Service Bulletin No: 51-001 Ref No: 155 Modification No: Inspection ATA Chapter: 51 SERVICE BULLETIN
PILATUS AIRCRAFT LTD. STANS, SWITZERLAND

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 1 of 66 AIRCRAFT STRUCTURE - GENERAL DO A CHECK OF THE MATERIAL SPECIFICATION USED DURING MANUFACTURE AND, IF NECESSARY, DO A CHECK FOR CRACKS OR REPLACE THE PART 1. Planning Information A. Effectivity (1) PC-7 aircraft MSN 101 thru MSN 618. (2) All of these parts, held as spare or in stock:

B. Concurrent Requirements None. ITEM PARA PART NUMBER DESCRIPTION

1 1 116.35.07.272 LEFT AND RIGH T AILERON OUTER CONTROL-ROD 2 2 116.35.07.270 ELEVATO R FORWARD CONTROL-ROD 3 2 116.35.07.271 ELEVATOR CENTER CONTROL-ROD 4 2 116.35.07.269 ELEVATOR REAR CONTROL-ROD 5 2 116.35.07.183 SHACKLE 6 2 116.35.07.092 SHACKLE 7 3 112.35.07.796 CENTER TANK SUPPORT-BRACKET 8 4 112.35.07.009 FRAME 3 PICK-UP BRACKET, LH 9 5 112.35.07.010 FRAME 3 PICK-UP BRACKET, RH 10 5 112.35.07.251 FRONT AND REAR RUDDER-PEDALS OUTBOARDBEARINGS
11 6 555.30.09.039 or 555.30.09.040 RUDDER LOWER-HING E BEARING-BRACKET or RUDDER LOWER-HINGE BEARING-BRACKET ASSY 12 7 111.34.07.329 FLAP BEARING SUPPORT BRACKET, LH 13 7 111.34.07.330 FLAP BEARING SUPPORT BRACKET, RHService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 2 of 66 SERVICE BULLETIN

C. Reason (1) Problem Pilatus has highlighted the po ssibility that some critical parts can crack due to stress corrosion. (2) Cause The investigation found that in itially the material of the pa rts was AA2024-T351 which is susceptible to Stress Corrosion Cracking (S CC). The material was subsequently changed to AA2124-T851, a new material with improved mechanical properties. The part number was not always changed when the new materi al was introduced (Ref. Table 1 - Summary). (3) Solution (a) Do a one time conductivity test of items 6 thru 9 and 11 thru 13 (both on aircraft and those held in stores) listed in Para. 1.A. (2) to check the material of the parts. (b) If the parts are made from AA2124-T851, make an entry in the aircraft logbook as required in paragraph 3.D.(3). (c) Because it is difficult to inspect for cracks on the elevator center control-rods (Item 3), these type of control rods will be replaced. (d) Parts (Items 1, 2, 4, 5 and 10) are made from AA2024-T351. Therefore: • Do a one time inspection for cr acks of Items 1, 2, 4 and 10 • Replace Item 5. (e) If the conductivity test shows the parts are made from AA2024-T351: 1 For Items 7 thru 9 and 11 thru 13, do a one time inspection for cracks. If cracks are found, contact Pilatus. NOTE: Repetitive mandatory in spections will be added to Chapter 5 of the Aircraft Maintenance Manual (A MM). The inspections will give instructions on how to examine the parts for cracks. The inspections will only be applicable to pa rts made from AA2024-T351. 2 For Item 6, replace the part with a part made from AA2124-T851.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 3 of 66 Summary

Table 1ItemParaDescriptionInstalled Item P/N beforeaccomplishment of SBAA2024-T351AA2124-T85111LEFT AND RIGHT AILERON OUTER CONTROL-ROD116.35.07.272N/A22ELEVATOR FORWARD CONTROL-ROD116.35.07.270N/A32ELEVATOR CENTER CONTROL-ROD116.35.07.271 / .345N/A42ELEVATOR REAR CONTROL-ROD116.35.07.269N/A52SHACKLE116.35.07.183N/A62SHACKLE116.35.07.092116.35.07.09273TANK BRACKET112.35.07.796112.35.07.79684FRAME 3 PICK-UP BRACKET, LH112.35.07.009112.35.07.00994FRAME 3 PICK-UP BRACKET, RH112.35.07.010112.35.07.010105FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGS112.35.07.251N/A116RUDDER LOWER-HINGE BEARING-BRACKETorRUDDER LOWER-HINGE BEARING-BRACKET ASSY555.30.09.039or555.30.09.040555.30.09.039or555.30.09.040127FLAP BEARING SUPPORT BRACKET, LH111.34.07.329111.34.07.329137FLAP BEARING SUPPORT BRACKET, RH111.34.07.330111.34.07.330Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 4 of 66 SERVICE BULLETIN

D. Description This Service Bulletin gives the data and instructions necessary to do the: (1) Inspection of the Aileron Outer Control-Rods. (2) Inspection and, if necessary, Replacement of the Suspect Parts Installed in the Elevator Control System (a) Inspection of the Elevator Forward Control-Rod. (b) Inspection and, if Necessary, Replacem ent of the Elevator Center Control-Rod. (c) Inspection of the Elev ator Rear Control-Rod. (d) Replacement of the Forward Shac kle on the Elevat or Control Cable. (e) Inspection and, if Necessary, Replacem ent of the Aft Shackle on the Elevator Control Cable. (3) Inspection of the Center Tank Support-Bracket. (4) Inspection of Frame 3 Pick-Up Brackets. (5) Inspection of the Rudder -Pedal Outboard-Bearings. (6) Inspection of the Rudder Lower-Hinge Bearing-Bracket. (7) Inspection of the Flap Bearing Support-Brackets. E. Compliance Mandatory. Accomplishment required not later than 365 days af ter the effective date of this Service Bulletin. F. Approval The technical content of this Se rvice Bulletin is approved under the authority of Letter of DOA Acceptance ref. FOCA.21J.002. Pilatus advises Operators/Owners to check with their designated Airworthiness Authorities for any changes, local regulations or sanctions th at may affect the embodiment of this Service Bulletin. G. Copyright Information © 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.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 5 of 66 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), 07-10- 00, 12-00-00, 20-31-00, 25-10-00, 25-10-05, 27-10-00, 27-20-01, 27-30-00, 27-30-04, 27-30-06. Illustrated Parts Catalog (IPC), 25-10-01, 27-30-01, 55-30-01. Structural Repair Manual (SRM), 53-10-00. M. Publications Affected AMM, Chapter 05. IPC, 27-30-01. N. Interchangeability of Parts One way interchangeable. Pre Service Bulletin pa rts must not be installed on Post Service Bulletin aircraft. Total Total Total Preparation 5.0 Inspection 14.0 Replacement of the Shackle (P/N 116.35.07.183) 2.0 Replacement of the Shackl e (P/N 116.35.07.092) 2.0 Close up 5.0 TOTAL MAN-HOURS 24.0 2.0 2.0Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 6 of 66 SERVICE BULLETIN

2. Material Information
Operators who require fu rther information on Price and Av ailability should contact their Customer Liaison Manager at: Pilatus Aircraft Ltd, 6371 Stans, Switzerland. Operators are requested to advise Pilatus Aircraft Ltd. of the Manufacturer’s Serial Number (MSN), the flying hours and landings of aircraft wh ich are allocated for this Service Bulletin using the Service Bulletin Evaluation Form. A. Material - Price and Availability

B. Material Necessary for Each Aircraft (1) Material to be Procured Kit No. 500.50.07.035 has these parts:

(2) Operator Supplied Materials (Ref. AMM 20-31-00)

C. Material Necessary for Each Spare Not applicable. KIT NUMBER PRICE AVAILABILITY 500.50.07.035 Contact address above Contact address above

New Part No. Description Old Part No. Qty Disp. Code Fig Item 527.30.07.021 SHACKLE 116.35.07.183 1 D 8 14 527.30.09.231 SHACKLE 116.35.07.092 1 D 8 3 940.17.02.512 COTTER PIN 940.17.02.341 2 D 8 7 21 Disposition Codes: D - Discard / R - Return to Stores

MATERIAL NO. DESCRIPTION QTY REMARKS P01-010 SOLVENT A/R Or equivalent P02-031 ABSORBENT PAPER A/R Or equivalent P04-011 SPRAY LUBRICANT A/R Or equivalent P04-028 GREASE A/R Or equivalent P04-039 CORROSION PREVEN TATIVE A/R Or equivalentSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 7 of 66 D. Re-identified Parts If the parts, either installed on the aircraft or held as spare, are made from AA2124-T851, change the part numbers as follows:

DESCRIPTION INSTALLED ITEM PART NUMBER RE-IDENTIFIED PART NUMBER (AA2124-T851) LEFT AND RIGHT AILERON OUTER CONTROL-ROD 116.35.07.272 N/A ELEVATOR FORWARD CONT ROL-ROD 116.35.07.270 N/A ELEVATOR CENTER CONT ROL-ROD 116.35.07.271 N/A ELEVATOR REAR CONTROL-ROD 116.35.07.269 N/A SHACKLE 116.35.07.183 N/A SHACKLE 116.35.07.092 527.30.09.232 CENTER TANK SUPPORT-BRACKET 112.35.07.796 553.10.07.034 FRAME 3 PICK-UP BRACKET, LH 112.35.07.009 553.10.07.015 FRAME 3 PICK-UP BRACKET, RH 112.35.07.010 553.10.07.016 FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGS 112.35.07.251 N/A RUDDER LOWER-HINGE BEARING-BRACKET or RUDDER LOWER-HINGE BEARING-BRACKET ASSY 555.30.09.039 or 555.30.09.040 555.30.09.168

FLAP BEARING SUPPORT BRACKET, LH 111.34.07.329 557.21.09.117 FLAP BEARING SUPPORT BRACKET, RH 111.34.07.330 557.21.09.118Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 8 of 66 SERVICE BULLETIN

E. Tooling - Cost and Availability

NOTE: Because of the difficult access for some parts, Pilatus recommends that the maximum diameter of the measurement probe is 6,25 mm (0.25 in.). NOTE: Because of the small access in the control rods, Pilatus recommends that the maximum diameter of the borescope is 3,9 mm (0.15 in.) with a length of 2 m (78.80 in). NOTE: Kit No. 500.60.09.146 is the kit for the re ference pieces used to help identify the material of the suspect parts. NOTE: Kit No. 500.60.09.146 is the same kit used for the accomplishmen t of Service Bulletin 53-008. If you have the pieces from that kit, you do not need to procure the kit again. NOTE: Kit No. 500.60.09.146 has these parts: PART No. DESCRIPTION QTY REMARKS 500.60.09.146 REFERENCE PLATES KIT 1 - EDDY-CURRENT EQUIPMENT WITH CONDUCTIVITY MEASUREMENT PROBE 1 Local supply
OR - CONDUCTIVITY MEASUREMENT EQUIPMENT 1 Local supply - BORESCOPE 1 Local supply - ALUMINIUM OR STEEL TUBE OF APPROXIMATELY 800 MM LENGTH X 10 MM DIAMETER 1 Local supply

PART No. DESCRIPTION QTY REMARKS 513.57.09.149 AA2024-T351 REFERENCE PLATE 1 513.57.09.150 AA2124-T851 REFERENCE PLATE 1SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 9 of 66 3. Accomplishment Instructions WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS. NOTE: Obey the manufacturer's instructions when you mix and use the consumable materials. A. Preparation (1) Put a warning sign (DO NOT OPERATE THE FLIGHT CONTROLS) in the front and rear cockpits. (2) Disengage the flight control lock. (3) Install the tail stand and the adapter (Ref. AMM, 07-10-00, Page Block 201). (4) Install ballast on the ballast-bar support-tube (Ref. AMM, 07-10-00, Page Block 201). (5) Remove the front and rear seats (Ref. AMM, 25-10-00, Page Block 201). (6) In the front cockpit, open and install a safety clip to the circuit breaker: BAT SWITCH (BATTERY BUS CB panel). NOTE: For the location of the access items, refer to AMM, 12-00-00, Page Block 1. (7) Open the battery compartment access-panel F15. (8) Disconnect the battery connector. (9) Disconnect the battery hot connector (if installed). (10) Open the access panel F12. (11) Remove the access panels F5, F17, F18, LB2, RB2, LT8 and RT8. (12) Remove the side panels and linings from the fr ont cockpit to get access to the left and right frame 3 pick-up brackets (Ref. AMM, 25-10-05, Page Block 401). (13) Remove the floor panels from the front cockpi t to get access to the left and right frame 3 pick-up brackets (Ref. IPC, 25-10-01). (14) Remove the side panels and linings from the front and rear cockpits to get access to the left and right rudder pedals outboard-bearings (Ref. AMM, 25-10-05, Page Block 401). (15) Remove the floor panels from the front and rear cockpits to get access to the elevator forward and center control-rods (Ref. IPC, 25-10-01).Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 10 of 66 SERVICE BULLETIN

B. Inspection Obey the manufacturer’s operating instructions and calibrate the conductivity measurement equipment. NOTE: The temperature of the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150) must be approximately the same as the part to be checked. (1) Inspection of the left and right aileron outer control-rods NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. NOTE: This Step is applicable to left and right aileron outer control-rods, P/N 116.35.07.272. NOTE: All aileron rear control-rods have the clevis end and the end piece made from AA2024-351 and are therefore subject to stress corrosion. (a) Disconnect the left-aileron outer control-rod (Ref. Fig. 1): 1 Remove the nut (5), the washer (4) and the bolt (1). 2 Disconnect the aileron outer control-rod (6). 3 Measure, and make a note of, the distance between: • The center of the hole for the attachment bolt (1) • The outboard end of the tube on the control rod (6). 4 Loosen the lock nut (3) sufficiently to tu rn the end fitting (2) on the control rod (6). 5 Hold the lock nut (3) and remove the end fitting (2). (b) Do an inspection for cracks (Ref. Fig. 1): 1 Put the borescope into the left aileron outer control-rod (6). Do this through the hole for the end fitting (2). 2 Obey the manufacturer’s instructions and use the borescope to examine the eight inspection areas of the left-aileron outer control-rod (6) for cracks. (c) Do Step 3.B.(1)(a) and (b) again for the right aileron outer control-rod.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 11 of 66 (d) If you find cracks: 1 You must contact Pilatus Customer Support before next flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@pilatus-aircraft.com. 2 Make a report of the inspection results, refer to Step 3.B.(1)(f). (e) If you do not find cracks, make a report of the inspection results, refer Step 3.B.(1)(f). (f) Report the Inspection Results 1 Make a copy of the Inspection Report Form(s) (Ref. Fig. 2). 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details. 3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@pilatus-aircraft.com. (g) Connect the left-aileron outer control-rod (Ref. Fig. 1): 1 Install the end fitting (2). 2 Adjust the end fitting (2) until the distance between: • The center of the hole for the attachment bolt (1) • The outboard end of the tube on the control rod (6) is the same as noted in Step 3.B.(1)(a)3

. 3 Tighten the lock nut (3).Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 12 of 66 SERVICE BULLETIN

4 Put the left-aileron outer control-rod (6) in position. 5 Install the bolt (1), the washer (4) and the nut (5). (h) Do Step 3.B.(1)(g) again for the right aileron outer control-rod. (i) Do the adjustment / test of the aileron controls (Ref. AMM, 27-10-00, Page Block 501).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 13 of 66 Aileron Outer Cont rol-Rod - Inspection Figure 1SB 2440 

# A LH SHOWN RH SIMILAR 

# C D

E F

J 1



# B

G H

K A A B B

LH SHOWN RH SIMILAR 2 3

4 5 6

6Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 14 of 66 SERVICE BULLETIN

Aileron Outer Control-Rod - Inspection Form Figure 2, Sheet 1 of 2SB 2307 DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm 

# F E D CSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 15 of 66 Aileron Outer Control-Rod - Inspection Form Figure 2, Sheet 2 of 2SB 2308 

# H G

J DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm 

# KService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 16 of 66 SERVICE BULLETIN

(2) Inspection and, if necessary, Replacement of the Suspect Parts Installed in the Elevator Control System (a) Inspection of the Elevator Forward Control-Rod NOTE: All elevator forward control-rods have the forward clevis end made from AA2024-351 and are therefore subject to stress corrosion. 1 Remove the elevator forward control- rod, (Ref. AMM, 27-30-06, Page Block 401). 2 Do an inspection for cracks (Ref. Fig. 3):
a Put the borescope into the elevator forward control-rod (1). Do this through the holes at the aft end of the elevator forward control-rod (1). b Obey the manufacturer’s instruct ions and use the borescope to examine the four inspection areas of the elevator forward control-rod (1) for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before ne xt flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@p ilatus-aircraft.com. b Make a report of the inspection results, refer to Step 3.B.(2)(a)5

. 4 If you do not find cracks, make a report of the inspection results, refer to Step 3.B.(2)(a)5

. 5 Report the Inspection Results
a Make a copy of the Inspection Report Form(s) (Ref. Fig. 4). b Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 17 of 66 c Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@pilatus-aircraft.com. 6 Install the elevator forward control- rod, (Ref. AMM, 27-30-06, Page Block 401). NOTE: The adjustment / test of the elevator control system (Ref. AMM, 27-30-00, Page Block 501) can be done at Step 3.B.(2)(d)5j

.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 18 of 66 SERVICE BULLETIN

Elevator Forward Control-Rod - Inspection Figure 3SB 2450 

# A

C D
B 1

INSERT BOROSCOPE IN HERE

INSERT BOROSCOPE IN HERESERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 19 of 66 Elevator Forward Control-Rod - Inspection Form Figure 4SB 2451 

# D C A

B DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mmService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 20 of 66 SERVICE BULLETIN

(b) Inspection and, if Necessary, Replacement of the Elevator Center Control-Rod For MSNs 312 thru 349 Only 1 Identify the Part Number of th e Elevator Center Control-Rod NOTE: All elevator center control-rods (P /N 116.35.07.271) have the clevis end and the rod end made from AA2024-351 and are therefore subject to stress corrosion. Because there is no access to inspect the internal attachments for the clevis end and the rod end, the control rod will be replaced. The other type of elevat or center control-rods (P/N 116.35.07.345) also have the clevis end and the rod end made from AA2024-351, but can be easily inspected. a Look at the elevator center control-rod. b If the clevis end and the rod end are in stalled inside the tube (Ref. Fig. 5, Sheet 1), the part number of the elevator center control-rod is 116.35.07.271. Continue this Serv ice Bulletin from Para. 3.B.(2)(b)2

. c If the tube is installed inside the clev is end and the rod end (Ref. Fig. 5, Sheet 2), the part number of the elevator center control-rod is 116.35.07.345. Continue this Serv ice Bulletin from Para. 3.B.(2)(b)3

. 2 Replace the elevator center control-r od, refer to Service Bulletin 27-017. NOTE: The adjustment / test of the elevator control system (Ref. AMM, 27-30-00, Page Block 501) can be done at Step 3.B.(2)(d)5j

. 3 Report the Results NOTE: The Results are used to tell Pilatus Aircraft Ltd. the aircraft details. Send or fax the results of the findings to: Pilatus Aircraft Ltd. Customer Techni cal Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@p ilatus-aircraft.com.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 21 of 66 Identification of the Elev ator Center Control-Rod Figure 5, Sheet 1 of 2SB 2445 

# B 

# A A



# B C

D 

# C

DService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 22 of 66 SERVICE BULLETIN

Identification of the Elevator Center Control-Rod Figure 5, Sheet 2 of 2SB 2444 

# B B 

# A A

C

D 

# C

DSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 23 of 66 (c) Inspection of the Elevator Rear Control-Rod NOTE: All elevator rear control-rods have the clevis end and the end piece made from AA2024-351 and are therefore subject to stress corrosion. NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. 1 Disconnect the elevator rear control-rod (Ref. Fig. 6):
a Remove the nut (2), the washers (3 and 6) and the bolt (7). b Disconnect the elevator rear control-rod (1).
c Measure, and make a note of, the distance between: • The center of the hole for the attachment bolt (7) • The AFT end of the tube on the control rod (1). d Loosen the lock nut (4) sufficiently to turn the end fitting (5).
e Hold the lock nut (4) and remove the end fitting (5). 2 Do an inspection for cracks (Ref. Fig. 6):
a Put the borescope into the elevator re ar control-rod (1). Do this through the hole for the end fitting (5). b Obey the manufacturer’s instructions and use the borescope to examine the eight inspection areas of the elevator rear control-rod (1) for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before next flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@pilatus-aircraft.com. b Make a report of the inspection re sults, refer to Step 3.B.(2)(c)6

. 4 If you do not find cracks, make a report of the inspection results, refer Step 3.B.(2)(c)6

.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 24 of 66 SERVICE BULLETIN

5 Connect the elevator rear control-rod (Ref. Fig. 6):
a Install the end fitting (5). b Adjust the end fitting (5) until the distance between: • The center of the hole for the attachment bolt (7) • The AFT end of the tube on the control rod (1) is the same as noted in Step 3.B.(2)(c)1c

. c Tighten the lock nut (4). d Put the elevator center control-rod (1) in position.
e Install the bolt (7), the washers (6 and 3) and the nut (2). NOTE: The adjustment / test of the elevator control system (Ref. AMM, 27-30-00, Page Block 501) can be done at Step 3.B.(2)(d)5j

. 6 Report the Inspection Results
a Make a copy of the Inspection Report Form(s) (Ref. Fig. 7). b Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details.
c Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@p ilatus-aircraft.com.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 25 of 66 Elevator Rear Control-Rod - Inspection Figure 6SB 2443 

# B A 

# A

G
H J K 7
6

3 2 1

5 

# C

D E F B

1 4Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 26 of 66 SERVICE BULLETIN

Elevator Rear Control-Rod - Inspection Form Figure 7, Sheet 1 of 2SB 2297 

# E D C DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm 

# FSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 27 of 66 Elevator Rear Control-Rod - Inspection Form Figure 7, Sheet 2 of 2SB 2298 

# H G

J DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm 

# KService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 28 of 66 SERVICE BULLETIN

(d) Inspection and Replacement of the Shackles on the Elevator Control Cable NOTE: The shackles (P/N 116.35.07.183 and P/N 116.35.07.092) are installed on the elevator control cable (P/N 11 6.35.07.093) (Ref. IPC, 27-30-01). NOTE: All shackles (P/N 116.35.07.183) are made from AA2024-351 and are therefore subject to stre ss corrosion. These sha ckles will therefore be replaced. NOTE: The shackles (P/N 116.35.07.092) can be made from AA2024-351 or AA2124-T851. Th ese shackles will therefore be inspected to identify which material they are made from, and, if necessary, replaced. 1 Do the conductivity test to find the material of the shackles, P/N 116.35.07.092 (Ref. IPC, 27-30-01). NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test.
a Get access to the rear attachment point of the elevator control cable (P/N 116.35.07.093) (Ref. IPC, 27-30 -01) (Refer to AMM, 27-30-04 for further information). b Remove the dirt and grease from th e areas (where you will do the test) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove the layers of surface protection (including paint) to do the test.
c Do a check of the conductivit y of the reference plates: • Make sure the conductivity me asurement equipment has been calibrated (Ref. Step at beginning of Para. 3.B.). • Put the eddy current probe in position on the reference plates (P/N 513.57.09.149 an d P/N 513.57.09.150). • Record the value shown on the test equipment. NOTE: Make sure the temperature of the reference plates (P/N 513.57.09.149 and P/N 513.57.0 9.150) is approximately the same as the shackle (P/N 116.35.07.092). d Put the eddy current probe in po sition on the AFT shackle (P/N 116.35.07.092).
e Record the value shown on the test equipment. f Compare the value recorded above with the values recorded in Step 3.B.(2)(d)1c and determine if the shackle is manufactured from AA2024-T351 or AA2124-T851. g Do Steps 3.B.(2)(d)1d thru f again to make sure th e result is the same. h Write the type of material that the AFT shackle (P/N 116.35.07.092) is made from on the Status of Parts Form (Ref. Fig. 19).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 29 of 66 2 If you find a shackle (P/N 116.35.07.092) made from AA2024-T351, continue this Service Bulletin from Step 3.B.(2)(d)4

. 3 If you find a shackle (P/N 116.35.07.092) made from AA2124-T851, reidentify it (Ref. Para. 2.D.) and conti nue this Service Bulletin from Step 3.B.(2)(d)4

. 4 Replace the shackle (P/N 11 6.35.07.183) (Ref. Fig. 8):
a Make sure that the elevator is in the neutral position. b Install rigging pins (P/Ns 110.85.07.0 50) at the front and rear levers (22 and 2).
c At the front lever (2 2), identify the control cable (1) (P/N 116.35.07.093). d Remove and discard the locking clips from the turnbuckles (11) (Refer to AMM, 27-30-04 for further information).
e Loosen the turnbuckles (12) to release the tension from the control cable (1). f Remove, and discard, the cotter pin (21). g Remove the nut (20), the washer (19) and the bolt (13) that connect the shackle (14) to the control cable (1). h Remove the nut (18), the washers (17) and the bolt (16) that connect the shackle (14) to the elevator center control-rod (24) and the lever (22). i Carefully disconnect the shackle (1 4) (P/N 116.35.07.183) from the elevator center control-rod (24) and the lever (22). Catch, and keep, the washers (23) and the spacers (15). j Discard the shackle (14). CAUTION: DO NOT LET THE SOLVENT (MATERIAL NO. P01-010) GO INTO THE BEARING IN THE LEVER (22). k Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and clean the attachment points on the center control rod (24) and the cable (1). l Put the spacers (15) in the new shackle (14) (P/N 527.30.07.021).
m Put the new shackle (14) (P/N 527.30.07.021) and the washers (23) in position between the center control rod (24) and the cable (1).
n Put a layer of the spray lubricant (Material No. P04-011) on the shank of the bolt (13).
o Install the bolt (16), the washers (17) and the nut (18) that connect the shackle (14) (P/N 527.30.07.021) to the center control rod (24) and the lever (22).Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 30 of 66 SERVICE BULLETIN

p Install the bolt (13), the washer (19) and the nut (20) that connect the shackle (14) (P/N 527.30.07.021) to the cable (1). q Safety the nut (20) with the new cotter pin (21) (P/N 940.17.02.341).
r If the shackle (P/N 116.35.07.092) is made from AA2024-T351, continue this Service Bulletin from Step 3.B.(2)(d)5

. s If the shackle (P/N 116.35.07.092) is made from AA2124-T851, continue this Service Bulletin from Step 3.B.(2)(d)5j

. 5 Replace the shackle (P/N 116.35.07.092) (Ref. Fig. 8): NOTE: Step 3.B.(2)(d)5 is only applicable to shackles (P/N 116.35.07.092) made from AA2024-T351.
a Remove, and discard, the cotter pin (7). b Remove the nut (6), the washer (5) and the bolt (4) that connect the shackle (3) (P/N P/N 116.35.07.092) to the control cable (1). NOTE: Pull the control cable (1) rearwards to make the removal of bolt (4) easier.
c Remove the nut (8), the washer (9) and the bolt (10) that connect the shackle (3) (P/N 116.35.07.092) to the lever (2). d Remove, and discard, the shackle (3) (P/N 116.35.07.092) from the aircraft. CAUTION: DO NOT LET THE SOLVENT (M ATERIAL NO. P01-010) GO INTO THE BEARING IN THE LEVER (9).
e Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and clean the attachment points on the lever (3) and the cable (1). f Put the new shackle (3) (P/N 527.30. 09.231) in position between the lever (2) and the control cable (1). g Install the bolt (4), the washer (5) and the nut (6) that connect the shackle (3)) (P/N 527.30.09.231) to the control cable (1). h Safety the nut (6) with the new cott er pin (7) (P/N 940.17.02.341). i Install the bolt (10), the washer (9 ) and the nut (8) that connect the shackle (3)) (P/N 527.30.09.231) to the lever (2). j Do the elevator control system, adjustment / test (Ref. AMM, 27-30-00, Page Block 501).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 31 of 66 Inspection and, if necessary, Replacement of the Shackles on the Elevator Control Cable Figure 8, Sheet 1 of 2SB 2447 

# A B



# B A SHACKLE P/N 116.35.07.092

SHACKLE P/N 116.35.07.183Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 32 of 66 SERVICE BULLETIN

Inspection and, if necessar y, Replacement of the Shackles on the Elevator Control Cable Figure 8, Sheet 2 of 2SB 2448 

# A B



# B A

RIGGING PIN RIGGING PIN 1

1 1 2 4 3

5 6 7 8 9 10

11

11 12 13 14 17

15 16 17 18
19 20 21
22 23 23

24 15SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 33 of 66 (3) Inspection of the Center Tank Support-Bracket NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. (a) Do the conductivity test to find the material of the center tank support-bracket (Ref. Fig. 9). 1 Remove the dirt and grease from th e areas (where you will do the test) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove the layers of surface protection (including paint) to do the test. 2 Do a check of the conductivity of the reference plates:
a Make sure the conductivity measurement equipment has been calibrated (Ref. Step at beginning of Para. 3.B.). b Put the eddy current probe in position on the reference plates (P/N 513.57.09.149 and P/ N 513.57.09.150).
c Record the value shown on the test equipment. NOTE: Make sure the temperature of the re ference plates (P/N 513.57.09.149 and P/N 513.57.09.150) is approximat ely the same as the center tank support-bracket (P/N 112.35.07.796). 3 Put the eddy current probe in position on the center tank support-bracket (P/N 112.35.07.796). 4 Record the value shown on the test equipment. 5 Compare the value recorded above with the values recorded in Step 3.B.(3)(a)2c and determine if the bracket is manufactured from AA2024-T351 or AA2124-T851. 6 Do Steps 3.B.(3)(a)3 thru 5 again to make sure the result is the same. 7 Write the type of material that the center tank support-bracket (P/N 112.35.07.796) is made from on the Status of Parts Form (Ref. Fig. 19). (b) If you find a bracket made from AA2024-T351, continue this Service Bulletin from Step 3.B.(3)(d). (c) If the brackets are made from AA2124-T8 51, re-identify them (Ref. Para. 2.D.) and continue this Service Bu lletin from Step 3.B.(4).Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 34 of 66 SERVICE BULLETIN

(d) Do an inspection for cracks (Ref. Fig. 9): NOTE: Step 3.B.(3)(d) is only applicable to center tank support-brackets made from AA2024-T351. 1 Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and remove the dirt and grease from the inspection areas of the center tank supp ort-bracket (P/N 112.35.07.796). NOTE: It is not necessary to remove the la yers of surface protection to do the inspection. 2 Obey the manufacturer’s instructions and use a borescope to examine the inspection areas of the center tank support-bracket for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before ne xt flight. The address is: PILATUS AIRCRAFT LTD., Customer Technica l Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@p ilatus-aircraft.com. b Make a report of the inspection results, refer to Step 3.B(3)(e). 4 If you do not find cracks, make a report of the inspection results, refer Step 3.B.(3)(e). (e) Report the Inspection Results 1 Make a copy of the Inspection Report Form (Ref. Fig. 10). 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 35 of 66 3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@pilatus-aircraft.com.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 36 of 66 SERVICE BULLETIN

Center Tank Support-Bracket - Inspection Figure 9SB 2422 

# A

C 

# C B

INSPECTION AREA

TYPICAL CRACK AROUND RIVET HOLE TYPICAL CRACK AROUND RIVET HOLE

INSPECTION AREA 

# A
BSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 37 of 66 Center Tank Support-Bracket - Inspection Form Figure 10SB 2423 SECTION



## A-A HOLE 1 HOLE 2

HOLE 3

HOLE 4

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS: HOLE 1
HOLE 2 HOLE 3 HOLE 4 ADDITIONAL COMMENTS CRACK LENGTH mm
CRACK LENGTH CRACK LENGTH CRACK LENGTH mm

mm
mm SECTION 

## B-B A A B

B

HOLE 1 HOLE 2

HOLE 4 HOLE 3Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 38 of 66 SERVICE BULLETIN

(4) Inspection of the Frame 3 Pick-Up Brackets NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. NOTE: This Step is applicable to the left and right frame 3 pick-up brackets. NOTE: The left and right frame 3 pick-up brackets are referred to as “the brackets”. (a) Do the conductivity test to find the materi al of the left bracket (P/N 112.35.07.009) and the right bracket (P/N 112.35 .07.010) (Ref. SRM, 53-10-00). 1 Remove the dirt and grease from the areas (where you will do the test) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove th e layers of surface protection (including paint) to do the test. 2 Do a check of the conductivi ty of the reference plates:
a Make sure the conductivity measurement equipment has been calibrated (Ref. Step at beginning of Para. 3.B.). b Put the eddy current probe in positi on on the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150).
c Record the value shown on the test equipment. NOTE: Make sure the temperature of the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150) is approximat ely the same as the left bracket (P/N 112.35.07.009) and right bracket (P/N 112.35.07.010). 3 Put the eddy current probe in position on the left bracket (P/N 112.35.07.009). 4 Record the value shown on the test equipment. 5 Compare the value recorded above with the values recorded in Step 3.B.(4)(a)2c and determine if the bracket is manufactured from AA2024-T351 or AA2124-T851. 6 Do Steps 3.B.(4)(a)3 thru 5 again to make sure the result is the same. 7 Write the type of material that the le ft bracket (P/N 112.35.07.009) is made from on the Status of Parts Form (Ref. Fig. 19). (b) Do Step 3.B.(4)(a)1 thru 7 again on the right bracket (P/N 112.35.07.010). (c) If you find a bracket made from AA2024-T351, continue this Service Bulletin from Step 3.B.(4)(e). (d) If a bracket is made from AA2124-T851, re -identify it (Ref. Para. 2.D.) and continue this Service Bulletin from Step 3.B.(5).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 39 of 66 (e) Do an inspection for cracks (Ref. Fig. 11): NOTE: Step 3.B.(4)(e) is only applicable to brackets made from AA2024-T351. NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. 1 Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and remove the dirt and grease from the inspection areas of the left bracket (P/N 112.35.07.009). NOTE: It is not necessary to remove the layers of surface protection to do the inspection. 2 Obey the manufacturer’s in structions and use a borescope to examine the inspection areas of the left bracket for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before next flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@pilatus-aircraft.com. b Make a report of the inspection re sults, refer to Step 3.B.(4)(f). 4 If you do not find cracks, make a report of the inspection results, refer Step 3.B.(4)(f). 5 Do Step 3.B.(4)(e)1 thru 4 again on the right bracket (P/N 112.35.07.010). (f) Report the Inspection Results 1 Make a copy of the Inspection Report Form(s) (Ref. Fig. 12). 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 40 of 66 SERVICE BULLETIN

3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Techni cal Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@p ilatus-aircraft.com.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 41 of 66 Frame 3 Pick-Up Brackets - Inspection (If Necessary) Figure 11SB 2424 

# C

B LH SHOWN RH SIMILAR LH SHOWN RH SIMILAR 

# A

INSPECTION AREA
TYPICAL CRACK AROUND RIVET HOLE 

# A

FRAME 3 FRAME 3



# B B

C INSPECTION AREA

TYPICAL CRACK AROUND RIVET HOLEService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 42 of 66 SERVICE BULLETIN

Frame 3 Pick-Up Brackets - Inspection Form Figure 12, Sheet 1 of 2 LH PICK UP BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm LH PICK UP BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

SECTION



## A-A

SECTION 

## B - BSB 2425 LH SHOWN 

## B

B A

ASERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 43 of 66 Frame 3 Pick-Up Brackets - Inspection Form Figure 12, Sheet 2 of 2 RH PICK UP BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm RH PICK UP BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm

RH SHOWN 

## B SECTION



## A-A

B A

A SECTION 

## B - BSB 2426Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 44 of 66 SERVICE BULLETIN

(5) Inspection of the Rudder-Pedal Outboard-Bearings NOTE: All front and rear, left and right rudder-pedal outboard-bearings (P/N 112.35.07.251) are made from AA2024-351. NOTE: The front and rear, left and right rudder-pedal outboard-bearings are referred to as “the outboard bearings”. (a) Do an inspection for cracks of the outboard bearings (Ref. Fig. 13): NOTE: The outboard bearings (P/N 112.35.07.251) are attached to the support plate (P/N 112.35.07.252) (Ref. SRM, 53-10-00). 1 Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and remove the dirt and grease from the inspection areas of the outboard bearings (P/N 112.35.07.251). NOTE: It is not necessary to remove the la yers of surface protection to do the inspection. 2 Obey the manufacturer’s instructions and use a borescope to examine the inspection areas of the outboard bearings (P/N P/N 112.35.07.252) for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before ne xt flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@p ilatus-aircraft.com. b Make a report of the inspection results, refer to Step 3.B.(5)(c). (b) If you do not find cracks, make a repor t of the inspection results, refer Step 3.B.(5)(c). (c) Report the Inspection Results 1 Make a copy of the Inspection Report Form(s) (Ref. Fig. 14).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 45 of 66 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details. 3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@pilatus-aircraft.com.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 46 of 66 SERVICE BULLETIN

Front and Rear Rudder-Pedal Outboard-B earings (P/N 112.35.07.251) - Inspection Figure 13SB 2436 

# A FRAME 1

FWD LH SHOWN

TYPICAL CRACK AROUND RIVET HOLE INSPECTION AREA 

# A

A A
ASERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 47 of 66 Front and Rear Rudder-Pedal Outboard-Bea rings (P/N 112.35.07.251) - Inspection Form Figure 14, Sheet 1 of 2SB 2437 FWD RH SUPPORT BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm FWD LH SUPPORT BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mmService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 48 of 66 SERVICE BULLETIN

Front and Rear Rudder-Pedal Outboard-Beari ngs (P/N 112.35.07.251) - Inspection Form Figure 14, Sheet 2 of 2SB 2438 REAR RH SUPPORT BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm REAR LH SUPPORT BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mmSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 49 of 66 (6) Inspection of the Rudder Lower-Hinge Bearing-Bracket NOTE: The rudder lower-hinge bearing-bracket (P/N 555.30.09.039) is part of the rudder lower-hinge bearing-bracket assembly (P/N 555.30.09.040). NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. (a) Do the conductivity test to find the material of the rudder lower-hinge bearingbracket (Ref. IPC, 55-30-01). 1 Remove the dirt and grease from th e areas (where you will do the test) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove the layers of surface protection (including paint) to do the test. 2 Do a check of the conductivity of the reference plates:
a Make sure the conductivity measurement equipment has been calibrated (Ref. Step at beginning of Para. 3.B.). b Put the eddy current probe in position on the reference plates (P/N 513.57.09.149 and P/ N 513.57.09.150).
c Record the value shown on the test equipment. NOTE: Make sure the temperature of the re ference plates (P/N 513.57.09.149 and P/N 513.57.09.150) is approximat ely the same as the rudder lowerhinge bearing-bracket (P/N 555.30.09.039). 3 Put the eddy current probe in position on the rudder lower-hinge bearingbracket. 4 Record the value shown on the test equipment. 5 Compare the value recorded above with the values recorded in Step 3.B.(6)(a)2c and determine if the rudder lower-hinge bearing-bracket is manufactured from AA2024-T351 or AA2124-T851. 6 Do Steps 3.B.(6)(a)3 thru 5 again to make sure the result is the same. 7 Write the type of material that the rudder lower-hinge bearing-bracket is made from on the Status of Parts Form (Ref. Fig. 19). (b) If you find a rudder lower-hinge bearing-bracket made from AA2024-T351, continue this Service Bulletin from Step 3.B.(6)(d).(c) If you find a rudder lower-hinge bearing-bracket made from AA2124-T851, reidentify it (Ref. Para. 2.D.) and continue this Service Bulleti n from Step 3.B.(7).Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 50 of 66 SERVICE BULLETIN

(d) Do an eddy-current Non-Destructive-In spection (NDI) for cracks (Ref. Fig. 15): NOTE: Step 3.B.(6)(d) is only applicable to rudder lower-hinge bearing-brackets made from AA2024-T351. NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. 1 Remove the rudder assembly (Ref. AMM, 27-20-01, Page Block 401). CAUTION: DO NOT PUT LOADS ON THE RUDDER LOWER-HINGE-BRACKET (4) WHEN THE BOLTS (1) ARE REMOVED. THIS COULD CAUSE THE RUDDER LOWER-HINGE-BRACKET (4) TO MOVE SLIGHTLY. 2 Remove the nuts (3), the washers (2) and the bolts (1) from the four attachment bolt holes of the rudder lower-hinge-bracket (4). 3 Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and remove the dirt and grease from the inspection areas of the rudder lower-hinge bearing-bracket. NOTE: It is not necessary to remove the la yers of surface protection to do the inspection. 4 Obey the manufacturer’s instructions and calibrate the eddy-current NDI equipment. 5 Obey the manufacturer’s instructions and move the probe of the eddy-current NDI equipment over the inspection areas shown in Fig. 15. 6 Apply a layer of the corrosion preventative (Material No. P04-039) to the shank of the bolts (1). 7 Install the bolts (1), the washers (2) and nuts (3) in the four attachment bolt holes of the rudder lower-hinge-bracket (4). 8 If you find cracks:
a You must contact Pilatus Customer Support before ne xt flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@p ilatus-aircraft.com. b Make a report of the inspection results, refer to Step 3.B.(6)(e). 9 If you do not find cracks, make a report of the inspection results, refer to Step 3.B.(6)(e). 10 Install the rudder assembly (Ref. AMM, 27-20-01, Page Block 401).SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 51 of 66 (e) Reporting of Inspection Results (Ref. Fig. 16) 1 Make a copy of the Inspection Report Form (Ref. Fig. 16). 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there no crack indications, the In spection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details. 3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Technical Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@pilatus-aircraft.com.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 52 of 66 SERVICE BULLETIN

Lower Rudder Bracket - Inspection (If Necessary) Figure 15SB 2446 

# C



# C B A

C C C

INSPECTION AREA

TYPICAL HOLE 1

HOLE 2 HOLE 3

HOLE 4 

# B A

1 2 3

4SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 53 of 66 Lower Rudder Bracket - Inspection Form Figure 16SB 2258 

## A

SECTION



## A-A HOLE 1

HOLE 2

HOLE 3

HOLE 4

HOLE 1

HOLE 2 HOLE 3

HOLE 4

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS: HOLE 1
HOLE 2 HOLE 3 HOLE 4 ADDITIONAL COMMENTS CRACK LENGTH mm
CRACK LENGTH CRACK LENGTH CRACK LENGTH mm

mm
mm 

## A B

B

SECTION



## B-BService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 54 of 66 SERVICE BULLETIN

(7) Inspection of the Left and Right Flap Bearing Support-Brackets NOTE: Only personnel that are qualified and authorized by their designated Airworthiness Authorities are allowed to do this test. (a) Do the conductivity test to find the mate rial of the left flap bearing support-bracket (P/N 111.34.07.329) and the right flap bearing support-bracket (P/N 111.34.07.330) (Ref. Fig. 17). 1 Remove the dirt and grease from the areas (where you will do the test) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove th e layers of surface protection (including paint) to do the test. 2 Do a check of the conductivi ty of the reference plates:
a Make sure the conductivity measurement equipment has been calibrated (Ref. Step at beginning of Para. 3.B.). b Put the eddy current probe in positi on on the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150).
c Record the value shown on the test equipment. NOTE: Make sure the temperature of the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150) is approximatel y the same as the left flap bearingsupport-bracket (P/N 111.34.07.329) and the right flap bearing supportbracket (P/N 111.34.07.330). 3 Put the eddy current probe in position on the left flap bearing support-bracket. 4 Record the value shown on the test equipment. 5 Compare the value recorded above with the values recorded in 3.B.(5)(a)2c and determine if the flap bearing support-bracket is manufactured from AA2024-T351 or AA2124-T851. 6 Do Steps 3.B.(5)(a)3 thru 5 again to make sure the result is the same. 7 Write the type of material that the left flap bearing support-bracket is made from on the Status of Parts Form (Ref. Fig. 19). 8 Do Step 3.B.(5)(a)1 thru 7 again on the right flap bearing support-bracket. (b) If you find a flap bearing support-bracket made from AA2024-T351, continue this Service Bulletin from Step 3.B.(7)(d). (c) If you find a flap bearing support-bracket is made from AA2124-T851, re-identify it (Ref. Para. 2.D.) and continue this Service Bulletin from Step 3.C.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 55 of 66 (d) Do an inspection for cracks (Ref. Fig. 17): NOTE: Step 3.B.(7)(d) is only applicable to flap bearing support-brackets made from AA2024-T351. 1 Use the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010) and remove the dirt and grease from the inspection areas of the left flap bearing support-bracket. NOTE: It is not necessary to remove the layers of surface protection to do the inspection. 2 Obey the manufacturer’s in structions and use a borescope to examine the inspection areas of the left flap bearing sup port-bracket for cracks. 3 If you find cracks:
a You must contact Pilatus Customer Support before next flight. The address is: PILATUS AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992 6371 Stans, Switzerland Fax: + 41 (0) 41 619 67 73 Email: Techsupport@pilatus-aircraft.com. b Make a report of the inspection re sults, refer to Step 3.B.(7)(e). 4 If you do not find cracks, make a report of the inspection results, refer Step 3.B.(7)(e). 5 Do Step 3.B.(7)(d)1 thru 4 again on the right flap bearing support-bracket. (e) Report the Inspection Results 1 Make a copy of the Inspection Report Form(s) (Ref. Fig. 18). 2 Complete the Inspection Report Form: • Give the date of the inspection. • Give the aircraft details. • Show the location(s) and dimensions of the crack(s) found (if applicable). • Add any necessary comments. NOTE: If there are no crack indications, the Inspection Report Form is used to tell Pilatus Aircraft Ltd. the aircraft details.Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 56 of 66 SERVICE BULLETIN

3 Send or fax the completed form(s) to: Pilatus Aircraft Ltd. Customer Techni cal Support (MCC) P.O.Box 992 6371 Stans, Switzerland Fax No. + 41 (0) 41 619 67 73. Email: Techsupport@p ilatus-aircraft.com.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 57 of 66 Left and Right Flap Bearing Support-Bracket - Inspection (If Necessary) Figure 17SB 2427 

# A A A

LH SHOWN RH SIMILAR

TYPICAL CRACK AROUND RIVET HOLE INSPECTION AREAService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 58 of 66 SERVICE BULLETIN

Left and Right Flap Bearing Support-Bracket - Inspection Form Figure 18SB 2266 RIGHT FLAP SUPPORT BRACKET DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm LEFT FLAP SUPPORT BRACKET

WING S/N OUTBOARD SIDE

OUTBOARD SIDE DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:
ADDITIONAL COMMENTS CRACK 1 LENGTH mm CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH mm
mm mm WING S/NSERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 59 of 66 INTENTIONALLY BLANKService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 60 of 66 SERVICE BULLETIN

Status of Parts Form Figure 19Aircraft Tail No.Line No.ComponentPart NumberMaterial, after accomplishment ofthis Service BulletinPart Number, after accomplishment ofthis Service Bulletin1LEFT AND RIGHT AILERON OUTERCONTROL-ROD116.35.07.2722ELEVATOR FORWARD CONTROL-ROD116.35.07.2703ELEVATOR CENTER CONTROL-ROD116.35.07.2714ELEVATOR REAR CONTROL-ROD116.35.07.2695SHACKLE116.35.07.1836SHACKLE116.35.07.0927TANK BRACKET112.35.07.7968FRAME 3 PICK-UP BRACKET, LH112.35.07.0099FRAME 3 PICK-UP BRACKET, RH112.35.07.01010FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGS112.35.07.25111RUDDER LOWER-HINGE BEARINGBRACKETorRUDDER LOWER-HINGE BEARINGBRACKET ASSY555.30.09.039or555.30.09.04012FLAP BEARING SUPPORT BRACKET,LH111.34.07.32913FLAP BEARING SUPPORT BRACKET,RH111.34.07.330SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 61 of 66 INTENTIONALLY BLANKService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 62 of 66 SERVICE BULLETIN

C. Close-Up (1) Remove all the equipment, tools and materials from the work area. Make sure that the work area is clean. (2) Install the left and right floor panels from the rear cockpit that you removed to get access to the left and right frame 3 pick-up brackets (Ref. IPC, 25-10-01 for more information). (3) Install the left and right side panels and linings from the front and rear cockpits that you removed to get access to the left and right rudder pedals outboard support-bearings (Ref. AMM, 25-10-05, Page Block 401). (4) Install the left and right side panels and linings from the front cockpit that you removed to get access to the left and right frame 3 pi ck-up brackets (Ref. AMM, 25-10-05, Page Block 401). (5) Connect the battery mating connector. (6) If necessary, safety the battery mating connector with the lockwire (Material No. P02-001). (7) Connect the battery hot plug P202. (8) In the front cockpit, remove the safety clip and close the circuit breaker: BAT SWITCH (BATTERY BUS CB panel). (9) Install the front and rear seats (Ref. AMM, 25-10-00, Page Block 201). (10) Remove the ballast from the tail mooring point (Ref. AMM, 07-10-00, Page Block 201). (11) Remove the tail jack and the adapter (Ref. AMM, 07-10-00, Page Block 201). (12) Engage the flight control lock. (13) Remove the warning signs (DO NOT OPER ATE THE FLIGHT CONTROLS) from the front and rear cockpits. NOTE: For the location of the access items, refer to AMM, 12-00-00, Page Block 1. (14) Close the access panel F15. (15) Install the access panels F5, F17, F18, LB2, RB2, LT8 and RT8. D. Documentation (1) Make an entry in the Aircraft Logbook that this Service Bulletin has been incorporated. (2) Use the Service Bulletin Evaluation Sheet an d report your results and the serial number(s) of the aircraft to Pilatus. (3) Put the Status of Parts Form (Ref. Fig. 19) in the Aircraft Logbook. NOTE: If any parts are made from AA2024-T351 but have no cracks, you will need to do repetitive mandatory inspections (Ref . AMM, Chapter 05). You will need this Form (Ref. Fig. 19) to tell you wh ich parts require the inspection.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 63 of 66 4. Accomplishment Instructions - Equipment Held as Spare or in Stock NOTE: This procedure is applicable to all of the part s listed below, held as spare or in stock:

NOTE: All these parts are made from AA2024-T351:

Send these parts to Pilatus Customer Suppor t. Pilatus will send a replacement part made from AA2124-T851. PART NUMBER DESCRIPTION 116.35.07.272 LEFT AND RIGHT AILERON OUTER CONTROL-ROD (SEE NOTE) 116.35.07.270 ELEVATOR FORWARD CONTROL-ROD (SEE NOTE) 116.35.07.271 ELEVATOR CENTER CONTROL-ROD (SEE NOTE) 116.35.07.269 ELEVATOR REAR CONTROL-ROD (SEE NOTE) 116.35.07.183 SHACKLE (SEE NOTE) 116.35.07.092 SHACKLE 112.35.07.796 CENTER TANK SUPPORT-BRACKET 112.35.07.009 FRAME 3 PICK-UP BRACKET, LH 112.35.07.010 FRAME 3 PICK-UP BRACKET, RH 112.35.07.251 FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGS (SEE NOTE) 555.30.09.039 or 555.30.09.040 RUDDER LOWER-HINGE BEARING-BRACKET or RUDDER LOWER-HINGE BEARING-BRACKET ASSY 111.34.07.329 FLAP BEARING SUPPORT BRACKET, LH 111.34.07.330 FLAP BEARING SUPPORT BRACKET, RH

116.35.07.272 LEFT AND RIGHT AILERON OUTER CONTROL-ROD 116.35.07.270 ELEVATOR FORWARD CONTROL-ROD 116.35.07.271 ELEVATOR CENTER CONTROL-ROD 116.35.07.269 ELEVATOR REAR CONTROL-ROD 116.35.07.183 SHACKLE 112.35.07.251 FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGSService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 64 of 66 SERVICE BULLETIN

A. Preparation (1) Obey the manufacturer’s operating inst ructions and calibrate the conductivity measurement equipment. (2) Put the eddy current probe in position on the reference plates (P/N 513.57.09.149 and P/N 513.57.09.150). (3) Record the value shown on the test equipment. (4) Make a note of the temperature of the re ference plates (P/N 513.57.09.149 and P/N 513.57.09.150). NOTE: The temperature of the reference pl ates (P/N 513.57.09.149 and P/N 513.57.09.150) must be approximately th e same as the part to be checked. B. Do the conductivity test to find the material WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE MANUFACTURER‘S HEALTH AND SAFETY INSTRUCTIONS. NOTE: Only personnel that are qua lified and authorized by their delegated Airworthiness Authorities are allow ed to do this test. (1) If necessary, remove the grease from the areas of the part to be tested with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-010). NOTE: It is not necessary to remove the layers of surface prot ection (including paint) to do the test. (2) Put the eddy current probe in position on the part to be tested. (3) Record the value shown on the test equipment. (4) Compare the value recorded above with the values recorded in Section 4.A.(3) and determine if the part is made from AA2024-T351 or AA2124-T851. (5) Do Steps 4.B(1) thru (4) again to make sure the result is the same. (6) If the part is made from AA2024-T351, send it to Pilatus Customer Support. Pilatus will send a replacement part made from AA2124-T851. (7) If the part is made from AA2124-T851: • Re-identify the part (Ref. Para. 2.D.) with a permanent marker pen (or equivalent) • Return the part to stores. C. Documentation (1) Make an entry on the serviceable label (attache d to the part) that this Service Bulletin has been accomplished. (2) Use the Service Bulletin Evaluation Shee t and report your results to Pilatus.SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 65 of 66



## SERVICE BULLETIN EVALUATION SHEET FOR SB No. 51-001 Title Aircraft Structure - General Do a Check of the Material Specificati on Used During Manufacture and, If Necessary, Do a Check for Cracks or Replace the Part Customer Service Center 

### EMBODIMENT REPORTING This SB has been embodied: On the entire fleet Only partially Provide embodiment details per aircraft (use additional copies of this table, if necessary) 

### MSN Flying Hours MSN Flying Hours

Additional embodiment comments/findings

EDITORIAL COMMENTS (procedure, kit quality, su ggested improvements, etc.)

Name Signature Date Please complete and forward this form to: Pilatus Aircraft LTD, Customer Technical Support (MCC), P.O. BOX 992, 6371 Stans, Switzerland Fax: +41 (0)41 619 6773 Email: Techsupport@ pilatus-aircraft.com 

### SERVICE BULLETIN EVALUATION SHEETService Bulletin No: 51-001 Date: Jun 20/14 Rev. No. Date: Page 66 of 66 SERVICE BULLETIN

INTENTIONALLY BLANK