[Federal Register Volume 60, Number 182 (Wednesday, September 20, 1995)]
[Rules and Regulations]
[Pages 48633-48635]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22856]



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[[Page 48634]]



DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-111-AD; Amendment 39-9373; AD 95-19-11]


Airworthiness Directives; British Aerospace Model Viscount 744, 
745D, and 810 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 British Aerospace Model Viscount 744, 745D, and 810 
airplanes, that requires inspections to detect cracking of certain 
fittings of the tailplane spar, and replacement of the fittings with 
serviceable parts, if necessary. This amendment is prompted by reports 
of fatigue cracking of certain fittings in the tailplane spar. The 
actions specified by this AD are intended to prevent such cracking, 
which could result in structural degradation of the attachment of the 
horizontal stabilizer to the fuselage.

DATES: Effective October 20, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 20, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace Regional Aircraft Ltd., Engineering 
Support Manager, Military Business Unit, Chadderton Works, 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: William Schroeder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2148; fax (206) 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 British Aerospace Model 
Viscount 744, 745D, and 810 airplanes was published in the Federal 
Register on May 1, 1995 (60 FR 21056). That action proposed to require 
repetitive high frequency eddy current inspections to detect cracking 
of certain fittings of the tailplane spar, and replacement of the 
fittings with serviceable parts, if necessary.
    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. 
The FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed.
    The FAA estimates that 29 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $6,960, or $240 
per airplane.
    The total 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.
    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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-19-11  British Aerospace Regional Aircraft Limited (Formerly 
British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs 
Aircraft Limited): Amendment 39-9373. Docket 94-NM-111-AD.

    Applicability: All Model Viscount 744, 745D, and 810 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 use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent structural degradation of the attachment of the 
horizontal stabilizer to the fuselage, accomplish the following:
    (a) For Model Viscount 744 and 745D airplanes: Within 3,000 
landings or 3 years after the effective date of this AD, whichever 
occurs first, perform a high frequency eddy current (HFEC) 
inspection to detect cracking of the bolt holes on the top fittings 
of the root joint of the tailplane spar, in accordance with British 
Aerospace Alert Preliminary Technical Leaflet (PTL) 264, Issue 3, 
dated September 1, 1992. Repeat the inspection thereafter at 
intervals not to exceed 3,000 landings or 3 years, whichever occurs 
first.
    (b) For Model Viscount 810 airplanes: Within 1,000 landings or 1 
year after the effective date of this AD, whichever occurs first, 
perform an HFEC inspection to detect cracking of the bolt holes on 
the top fittings of the root joint of the tailplane spar, in 
accordance with British Aerospace Alert PTL 127, Issue 3, dated June 
1, 1992. Repeat the inspection thereafter at intervals not to exceed 
3,000 landings or 3 years, whichever occurs first. 

[[Page 48635]]

    (c) If any cracking is found during the inspections required by 
paragraph (a) or (b) of this AD, prior to further flight, replace 
the cracked fitting with a serviceable part, in accordance with 
British Aerospace Alert PTL 264, Issue 3, dated September 1, 1992 
(for Model 744 and 745D airplanes), or Alert PTL 127, Issue 3, dated 
June 1, 1992 (for Model 810 airplanes); as applicable.
    (d) 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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (e) 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.
    (f) The inspection and replacement shall be done in accordance 
with British Aerospace Alert Preliminary Technical Leaflet (PTL) 
264, Issue 3, dated September 1, 1992; or British Aerospace Alert 
PTL 127, Issue 3, dated June 1, 1992; as applicable. 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 
Ltd., Engineering Support Manager, Military Business Unit, 
Chadderton Works, 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.
    (g) This amendment becomes effective on October 20, 1995.

    Issued in Renton, Washington, on September 7, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-22856 Filed 9-19 -95; 8:45 am]
BILLING CODE 4910-13-U