[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]
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