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 RIGHT AILERON OUTER CONTROL-ROD

2 2 116.35.07.270 ELEVATOR 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-HINGE 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, RH
Service 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 possibility that some critical parts can crack due to stress 

corrosion.

(2) Cause

The investigation found that initially the material of the parts was AA2024-T351 which is 

susceptible to Stress Corrosion Cracking (SCC). 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 material 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 cracks 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 inspections will be added to Chapter 5 of the 

Aircraft Maintenance Manual (AMM). The inspections will give 

instructions on how to examine the parts for cracks. The inspections 

will only be applicable to parts 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 1

Item Para Description 

Installed Item P/N before accomplishment of SB 

AA2024-T351 AA2124-T851 

1 1 LEFT AND RIGHT AILERON OUTER CONTROL-ROD 116.35.07.272 N/A 2 2 ELEVATOR FORWARD CONTROL-ROD 116.35.07.270 N/A 3 2 ELEVATOR CENTER CONTROL-ROD 116.35.07.271 / .345 N/A 4 2 ELEVATOR REAR CONTROL-ROD 116.35.07.269 N/A 5 2 SHACKLE 116.35.07.183 N/A 6 2 SHACKLE 116.35.07.092 116.35.07.092 7 3 TANK BRACKET 112.35.07.796 112.35.07.796 8 4 FRAME 3 PICK-UP BRACKET, LH 112.35.07.009 112.35.07.009 9 4 FRAME 3 PICK-UP BRACKET, RH 112.35.07.010 112.35.07.010 

10 5 FRONT AND REAR RUDDER-PEDALS OUTBOARD-BEARINGS 112.35.07.251 N/A 11 6 

RUDDER LOWER-HINGE BEARING-BRACKET orRUDDER LOWER-HINGE BEARING-BRACKET ASSY 

555.30.09.039 

or 

555.30.09.040 

555.30.09.039 

or 

555.30.09.040 

12 7 FLAP BEARING SUPPORT BRACKET, LH 111.34.07.329 111.34.07.329 13 7 FLAP BEARING SUPPORT BRACKET, RH 111.34.07.330 111.34.07.330 
Service 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, Replacement of the Elevator Center Control-Rod.

(c) Inspection of the Elevator Rear Control-Rod.

(d) Replacement of the Forward Shackle on the Elevator Control Cable.

(e) Inspection and, if Necessary, Replacement 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 after the effective date of this Service Bulletin.

F. Approval

The technical content of this Service 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 that 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 parts 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 Shackle (P/N 116.35.07.092) 2.0

Close up 5.0

TOTAL MAN-HOURS 24.0 2.0 2.0
Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 6 of 66

SERVICE BULLETIN

2. Material Information

Operators who require further information on Price and Availability 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 which 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 PREVENTATIVE A/R Or equivalent
SERVICE 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 CONTROL-ROD 116.35.07.270 N/A

ELEVATOR CENTER CONTROL-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 111.34.07.330 557.21.09.118
Service 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 reference 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 accomplishment 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 1
SERVICE 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 front 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 cockpit 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 turn 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 Control-Rod - Inspection

Figure 1

SB 2440

A

LH SHOWN

RH SIMILAR

C

D

F E

J

1

B

G

H

K

A

A

B

B

LH SHOWN

RH SIMILAR

2

3

4

5

6

6
Service 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 2

SB 2307

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

F

E

D

C
SERVICE 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 2

SB 2308

H

G

J

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

K
Service 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 instructions 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 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 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 3

SB 2450

A

C

D

B

1

INSERT BOROSCOPE

IN HERE

INSERT BOROSCOPE

IN HERE
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 19 of 66

 Elevator Forward Control-Rod - Inspection Form

Figure 4

SB 2451

D

C

A

B

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm
Service 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 the 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 elevator 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 installed inside the tube (Ref. Fig. 

5, Sheet 1), the part number of the elevator center control-rod is 

116.35.07.271. Continue this Service Bulletin from Para. 3.B.(2)(b)2.

c If the tube is installed inside the clevis 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 Service Bulletin from Para. 3.B.(2)(b)3.

2 Replace the elevator center control-rod, 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 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

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 21 of 66

 Identification of the Elevator Center Control-Rod

Figure 5, Sheet 1 of 2

SB 2445

B

A A

B

C

D

C

D
Service 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 2

SB 2444

B

B

A A

C

D

C

D
SERVICE 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 rear 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 results, 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@pilatus-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 6

SB 2443

B

A

A

G

H

J

K

7

6

3

2

1

5

C

D

E

F

B

1

4
Service 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 2

SB 2297

E

D

C

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

F
SERVICE 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 2

SB 2298

H

G

J

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

K
Service 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 116.35.07.093) (Ref. IPC, 27-30-01).

NOTE: All shackles (P/N 116.35.07.183) are made from AA2024-351 and are 

therefore subject to stress corrosion. These shackles will therefore be 

replaced.

NOTE: The shackles (P/N 116.35.07.092) can be made from AA2024-351 or 

AA2124-T851. These 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 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 the layers of surface protection 

(including paint) to do the test.

c Do a check of the conductivity of the reference plates:

• Make sure the conductivity measurement 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 and 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 513.57.09.150) is approximately the 

same as the shackle (P/N 116.35.07.092).

d Put the eddy current probe in position 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 the 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 continue this Service Bulletin from Step 

3.B.(2)(d)4.

4 Replace the shackle (P/N 116.35.07.183) (Ref. Fig. 8):

a Make sure that the elevator is in the neutral position.

b Install rigging pins (P/Ns 110.85.07.050) at the front and rear levers (22 

and 2).

c At the front lever (22), 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 (14) (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 (MATERIAL 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 cotter 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 2

SB 2447

A

B

B

A SHACKLE

P/N 116.35.07.092

SHACKLE

P/N 116.35.07.183
Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 32 of 66

SERVICE BULLETIN

 Inspection and, if necessary, Replacement of the Shackles on the Elevator Control Cable

Figure 8, Sheet 2 of 2

SB 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

17 14

15

16

17

18

19

20 21

22

23

23

24

15
SERVICE 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 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 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 reference plates (P/N 513.57.09.149 

and P/N 513.57.09.150) is approximately 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-T851, re-identify them (Ref. Para. 2.D.) and 

continue this Service Bulletin 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 support-bracket (P/N 112.35.07.796).

NOTE: It is not necessary to remove the layers 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 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 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 9

SB 2422

A

C

C

B

INSPECTION AREA

TYPICAL CRACK

AROUND RIVET HOLE

TYPICAL CRACK

AROUND RIVET HOLE

INSPECTION AREA

A

B
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 37 of 66

 Center Tank Support-Bracket - Inspection Form

Figure 10

SB 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 3
Service 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 material 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 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 reference plates (P/N 513.57.09.149 

and P/N 513.57.09.150) is approximately 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 left 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 instructions 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 results, 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 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

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 11

SB 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 HOLE
Service 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:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

LH PICK UP

BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

SECTION

A-A

SECTION

B-B

SB 2425

LH SHOWN

B

B

A

A
SERVICE 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:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

RH PICK UP

BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

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-B

SB 2426
Service 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 layers 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 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 results, refer to Step 3.B.(5)(c).

(b) If you do not find cracks, make a report 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-Bearings (P/N 112.35.07.251) - Inspection

Figure 13

SB 2436

A

FRAME 1

FWD LH SHOWN

TYPICAL CRACK AROUND

RIVET HOLE

INSPECTION AREA

A

A

A

A
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 47 of 66

 Front and Rear Rudder-Pedal Outboard-Bearings (P/N 112.35.07.251) - Inspection Form

Figure 14, Sheet 1 of 2

SB 2437

FWD RH SUPPORT BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

FWD LH SUPPORT BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm
Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 48 of 66

SERVICE BULLETIN

 Front and Rear Rudder-Pedal Outboard-Bearings (P/N 112.35.07.251) - Inspection Form

Figure 14, Sheet 2 of 2

SB 2438

REAR RH SUPPORT BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

REAR LH SUPPORT BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm
SERVICE 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 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 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 reference plates (P/N 513.57.09.149 

and P/N 513.57.09.150) is approximately 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 Bulletin 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-Inspection (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 layers 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 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 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 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 52 of 66

SERVICE BULLETIN

 Lower Rudder Bracket - Inspection (If Necessary)

Figure 15

SB 2446

C

C

B

A

C

C

C

INSPECTION AREA

TYPICAL

HOLE 1

HOLE 2

HOLE 3

HOLE 4

B

A

1 2

3

4
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 53 of 66

 Lower Rudder Bracket - Inspection Form

Figure 16

SB 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-B
Service 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 material 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 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 reference plates (P/N 513.57.09.149 

and P/N 513.57.09.150) is approximately the same as the left flap bearing 

support-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 instructions and use a borescope to examine the 

inspection areas of the left flap bearing support-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 results, 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 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

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 17

SB 2427

A

A

A

LH SHOWN

RH SIMILAR

TYPICAL CRACK AROUND

RIVET HOLE

INSPECTION AREA
Service 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 18

SB 2266

RIGHT FLAP SUPPORT BRACKET

DATE: AIRCRAFT MSN: FLYING HOURS: LANDINGS:

CRACK 1 ADDITIONAL COMMENTS

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:

CRACK 1 ADDITIONAL COMMENTS

LENGTH mm

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

LENGTH

mm

mm

mm

WING S/N
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 59 of 66

INTENTIONALLY BLANK
Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 60 of 66

SERVICE BULLETIN

 Status of Parts Form

Figure 19

 Aircraft Tail No. 

Line No. Component Part Number Material, after accomplishment of this Service Bulletin Part Number, after accomplishment of this Service Bulletin

1 LEFT AND RIGHT AILERON OUTER CONTROL-ROD 116.35.07.272 2 ELEVATOR FORWARD CONTROL- ROD 116.35.07.270 3 ELEVATOR CENTER CONTROL-ROD 116.35.07.271 4 ELEVATOR REAR CONTROL-ROD 116.35.07.269 5 SHACKLE 116.35.07.183 6 SHACKLE 116.35.07.092 7 TANK BRACKET 112.35.07.796 8 FRAME 3 PICK-UP BRACKET, LH 112.35.07.009 9 FRAME 3 PICK-UP BRACKET, RH 112.35.07.010 

10 FRONT AND REAR RUDDER- PEDALS OUTBOARD-BEARINGS 112.35.07.251 11

RUDDER LOWER-HINGE BEARINGBRACKET orRUDDER LOWER-HINGE BEARINGBRACKET ASSY 

555.30.09.039 

or 

555.30.09.040 

12 FLAP BEARING SUPPORT BRACKET, LH 111.34.07.329 13 FLAP BEARING SUPPORT BRACKET, RH 111.34.07.330 
SERVICE BULLETIN

Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 61 of 66

INTENTIONALLY BLANK
Service 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 pick-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 OPERATE 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 and 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 which 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 parts listed below, held as spare or in stock: 

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

Send these parts to Pilatus Customer Support. 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-BEARINGS
Service 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 instructions 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 reference plates (P/N 513.57.09.149 and P/N 

513.57.09.150).

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.

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 qualified and authorized by their delegated Airworthiness 

Authorities are allowed 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 protection (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 (attached to the part) that this Service Bulletin has 

been accomplished.

(2) Use the Service Bulletin Evaluation Sheet 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 Specification 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, suggested 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 SHEET
Service Bulletin No: 51-001 Date: Jun 20/14

Rev. No. Date: Page 66 of 66

SERVICE BULLETIN

INTENTIONALLY BLANK