Airworthiness Directives; Aerospatiale Model SN 601 (Corvette) Series Airplanes

[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

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