Commonwealth legislation

AD/BEECH 35/68 - Ruddervator Differential Tail Control Rod Assembly

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legislative instrument

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This Airworthiness Directive requires owners/operators of specified Beechcraft 35‑series aeroplanes (listed serial-number ranges) to inspect the ruddervator differential tail control rod assembly for cracks and corrosion, repair or replace any defective parts, and apply anti‑corrosion sealant in accordance with Raytheon MSB 2668 (or Revision 1). It must be completed within 100 hours time‑in‑service after 17 July 1997. The action responds to a reported pushrod split caused by water freezing inside the component; owners pay for inspections, repairs and any parts.

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AD/BEECH 35/68 - Ruddervator Differential Tail Control Rod Assembly

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Beechcraft 35 (Bonanza) Series Aeroplanes

AD/BEECH 35/68 Ruddervator Differential Tail Control Rod Assembly

8/97

Applicability: Models 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35,

P35, S35, V35, V35TC, V35A, V35A-TC, V35B, and V35B-TC aircraft with serial numbers D-1 through D-10403, D-15001, and D-15002.

Requirement: Inspect the ruddervator differential tail control rod assembly for cracks and corrosion in accordance with the Accomplishment Instructions section of Raytheon Mandatory Service Bulletin (MSB) 2668 , or Raytheon MSB 2668 Revision 1.

Repair or replace any corroded or cracked part as specified in and in accordance with the Service Bulletins referenced above.

Apply anti-corrosion sealant to the ruddervator control pushrods in accordance with the Accomplishment Instructions section of Raytheon MSB 2668, or Raytheon MSB 2668 Revision 1.

Note: FAA AD 97-06-11 Amdt 39-9968 refers.

Compliance: Unless already accomplished, within 100 hours time in service after 17 July 1997.

This airworthiness directive becomes effective on 17 July 1997.

Background: The FAA received a report of a split in the ruddervator control push rod that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod, and then expanded. Failure of the differential tail control rod assembly could result in loss of control of the aircraft.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/BEECH 35/68 - Ruddervator Differential Tail Control Rod Assembly