AD/LUSCOMBE/2 Amdt 1 - Wing Spar Corrosion

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Legislation au F2006B11190 In force Legislative Instrument

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Luscombe Model 8 Series Aeroplanes

 

AD/LUSCOMBE/2

Amdt 1


Wing Spar Corrosion 3/98 DM

 

Applicability: Models 8, 8A, 8B, 8C, 8D, 8E, 8F, and T-8F (all serial numbers).

 

Requirement: 1. For all aircraft, inspect for intergranular corrosion in the areas of the front and rear spar extrusions of the wing installations and if corrosion is found, prior to further flight, replace the corroded part in accordance with the Compliance Procedures section, paragraph "1A. Fabric Covered Wings." or paragraph "2. Inspect" of The Don Luscombe Aviation History Foundation Recommendation #2, dated 15 December 1993, REVISED 21, November 1995, whichever paragraph is applicable to the wing construction of the aircraft.

 

2.    For aircraft with metal covered wings:

 

  1. Install two additional wing inspection holes (left wing and right wing) using the Don Luscombe Aviation History Foundation (DLAHF) Kit #8007, Wing Access and Inspection Kit, in accordance with the Compliance Procedures section, paragraphs "1B Metal Covered Wings.", (a), (a1.) to (a9.), and (b.) of The Don Luscombe Aviation History Foundation Recommendation #2, dated 15 December 1993, Revised 21 November 1995; and

 

b.    Modify the wing tip fairing using the DLAHF Kit #8007, Wing Access and Inspection Kit, in accordance with the Compliance Procedures section, paragraphs "1B Metal Covered Wings.", (c), and (c1.) to (c5.) of The Don Luscombe Aviation History Foundation Recommendation #2, dated 15 December 1993, Revised 21 November 1995; or

 

c.    an alternative method of compliance for the modifications required by (a) and

(b) above may be accomplished in accordance with the procedures contained in the Appendix to this Directive.

 

Note: FAA AD 96-24-17R1 refers.

 

Compliance: Unless already accomplished in accordance with the initial issue of this directive, before 31 March 1998.

 

The compliance of the initial issue of this directive remains unchanged. This amendment becomes effective on 21 January 1998.

Background:  This directive was issued to detect intergrannular corrosion in the wing spars, which if not found and repaired could cause structural failure of the wings.

 

Amendment 1 is issued in response to a revision of the related FAA AD, which clarifies certain inspections and procedures of the AD Appendix.

 

The original issue of this airworthiness directive became effective on 27 March 1997.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 

Appendix to AD/LUSCOMBE/2 Amdt 1

INSPECTION PROCEDURES FOR LUSCOMBE MODEL 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F AIRCRAFT THAT HAVE NOT ACCOMPLISHED THE INSPECTION IN ACCORDANCE WITH THE PROCEDURES IN THE DON LUSCOMBE AVIATION HISTORY FOUNDATION RECOMMENDATION #2, DATED DECEMBER 15, 1993; REVISED NOVEMBER 21, 1995.

 

  1. Remove all existing wing root fairings, wing inspection hole covers, and wing strut cover plates on both the right and left wing.

 

2.        Loosen the rear wing spar root attach bolts on both the right and left wings (one each wing) to permit a small wing deflection.

 

3.        Perform a visual inspection of the extruded rear spar aft face of the left and right wing.

 

4.        Inspect the face of the aft rear spar from the root to the spliced sheet metal tip spar at the wing root fairing location.

 

5.         To permit removal of the wing strut, unbolt the wing strut and remove the strut

carefully.

 

Note: In the location under the forward spars, support the wing half at normal height by any stable means, such as a ladder and padded lashed block. This will support the wing as the wing strut is removed. Avoid excess vertical deflection of the wing as this may stress the wing root attach point.

 

6.        Using suitable light and the access gained by the wing strut hole, visually inspect the front of the rear spar and the rear of the front spar for abnormal bulges or erupted spar surfaces.

 

7.        Remove the wing tip fairing by drilling out the rivets (using a #30 drill or smaller), and inspect the spars for abnormal bulges or erupted spar surfaces in the “U channel attach area" of each spar, and the outer lengths to the splices of the sheet metal spar extrusions.

 

Note: Inspection of the front of the front spar may be performed by using the existing inspection holes and a “light trolley" on the upper aileron cable ( the illumination from the light trolley must be sufficient to provide for adequate inspection). Attach the light trolley to the upper aileron cable with a tie wrap, connect a wire or rope of suitable length to the tie wrap and use this as a means to move the light along the face of the spar.

 

8.        Replace rivets through the skin and front / rear spars with AN426 flush rivets to secure former, spar and skin. Install at least 6 rivnuts (3 on top / 3 on bottom) through the skin and former. Reattach wing tip fairings with #8/32 rivnuts or #8/32 x ½ machine screws, through the fairing, skin, and formers.

 

9.        Reassemble wing strut on inspected wing, protecting the root joint by avoiding excess vertical deflection. Check the lock nuts for wear and replace as necessary. Torque the strut ends and wing root bolts using the appropriate torque.

 

10.    If evidence of intergranular corrosion is detected, remove and replace the corroded part with an airworthy part.

 

11.    Upon completion of the inspection, replace the wing root fairings, wing inspection hole covers and wing strut covers.

 

Note: Text in the above Appendix that is highlighted in “bold”, is the text that has been changed from or added to the Appendix of the initial issue of this Directive.

Overview

The Civil Aviation Regulations 1998, Part 39, Schedule of Airworthiness Directives, pertains to the regulations governing the maintenance and inspection of aircraft to ensure their airworthiness. One specific directive, AD/LUSCOMBE/2 Amdt 1, addresses the problem of intergranular corrosion in the wing spars of Luscombe Model 8 Series Aeroplanes, including models 8, 8A, 8B, 8C, 8D, 8E, 8F, and T-8F. This directive was enacted to prevent structural failure of the wings due to undetected corrosion, which could lead to catastrophic consequences during flight. The Civil Aviation Safety Authority, as the enacting body, aims to ensure that all affected aircraft undergo thorough inspections and necessary repairs to maintain safety standards. Compliance with this directive is mandatory, and it requires all aircraft of the specified models to be inspected for corrosion and, if found, to have the corroded parts replaced before further flight. Additionally, for aircraft with metal-covered wings, specific modifications such as installing additional inspection holes and modifying wing tip fairings are mandated to facilitate better inspection and maintenance practices.

Scope and Application

This legislative instrument, F2006B11190, applies specifically to all models of Luscombe Model 8 series aeroplanes, including the 8, 8A, 8B, 8C, 8D, 8E, 8F, and T-8F (all serial numbers). The primary objective of this legislation is to mandate the inspection of these aircraft for intergranular corrosion in the front and rear spar extrusions of the wing installations, with specific requirements for replacement if corrosion is detected. For aircraft with fabric-covered wings, the inspection must adhere to the procedures outlined in the Compliance Procedures section, paragraph "1A. Fabric Covered Wings." Alternatively, for metal-covered wings, additional wing inspection holes must be installed, and the wing tip fairing must be modified as per specified DLAHF Kit instructions. This directive is effective across the Commonwealth of Australia and aligns with the Civil Aviation Regulations 1998, specifically under PART 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives. Compliance with this directive must be completed by 31 March 1998, unless already addressed in the initial directive issued on 27 March 1997.

Key Provisions

The Luscombe Model 8 Series Aeroplanes Airworthiness Directive (AD/LUSCOMBE/2Amdt 1) specifies the necessary measures to address intergranular corrosion in the wing spars of affected aircraft models (Section 1). The directive applies to Luscombe Model 8, 8A, 8B, 8C, 8D, 8E, 8F, and T-8F (all serial numbers). It mandates inspections for corrosion in the front and rear spar extrusions of the wing installations (Section 1.1). If corrosion is detected, the directive requires the replacement of the corroded part in accordance with the specified procedures (Section 1.1). For aircraft with metal-covered wings, the directive further requires the installation of additional wing inspection holes and modification of the wing tip fairing (Section 1.2). The directive provides an alternative method for compliance with these modifications through procedures detailed in the Appendix (Section 1.2.c). Compliance with the directive must be achieved before 31 March 1998, unless already completed under the initial directive issue (Section Compliance). The obligations imposed by this directive include conducting thorough inspections for intergranular corrosion in the specified wing spar areas of the aircraft (Section 1). Aircraft owners and operators must ensure that any detected corrosion is rectified by replacing the affected parts in accordance with the procedures outlined in the directive (Section 1.1). For aircraft with metal-covered wings, additional obligations include installing two more wing inspection holes and modifying the wing tip fairing as specified (Section 1.2). Owners and operators must follow the detailed procedures in the Appendix if they choose to use the alternative compliance method (Section 1.2.c). The directive also requires reassembly of the wing components after inspection, ensuring all fasteners are properly installed and torqued (Section 8). Failure to comply with the AD/LUSCOMBE/2Amdt 1 could result in significant safety risks, as intergranular corrosion in the wing spars can lead to structural failure. Although the directive does not explicitly state penalties for non-compliance, non-compliance could result in the aircraft being deemed unairworthy, which could lead to grounding and potential legal consequences under civil aviation safety regulations. Operators found to be in violation of airworthiness directives may face enforcement actions from the Civil Aviation Safety Authority (CASA), including fines, suspension of operating certificates, or other regulatory penalties as deemed appropriate under the Civil Aviation Act 1988 and Civil Aviation Regulations 1998.

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