SCHEDULE OF AIRWORTHINESS DIRECTIVES
Cessna 340 · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Cessna 340 and 340A series aircraft. It outlines critical requirements for the retirement of certain components of the aircraft's wing and airframe based on fatigue life assessments. The directive is aimed at ensuring the safety and airworthiness of these aircraft by mandating compliance with specified operational limits regarding flight hours and number of flights. The document provides essential guidelines for operators and maintenance personnel to adhere to in order to maintain compliance and safety standards.
- Retire wing main spar lower cap and attachment fittings before 22,300 hours or 20,300 flights.
- Retire the airframe before 44,600 hours or 40,600 flights.
- For unknown flight counts, estimate by dividing total hours by an average flight time of 0.8 hours.
- Fatigue data covers only wing main spars; other parts' durability is unknown.
- Operators may apply for an extension of retirement life with proper substantiation.
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
- 1995
- Pages
- 1
- File size
- 11 KB
- Publisher
- services.casa.gov.au
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Most owners only have the POH. Here's the essential set for the Cessna 340.
- 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 all Cessna Model 340 and 340A Series aircraft, ensuring that all operators of these models are aware of the requirements outlined in the directive.
Requirements
The directive specifies two main requirements: first, the retirement of the wing main spar lower cap and wing attachment fittings from service; second, the retirement of the remainder of the airframe. These actions are mandated to prevent potential structural failures due to fatigue.
Compliance
Operators must comply with the retirement requirements before exceeding 22,300 hours of time in service or 20,300 flights for the wing components, and 44,600 hours or 40,600 flights for the airframe. For aircraft with unknown flight counts, an estimation method is provided.
Background
The directive is based on results from full-scale fatigue testing and analysis of flight load data, which established the fatigue life for the wing spar and attachment fittings. The airframe is allowed a retirement life equal to double that of the wing spar, pending further substantiation.
Safety notes
- Failure to comply with the retirement requirements may lead to structural failure and endanger safety.
- Operators must ensure accurate tracking of flight hours and counts to comply with the directive.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Cessna 340 Series Aeroplanes AD/CESSNA 340/32 Wing and Airframe 10/95 Applicability: All Cessna Model 340 and 340A Series aircraft. Requirement: 1. Retire the wing main spar lower cap and wing upper and lower attachment fittings from service. Note: The centre section spar caps and attachment fittings are not affected by this Requirement. 2. Retire the remainder of the airframe from service. Compliance: 1. Retire components, in accordance with Requirement 1, before exceeding 22 300 hours time in service or 20 300 flights, whichever occurs first. 2. Retire airframe, in accordance with Requirement 2, before exceeding 44 600 hours time in service or 40 600 flights, whichever occurs first. Note 1: For aircraft with an unknown number of flights an estimate shall be made by dividing the number of hours flown by an average flight time of 0.8 hours. Note 2: The available fatigue data covers wing main spars only. The durability of other parts of the airframe has not been evaluated, and is therefore unknown. Based on experience, the Authority is prepared to credit unevaluated structure with a retirement life equal to double the life for the wing spar (Requirement 2). An extension beyond this may be available, but any application must be supported by a fatigue substantiation covering all the remaining primary structure. This should include empennage, wing centre section, wing rear spar, control surfaces, fuselage, etc. The substantiation may take the form of a safe life assessment, or a sufficiently rigorous revised inspection schedule to ensure that any fatigue cracking which could occur in service will be detected before the aircraft is endangered. Background: Results of full scale fatigue testing of the wing, flight load data analysis and fleet usage have been used to establish the fatigue life for the Cessna 340 Series wing spar and attachment fittings. The remainder of the airframe is allowed two spar lives without further substantiation.
What's in the Cessna 340 TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.
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