AD/ML-M5/10 Amdt 1 - Wing Lift Struts

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

Legislation au F2006B11297 Not in force Legislative Instrument

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


Maule M-5 Series Aeroplanes

 

AD/ML-M5/10

Amdt 1


Wing Lift Struts 11/98

 

Applicability: All the following aircraft models that are equipped with part number (P/N) 2079E rear wing lift struts or P/N 2080E front wing lift struts:

 

M-5-180C

M-5-200

M-5-210C

M-5-210TC

M-5-220C

M-5-235C

 

 

 

Note 1: This Directive does not apply to aircraft equipped with four Maule sealed lift struts, P/N 2200E and P/N 2201E. These sealed lift struts are identified by two raised weld spots on the upper end of the strut just below the serial number plate. Removal of the upper cuff is needed to locate the weld spots.

 

Requirement: Remove the wing lift struts in accordance with the Instructions section of Maule Service Bulletin (SB) 11, and accomplish Requirement 1, or 2, or 3, or 4.

 

  1. Inspect the wing struts for corrosion in accordance with the Inspection Procedure section of Maule SB 11.

 

  1. If no perceptible dents (as defined in the above SB) are found in the wing lift strut and no corrosion is externally visible, apply corrosion inhibitor to each strut in accordance with Maule SB 11. Re-inspect the wing lift struts provided no perceptible dents or external corrosion is found.

 

b.    If a perceptible dent (as defined in the above SB) is found in the wing lift strut or external corrosion is found, before further flight, accomplish one of the installations (and subsequent actions) specified in Requirements 3 and 4 of this Directive.

 

2.    Inspect the wing lift struts for corrosion in accordance with an approved ultrasonic inspection method.

 

  1. If no external corrosion is found and all requirements in an approved ultrasonic inspection method are met, before further flight, apply corrosion inhibitor to each strut in accordance with Maule SB 11. Re-inspect the lift struts provided no external corrosion is found and all of the requirements in an approved ultrasonic inspection method are met.

 

b.    If external corrosion is found or if any of the requirements of an approved ultrasonic inspection method are not met, before further flight, accomplish one of the installations (and subsequent actions) specified in Requirement 3 and 4 of this Directive.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 

3.    Install original equipment manufacturer (OEM) part number wing lift struts that have been inspected in accordance with the specifications presented in either Requirement 1 or 2 of this Directive, and are found to be serviceable according to the inspection requirements of Requirement 1 or 2 of this Directive. Accomplish this installation in accordance with the applicable maintenance manual. Thereafter, inspect these wing lift struts in accordance with the specifications presented in either Requirements 1 or 2 of this Directive.

 

4.    Install new Maule sealed wing lift struts, P/N 2200E or 2201E, as applicable on each wing as specified in the Instructions section in Part II of Maule SB 11.

 

5.    If holes are drilled into the sealed wing lift strut assemblies installed as specified in Requirement 4 of this Directive in order to attach cuffs, door clips, or other hardware, inspect the wing lift struts using the procedures specified in either Requirement 1 or 2 of this Directive.

 

Note 2: Appendix to FAA AD 98-15-18, Procedures and Requirements for Ultrasonic Inspection of Maule Wing Lift Struts is an approved ultrasonic inspection method, and may be obtained from the Authority on request.

 

Note 3: The repetitive inspections required by this Directive may be terminated after installing new wing lift strut assemblies as specified in Requirement 4 of this Directive provided no holes are drilled in these strut assemblies as specified in Requirement 5 of this Directive.

 

Note 4: FAA AD 98-15-18 Amdt 39-10669 refers.

 

Compliance: For Requirements 1,2,3, and 4, as applicable:

 

Upon accumulating 2 years on a lift strut affected by this Directive, within 3 calendar months after 8 October 1998, or within 2 years after the last inspection accomplished in accordance with the initial issue of this Directive; whichever occurs later.

 

For Requirements 1(a), 2(a), 3, and 5, as applicable:

 

Inspect at intervals not to exceed 24 calendar months. This amendment becomes effective on 8 October 1998.

Background:  The wing of a Maule aircraft separated in flight. Investigation revealed that the unsealed lift strut failed due to internal corrosion.

 

Amendment 1 is issued in response to a new FAA AD which retains the initial inspection and possible replacement requirements of the previous AD, but now requires the inspections to be repetitive, while providing the option of using ultrasonic procedures to accomplish the inspection requirements.

 

The original issue of this airworthiness directive became effective on 14 February 1996.

Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, form a comprehensive framework governing civil aviation within the country, ensuring safety and efficiency in air travel. The 1998 Regulations were introduced to address the need for an updated and consolidated set of rules governing all aspects of civil aviation, superseding numerous earlier pieces of legislation and aiming to provide a more streamlined and effective regulatory environment. Part 39 - 105 within these Regulations pertains specifically to airworthiness directives, which are legally enforceable rules that mandate corrective actions to be taken when safety issues are identified. The Civil Aviation Safety Authority (CASA) is the enforcing body, with the overarching policy objective being to maintain and enhance the safety standards of civil aviation operations in Australia. This is achieved through the continuous review and amendment of airworthiness directives, such as the recent amendment to the Maule M-5 Series Aeroplanes, which responds to identified safety concerns regarding wing lift struts.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, applies to all Maule M-5 Series aeroplanes equipped with certain wing lift struts. These include part numbers 2079E and 2080E, and the affected models are M-5-180C, M-5-200, M-5-210C, M-5-210TC, M-5-220, and M-5-235C. The directive does not apply to aircraft equipped with sealed lift struts, part numbers 2200E and 2201E, identifiable by specific weld spots. This directive governs the inspection, maintenance, and replacement of the specified wing lift struts to prevent failures due to corrosion, which was identified as the cause of a previous wing separation incident. The requirement is to inspect and maintain the struts in accordance with the specified procedures and intervals, with an initial compliance deadline within three calendar months after 8 October 1998, or within two years from the last inspection under the initial directive issued on 14 February 1996. The directive extends its application through the use of subordinate instruments such as maintenance manuals and service bulletins, and specifies ultrasonic inspection methods as an approved alternative.

Key Provisions

The Civil Aviation Regulations 1998 (CAR) under Part 39, Section 105, mandates specific requirements for the maintenance and inspection of certain Maule M-5 Series Aeroplanes to ensure airworthiness. Section 105 of the CAR includes an Airworthiness Directive (AD) for Maule M-5 Series Aeroplanes, specifically addressing the wing lift struts, identified by part numbers 2079E and 2080E (AD/ML-M5/10 Amdt 1). This directive applies to certain models of Maule aircraft, excluding those equipped with sealed lift struts, P/N 2200E and P/N 2201E. The directive requires the removal and inspection of the wing lift struts to check for corrosion, as outlined in the Instructions and Inspection Procedure sections of Maule Service Bulletin 11. Depending on the findings, the directive stipulates either the application of corrosion inhibitor or the replacement of the struts with new ones. The AD imposes specific obligations on the aircraft operators and maintenance personnel to ensure compliance. Operators must conduct inspections and maintenance actions as prescribed, either through the manual inspection method or an approved ultrasonic inspection method. For instance, if no perceptible dents or external corrosion are found, the struts must be treated with a corrosion inhibitor. Conversely, if any corrosion is detected, the struts must be replaced with new ones, following the specifications provided in the maintenance manual. The repetitive inspections required by this directive must be completed within specified timeframes, either within three calendar months from 8 October 1998, or within two years from the last inspection, whichever is later. Failure to comply with the AD may result in civil or criminal consequences. The regulations do not specify maximum penalties directly, but non-compliance with ADs can lead to severe repercussions, including the grounding of the aircraft, fines, and potential prosecution under aviation safety laws. The AD aims to prevent failures due to internal corrosion, which was the cause of a previous incident where a wing separated in flight. Therefore, adherence to the AD is crucial to maintain the safety and airworthiness of the affected aircraft.

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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.