British Gliding Association Aircraft Inspection Recommended

Number:
036/06/2003
Date: 26 June 2003

Issue:
1

Subject:

Vertical Elevator Control Rod

Applicability:

Grob G109 series

Accomplishment:

At next Annual inspection Repeat Annually for aircraft stored outside Repeat every 3 years for aircraft stored exclusively in dry conditions

Reason:

To detect corrosion inside the elevator control rod and mass balance weight located in the vertical fin and prevent failure of the rod and control disconnection.

Instructions:

1. Gain access to elevator rod in fin by removing rudder and Tailplane. 2. Remove nut and bolt from lower end of elevator control rod and withdraw rod through fin. 3. Remove tubular rivet at lower end of rod and withdraw balance weight (approx. 0.75 m long steel bar with “O” ring at top. 4. Inspect external area of control rod at a point where the top of the weight would be located. If necessary paint strip the area. If any corrosion is found having penetrated through the control rod wall, replace the control rod assembly before further flight. 5. Inspect the rod internally as far as possible and the balance weight. Only light corrosion is permissible. If severe corrosion is found replace the control rod assembly before further flight. 6. Remove any light corrosion found. (A long extension bar on a drill and a piece of emery will be required)
Continued..

Issued by - The British Gliding Association Ltd, Kimberley House, Vaughan Way, Leicester, LE1 4SE, U.K. Note: Mandatory inspections must be recorded in the aircraft log book, unless specified, and certified by an appropriately rated BGA inspector.
Optional inspections should be entered into the D.I. book or log book as appropriate. Optional inspections may be certified by a BGA Pilot. Alternative methods of compliance will be considered providing an equal level of safety is accomplished. Contact BGA for authorisation.

BGA 036/06/2003 issue 1, continued

7. Re-protect the rod internally and externally and the balance weight with primer and topcoat. 8. It is also recommended to treat the inside of the rod with protection fluid such as “Tube Oil” or “Lanolin” (PX1) 9. Re-assemble the control rod using a new “O” ring and tubular rivet. Special tools are required to replace the rivet (The Tubular rivet may be replaced by a 6mm nut and bolt provided adequate clearance exists when refitted to aircraft). 10. Refit control rod to aircraft. 11. Carry out duplicate inspection of rod installation. (Check that adequate clearance exists especially if using a 6mm nut and bolt) 12. Refit removed components. 13. Make logbook entry showing compliance and Pink Page entry indicating when next due.

In case of difficulty, Please contact Tim Dews at Airborne Composites.

Parts & materials required;

O ring

P/No 14-2/872

Tubular rivet

P/No LN340-1.4544.9

(Bolt/nut/washer P/No LN9037 M6x26, LN9348M6, LN9025-6.4)

Protection fluid Tube oil or PX1

Primer and paint

Approved By Jim Hammerton, Chief Technical Officer

Issued by - The British Gliding Association Ltd, Kimberley House, Vaughan Way, Leicester, LE1 4SE, U.K. Note: Mandatory inspections must be recorded in the aircraft log book, unless specified, and certified by an appropriately rated BGA inspector.
Optional inspections should be entered into the D.I. book or log book as appropriate. Optional inspections may be certified by a BGA Pilot. Alternative methods of compliance will be considered providing an equal level of safety is accomplished. Contact BGA for authorisation.