. 1) (P/N 971.32.18.105 ) in position on top of the VHF 1 antenna cable. 9 Put the wires F6A20N and F4H22N on top of the three retaining clips (6, Fig. 1) (P/N 971.32.18.105 ) and hold everything in positi on with cable ties (5, Fig. 1) (Material No. P09-005).Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 10 of 18 SERVICE BULLETIN

(b) For Config. 2 aircraft (Ref. Fig. 1 and 5):
1 For the wire F81A22N.

a Make a note of the position of the cable ties that attach this wire to other wires in the aircraft. b Cut the cable ties, if necessary, to remove this wire from the other wires in the aircraft.

c Route the wire to the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031) (Ref. Fig. 5). d Cut the wire to length and install a terminal lug (2, Fig. 1) (P/N 971.31.18.830) (Ref. Line 6 of the Hook-Up Chart, Fig. 6).

e Use the cable ties (Material No. P09-005, Material No. P09-008 or Material No. P09-014) to attach the cables you released in Step 3.B.(3)(b)1 b

. 2 Put the terminal lug (2, Fig. 1) (P/N 971.31.18.830 ) (complete with the wire F81A22N) on the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031 ). 3 Install the washer (3, Fig. 1) (P/N 938. 77.11.112) and the nut (4, Fig. 1) (P/N 938.07.68.304 ).
4 Apply a layer of the masking varnish (Mat erial No. P08-076) to both sides of the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031).
5 Put the three retaining clips (6, Fig. 1) (P/N 971.32.18.105 ) in position equally spaced along the wire F81A22N between FR11 and FR12, LH. 6 At these positions, wrap a piece of th e protective tape (7, Fig. 1) (P/N 917.40.60.311) around the wire F81A22N.
7 Put the three retaining clips (6, Fig. 1) (P/N 971.32.18.105 ) in position on top of the VHF 1 antenna cable. 8 Put the wire F81A22N on top of th e three retaining clips (6) (P/N 971.32.18.105 ) and hold everything in position with cable ties (5, Fig. 1) (Material No. P09-005). (4) Install the placard (GS125) (8, Fig. 1) (P/N 511.36.12.986 ) adjacent to the ground stud GS125 (1, Fig. 1) (P/N 591.30.12.031 ) in a position it can be easily read. C. Close-Up (1) Remove all equipment, materials and tools from the work area. Make sure that the work area is clean. (2) Install the upper MFD (Ref. AMM, 12-B-46-30-03-00A-920A-A). (3) Install the pilot’s PFD (Ref. AMM, 12-B-46-30-01-00A-920A-A). (4) Do a Power On Check (Ref. AMM, 12-B-46-30-00-00A-903A-A).Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 11 of 18 SERVICE BULLETIN

(5) Do a test of the ESIS (Ref. AMM, 12-B-34 -26-40-00A-903A-A or AMM, 12-B-34-26-40- 00A-903B-A). (6) Install the left bottom sidewall (Ref. AMM, 12-B-25-10-03-00A-920A-A). D. Documentation (1) Record in the aircraft logbook and the Aircraft Flight Manual that this Service Bulletin has been accomplished. (2) Use the Service Bulletin Evaluation Sheet to report your results to PILATUS.SB2315 1

2

3 4

5

6

7 8 9 10
NOTE: CONFIG. 1 SHOWN CONFIG. 2 IS THE SAME BUT WITH ONLY ONE WIRE ATTACHED TO THE GROUND STUD FR 12. LH

Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 12 of 18 SERVICE BULLETIN

Installation of the Ground Stud GS125 Figure 1Sansome CliveJohnson Mark ECAHoler Daniel

Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 13 of 18 SERVICE BULLETIN

Wiring Diagram - Config 1 Aircraft - Pre Service Bulletin Figure 2© Pilatus Aircraft Ltd. All rights are reserved. No part of this document may be copied or re produced without the prior written consent of Pilatus Aircraft Ltd. © Pilatus Flugzeugwerke AG. Alle Rechte vorbehalten. Dieses Dokument darf ohne vorherige Zustimmung der Pilatus Flugzeugwerke A G weder ganz noch teilweise kopiert oder reproduziert werden.	


	




	



	



 

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Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 14 of 18 SERVICE BULLETIN

Wiring Diagram - Config 1 Aircraft - Post Service Bulletin Figure 3	





	
 	
	

	

 	
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			%	%&	!	&		!		%'	'"""%!Tignonsini OsvaldoIsabelle DavidGibson Paul

Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 15 of 18 SERVICE BULLETIN

Wiring Diagram - Config 2 Aircraft - Pre Service Bulletin Figure 4Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 16 of 18 SERVICE BULLETIN

Wiring Diagram - Config 2 Aircraft - Post Service Bulletin Figure 5 © Pilatus Aircraft Ltd. All rights are reserved. No part of this document may be copied or re produced without the prior written consent of Pilatus Aircraft Ltd. © Pilatus Flugzeugwerke AG. Alle Rechte vorbehalten. Dieses Dokument darf ohne vorherige Zustimmung der Pilatus Flugzeugwerke A G weder ganz noch teilweise kopiert oder reproduziert werden.

	

 


	




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" """ """$ " "$"#"""" "LineEnd 1Wire No.End 2RemarksIdent. No.TerminalNo.Terminal P/N.Terminal P/N.TerminalNo.Ident. No.For Config. 1 Aircraft1M127PE -F6A20N- 4GB109Disconnect End 2 and remove theterminal pin2TB109-01X -F4H22N- 1GB109Removecompletely3M127PE -F6A20N971.31.18.830-GS125Connect End 24TB109-01X971.42.31.535F4H22N971.31.18.830-GS125Install newFor Config. 2 Aircraft5M127P3 -F81A22N- 4GB109Disconnect End 2 and remove theterminal pin6M127P3 -F81A22N971.31.18.830-GS125Connect End 2

Service Bulletin No: 34-038 Date:Mar 26/13 Rev No. Date: Page 17 of 18 SERVICE BULLETIN

Hook-Up Chart (Config 1 and 2 Aircraft) Figure 6Service Bulletin No: 34-038 Date: Mar 26/13 Rev No. Date: Page 18 of 18 SERVICE BULLETIN

INTENTIONALLY BLANKPlease forwoard this form to:

PILATUS AIRCRAFT LTD, CUSTOMER SUPPORT PC-12 (GC) CH 6371 Stans, Switzerland Fax: +41 41 619 73 11 Email: supportpc12@pilatus-aircraft.com 

## Important Note: If a parts replacement are involved, please provide the applicable work card including the component detail s (part number(s) and serial number(s)) together with the feedback sheet. The purpose of this Feedback Form is to allow you, the customer, to comment on this Service Bulletin. Your comments will be used to further improve our Service Bulletin program. It al so provides Pilatus Aircraft with current informati on on each individual aircraft.

 We have embodied/accomplished this SB  Fully



## FEEDBACK SHEET FOR ACCOMPLISHMENT OF SB No: _____________ Ref No: ____________

Aircraft Registration
Owner

Service Center Total Airframe Hours Aircraft MSN Total Landings

Comments (procedure, kit quality, suggested improvm ents etc.) Date of accomplishment Name Signature

The undersigned confirms the accomplishment of this Service Bulletin  We will not embody/accomplish this SB  Partially Operator