Viking Air SB V2/003: Revision NC, text

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Page 1Open in PDF

Page 1 of 2 ATA Ref: 32-00 28 November 2012 Service Bulletin V2/003

SERVICE BULLETIN TRANSMITTAL SHEET GROSS WEIGHT INCREASE STC SA92-63 OR SA00299NY, PART REPLACEMENT – FRONT WIRE PULL FITTING VALTBS1245-1/-2 & VALTBS1244-1 REAR FLOAT STRUT & WIRE PULL FITTINGS Service Bulletin No.: V2/003 Date of Original Issue: 28 November 2012 Revision No.: Revision NC Date of Issue: 28 November 2012 The purpose of this Service Bulletin is to notify o perators of DHC-2 MK. I aircraft incorporating 5600 lb Gross Weight increase STC SA92-63 or SA00299NY with wire pull fittings VALTBS1244-1 and/or VALTBS1245-1/-2 that a replacement front wire pull fitting is required to address a recent part failure.

1. A service difficulty investigation has revealed t hat:

(a) The front wire pull fitting VALTBS1245-1/-2 is p rone to stress corrosion cracking an d therefore a replacement fitting VALTBS1245-3/-4 is required.

(b) Clarifying the tensioning procedure of the floa t strut bracing wires is required for aircraft incorporating STC SA92-63 or SA00299NY.

2. In addition, it was found that the aft fitting (V ALTBS1244-1) is also prone to stress corrosion cracking a nd requires replacement with VALTBS1244-3 (LH) and -4 (RH) fittings.

Page 2Open in PDF

Page 2 of 2 ATA Ref: 32-00 28 November 2012 Service Bulletin V2/003

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Page 3Open in PDF

28 November 2012 S.B. V2/003 Revision ‘NC’ Page 1 of 4 1959 de Havilland Way Sidney, B.C.

Canada V8L 5V5 Tel.: (250) 656-7227 DHC-2 Beaver

SERVICE BULLETIN ATA SYSTEM: 32-00 Number: V2/003 I. PLANNING INFORMATION A. Effectivity Aircraft Affected: All DHC-2 MK.I aircraft incorpora ting 5600lb Gross Weight increase STC SA92-63 or SA00299NY with wire pull fittings VALTBS 1244-1 and/or VALTBS1245-1/-2.

B. Reason The purpose of this Service Bulletin is to notify o perators that replacement front wire pull fitting are required to address a failure.

1. A service difficulty investigation has revealed t hat:

(a) The front wire pull fittings VALTBS1245-1/-2 are prone to stress corrosion cracking and therefore replacement fitting VALTBS1245-3/-4 are required.

(b) Clarifying the tensioning procedure of the float strut bracing wires is required for aircraft incorporating STC SA92-63 or SA00299NY.

2. In addition, it was found that the aft fitting (V ALTBS1244-1) are also prone to stress corrosion cracking and require replacement with VAL TBS1244-3 (LH) and -4 (RH) fittings.

C. Description

1. Some in-service installations employ Viking Front Wire-Pull Fittings VALTBS1245-1/-2.

These fittings have failed due to stress corrosion cracking at low cycles/hours.

(a) Where VALTBS1245-1/-2 fittings exist, they must be replaced with VALTBS1245-3/-4 fittings within 90 days of the issuance of this Service Bulletin.

The replacement fittings are geometrically identica l to the legacy fittings but are made from a superior aluminum alloy.

(b) The original DHC-2 tensioning instructions for the Strut Bracing Wires are appropriate for STC SA92-63 or SA00299NY. See Part II, Para 1. Step 8.

SUBJECT: GROSS WEIGHT INCREASE STC SA92-63 OR SA002 99NY, PART REPLACEMENT – FRONT WIRE PULL FITTINGS VALTBS1245-1/-2 & VALTBS 1244-1 REAR FLOAT STRUT & WIRE PULL FITTINGS.

Page 4Open in PDF

SERVICE BULLETIN V2/003 28 November 2012 S.B. V2/003 Revision ‘NC’ Page 2 of 4

2. Some in-service installations employ Viking Aft W ire-Pull Fittings VALTBS1244-1.

These fittings have been shown to be prone to failure.

(a) For all cases where VALTBS1244-1 fittings are in stalled, they must be replaced with VALTBS1244-3/-4 fittings within 180 days of th e issuance of this Service Bulletin. The replacement fittings are now differen tiated for installation (-3 [LH] and -4 [RH]) and are of improved geometry and aluminum alloy.

(b) A visual inspection of the wire pull fittings at every 100 hours is required.

D. Compliance Viking Air requires operators to:

1. Replace the front fittings within 90 days of the original issue date of this Service Bulletin.

2. Replace the rear fittings within 180 days of the original issue date of this Service Bulletin.

3. Incorporate the 100 hour visual inspection requir ement to the operator’s Maintenance Schedule.

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 Approximately 4-6 man-hours will be required to rep lace the front float strut wire pull fittings and another 4-6 man-hours will be required to repla ce the rear float strut wire pull fittings.

These estimates are for direct labour performed by an experienced crew and does not include set-up, planning or other such activities.

G. Weight and Balance Not applicable.

H. Electrical Load Data Not applicable.

I. Publications Affected Not applicable.

II. ACCOMPLISHMENT INSTRUCTIONS A. VALTBS1245-1/-2 Front Float Strut Wire Pull Fitti ngs Replacement Note: Retain and inspect all hardware. Inspect all m ating parts for signs of corrosion or cracking. Replace any damaged hardware and/or parts as required.

1. Trestle/support the aircraft for removal of the f ront float strut-fuselage attachments in accordance with PSM 1-2-2.

2. Loosen the front float strut bracing wires and ja m nuts.

3. Remove the cotter pins from the upper bracing wir e attachment clevis pins.

4. Remove front float strut attachment locking nuts and washers.

Page 5Open in PDF

SERVICE BULLETIN V2/003 28 November 2012 S.B. V2/003 Revision ‘NC’ Page 3 of 4

5. Drive float strut attachment bolts out using a so ft punch, taking care not to damage exposed threads.

6. Remove strut bracing wires clevis pins and front wire pull fittings from aircraft.

7. Install replacement front wire pull fittings – in a manner opposite to removal.

8. Tension front strut bracing wires as follows:

(a) Insert the streamline bracing wires into the for k ends with the 4 inch long circular section uppermost and crank wires to obtain correct alignment and tension.

Note: Wire tension is correct when a 15 lb load appl ied perpendicular to the centre of the wire produces a deflection at this po int of between 0.11 –

0.125 inch.

Note: Wires are correctly installed when there is an equal amount of thread visible between the wire and the base of the fork end – approximately 0.8 inch.

9. Cracked VALTBS1245-1/-2 fittings shall be reporte d to Viking (see Part III).

Note: Fittings that are not cracked shall be dispose d of by cutting them in half.

10. Inspect the front strut wire pull fittings every 100 hours for signs of corrosion and/or cracking. See Part IV – Maintenance Instructions.

B. VALTBS1244-1 Rear Float Strut Wire Pull Fittings Replacement Note: Retain and inspect all hardware. Inspect all m ating parts for signs of corrosion or cracking. Replace any damaged hardware and/or parts as required.

1. Trestle/support the aircraft for removal of the r ear float strut-fuselage attachments in accordance with PSM 1-2-2.

2. Loosen the rear float strut bracing wires and jam nuts.

3. Remove the cotter pins from the upper bracing wir es attachment clevis pins.

4. Remove rear float strut attachment locking nuts a nd washers.

5. Drive float strut attachment bolts out using a so ft punch, taking care not to damage exposed threads.

6. Remove strut bracing wires clevis pins and rear w ire pull fittings from aircraft.

7. Install replacement rear wire pull fittings – in a manner opposite to removal.

8. Tension rear strut bracing wires as follows:

Note: Insert the streamline bracing wires into the f ork ends with the 4 inch long circular section uppermost and crank wires to obtai n correct alignment and tension. Wire tension is correct when a 15 lb load applied perpendicular to the centre of the wire produces a deflection at this po int of between 0.11 – 0.125 inch.

Note: Wires are correctly installed when there is an equal amount of thread visible between the wire and the base of the fork end – approximately 0.8 inch.

9. Cracked VALTBS1244-1 fittings shall be reported t o Viking Air Limited (see contact information at Part III, Para A.).

Note: Fittings that are not cracked shall be dispose d of by cutting them in half.

Page 6Open in PDF

SERVICE BULLETIN V2/003 28 November 2012 S.B. V2/003 Revision ‘NC’ Page 4 of 4

10. Inspect the rear strut wire pull fittings every 100 hours for signs of corrosion and or cracking. See Part IV – Maintenance Instructions.

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

“Service Bulletin No. V2/003 - GROSS WEIGHT INCREAS E STC SA92-63 OR SA00299NY, PART REPLACEMENT – FRONT WIRE PULL FITTI NG VALTBS1245-1/-2 & VALTBS1244-1 REAR FLOAT STRUT & WIRE PULL FITTINGS has been incorporated”.

III. MATERIAL INFORMATION AND TOOLING A. Material Information The following parts can be obtained by contacting Viking Air Product Support:

Note: This Service Bulletin is self-contained. No dr awings 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-ATL AS Canada, V8L 5V5 International: 1-800-6727-6727 technical.support@vikingair.com B. Tooling – Price and Availability

• Standard Aircraft Mechanics Tools.

IV. MAINTENANCE INSTRUCTIONS Incorporate a visual inspection of the VALTBS1244-3/-4 rear wire pull fittings and VALTBS1245-3/ -4 front wire pull fittings for corrosion and/or cracking into the recommended 100 hour inspection.

PART NUMBER DESCRIPTION VALTBS1244-3 Rear Wire Pull Fitting VALTBS1244-4 Rear Wire Pull Fitting VALTBS1245-3 Front Wire Pull Fitting VALTBS1245-4 Front Wire Pull Fitting