AD/ML-M7/2 Amdt 1 - Wing Lift Struts

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Maule M-7 Series Aeroplanes

AD/ML-M7/2

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:

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.