[Federal Register Volume 60, Number 141 (Monday, July 24, 1995)]
[Rules and Regulations]
[Pages 37817-37818]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17032]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-112-AD; Amendment 39-9305; AD 95-15-02]
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 an inspection of fittings of the engine mount
structure to determine whether fasteners have been installed in
inspection holes and to determine whether those holes are oversized. It
also requires various follow-on actions, depending upon the results of
the inspection. This amendment is prompted by reports indicating that
fasteners were installed in the inspection hole of the engine ``W''
frame socket fittings and the inspection hole was oversized due to
fatigue cracking. The actions specified by this AD are intended to
prevent such fatigue cracking, which could lead to failure of the
fasteners and consequent separation of the engine from the airframe.
DATES: Effective August 23, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 23, 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 April 19, 1995 (60 FR 19551). That action proposed to
require performing a detailed visual inspection of ``W'' frame socket
fittings of the engine mount structure to determine whether drive
screws or blind rivets have been installed in inspection holes and to
determine whether those holes are oversized. It also proposed to
require various follow-on actions, depending upon the results of the
inspection.
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 25 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 $43,500, or
$1,500 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
[[Page 37818]]
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-15-02 British Aerospace Regional Aircraft Limited (Formerly
British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs
Aircraft Limited): Amendment 39-9305. Docket 94-NM-112-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 (c) 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 fatigue cracking, which could lead to the possible
separation of the engine from the airframe, accomplish the
following:
(a) Within 12 months after the effective date of this AD,
perform a detailed visual inspection of ``W'' frame socket fittings
of the engine mount structure to determine whether drive screws or
blind rivets have been installed in inspection holes and to
determine whether those holes are oversized, in accordance with the
Accomplishment Instructions, section 2.1 PART ONE, paragraphs A.,
B., C., D., E., and F., of British Aerospace Preliminary Technical
Leaflet (PTL) 501, dated May 1, 1994.
(b) If drive screws or blind rivets are found installed, or if
the inspection holes are found to be oversized, during the
inspection required by paragraph (a) of this AD, at the next
scheduled engine removal, but no later than 12 months after the
effective date of this AD, perform a nondestructive test (NDT) to
detect discontinuities (i.e., cracks, corrosion, and mechanical
damage) at inspection holes; rework the hole or replace the ``W''
frame fitting with a new or serviceable part; and perform the
specified follow-on actions; in accordance with the Accomplishment
Instructions, section 2.2 PART TWO, paragraphs A., B., C., D., E.,
and F., of British Aerospace Preliminary Technical Leaflet (PTL)
501, dated May 1, 1994.
(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, 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.
(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 inspection and test shall be done in accordance with
British Aerospace Preliminary Technical Leaflet (PTL) 501, dated May
1, 1994, which contains the following list of effective pages:
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Revision level shown Date shown on
Page No. on page page
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1-9.............................. Original............ May 1, 1994.
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Appendix 1
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1-6.............................. Original............ January 1,
1994.
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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 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.
(f) This amendment becomes effective on August 23, 1995.
Issued in Renton, Washington, on July 6, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-17032 Filed 7-21-95; 8:45 am]
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