AIRWORTHINESS DIRECTIVE
Cessna 402 · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) of Australia, specifically addressing safety concerns related to the Cessna 400 series aircraft, including the Cessna 402. The directive mandates inspections of the auxiliary wing spars for cracks, particularly in the area where the main landing gear trunnion is mounted. The AD outlines the compliance requirements, including inspection intervals and actions to take if cracks are found. It is crucial for operators of the affected aircraft models to adhere to these directives to ensure safety and prevent potential accidents related to wing structure failure.
- The AD applies to Cessna 402 aircraft, serial numbers 402-0001 to 402-0322.
- Visual inspections of the auxiliary wing spar for cracks are mandatory.
- Cracks of 0.5 inches or more require immediate part replacement before further flight.
- For cracks less than 0.5 inches, inspections must occur every 50 hours, with parts replaced within 200 hours or 12 months.
- Initial inspections must be completed within 10 hours of service after March 2, 2009.
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
- 2009
- Pages
- 2
- File size
- 21 KB
- Publisher
- services.casa.gov.au
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In this document
Applicability
The AD applies to several models within the Cessna 400 series, specifically the Model 402 aircraft, including serial numbers 402-0001 through 402-0322, as well as the 402A and 402B variants with specified serial ranges.
Requirement
Operators are required to visually inspect the auxiliary wing spar for cracks. If a crack of 0.5 inches or more is found, the affected part must be replaced before further flight. For cracks less than 0.5 inches, repetitive inspections are mandated at intervals not exceeding 50 hours, with replacement required within 200 hours or 12 months, whichever comes first.
Compliance
The initial inspection must be completed within 10 hours of service after March 2, 2009, unless already done. Additionally, inspections are required after any hard landing, and results must be reported to Cessna Aircraft Company.
Background
The directive was issued due to reports of fatigue cracking in the auxiliary wing spar area of the Cessna 402A and 402B models, which could lead to wing failure and landing gear collapse, posing significant safety risks.
Safety notes
- Failure to comply with the AD may result in wing structure failure and landing gear collapse, leading to loss of control and potential passenger injury.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 1 of 2 AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. Cessna 400 Series Aeroplanes AD/CESSNA 400/118 Auxiliary Wing Spars 4/2009 DM Applicability: Model 401 aircraft, serial numbers 655 and 401-0001 through 401-0322. Model 401A aircraft, serial numbers 655 and 401A0001 through 401A0132. Model 401B aircraft, serial numbers 401B0001 through 401B0221. Model 402 aircraft, serial numbers 402-0001 through 402-0322. Model 402A aircraft, serial numbers 402A0001 through 402A0129. Model 402B aircraft, serial numbers 402B0001 through 402B0122, 402B0201 through 402B0249, 402B0301 through 402B0455, 402B0501 through 402B0640, 402B0801 through 402B0935, 402B1001 through 402B1100, 402B1201 through 402B1250, and 402B1301 through 402B1384. Requirement: Visually inspect the auxiliary wing spar near the location where the main landing gear trunnion is mounted, for cracks; in accordance with Cessna Service Bulletin MEB08-8 original issue, or later FAA approved revision. If any crack is detected during any inspection that is 0.5-inch or more, before further flight, replace the cracked part(s). If any cracks are detected during any inspection that are less than 0.5-inch, accomplish the following: Repetitively inspect the crack(s) for length at intervals not to exceed 50 hours time in service and, before further flight, replace any part that has a crack with a length of 0.50-inch or more; and, Replace the cracked part within 200 hours time in service after the original crack was detected, or within 12 months after the original crack was detected, whichever occurs first. If cracks are detected as a result of any inspection, report the results to the Cessna Aircraft Company at whichever of the following occurs later: Within 10 days after the inspection is accomplished; or, COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Cessna 400 Series Aeroplanes AD/CESSNA 400/118 (continued) Page 2 of 2 Within the next 10 days after 2 March 2009. Note 1: Supplemental Inspection Numbers 57-10-09 and 57-10-13 of the Cessna 401/402 Supplemental Inspection Document (SID) inspect the auxiliary spar caps, but not the webs. Hence, this Airworthiness Directive applies even to SID-compliant aircraft. Note 2: FAA AD 2009-04-04 Amdt 39-15810. Compliance: Accomplish the initial inspection within 10 hours time in service after 2 March 2009, unless already accomplished; and, in addition, before further flight anytime the aircraft experiences a hard landing. Inspect thereafter if cracking is detected, as specified in the Requirement section of this Directive. This Airworthiness Directive becomes effective on 2 March 2009. Background: The FAA received several reports of fatigue cracking on Models 402A and 402B aircraft, in the area of the auxiliary wing spar where the main landing gear trunnion is mounted. This condition, unless corrected, could result in failure of the wing auxiliary spar web and cause landing gear collapse during normal landing. This could lead to loss of control and passenger injury. David Villiers Delegate of the Civil Aviation Safety Authority 23 February 2009
What's in the Cessna 402 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.