[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