SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft A36TC Bonanza · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Beechcraft 36 (Bonanza) series aeroplanes, including the A36 and A36TC models. The directive outlines the requirements for inspecting the rudder forward spar due to identified fatigue issues that could lead to loss of aircraft control. It specifies compliance timelines and actions to be taken to mitigate the risk of failure. The document serves as a critical safety measure for operators of the affected aircraft models, ensuring that necessary inspections and repairs are conducted in a timely manner to maintain airworthiness.
- Applicable models: Beechcraft 36, A36, A36TC, B36TC.
- 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 kit 33-6001-1S or 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
- Airworthiness Directives
- 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 A36TC Bonanza.
- 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 Beechcraft 36 series aeroplanes, specifically the A36 models with serial numbers E-1 through E-2518 and the A36TC and B36TC models with serial numbers EA-1 through EA-500.
Requirement
Operators are required to inspect the rudder forward spar in accordance with Beech Service Bulletin SB 2333 Revision 1, dated November 1991. This inspection is crucial to identify any potential fatigue-related issues.
Compliance
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. Inspections must then be conducted at intervals not exceeding 500 hours TIS.
Terminating Actions
The directive outlines several actions that can terminate the requirements of this AD, including the installation of a repair kit, replacement of the rudder assembly, and installation of rudder spar reinforcements as specified in various Beech Service Bulletins and FAA STCs.
Background
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 emphasizes the importance of addressing this issue 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 36 (Bonanza) Series Aeroplanes AD/BEECH 36/36 Amdt 1 Rudder Forward Spar 5/98 Applicability: Models Serial Numbers 36, A36 E-1 through E-2518 A36TC, B36TC EA-1 through EA-500 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 considered 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. The original issue of this airworthiness directive became effective in August 1990.