Airworthiness Directives; British Aerospace Model Viscount 744, 745, 745D, and 810 Series Airplanes

[Federal Register Volume 63, Number 218 (Thursday, November 12, 1998)]
[Rules and Regulations]
[Pages 63130-63132]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30053]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-217-AD; Amendment 39-10880; AD 98-23-13]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Model Viscount 744, 
745, 745D, and 810 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all British Aerospace Model Viscount 700, 800, and 
810 series airplanes, that currently requires repetitive inspections to 
detect cracks and corrosion in the inboard and outboard engine nacelle 
structures on the wings; replacement of any cracked fittings and mating 
struts; and treatment or replacement of any corroded fittings or 
struts. This amendment requires repetitive inspections to detect 
cracking or corrosion of the eye end fittings of the outboard engine 
lower support or of the bore of the taper pin holes, and repair, if 
necessary. This amendment also limits the applicability of the existing 
AD. This amendment is prompted by reports of cracked and separated 
lower eye end fittings. The actions specified by this AD are intended 
to detect and correct cracking of the eye end fittings of the outboard 
engine lower support, which could result in reduced structural 
integrity of the engine nacelle support structures.

DATES: Effective December 17, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director

[[Page 63131]]

of the Federal Register as of December 17, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace Regional Aircraft Limited, Chadderton 
Division, Engineering Support, Greengate, Middleton, Manchester M24 
1SA, England. 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) by superseding AD 90-20-17, 
amendment 39-6744 (55 FR 38539, September 19, 1990), which is 
applicable to all British Aerospace Model Viscount 700, 800, and 810 
series airplanes, was published in the Federal Register on September 8, 
1998 (63 FR 47440). The action proposed to require new repetitive 
inspections to detect cracking or corrosion of the eye end fittings of 
the outboard engine lower support or of the bore of the taper pin 
holes, and repair, if necessary. The action also proposed to limit the 
applicability of the existing AD.

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

    There are approximately 29 airplanes of U.S. registry that will be 
affected by this AD.
    The new eddy current inspections that are required in this AD take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the inspections required by this AD on U.S. operators is 
estimated to be $3,480, or $120 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 removing amendment 39-6744 (55 FR 
38539, September 19, 1990), and by adding a new airworthiness directive 
(AD), amendment 39-10880, to read as follows:

98-23-13  British Aerospace Regional Aircraft Limited (Formerly 
British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs 
Aircraft Limited): Amendment 39-10880. Docket 98-NM-217-AD. 
Supersedes AD 90-20-17, amendment 39-6744.

    Applicability: Model Viscount 744, 745, and 745D series 
airplanes, on which British Aerospace Modification D3227 has not 
been accomplished; and Model Viscount 810 series airplanes, on which 
British Aerospace Modification FG 2103 has not been accomplished; 
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 detect and correct cracking of the eye end fittings of the 
outboard engine lower support, which could result in reduced 
structural integrity of the engine nacelle support structures, 
accomplish the following:
    (a) Perform an eddy current inspection to detect cracking or 
corrosion of the eye end fittings of the outboard engine lower 
support, or of the bore of the taper pin holes, in accordance with 
the Accomplishment Instructions of British Aerospace Preliminary 
Technical Leaflet (PTL) No. 326, Issue 2, including Appendices 1 and 
2, all dated December 1, 1994 (for Model Viscount 744, 745, and 745D 
series airplanes); or PTL 197, Issue 3, including Appendices 1 and 
2, all dated November 20, 1993 (for Model Viscount 810 series 
airplanes); at the applicable time specified in either paragraph 
(a)(1) or (a)(2) of this AD. Thereafter, repeat the inspection at 
intervals not to exceed 900 landings.
    (1) For Model Viscount 744, 745, and 745D series airplanes: 
Inspect within 3 months after the effective date of this AD.
    (2) For Model Viscount 810 series airplanes: Inspect within 900 
landings after the last inspection performed in accordance with PTL 
197, Issue 2, dated July 10, 1992; or within 3 months after the 
effective date of this AD; whichever occurs later.
    (b) If any cracking is found during any inspection performed in 
accordance with paragraph (a) of this AD, prior to further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Civil Aviation Authority (or its delegated agent).

[[Page 63132]]

    (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) The inspections shall be done in accordance with the 
following British Aerospace Regional Aircraft Preliminary Technical 
Leaflets, which contain the specified effective pages:

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Preliminary technical leaflet referenced    Page number   Revision level
                and date                   shown on page   shown on page            Date shown on page
----------------------------------------------------------------------------------------------------------------
PTL 326, Issue 2, December 1, 1994......             1-6               2  December 1, 1994.
                                                    APPENDIX 1
                                                     1-6               2  December 1, 1994.
                                                    APPENDIX 2
                                                     1-6               2  December 1, 1994.
PTL 197, Issue 3, November 20, 1993.....             1-8               3  November 20, 1993.
                                                    APPENDIX 1
                                                     1-6               3  November 20, 1993.
                                                    APPENDIX 2
                                                     1-7        Original  November 20, 1993.
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    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 British Aerospace Regional 
Aircraft Limited, Chadderton Division, Engineering Support, 
Greengate, Middleton, Manchester M24 1SA, England. 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.
    (f) This amendment becomes effective on December 17, 1998.

    Issued in Renton, Washington, on November 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-30053 Filed 11-10-98; 8:45 am]
BILLING CODE 4910-13-P

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