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

Rev. No. Date: Page 1 of 10

Service Bulletin No: 27-022 Ref No: 334

Modification No: - ATA Chapter: 27

SERVICE BULLETIN

PILATUS AIRCRAFT LTD, STANS, SWITZERLAND

FLIGHT CONTROLS - AILERON CONTROL SYSTEM

REPLACEMENT OF THE UNIVERSAL JOINTS IN THE FLIGHT CONTROLS

1. Planning Information

A. Effectivity

PC-12/47E aircraft MSN 1447 thru 1450, 1461, 1462, 1466 thru 1514, 1516 thru 1520 and 1523. 

PC-12 Series aircraft where the universal joints (P/N 944.61.73.012 or 527.10.12.195), 

purchased from March 2014 to, and including, February 2015 were installed as replacement 

parts.

PC-12 Series aircraft modified with the inspection kit (P/N 500.50.12.314) for the aileron control 

system, purchased from March 2014 to, and including, February 2015. 

Universal joints (P/N 944.61.73.012 or 527.10.12.195) held as spares purchased from March 

2014 to, and including, February 2015. 

Inspection kits (P/N 500.50.12.314) held as spares purchased from March 2014 to, and 

including, February 2015.

NOTE: The inspection kit (P/N 500.50.12.314) is used for:

• SB 04-009 (Airworthiness Limitations - Life Extension to 25,000 flying hours or 

30,000 landings)

• SSID Task 27-10/394 (Aileron Control System – Examine). 

This task is performed initially at 32,500 flying hours or 42,000 landings, whichever 

comes first, and every 12,500 flying hours or 15,000 landings or 6 years whichever 

comes first. 

B. Concurrent Requirements

None.

C. Reason

A universal joint installed between the control tube assembly and the control column 

malfunctioned.

D. Solution

Replace the universal joints, as defined in 1. A., with new parts ordered from Pilatus.
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 2 of 10

SERVICE BULLETIN

E. Description

This Service Bulletin gives the data and instructions necessary to replace the universal joints 

(P/N 527.10.12.195):

• Part A is for on-aircraft

• Part B is for parts held as spare.

F. Compliance

Mandatory.

For aircraft with less than 200 flights since new or less than 200 flights since the installation of a

spare part as defined in 1. A.:

• No more than 10 flights or 

• 3 months from the issue date of this Service Bulletin.

For aircraft with more than 200 flights since new or more than 200 flights since the installation of 

a spare part as defined in 1. A.:

• No later than 1 year after the issue date of this Service Bulletin. This Service Bulletin can 

be performed at annual inspection.

G. Approval

The technical content of this document is approved under the authority of 

DOA No. EASA. 21J. 357.

PILATUS advises operators/owners to check with their designated Airworthiness Authority for 

any changes, local regulations or sanctions that may affect the embodiment of this Service 

Bulletin.

H. Copyright

© Pilatus Aircraft Ltd. This document contains 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.

I. Manpower

J. Weight and Balance

No change.

Task Man-hours Man-hours

At Annual Inspection

Preparation 1.0 0.0

Modification 1.0 1.0

Close-Up 1.0 0.0

TOTAL MAN-HOURS 3.0 1.0
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 3 of 10

SERVICE BULLETIN

K. Electrical load Data

No change.

L. Software

No change.

M. References

Aircraft Maintenance Manual (AMM) 

N. Publications Affected

No change.

O. Interchangeability of Parts

Not interchangeable.

12-B-07-10-00-00A-901A-A 12-B-20-20-01-00A-040A-A 12-B-20-31-00-00A-070A-A

12-B-24-00-00-00A-901A-A 12-B-25-10-01-00A-920A-A 12-B-27-10-00-00A-903A-A

12-B-27-30-00-00A-903A-A
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 4 of 10

SERVICE BULLETIN

2. Material Information

A. Material - Price and Availability

If you require more information about this modification, please contact us as follows:

Operators are requested to advise Pilatus Aircraft Ltd, of the Manufacturer’s Serial Number 

(MSN) and the flying hours of aircraft which are affected by this Service Bulletin.

B. Warranty

Credit will be issued for parts and labour for all affected aircraft on approval of a warranty claim, 

provided the work is accomplished by an authorised Service Center within 12 months of the 

issue date of this Service Bulletin. 

C. Material Necessary for one Aircraft

NOTE: Part Numbers given in this Service Bulletin are correct at the time of approval. Pilatus 

Aircraft Ltd. reserves the right to change the part numbers as necessary. Operators are 

requested to check the IPC for delivered parts which differ from those listed in the 

Service Bulletin.

PILATUS AIRCRAFT LTD

CUSTOMER SUPPORT MANAGER

CH-6371 STANS

SWITZERLAND

General Aviation:

Tel: + 41 41 619 3333

Fax: + 41 41 619 7311

eMail: SupportPC12@pilatus-aircraft.com

PILATUS BUSINESS AIRCRAFT LTD

PRODUCT SUPPORT DEPARTMENT

11755 AIRPORT WAY

BROOMFIELD, CO 80021

UNITED STATES OF AMERICA

Tel: +1 303 465 9099

Fax: +1 303 465 6040

eMail: supportPC12@PilBal.com

PILATUS AUSTRALIA PTY LTD

17 JAMES SCHOFIELD DRIVE

ADELAIDE AIRPORT SA 5950

AUSTRALIA

Tel: +61 8 8238 1600

Fax: +61 8 8234 4499

Free Call: +61 1800 PILATUS (745 2887)

eMail: supportpc12@pilatus.com.au
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 5 of 10

SERVICE BULLETIN

(1) Parts to be ordered from Pilatus

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

E. Tooling - Cost and Availability

None.

New Part No. Description Old Part No. Qty Disp. 

Code

Fig Item

527.10.12.195 Universal joint

(New parts are marked 

with a placard)

527.10.12.195 2 R 1 1,16

932.19.60.814 BOLT, HEX 932.19.60.814 2 D 1 6, 12

938.77.11.115 WASHER, FLAT 938.77.11.115 2 D 1 10, 14

938.07.68.505 NUT, HEX 938.07.68.505 2 D 1 11, 15

932.35.14.016 BOLT, HEX 932.35.14.016 1 D 1 20

932.35.14.012 BOLT, HEX 932.35.14.012 1 D 1 2

938.77.11.112 WASHER, FLAT 938.77.11.112 2 D 1 3, 17

938.07.68.304 NUT, HEX 938.07.68.304 2 D 1 4, 18

Disposition Codes: D - Discard / N - New / R - Return to Pilatus

Material No. Description Qty Remarks

P04-039 Corrosion preventive AR
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 6 of 10

SERVICE BULLETIN

3. Part A: Accomplishment Instructions - On Aircraft

A. Preparation

(1) Raise the aircraft on jacks, refer to AMM 12-B-07-10-00-00A-901A-A.

(2) De-energize the aircraft electrical system, refer to AMM 12-B-24-00-00-00A-901A-A.

(3) Open and install a safety clip (Circuit breaker hold open) (P/N 110.88.07.065) on the circuit 

breaker:

A/P SERVO (AVIONICS BUS).

(4) Put a warning sign in the cockpit: DO NOT MOVE FLYING CONTROLS.

(5) Remove the crew seats, refer to AMM 12-B-25-10-01-00A-920A-A.

B. Removal - Pilot Side

Refer to Figure 1.

CAUTION: BE CAREFUL NOT TO DAMAGE THE ADJACENT WIRING LOOM.

(1) Remove the nut (22) and the bolt (23).

(2) Remove and discard the nut (15), washer (14) and the bolt (12).

(3) Remove and discard the nut (18), washer (17) and the bolt (20).

(4) Move back the control wheel and remove the universal joint (16) (P/N 527.10.12.195) from 

the control tube assembly (13) and the control column (21).

(5) Remove the stop block (19) from the universal joint.

C. Installation - Pilot Side

Refer to Figure 1.

(1) Apply corrosion preventive (Material No. P04-039) to the internal surface of the stop block 

(19).

(2) Apply corrosion preventive (Material No. P04-039) to the mating surfaces of the control 

tube assembly (13) the control column (21) and the new universal joint (16) (P/N 

527.10.12.195).

(3) Put the stop block (19) on the universal joint (16) (P/N 527.10.12.195) and align the holes. 

(4) Install the new universal joint (16) (P/N 527.10.12.195) to the control column (21).

(5) Install the control tube assembly (13) to the universal joint (16) (P/N 527.10.12.195) and 

align the holes.

(6) Install the new bolt (20) (P/N 932.35.14.016), washer (17) (P/N 938.77.11.112) and the nut 

(18) (P/N 938.07.68.304).
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 7 of 10

SERVICE BULLETIN

(7) Install the new bolt (12) (P/N 932.19.60.814), washer (14) (P/N 938.77.11.115) and the nut 

(15) (P/N 938.07.68.505).

(8) Install the bolt (23) and the nut (22).

(9) Torque the nuts to the standard torque values, refer to AMM 12-B-20-20-01-00A-040A-A.

D. Removal - Co-pilot Side

Refer to Figure 1.

CAUTION: BE CAREFUL NOT TO DAMAGE THE ADJACENT WIRING LOOM.

(1) Remove the nut (8) and the bolt (9).

(2) Remove and discard the nut (11), washer (10) and the bolt (6).

(3) Remove and discard the nut (4), washer (3) and the bolt (2).

(4) Move back the control wheel and remove the universal joint (1) (P/N 527.10.12.195) from 

the control tube assembly (7) and the control column (5).

E. Installation - Co-pilot Side

Refer to Figure 1.

(1) Apply corrosion preventive (Material No. P04-039) to the mating surfaces of the control 

tube assembly (7) the control column assembly (5) and the new universal joint (1) (P/N 

527.10.12.195).

(2) Install the new universal joint (1) (P/N 527.10.12.195) to the control column (5).

(3) Install the control tube assembly (7) to the universal joint (1) (P/N 527.10.12.195) and align 

the holes.

(4) Install the new bolt (2) (P/N 932.35.14.012), washer (3) (P/N 938.77.11.112) and the nut 

(4) (P/N 938.07.68.304).

(5) Install the new bolt (6) (P/N 932.19.60.814), washer (10) (P/N 938.77.11.115) and the nut 

(11) (P/N 938.07.68.505).

(6) Install the bolt (9) and the nut (8).

(7) Torque the nuts to the standard torque values, refer to AMM 12-B-20-20-01-00A-040A-A.

F. Close Up

(1) Do an functional test of the aileron control system, refer to AMM 12-B-27-10-00-00A903A-A.

(2) Do an functional test of the elevator control system, refer to AMM 12-B-27-30-00-00A903A-A.

(3) Make sure that the work area is clean and clear of tools and other items.

(4) Install the crew seats, refer to AMM 12-B-25-10-01-00A-920A-A.
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 8 of 10

SERVICE BULLETIN

(5) Remove the safety clip and close the circuit breaker:

A/P SERVO (AVIONICS BUS).

(6) Remove the warning sign from the cockpit.

(7) Lower the aircraft to the ground and remove the jacks, refer to AMM 12-B-07-10-00-00A901A-A.

G. Documentation

(1) Record in the aircraft logbook that this Service Bulletin has been accomplished.

(2) Mark the removed universal joints “unserviceable” and return to Pilatus at the applicable 

address below: 

PILATUS AIRCRAFT LTD

WARRANTY COORDINATOR

ENNETBÜRGENSTRASSE 101

CH-6371 STANS

SWITZERLAND

Attn: Mr Stefan Brun

Tel: + 41 41 619 3333

PILATUS BUSINESS AIRCRAFT LTD

PARTS SALES AND SERVICES

11755 AIRPORT WAY

BROOMFIELD, CO 80021

UNITED STATES OF AMERICA

Attn: Mr Jerry Frank

Tel: +1 303 465 9099
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 9 of 10

SERVICE BULLETIN

4. Part B: Accomplishment Instructions - Spares

A. Instruction

Parts held as spares must be marked “unserviceable” and return to Pilatus at the applicable 

address below: 

PILATUS AIRCRAFT LTD

WARRANTY COORDINATOR

ENNETBÜRGENSTRASSE 101

CH-6371 STANS

SWITZERLAND

Attn: Mr Stefan Brun

Tel: + 41 41 619 3333

PILATUS BUSINESS AIRCRAFT LTD

PARTS SALES AND SERVICES

11755 AIRPORT WAY

BROOMFIELD, CO 80021

UNITED STATES OF AMERICA

Attn: Mr Jerry Frank

Tel: +1 303 465 9099
Service Bulletin No: 27-022 Date: Mar 17/15

Rev No. Date: Page 10 of 10

SERVICE BULLETIN

Universal Joint - Removal/Installation

Figure 1

A

A

1

2

3

5

6

8

9

10

11

12

FRAME 12

4

B

B

7

13

14

15

16

17

18

20

22

23

21

SB2603

19