SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 33 Debonair · Other Documents
Overview
This document is a Schedule of Airworthiness Directives issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Beechcraft 33 and 35-33 (Debonair/Bonanza) series aeroplanes. It outlines the requirements for inspecting the rudder forward spar, detailing compliance timelines and necessary actions to ensure airworthiness. The directive emphasizes the importance of addressing potential fatigue-related issues in the rudder assembly to prevent loss of aircraft control. Pilots and maintenance personnel are advised to adhere to the specified inspection intervals and corrective measures to maintain safety standards.
- Applicable to Beechcraft 33 and 35-33 series aeroplanes.
- Inspect rudder forward spar per Beech SB 2333 Revision 1.
- Initial compliance before 1000 hours TIS or 100 hours after Nov 1, 1990.
- Subsequent inspections every 500 hours TIS.
- Terminating actions include installation of repair kits and rudder assembly replacement.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Other Documents
- Year
- 1998
- Pages
- 1
- File size
- 11 KB
- Publisher
- services.casa.gov.au
Most owners only have the POH. Here's the essential set for the Beechcraft 33 Debonair.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Applicability
The airworthiness directive applies to various models of the Beechcraft 33 and 35-33 series, specifically listing serial numbers for models such as 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33, and others. This ensures that all affected aircraft are identified for compliance.
Inspection Requirements
The directive mandates an inspection of the rudder forward spar in accordance with Beech Service Bulletin SB 2333 Revision 1, dated November 1991. This inspection is crucial for identifying potential cracks that could lead to structural failure.
Compliance Timeline
Compliance with the directive is required before exceeding 1000 hours of component Time In Service (TIS) or 100 hours TIS after November 1, 1990, whichever occurs later. Subsequent inspections must occur at intervals not to exceed 500 hours TIS.
Terminating Actions
The document outlines several terminating actions for the directive, including the installation of a repair kit, replacement of the rudder assembly, and installation of rudder spar reinforcements as per FAA STCs. These actions are necessary to mitigate the identified risks.
Background Information
The directive was issued following reports of cracks at the hinge bracket attachments in the rudder forward spar, attributed to fatigue from drilled holes for nut plates. The document stresses the critical nature of addressing these issues to prevent loss of aircraft control.
Safety notes
- Failure to correct the condition may result in loss of aircraft control.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Beechcraft 33 and 35-33 (Debonair/Bonanza) Series Aeroplanes AD/BEECH 33/36 Amdt 2 Rudder Forward Spar 5/98 Applicability: Models Serial Numbers 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33 CD-1 through CD1304 35-C33A, E33A, F33A CE-1 through CE-1425 E33C, F33C CJ-1 through CJ-179 Requirement: 1. Inspect the rudder forward spar in accordance with Beech Service Bulletin SB 2333 Revision 1 dated Nov 1991. Note: FAA AD 93-24-03 Amendment 39-8752 refers. Compliance: 1. Before exceeding 1000 hrs component TIS or 100 hrs TIS after 1 Nov 1990, whichever occurs later and thereafter at intervals not to exceed 500 hrs TIS. The following are terminating actions for this Directive: a. Installation of repair kit 33-6001-1S in accordance with the Beech SB 2333 Revision 1; b. Replacement of the rudder assembly with the applicable part number in accordance with Beech SB2333 Revision 1; c. Installation of rudder spar reinforcements in accordance with FAA STC SA4899NM; and, d. Installation of rudder spar reinforcements in accordance with FAA STC SA00044LA. This amendment becomes effective on 23 April 1998. Background: This AD was raised as a result of eight reports of cracks at the hinge bracket attachments in the rudder forward spar. The cause is fatigue initiating at holes drilled to install nut plates. Failure to correct this condition may result in loss of aircraft control. This amendment calls up the latest FAA AD information and highlights the presence of other terminating action. Amendment 1 of this airworthiness directive became effective in January 1993. The original issue of this airworthiness directive became effective in August 1990.