CTHIn ForceLegislation
AD/DHC-3/30 Amdt 1 - Elevator Connecting Rod
DHC-3 (Otter) Series AeroplanesDHC-3 (Otter) Series Aeroplanes
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DHC-3 (Otter) Series Aeroplanes
| AD/DHC-3/30 Amdt 1 | Elevator Connecting Rod | 1/2009 |
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| Applicability: | All Model DHC-3 aircraft. |
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| Requirement: | 1. Visually inspect the elevator pushrod (part number C3-CF-167 or replacement pushrod part number C3-CF-633-1); and the elevator pushrod to rear quadrant attachment bolt (part number AN174-16 or replacement bolt part number NAS1954-24D) and associated hardware.The inspection should concentrate on the detection of bowing of the pushrod, cracking of the pushrod threaded ends or bending of the attachment bolt. If evidence of component damage is found, before further flight, replace the damaged parts in accordance with de Havilland Service Bulletin (SB) No.3/35 Revision A and SB No.3/43 original issue, or later Transport Canada approved revisions; except that attachment bolt part number AN174-16 may be used in lieu of bolt part number NAS1954-24D until Requirement 2 of this Directive comes into effect. If bolt part number AN174-16 is replaced with bolt part number NAS1954-24D, the rudder pushrod to rear quadrant attachment bolt and associated hardware are also required to be replaced at the same time with hardware as specified in SB No.3/43 original issue, or later Transport Canada approved revision.2. Replace the elevator pushrod to rear quadrant attachment bolt and associated hardware in accordance with SB No.3/43 original issue, or later Transport Canada approved revision. Simultaneously, unless already accomplished, replace the rudder pushrod to rear quadrant attachment bolt in accordance with SB No.3/43 original issue, or later Transport Canada approved revision.3. Whenever a parked aircraft has been exposed to jet, propeller, or helicopter blast or winds with an estimated mean velocity of 55 km/h with gusting up to 100 km/h, compliance with Requirement 1 must be accomplished before further flight regardless of whether the new components of Requirement 2 have been installed or not. After exposure to these wind velocities visually inspect the remainder of the elevator control circuit for damage in accordance with de Havilland SB No.3/35 Revision A, or later Transport Canada approved revision.Note: Transport Canada AD CF-85-04 refers. |
| Compliance: | 1. Unless already accomplished, within 50 flight hours after 15 January 2009.2. Unless already accomplished, within 100 flight hours after 15 January 2009.3. As specified in Requirement 3. |
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