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

[Federal Register Volume 64, Number 218 (Friday, November 12, 1999)]
[Rules and Regulations]
[Pages 61475-61477]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28745]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-365-AD; Amendment 39-11402; AD 99-23-06]
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 all Aerospatiale Model SN-601 (Corvette) series 
airplanes, that requires repetitive inspections, and repair if 
necessary, of the locking indication system of the drag strut jack on 
the main landing gear (MLG) to detect corrosion and damage resulting 
from its operation. This proposal also requires replacement of seals 
and backup rings with new parts. 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 failure of the locking indication system of the drag strut 
jack on the MLG due to corrosion. Such corrosion could prevent the MLG 
from locking and result in the subsequent collapse of the MLG.

DATES: Effective December 17, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 17, 1999.

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

[[Page 61476]]

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 all Aerospatiale Model SN-601 
(Corvette) series airplanes was published in the Federal Register on 
September 10, 1999 (64 FR 49113). That action proposed to require 
repetitive inspections, and repair if necessary, of the locking 
indication system of the drag strut jack on the main landing gear (MLG) 
to detect corrosion and damage resulting from its operation. That 
action also proposed to require replacement of seals and backup rings 
with new parts.

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 2 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
airplane to accomplish the inspection, and that the average labor rate 
is $60 per work hour. The cost of required parts will be minimal. Based 
on these figures, the cost impact of this AD on U.S. operators is 
estimated to be $960, or $480 per airplane, 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:

99-23-06 Aerospatiale: Amendment 39-11402. Docket 98-NM-365-AD.

    Applicability: All Model SN-601 (Corvette) series airplanes, 
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 (b) 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 failure of the locking indication system of the drag 
strut jack on the main landing gear (MLG) due to corrosion that 
could prevent the MLG from locking and result in the subsequent 
collapse of the MLG, accomplish the following:
    (a) Within 3,600 flight hours or 36 months after the effective 
date of this AD, whichever occurs first, perform a detailed visual 
inspection to detect certain discrepancies of the locking indication 
system on the drag strut jack on the MLG, in accordance with 
Messier-Dowty Technical Instruction No. 20403, Issue 2, dated March 
1998. Prior to reassembling the parts, replace all the seals and 
backup rings with new parts, in accordance with the Technical 
Instruction.
    (1) If no corrosion is found on either plunger, prior to further 
flight, inspect for the free displacement of both plungers, in 
accordance with the Technical Instruction.
    (i) If the displacement of both plungers is free without any 
hard points, repeat the inspection required by paragraph (a) of this 
AD thereafter at intervals not to exceed 72 months.
    (ii) If the displacement of either plunger is not free, prior to 
further flight, replace the plunger with a new plunger, in 
accordance with the Technical Instruction. Repeat the inspection 
required by paragraph (a) of this AD thereafter at intervals not to 
exceed 72 months.
    (2) If corrosion is found on either plunger, prior to further 
flight, replace the plunger with a new plunger, in accordance with 
the Technical Instruction. Repeat the inspection thereafter at 
intervals not to exceed 72 months.
    (3) If no corrosion, marking, binding, or peening is found on 
any disassembled part removed from the stacking, other than the 
plungers, repeat the inspection thereafter at intervals not to 
exceed 72 months.
    (4) If any corrosion, marking, binding or peening is found on 
any disassembled parts removed from the stacking, other than the 
plungers, prior to further flight, replace the part with a new part, 
in accordance with the Technical Instruction. Repeat the inspection 
thereafter at intervals not to exceed 72 months.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Alternative Methods of Compliance

    (b) 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, FAA, 
Transport Airplane Directorate. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

[[Page 61477]]

Special Flight Permits

    (c) 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Messier-Dowty 
Technical Instruction No. 20403, Issue 2, dated March 1998. 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 4: The subject of this AD is addressed in French 
airworthiness directive 98-179-021(B), dated May 6, 1998.

    (e) This amendment becomes effective on December 17, 1999.

    Issued in Renton, Washington, on October 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-28745 Filed 11-10-99; 8:45 am]
BILLING CODE 4910-13-U

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