AD 96-24-17 R1

This document clarifies information in airworthiness directive (AD) 96-24-17, which applies to Don Luscombe Aviation History Foundation (Luscombe) Models 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F airplanes. AD 96-24-17 currently requires installing new inspection holes, modifying the wing tip fairings, and inspecting the wing spars for intergranular corrosion. The actions specified in AD 96-24-17 are intended to prevent wing spar failure from intergranular corrosion, which could result in structural failure of the wings and loss of control of the airplane. The AD was published with an Appendix providing an alternative method of compliance. Since issuance of AD 96-24-17, the FAA has re-examined the Appendix and has determined that clarification of certain inspections procedures is needed. This action clarifies the procedures specified in the Appendix of AD 96-24-17.

Final rule; correction.

96-24-17 R1 THE DON LUSCOMBE AVIATION HISTORY FOUNDATION (formerly The Luscombe Aircraft Company): Amendment 39-10229; Docket No. 95-CE-99-AD. Revises AD 96-24-17, Amendment 39-9841.

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

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required within the next 12 calendar months after January 27, 1997 (the effective date of AD 96-24-17), unless already accomplished (compliance with AD 96-24-17).

To prevent wing spar failure from intergranular corrosion, which could result in structural failure of the wings and loss of control of the airplane, accomplish the following:

(a) For airplanes 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.) through (a9.), and (b.) of The Don Luscombe Aviation History Foundation Recommendation #2, dated December 15, 1993, REVISED November 21, 1995; and,

(2) 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.) through (c5.) of The Don Luscombe Aviation History Foundation Recommendation #2, dated December 15, 1993, REVISED November 21, 1995.

(b) For all affected airplanes, inspect one time 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 December 15, 1993, REVISED November 21, 1995, whichever paragraph is applicable to the wing construction of the airplane.

(c) For airplanes with metal covered wings, an alternative method of compliance for the required modification in paragraphs (a)(1) and (a)(2) of this AD can be accomplished in accordance with the procedures contained in the Appendix to this AD, unless already accomplished (compliance with AD 96-24-17).

NOTE 2: Although not required by this AD, the FAA recommends inspection of the spars for other forms of corrosion which may be a result of nest residue from rodent, bird, or insect infestation within the cavity of the wing. Advisory Circular 43-4A, Corrosion Control for Aircraft, dated July 25, 1991, contains the recommended maintenance procedures for treatment of such corrosion.

(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(e) An alternative method of compliance (AMOC) or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., Lakewood, California, 90712. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. AMOC's approved in accordance with AD 96-24-17, are considered approved as AMOC's with this AD, including:

(1) DLAHF Service Recommendation #2, dated December 15, 1993, Revised: September 9, 1997, is an AMOC for the wing modifications, wing-tip modifications, corrosion inspection and replacement requirements, and general inspection/modification requirements of paragraphs (a)(1), (a)(2), (b), and (f) of this AD, respectively.

(2) J. Norris Luscombe Service Recommendation #97-1, Revision dated September 10, 1997, is an AMOC for the alternative inspection procedures in the Appendix to this AD.

(3) DLAHF Service Recommendation #7, dated October 23, 1997 (no revision), is an AMOC for the wing modifications, wing-tip modification, corrosion inspection and replacement requirements, and general inspection/modification requirements of paragraphs (a)(1), (a)(2), (b), and (f) of this AD, respectively.

NOTE 3: Information concerning the existence of AMOC's with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office.

(f) The inspections and modifications required by this AD shall be done in accordance with The Don Luscombe Aviation History Foundation Recommendation #2, dated December 15, 1993, REVISED November 21, 1995. This incorporation by reference was previously approved by the Director of the Office of the Federal Register as of January 27, 1997 (61 FR 66900, December 19, 1996), in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from The Don Luscombe Aviation History Foundation, P.O. Box 63581, Phoenix, Arizona 85082. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This amendment (39-10229) becomes effective on January 27, 1997.

APPENDIX TO AD 96-24-17 R1

I. ALTERNATIVE INSPECTION PROCEDURES FOR LUSCOMBE MODEL 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F AIRPLANES 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 angulation.

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.

NOTE: In the location under the forward spars, support both wings 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 angulation of the wing as this may stress the wing root attach point.

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

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. (See also Note 2 in the body of AD 96-24-17 R1).

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. (See Note 2 in the body of AD 96-24-17 R1).

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 light trolley is made from a standard clear 110 volt bathroom night light connected to a candelabra socket lamp extension cord. Attach the light trolley to the upper aileron cable with a tie wrap, connect a wire 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 1/2 machine screws, through the fairing, skin, and formers.

9. Reassemble the 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 adequate torque (do not over torque the attach fittings).

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.

Discussion
On November 25, 1996, the FAA issued AD 96-24-17, Amendment 39-9841 (61 FR 66900, December 19, 1996), which applies to Luscombe Models 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F airplanes. This AD currently requires installing a total of four additional wing inspection holes in the metal covered wings to assist in conducting a more thorough examination of the wing spars, modifying the wing tip fairing so that it is removable, and providing easier access to the interior of the wings. A one time inspection for intergranular corrosion is required for both metal covered and fabric covered wings on these Luscombe 8 series airplanes in the areas of the front and rear spar extrusions of the wing installations.

Need for the Correction
AD 96-24-17 was published with an Appendix that provided an alternative method of compliance. The FAA has received reports that certain portions of the Appendix need clarification. Therefore, the FAA re-examined the procedures specified in the Appendix and has clarified items 2, 4, 6, 7, and 8, as well as clarifying a note regarding additional wing support.

Correction of Publication
This document clarifies the Appendix to AD 96-24-17, and adds the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).

The AD, as corrected, is being printed in its entirety for the convenience of affected operators. The effective date of the AD remains January 27, 1997, which is the effective date of the AD as originally issued.

Since this action only clarifies the Appendix instructions, it has no adverse economic impact and imposes no additional burden on any person. Therefore, the FAA has determined that prior notice and opportunity for public comment are unnecessary.

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Correction
Accordingly, pursuant to the authority delegated to me by the Administrator, theFederal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13, is amended by removing Airworthiness Directive (AD) 96-24-17, Amendment 39-9841 (61 FR 66900, December 19, 1996), and by adding a new AD to read as follows: