[Federal Register Volume 63, Number 208 (Wednesday, October 28, 1998)]
[Rules and Regulations]
[Pages 57582-57583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28536]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-161-AD; Amendment 39-10855; AD 98-22-08]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model SN 601 (Corvette)
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Aerospatiale Model SN 601 (Corvette) series
airplanes, that requires repetitive inspections to detect discrepancies
of the upper and lower reinforcement panels and panel fasteners of the
wing roots; and corrective actions, if necessary. This amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
this AD are intended to prevent debonding of the upper and lower
reinforcement panels of the wing roots, which could result in reduced
structural integrity of the wing.
DATES: Effective December 2, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 2, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex
03, France. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Aerospatiale Model SN 601
(Corvette) series airplanes was published in the Federal Register on
August 27, 1998 (63 FR 45775). That action proposed to require
repetitive inspections to detect discrepancies of the upper and lower
reinforcement panels and panel fasteners of the wing roots; and
corrective actions, if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
The FAA estimates that 1 airplane of U.S. registry will be affected
by this AD, that it will take approximately 2 work hours per airplane
to accomplish the required inspection, and that the average labor rate
is $60 per work hour. Based on these figures, the cost impact of the
inspection required by this AD on the single U.S. operator is estimated
to be $120, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-22-08 Aerospatiale: Amendment 39-10855. Docket 98-NM-161-AD.
Applicability: Model SN 601 (Corvette) series airplanes on which
Aerospatiale Modification 1049 has been installed, certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 (c) 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 as indicated, unless accomplished
previously.
To prevent debonding of the upper and lower reinforcement panels
of the wing roots, which could result in reduced structural
integrity of the wing, accomplish the following:
(a) For airplanes that have been modified in accordance with
Aerospatiale Corvette Service Bulletin 57-25, dated November 21,
1990: Within 8,300 flight cycles after installation of the
modification, or within 100 flight cycles after the effective date
of this AD, whichever occurs later, perform a sonic resonance
inspection to detect debonding of the upper and lower
[[Page 57583]]
reinforcement panels of the wing roots and a visual inspection to
detect fatigue damage of the panel fasteners, in accordance with the
Accomplishment Instructions of Aerospatiale Corvette Service
Bulletin 57-24, Revision 1, dated May 30, 1994.
(1) If no panel debonding or fastener damage is found, repeat
the sonic resonance inspection and the visual inspection thereafter
at intervals not to exceed 1,000 flight cycles.
(2) If any panel debonding or fastener damage is found, prior to
further flight, repair in accordance with a method approved by
either the Manager, International Branch, ANM-116, or the Direction
Generale de l'Aviation Civile (DGAC), which is the airworthiness
authority for France (or its delegated agent).
(b) For airplanes that have not been modified in accordance with
Aerospatiale Corvette Service Bulletin 57-25, dated November 21,
1990: Prior to the accumulation of 8,200 total flight cycles, or
within 100 flight cycles after the effective date of this AD,
whichever occurs later, perform a sonic resonance inspection to
detect debonding of the upper and lower reinforcement panels of the
wing roots, and a visual inspection to detect fatigue damage of the
panel fasteners, in accordance with the Accomplishment Instructions
of Aerospatiale Corvette Service Bulletin 57-24, Revision 1, dated
May 30, 1994.
(1) For any reinforcement panel on which no debonding or
fastener damage is found, repeat the sonic resonance inspection and
the visual inspection thereafter at intervals not to exceed 2,500
flight cycles or three years, whichever occurs first.
(2) For any reinforcement panel on which debonding is detected,
and the total debonded area is less than or equal to 45% of the
total area, and no contiguous debonded area on the panel is greater
than 5% of the total area of the panel, repeat the sonic resonance
inspection and the visual inspection thereafter at the interval
specified in paragraph (b)(2)(i), (b)(2)(ii), or (b)(2)(iii), as
applicable, of this AD.
(i) If the total debonded area on the panel is less than or
equal to 10% of the total area, repeat the inspections of that panel
thereafter at intervals not to exceed 2,500 flight cycles or 3
years, whichever occurs first.
(ii) If the total debonded area on the panel is greater than 10%
and less than or equal to 30% of the total area, repeat the
inspections of that panel thereafter at intervals not to exceed
2,000 flight cycles or 3 years, whichever occurs first.
(iii) If the total debonded area of the panel is greater than
30% and less than or equal to 45% of the total area, repeat the
inspections of that panel thereafter at intervals not to exceed
1,000 flight cycles or 2 years, whichever occurs first.
(3) For any reinforcement panel on which debonding is detected,
and the total debonded area of the panel is greater than 45% of the
total area, or if any single debonded area on any single panel is
greater than 5% of the total area of that panel, or if any panel
fastener damage is detected, accomplish the actions specified in
paragraphs (b)(3)(i) and (b)(3)(ii) of this AD.
(i) Prior to further flight, inspect the skin to determine the
level of corrosion relative to the skin thickness in accordance with
a method approved by either the Manager, International Branch, ANM-
116, or the DGAC (or its delegated agent).
(A) If the depth of corrosion of the skin is less than or equal
to 10% of the skin thickness, remove and replace the panel and treat
the skin for corrosion, in accordance with the Accomplishment
Instructions of Aerospatiale Corvette Service Bulletin 57-25, dated
November 21, 1990.
(B) If the depth of corrosion of the skin exceeds 10% of the
skin thickness, repair in accordance with a method approved by the
Manager, International Branch, ANM-116, or in accordance with a
method approved by the DGAC (or its delegated agent).
(ii) For airplanes on which the actions of paragraph
(b)(3)(i)(A) of this AD have been accomplished: Within 8,300 flight
cycles after accomplishment of paragraph (b)(3)(i)(A) of this AD,
perform a sonic resonance inspection to detect debonding of the
panel and a visual inspection to detect fatigue damage of the panel
fasteners, in accordance with the Accomplishment Instructions of
Aerospatiale Corvette Service Bulletin 57-24, Revision 1, dated May
30, 1994.
(A) If no debonding or fastener damage is found, repeat the
inspection thereafter at intervals not to exceed 1,000 flight
cycles.
(B) If any debonding or fastener damage is detected, prior to
further flight, repair in accordance with a method approved by the
Manager, International Branch, ANM-116, or in accordance with a
method approved by the DGAC (or its delegated agent).
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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) Except as provided by paragraphs (a)(2), (b)(3)(i),
(b)(3)(i)(B), and (b)(3)(ii)(B) of this AD, the actions shall be
done in accordance with Aerospatiale Corvette Service Bulletin 57-
25, dated November 21, 1990, and Aerospatiale Corvette Service
Bulletin 57-24, Revision 1, dated May 30, 1994. This incorporation
by reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse,
Cedex 03, France. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
Note 3: The subject of this AD is addressed in French
airworthiness directive 91-045-010(B)R1, dated August 3, 1994.
(f) This amendment becomes effective on December 2, 1998.
Issued in Renton, Washington, on October 19, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-28536 Filed 10-27-98; 8:45 am]
BILLING CODE 4910-13-U
