AD/CESSNA 400/81 Amdt 4 - Engine Mount Beams

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B08365 In force Legislative Instrument

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Cessna 400 Series Aeroplanes

 

AD/CESSNA 400/81

Amdt 4


Engine Mount Beams 5/98

 

Applicability: All models 402C aircraft with serial numbers 402C0001 through 402C0808, and all models 414A aircraft with serial numbers 414A0001 through 414A1206.

 

Requirement:  1. For aircraft with Cessna Kit SK414-17 incorporated, incorporate Cessna Kit SK414-19-1, and one of the following, as applicable, in accordance with the instructions to Service Kit SK414-19B, Revised 4 March 1986:

 

(a)     Cessna Kit SK414-19-2: All of the affected Models 402C and 414A aircraft that are equipped with propeller unfeathering accumulators;

 

(b)     Cessna Kit SK414-19-3: Model 402C aircraft, serial numbers 402C0001 through 402C0468; and Model 414A aircraft, serial numbers 414A0001 through 414A0646;

 

(c)     Cessna Kit SK414-19-5: Model 402C aircraft, serial numbers 402C0469 through 402C0808; and Model 414A aircraft, serial numbers 414A0647 through 414A1206.

 

2.    For aircraft without Cessna Kit SK414-17 incorporated, incorporate Cessna Kit SK414-19-1, and one of the following, as applicable, in accordance with the instructions to Service Kit SK414-19B, Revised 4 March 1986:

 

(a)     Cessna Kit SK414-19-2: All of the affected Models 402C and 414A aircraft that are equipped with propeller unfeathering accumulators;

 

(b)     Cessna Kit SK414-19-4: Model 402C, serial numbers 402C0001 through 402C0468; and Model 414A aircraft, serial numbers 414A0001 through 414A0646;

 

(c)     Cessna Kit SK414-19-5: Model 402C aircraft, serial numbers 402C0469 through 402C0808; and Model 414A aircraft, serial numbers 414A0647 through 414A1206.

 

3.    Inspect, using radiographic methods, the engine mount beam for cracks in accordance with the Accomplishment Instructions section of Attachment to Service Bulletin MEB85-3, Revised 23 August 1985, as referenced in Cessna Service Bulletin MEB85-3, Revision 2, dated 23 October 1987.

 

(a)     If any crack is found in the left side (vertical portion) of the left engine beam of either nacelle, obtain a repair scheme from the manufacturer, and then incorporate this repair scheme.

 

(b)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is less than 1.75 inches (44.5 mm), stop drill each end of each crack using a 0.098 inch drill bit.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 

(c)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 1.75 inches, but less than

2.75 inches (70 mm), obtain a repair scheme from the manufacturer, and then incorporate this repair scheme.

 

(d)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 2.75 inches, replace the engine beam with a part number specified in the instructions to Service Kit SK414-19B, Revised 4 March 1986.

 

4.    If parts for any of the engine beam modifications required by Requirements 1 and 2 of this Directive have been ordered from the manufacturer but are not available, accomplish the following in accordance with the Accomplishment Instructions section of Attachment to Service Bulletin MEB85-3, Revised 23 August 1985; as referenced in Cessna Service Bulletin MEB85-3, Revision 2, dated 23 October 1987:

 

(a)     For aircraft with Cessna Kit SK414-17 incorporated, inspect the engine mount beams using radiographic methods.

 

(b)     For aircraft without Cessna Kit SK414-17 incorporated, fluorescent penetrant inspect the engine mount beams.

 

5.    If any of the following occurs during any of the inspections required by Requirement 4 of this Directive, accomplish the following specified actions:

 

(a)     If parts become available, terminate the repetitive inspections specified in Requirement 4 of this Directive, incorporate the modification kits required by Requirement 1 or 2 of this Directive, and inspect the engine mount beams as specified in Requirement 3 of this Directive;

 

(b)     If any crack is found in the left side (vertical portion) of the left engine beam of either nacelle, obtain a repair scheme from the manufacturer, incorporate this repair scheme, and continue the repetitive inspections required by Requirement 4 of this Directive.

 

(c)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is less than 1.75 inches, stop drill each end of each crack using a 0.098 inch drill bit, and continue the repetitive inspections required by Requirement 4 of this Directive;

 

(d)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 1.75 inches, but less than

2.75 inches, obtain a repair scheme from the manufacturer, incorporate this repair scheme, and continue the repetitive inspections required by Requirement 4 of this Directive; or,

 

(e)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 2.75 inches, replace the engine beam with a part number specified in the instructions to Service Kit SK414-19B, Revised 4 March 1986, and inspect the engine mount beams as specified in Requirement 3 of this Directive.

 

Note: FAA AD 97-26-16 Amdt 39-10259 refers.

 

Compliance: 1. Within 1,600 hours time in service after 23 April 1998 or at the next engine overhaul, whichever occurs first.

 

2.    Within 200 hours time in service after 23 April 1998.

 

3.    Within 9,600 hours time in service after the modification required by Requirement 1 or 2 of this Directive, as applicable, and thereafter at intervals not to exceed 9,600 hours time in service.

 

4.  (a) Within 1,600 hours time in service after 23 April 1998, and thereafter at intervals not to exceed 1,600 hours time in service; provided that no provision specified in Requirement 5 of this Directive occurs.

 

4. (b) Within 200 hours time in service after 23 April 1998, and thereafter at intervals not to exceed 200 hours time in service; provided that no provision specified in Requirement 5 of this Directive occurs.

 

This airworthiness directive becomes effective on 23 April 1998.

 

Background: Cracking of the engine mount beams has been experienced in service. Failure of the engine mount beam caused by fatigue cracks could result in loss of the engine with consequent loss of the aircraft.

 

Amendment 3 introduced Revision 1 of the Requirement document and noted the related FAA AD.

 

Amendment 4 is issued in response to a new FAA AD which requires incorporating engine mount kits that will eliminate the need for the on-going repetitive inspection requirement. The FAA has determined that reliance on critical repetitive inspections on aircraft utilised in commuter service carries an unnecessary safety risk when a design change exists that could eliminate or, in certain circumstances, reduce the number of those critical inspections.

 

Amendment 3 of this airworthiness directive became effective on 31 December 1985. Amendment 2 of this airworthiness directive became effective on 30 June 1985.

The original issue of this airworthiness directive became effective on 23 June 1981.

Overview

The Civil Aviation Safety Authority issued an Airworthiness Directive concerning Cessna 400 Series aeroplanes, specifically targeting models 402C and 414A. This directive, effective from 23 April 1998, was introduced to address the identified problem of engine mount beam cracking, which could lead to severe safety issues such as engine loss and potential aircraft failure. The directive mandates specific modifications and inspections to ensure the structural integrity of the engine mount beams, thereby enhancing the safety of these aircraft models. This legislative instrument is part of the broader framework of civil aviation safety regulations, aimed at mitigating risks and ensuring compliance with safety standards for aircraft in operation. The policy objective is to maintain and improve the safety of aviation by requiring timely and appropriate actions to address structural weaknesses identified in specific aircraft models.

Scope and Application

The Cessna 400 Series Aeroplanes AD/CESSNA 400/81Amdt 4 Engine Mount Beams applies to specific models of Cessna 402C and 414A aircraft with particular serial numbers, mandating modifications and inspections to address the issue of engine mount beam cracking. This legislative instrument pertains to all models 402C aircraft with serial numbers ranging from 402C0001 to 402C0808, and all models 414A aircraft with serial numbers ranging from 414A0001 to 414A1206. The directive requires the incorporation of specific Cessna kits, depending on whether the aircraft is equipped with propeller unfeathering accumulators, and mandates the replacement or repair of engine mount beams based on the extent of detected cracks. The directive further specifies the use of radiographic or fluorescent penetrant inspection methods for engine mount beams and outlines the frequency of inspections and repairs depending on the availability of parts and the results of the inspections. The directive is effective as of 23 April 1998, with compliance deadlines set within specific time frames or after engine overhauls. The application of this directive is governed by the Civil Aviation Regulations 1998, under the Commonwealth of Australia.

Key Provisions

The AD/CESSNA 400/81Amdt 4 primarily concerns the incorporation of specific Cessna kits and inspections for engine mount beams on certain Cessna 400 Series aeroplanes. According to section 1, for aircraft with Cessna Kit SK414-17 incorporated, Cessna Kit SK414-19-1 must be incorporated along with one of three additional kits, depending on the aircraft's serial number and whether it is equipped with propeller unfeathering accumulators. For aircraft without Cessna Kit SK414-17, Cessna Kit SK414-19-1 must be incorporated along with one of three other kits, also depending on the aircraft's serial number. Section 3 requires inspecting the engine mount beams using radiographic methods, with specific actions to take based on the findings, such as obtaining a repair scheme from the manufacturer, stop drilling cracks, or replacing the engine beam. The obligations imposed on the parties by this Act include incorporating the specified kits and conducting the required inspections. Section 1 mandates the incorporation of the correct Cessna kits based on the aircraft's serial number and equipment, while section 3 requires radiographic inspections of the engine mount beams. If cracks are found, the appropriate repair scheme must be obtained, or the engine beam must be replaced. There are no explicit offences, penalties, or civil/criminal consequences mentioned in the text for non-compliance with this airworthiness directive. However, failure to comply with airworthiness directives can lead to serious safety risks, including the potential for engine failure and loss of the aircraft. While specific penalties are not detailed in this document, non-compliance with airworthiness directives can result in enforcement actions by the Civil Aviation Safety Authority, including fines and potential grounding of the aircraft until compliance is achieved.

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.