SCHEDULE OF AIRWORTHINESS DIRECTIVES
CESSNA 414 · Service Bulletins
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Cessna 400 Series aircraft, including the Cessna 414A. It outlines mandatory requirements for inspections and modifications related to the engine mount beams due to reported cracking issues. The directive applies to all Cessna 414A aircraft with serial numbers 414A0001 through 414A1206. Compliance with the directive is crucial to ensure the safety and airworthiness of the aircraft, particularly in preventing potential engine failures that could lead to loss of control. The document specifies various kits and inspection methods that must be incorporated based on the aircraft's configuration and history of modifications.
- Cessna 414A aircraft with serial numbers 414A0001 through 414A1206 are affected by this directive.
- Mandatory inspections of engine mount beams must be conducted within specified timeframes: 1,600 hours or at the next engine overhaul.
- If cracks are found in the engine mount beam, specific actions must be taken based on the length and location of the cracks.
- Incorporation of Cessna Kits SK414-19-1, SK414-19-2, SK414-19-3, SK414-19-4, and SK414-19-5 is required depending on the aircraft's configuration.
- The directive emphasizes the need for modifications to eliminate ongoing repetitive inspections.
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
- Service Bulletins
- Year
- 1998
- Pages
- 3
- File size
- 15 KB
- Publisher
- services.casa.gov.au
Common. One of the most common aircraft types we track.
Full essential library on file for the CESSNA 414.
CESSNA 414 for sale now
Free — save the 414 to your watchlist and track it in one place.
More CESSNA 414manuals & documents
See all 33 →- C-414 Initial/Transition Ground Training Student Guide - Tom GorskiSystems Description
- C-414A Transition Flight Training Student GuideV Speeds Reference
- C-414 Initial/Transition Flight Training Student Guide - Tom GorskiNormal Procedures
- NAVIGATION - STALL WARNING HORN REPLACEMENTService Bulletins
- AC 150/5220-10F, Guide Specification for Aircraft Rescue and Fire ...Specifications
- SERVICE BULLETIN No. 058 Rev. A Turbocharger - Back Plate Assembly Replacement at OverhaulMaintenance Manual
- Aviation Accident Factual ReportOther Documents
- RAM Performance - Cessna 414 Series VIIPilot's Operating Handbook
- AAIB Bulletin: 4/2019 N414FZ EW/G2018/06/33Other Documents
- Type Acceptance Report TAR 6/21B/14 – Cessna 400 SeriesOther Documents
- Aviation Accident Final ReportOther Documents
- C-414 NORMAL CHECKLISTPilot's Operating Handbook
If you fly the CESSNA 414, you may also be researching these.
In this document
Applicability
The directive applies to all Cessna 402C aircraft with serial numbers 402C0001 through 402C0808 and all Cessna 414A aircraft with serial numbers 414A0001 through 414A1206.
Requirements
The document outlines several requirements for aircraft with and without Cessna Kit SK414-17. These include incorporating specific Cessna kits, conducting inspections using radiographic methods, and following detailed procedures based on the findings of these inspections.
Compliance
Compliance timelines are specified, including inspections within 1,600 hours time in service after 23 April 1998 or at the next engine overhaul, and subsequent inspections at intervals not exceeding 9,600 hours time in service.
Background
The directive was issued in response to incidents of cracking in engine mount beams, which could lead to engine failure and loss of the aircraft. It emphasizes the importance of modifications that can reduce the need for repetitive inspections.
Safety notes
- Cracking of the engine mount beams can lead to engine failure and loss of control of the aircraft.
- Timely compliance with the directive is critical for safety.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES 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. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES 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
Show full textShow less
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.
What's in the CESSNA 414 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.
1,386 CESSNA 414 parts for sale
See all →
Parts listed for sale by vetted eBay sellers — confirmed on eBay at checkout.