[Federal Register Volume 62, Number 232 (Wednesday, December 3, 1997)]
[Rules and Regulations]
[Pages 63828-63830]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-31680]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-99-AD; Amendment 39-10229; AD 96-24-17 R1]
RIN 2120-AA64


Airworthiness Directives; The Don Luscombe Aviation History 
Foundation Models 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F Airplanes; Correction

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: 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.

DATES: Effective January 27, 1997.
    The incorporation by reference of the Don Luscombe Aviation History 
Foundation Recommendation #2, dated December 15, 1993, revised November 
21, 1995, as listed in the regulations, was previously approved by the 
Director of the Federal Register as of January 27, 1997 (61 FR 66900, 
December 19, 1996).

FOR FURTHER INFORMATION CONTACT: Mr. Sol Davis, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, 3960 Paramount Boulevard, 
Lakewood, California 90712; telephone (562) 627-5233; facsimile (562) 
627-5210.

SUPPLEMENTARY INFORMATION:

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 Sec. 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, the Federal 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.


Sec. 39.13  [Amended]

    2. Section 39.13, is amended by removing Airworthiness Directive 
(AD) 96-24-17, Amendment 39-9841 (61 FR

[[Page 63829]]

66900, December 19, 1996), and by adding a new AD to read as follows:

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 
Secs. 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 Federal Register as of January 27, 
1997 (61 FR 66900, December 19, 1996). 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.

[[Page 63830]]

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.

    Issued in Kansas City, Missouri on November 25, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-31680 Filed 12-2-97; 8:45 am]
BILLING CODE 4910-13-U