# SERVICE BULLETIN TRANSMITTAL SHEET

Service Bulletin No.: V2/0005 Date of Original Issue: 26

- March

- 2012

Revision No.: Revision C Date of Issue: 17

- July

- 2015



### CORROSION INSPECTION

– ELEVATOR CONTROL ROD AND ELEVATOR ACTUATI NG LEVER ON THE CONTROL COLUMN

Reports have been made that corrosion was found at the elevator actuating lever on the control column and in the elevator control rod assembly (C2CF619A). Als o, an instance of rod end plug corrosion has been reported. Access is obtained to the area below the floor and a detailed visual inspection is done of the elevator control rod and elevator actuating lever on the control column. Control rod assembly is remo ved for a detail inspection. Control rods 15 years and older are replaced.

NOTE 1: ALL AIRCRAFT MUST INCORPORATE APPLICABLE INSPECTIONS IN ACCORDANCE WITH SB V2/0005 REVISION ‘ C ’.
NOTE 2 : This revision supersedes the previous revision of this Service Bulletin.
NOTE 3 : Revision bars in the left margin of this Service Bulletin denote changes from the previous revision.

This page transmits Revision ‘ C ’ of Service Bulletin V2/0005, pages 1 thru 14, dated 17

- July

- 2015

. Service Bulletin re

- issued to make changes to the Compliance Section I.D.

Remove Service Bulletin V2/0005 Revision ‘B’ dated 04 March 2015 and replace with attached.

Previous issues of Service Bulletin V2/0005:

Initial Issue

– 26

- March

- 2012)

– effectivity

– All DHC

- 2 aircraft
Rev A

– (07

- Nov

- 2014)

– effectivity

– All DHC

- 2 aircraft
Rev B

– (04

- March

- 2015)

– effectivity

– All DHC

- 2 aircraft

Page 1 of 2 ATA Ref: 27

- 30

17

- July

- 2015 Service Bulletin V2/0005THIS PAGE INTENTIONALLY LEFT BLANK

Page 2 of 2 ATA Ref: 27

- 30

17

- July

- 2015 Service Bulletin V2/00051959 deHavilland Way. Sidney, B.C. Canada V8L 5V5 Tel: (250) 656

- 7227 

# DHC -

2 

# Beaver

SERVICE BULLETIN

ATA SYSTEM: 27

- 30 NUMBER: V2 / 00 05



## I. PLANNING INFORMATION

A. Effectivity

Aircraft Affected: All DHC

- 2.



### B. Reason
There have been a number of r eports of corrosion at the elevator actuating lever on the control column

, in the elevator control rod(s) assembly (C2CF619A, Mk I , Mk II and Mk III and CT2CF1021

- 1 for Mk III)

. An instance of rod plug end corrosion has been reported. Also, potential cracks may have developed on the elevator control rods.



### C. Description
Control rod s P/N C2CF619A and P/N CT2CF1021

- 1 assembl ies are removed for a one time detailed inspection , and the associated controls parts are inspected in situ

. A n inspection every 400 hrs is added for P/N C2CF619A, P/N C2CF619A

- 9, P/N C2CF619A

- 11 and P/N CT2CF1021

- 1. This S ervice B ulletin includes a 15 years and older replacement requirement on P/N C2CF619A c ontrol rod assembl y only.



### D. Compliance

1. I nitial Detailed Visual Inspection of Control Rod Assembly P/Ns C2CF619A and CT2CF1021

- 1

, the Elevator Actuating Lever on the Control Column , and the Control Column Torque Tube :
(a) Perform an initial detailed visual inspection for corrosion, cracking, and/or other damages of the exterior of the elevator control rod assemblies

, the elevator actuating lever on the control column , and the control column torque tube, I n A ccordance W ith (IAW) A ccomplishment Instructions Section II.A through II.F

, within the time limits specified per the schedule in Table 1.

Note: Damaged parts shall be repaired or replaced before next flight as per Paragraph I .D. 1. (b)

. SUBJECT: ELEVATOR CONTROL ROD AND ELEVATOR ACTUATING LEVER ON THE CONTROL COLUMN

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### SERVICE BULLETIN V2/ 0005

Table 1

– Initial Inspection Schedule

Component Age of Assembly Previously Inspected IAW

SB V2/0005 revision NC, A

or B Action Required

Control Rod Assembly P/N C2CF619A 15 years or greater since

new or of unknown age Yes Par agraph I.D.1 of this SB is satisfied. Continue with Paragraph I.D. 2 and I.D. 3 of this SB

.

No Within 120 days or 100 air time hours, whichever occurs first

, from the effective date of this SB

. a) Inspect IAW Paragraph I.D.1 and continue with Paragraph I.D. 2 and I.D. 3 or b) Optionally replace control rod assembly with P/N C2CF619A

11 rod assembly. Continue with Paragraph I.D. 2

.

Less than 15 years since new Yes Paragraph I.D.1 of this SB is satisfied. Continue with Paragraph I.D. 2 and I.D. 3 of this SB

.

No Within 120 days or 100 air time hours, whichever occurs first from the effective date of this SB

, inspect IAW Paragraph I.D.1

. Continue with Paragraph I.D. 2 and I.D. 3

.

Control Rod Assembly P/N CT2CF1021

- 1 N/A Yes Paragraph I.D.1 of this SB is satisfied. Continue with Paragraph I.D. 2

.

No Within 120 days or 100 air time hours, whichever occurs first from the effective date of this SB, inspect IAW Paragraph I.D.1 and continue with Paragraph I.D. 2

.

Elevator Actuating Lever on the Control Column

Control Column Torque Tube N/A Yes Paragraph I.D.1 of this SB is satisfied. Continue with Paragraph I.D.2.

No Within 120 days or 100 air time hours, whichever occurs first from the effective date of this SB, inspect IAW Paragraph I.D.1 and continue with Paragraph I.D.2.

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### SERVICE BULLETIN V2/ 0005

(b) If corrosion, cracking or other damage is found on :
i. P/N C2CF619A control rod assembly, replace the rod assembly with P/N C2CF619A

- 11 rod assembly prior to next flight or contact Viking Air Ltd. for an approved repair and incorporate the repair prior to next flight.

ii. P/N CT2CF1021

- 1 control rod assembly, replac e the rod assembly with new CT2CF1021

- 1 rod assembly prior to next flight or contact Viking Air Ltd. for an approved repair and incorporate the repair prior to next flight.

iii. the elevator actuating lever, contact Viking Air Ltd. for an approved repair and incorporate the repair prior to next flight.

Note: All findings shall be reported to Viking Technical Support utilizing the Inspection Report form at the end of this S ervice Bulletin

.

2. Repetitive Inspection (applicable to rod assembly P/Ns C2CF619A, C2 CF619A

- 9, C2CF619A

- 11 and CT2CF1021

- 1 ) : Within 30 days from the effective date of this Service Bulletin

, Operators shall incorporate the applicable repetitive Inspectio n task into the applicable maintenance program as follows : (a) F or DHC

- 2 MK I , MK II and MK I II : DHC

- 2 Beaver Maintenance Manual, PSM 1

- 2

- 2, Appendix 2, Part 3 Item 20A. ( Refer to TR 2

- 38)
(b) F or DHC

- 2 MK III : DHC

- 2 Turbo Beaver Supplementary Maintenance Manual

, PSM 1

- 2T

- 2 , Part 4 Item 20 A. (Refer to TR

- 2T

- 14)

3. Service Life Limit of Rod Assemblies P/N C2CF619A : (a) P/N C2CF619A rod assemblies are life limited to 15 years and must be replaced with P/N C2CF619A

- 11 rod assembly prior to exceeding the life limit except as authorized by Paragraph I.D. 3

. ( b ) of this Service Bulletin

. (b) Replace all P/N C2CF619A rod assemblies 15 years or greater since new or of unknown age with P/N C2CF619A

- 11 rod assembly within one year from th e effective date of this Service Bulletin

. (c) From the effective date of this Service Bulleti n , no person shall install P/N C2CF619A or P/N C2CF619A

- 9 control rod assemblies as a replacement.

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### SERVICE BULLETIN V2/ 0005

E. Approval The technical content of this Service Bulletin has been approved under the authority of the Transport Canada Civil Aviation (TCCA) Design Approval Organization (DAO) 04

- V

- 02.



### F. Manpower
A pproximately 8 man

- hours for MK I and MK II (12 man

- hours for MK III) will be required to remove and re

- install the elevator control rod(s) assembly.

An additional 3.5 man

- hours will be required for the inspections. This estimate is for direct labor performed by an experienced crew and does not include setup, planning or other such activities.



### G. Weight and Balance Not applicable.



### H. Electrical Load Data
Not applicable.



### I. Publications Affected
PSM 1

- 2

- 2, Maintenance Manual PSM 1

- 2T

- 2 Supplementary Maintenance Manual



### J. References
PSM 1

- 2

- 2, Maintenance Manual PSM 1

- 2T

- 2, Supplementary Maintenance Manual

Note: This Service Bulletin is self

- contained. No drawings are supplied. For more information please contact:

Viking Air Limited Fax: 250

- 656

- 0673 Technical Support Telephone Numbers: 1959 De Havilland Way Regional: 250

- 656

- 7227 Sidney, British Columbia North America: 1

- 866

- 49

- ATLAS Canada, V8L 5V5 Interna tional: 1

- 800

- 663

- 8444 technical.support@vikingair.com

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### SERVICE BULLETIN V2/ 0005



## II. ACCOMPLISHMENT INSTR UCTIONS

A. Preparation

1. DHC

- 2 MK I and MK II Access: (a) Gain access to the elevator actuating lever ( 11, Figure 1 ) on the control column, the elevator control rod assembly ( 14, Figure 1 ) and bell crank (18, Figure 1) as follows:

i. Remove circular panel (PSM 1

- 2

- 2 Part 1, Figure 1

- 3, Item 16) below the mid part of fuselage.

ii. Remove the lower LH oil cooler duct assembly (PSM 1

- 2

- 4 P art 2, Figure 24, Item 1).

iii. Remove the left hand bottom panel (PSM 1

- 2

- 2 Part 1, Figure 1

- 3, Item 20).

iv. Remove the LH floor boards in the cabin.

v. Apply duct tape or a suitable anti

- chafe tape to each lightning hole on the floor bulkheads to protect the finish on the rod during removal and installation.

vi. Before loosening the control column, the aileron control chain needs to be clamped to avoid skipping a tooth inside the control column

. vii. Loosen the control column and move it out of the way to provide clearance. (b) Remove the elevator control rod assembly (1 4, Figure 1 ) from the attaching plate ( 8, Figure 1 ) and the elevator actuating lever (11

, Figure 1 ) on the control column.

Note: Measure and note the length between the center s of the two rod ends, this will help for final rigging (refer to Figure 2).

2. DHC

- 2 MK I I I Access: (a) Remove circular panel (PSM 1

- 2T

- 2 Supplement 6, Figure 6

- 3, Item 15) beneath mid part of the fuselage. (b) Remove the left hand bottom panel (PSM 1

- 2T

- 2 Supplement 6

, Figure 6

- 3

, Item 9)

. (c) Remove the LH (Pilot) seat and LH Cockpit floor board (PSM 1

- 2T

- 4 Part 2

, Figure 36, Item 1) (d) Apply duct tape or a suitable anti

- chafe tape to each lightning hole on the floor bulkheads to protect the finish on the rod during removal and installation. (e) The O UT B D control column bearing attach bolt has to be removed and the outboard end of the control column torque tube has to be raised up so the pushrod can be removed

. (f) Remove the elevator control rod assemblies (14 and 15, Figure 3) in accordance with (IAW) Aircraft Maintenance Manual, PSM 1

- 2T

- 2, Supplement 6, and Section 6.18.1.

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### SERVICE BULLETIN V2/ 0005

Note: Measure and note the length between the center s of the two rod ends, this will help for final rigging (refer to Figure 2).



### B. Detailed Visual Inspection

1. With a strong light and a 10x magnifying glass, inspect the exterior of the elevator control rod C2CF619A (1 4, Figure 1 ) for MK I and MK II and the elevator control rods C2CF619A and CT2CF1021

- 1 ( 14 & 15

, Figure 3 ) for MK III as follows: (a) Thoroughly clean the entire control rod (including the Plug End ( C2CF 1189

, Figure 2)

. (b) Inspect the C2CF1189 Plug End closely for signs of corrosion, cracking and/or other damage, particularly in the area where the diameter changes, at the mating surface with the steel nut and at the edge of the rod tube (see Figure 2). (c) Inspect the rod tube closely for signs of corrosion, cracking and/or other damage, particularly at the rivet attach points and in the area where the tube diameter changes at both tube ends (see Figure 2). (d) Inspect for signs of paint bubbling along the remaining rod tube. If bubbling is found, remove the paint for further inspection

. Note: Damaged parts shall be repaired or rep laced before next flight

.

2. Visually inspect the elevator actuating lever and the control column torque tube ( Item 11 & 12 in Figure 1 or Item 16 & 17 in Figure 3 ) in situ as follows : (a) Thoroughly clean the inside and out side of the fork area on the elevator actuating lever in situ

. (b) With a strong light and a 10x magnifying glass ( and/or a mirror as required)

, inspect the elevator actuating lever and the control column torque tube for cracking, distortion, corrosion and/or other damage.

Note: Damaged parts shall be repaired or rep laced before next flight

. 3. Visually inspect the idle bracket and spring (2 & 3, Figure 3), bellcrank, cable turnbuckle and attachment plate ( 8, 18 & 19 in Figure 1

, ; 4, 5 & 13 in Figure 3) as follows: (a) Thoroughly clean the parts listed in Paragraph 3 above in situ. (b) With a light and a 10x magnifying glass ( and/or a mirror as required ), inspect the parts listed in Paragraph 3 above and associated attachment hardware for cracking, distortion, corrosion and/or other damage.

Note: Damaged parts shall be repaired or rep laced before next flight

.

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### SERVICE BULLETIN V2/ 0005



### C. Installation of Serviceable Elevator Control Rod Assembly

1. DHC

- 2 MK I and MK II Installation : (a) Install the elevator control rod assembly (1 4 , Figure 1 ) IAW PSM 1

- 2

- 2, Part 2, Section 2.43

. Note: Adjust the length (between the center of the two rod end fittings) as required to the previously measured length noted in Para II.A.1.( b )

. Note that this is a preliminary adjustment only, and the system still requires to be

re

- rigged.

(b) Touchup surface finish as r equired (on bare metal surface, if any). Apply corrosion preventive compound LPS3 (or equivalent) to the inside and outside of the fork area on the elevator actuating lever (11, Figure 1), and to the control rod (14, Figure 1) exterior surface to cover app roximately 12 ” from the rod forward end.

2. DHC

- 2 MK III Installation : (a) Install the elevator control rod assemblies (14 and 15, Figure 3) IAW with Aircraft Supplementary Maintenance Manual, PSM 1

- 2T

- 2, Supplement 6, Section 6.18.2

. Note: Adjust the length (between the center of the two rod end fittings ) as required to the previously measured length noted in Para II.A.1.(c)

. that this is a preliminary adjustment only, and the system still requires to be re

rigged )

. (b) Touchup surface fini sh as required (on bare metal surface, if any). Apply corrosion preventive compound LPS3 (or equivalent) to the inside and outside of the fork area on the elevator actuating lever (16, Figure 3), and to the entire exterior surface of the control rod (15, Figure 3) , as well as 12” (from the rod forward end) of the exterior surface of the control rod (14, Figure 3)

.


### D. Rigging of the Elevator System

1. DHC

- 2 MK I and MK II Elevator Rigging Instructions : (a) Check the function of the elevator control system , and re

- r ig the system as required

, IAW Aircraft Maintenance Manual, PSM 1

- 2

- 2, Part 2, 2.43.5

. 2. DHC

- 2 MK III Elevator Rigging Instructions : (a) Check the function of the elevator control system , and re

- r ig the system as required IAW Aircraft Supplementary Maintenance Manual, PSM 1

- 2T

- 2, Supplement 6, Section 6.19

.

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### SERVICE BULLETIN V2/ 0005



### E. Close

- out

1. DHC

- 2 MK I and MK II close

- out : (a) Remove duct tape or suitable anti

- chafe tape from each lightning hole

. (b) Install LH floor boards in the cabin. (c) Re

- install and safety the control column, and remove chain block

. (d) Install the left hand bottom panel (Item 20, Figure 1

- 3 in PSM 1

- 2

- 2 Part 1). (e) Install the lower LH oil cooler duct assembly (PSM 1

- 2

- 4 Part 2, Figure 24, Item 1 )

. (f) Install the circular panel (Item 16, Figure 1

- 3 in PSM 1

- 2

- 2 Part 1) be low mid part of the fuselage

. 2. DHC

- 2 MK III close

- out : (a) Remove duct tape or suitable anti

- chafe tape from each lightning hole. (b) Re

- install O UT B D control column bearing attach bolt and safety (c) Reinstall the circular panel (PSM 1

- 2T

- 2 Supplement 6 , Figure 6

- 6 , Item 15 ) beneath mid part of the fuselage (d) Reinstall the left hand bottom panel (PSM 1

- 2T

- 2 Supplement 6 , Figure 6

- 6

, Item 9 )

. (e) Reinstall the LH (Pilot) seat and R H Cockpit floor board (PSM 1

- 2T

- 4 Part 2 Figure 36, Item 1)

.


### F. Recording On completion of this Service Bulletin, make the following entry in the aircraft log book:

1. For Aircraft inspected in accordance with paragraph I.D.1 of Service Bulletin V2/0005 Revisi on C , make the following entry:
“Service Bulletin No. V2/ 0005 Revision C

- ELEVATOR CONTROL ROD AND ELEVATOR ACTUATING LEVER ON THE CONTROL COLUMN

– Inspection in accordance with paragraph I.D.1. has been accomplished ”

. 2. If existing elevator control rod assembly was replaced with C2CF619A

- 11

, make the following entry :
“Service Bulletin No. V2/ 0005 Revision C

- ELEVATOR CONTROL ROD AND ELEVATOR ACTUATING LEVER ON THE CONTROL COLUMN

– E levator control rod assembly C2CF619A has been replaced with C2CF619A

- 11 ”

. 3. If existing elevator control rod extension assembly CT2CF1021

- 1 was replaced by a new rod extension assembly CT2CF1021

- 1

, make the following entry :
“Service Bulletin No. V2/ 0005 Revision C

- ELEVATOR CONTROL ROD AND ELEVATOR ACTUATING LEVER ON THE CONTROL COLUMN

– E levator control rod extension assembly CT2CF1201

- 1 has been replaced with new CT2CF1021

- 1”.

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### SERVICE BULLETIN V2/ 0005



## III. MATERIAL INFORMATION AND TOOLING

A. Material Information (Parts Required Per Aircraft )

.

TABLE 1

PART CURRENT PART NUMBER REPLACEMENT PART

Control Rod Assembly C2CF619A ( Pre Mod 2/1604 & 2/1606) , or C2CF619A

- 9 ( Post Mod 2/1604, 2/1606 & Pre Mod 2/160 8 ) C2CF619A

- 11 (Post Mod 2/ 160 8 )

Connecting Rod Extension CT2CF1021

- 1 (for MKIII) CT2CF1021

- 1

• LPS3 (or equivalent).



### B. Tooling

– Price and Availability

• Standard aircraft mechanic’s hand tools

.

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### SERVICE BULLETIN V2/ 0005



## IV. TABLES AND FIGURES

F IGURE 1

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### SERVICE BULLETIN V2/ 0005

F IGURE 2 CT2 CF 1021

- 11 CT2 CF 1021

- 13 CLEVIS

ROD TUBE

CENTRE TO CENTRE

ROD ASSY CT2CF1021

- 1 Potential crack on both tube ends C2 CF 1189 PLUG END MD 46 15 ROD END

Potential corrosion area on Plug End C2CF1189 PLUG END

C2 CF 1189 F4 W 19 MD 46 15 C2 CF 3371

ND OR OR

ROD END C2 CF 637 ND ROD END RE 4 H16 ROD TUBE Potential crack on both tube ends

ROD ASSY C2CF619A, C2CF619A

- 9 & C2CF619A

- 11 Potential corrosion area on Plug End C2CF1189

CENTRE TO CENTRE

C2 CF 1189

- 3 OR

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### SERVICE BULLETIN V2/ 0005

F IGURE 3

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### SERVICE BULLETIN V2/ 0005



## Service Bulletin V2/0005

- Inspection Report

Operator :

____________________________________________________
Contact Person:

_________________________________________________________
Contact Phone/Email:

_____________________________________________________
A/C Registration # A/C Serial #

_______________________
A/C TTSN

_____________________________ A /C TCSN

_________________________
Elevator Control Rod P/N TTSN TCSN

___________

Inspection Findings:

Please return form via email to technical.support@vikingair.com or via fax to 250

- 656

- 0673

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### SERVICE BULLETIN V2/ 0005

THIS PAGE IS INTENTIONALLY BLANK

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