[Federal Register Volume 60, Number 75 (Wednesday, April 19, 1995)]
[Proposed Rules]
[Pages 19549-19551]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-9624]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-166-AD]
Airworthiness Directives; British Aerospace Model Viscount 744,
745D, and 810 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all British Aerospace Model
Viscount 744, 754D, and 810 airplanes. This proposal would require an
inspection to detect corrosion of the tailplane assemblies, and
correction of discrepancies. This proposal is prompted by a report of
corrosion on the main spar top and bottom forward boom of the tailplane
assemblies and reports of cracking in the upper root joint attachment
fitting. The actions specified by the proposed AD are intended to
prevent such cracking or corrosion of the main spar forward booms or
the upper root joint attachment fitting, which consequently
[[Page 19550]] could lead to the failure of the tailplane assemblies;
this condition could result in reduced controllability of the airplane.
DATES: Comments must be received by May 30, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-166-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from 94-NM-166-AD. This information may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington.
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) 227-1320.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-166-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 94-NM-166-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority, which is the airworthiness authority
for the United Kingdom, recently notified the FAA that an unsafe
condition may exist on all British Aerospace Model Viscount 744, 754D,
and 810 airplanes. The CAA advises that it has received a report of
corrosion on the main spar top and bottom forward boom of the tailplane
assemblies. Several incidents of cracking have also been discovered in
the upper root joint attachment fitting. The effects of such cracking
or corrosion could lead to the failure of the main spar forward booms
or the upper root joint attachment fitting, which consequently could
lead to the failure of the tailplane assemblies. This condition, if not
corrected, could result in reduced controllability of the airplane.
British Aerospace has issued Viscount Alert Preliminary Technical
Leaflet (PTL) 182, Issue 2, dated August 7, 1992 (for Model Viscount
810 airplanes); and Viscount PTL 313, Issue 2, dated February 1, 1993
(for Model Viscount 744, 754D, airplanes), which describe procedures
for performing an inspection to detect corrosion of the tailplane
assemblies, and correction of discrepancies. The CAA classified these
PTL's as mandatory.
These airplane models are manufactured in the United Kingdom and
are type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require an inspection to
detect corrosion of the tailplane assemblies, and correction of
discrepancies. The actions would be required to be accomplished in
accordance with the PTL's described previously.
The FAA estimates that 29 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 160 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $278,400, or $9,600 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption addresses.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
[[Page 19551]] 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:
British Aerospace Regional Aircraft Limited (Formerly British
Aerospace Commercial Aircraft Limited, Vickers-Armstrongs Aircraft
Limited): Docket 94-NM-166-AD.
Applicability: All Model Viscount 744, 754D, 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 (b) 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 cracking or corrosion of the main spar forward booms
or the upper root joint attachment fitting, which consequently could
lead to the failure of the tailplane assemblies and reduce the
controllability of the airplane, accomplish the following:
(a) Prior to the accumulation of 8 years of service since date
of manufacture of this airplane, or within 18 months after the
effective date of this AD, whichever occurs later, perform an
inspection to detect corrosion of the tailplane assemblies, in
accordance with British Aerospace Regional Aircraft Limited Viscount
Alert Preliminary Technical Leaflet (PTL) 182, Issue 2, dated August
7, 1992 (for Model Viscount 810 airplanes), or Viscount PTL 313,
Issue 2, dated February 1, 1993 (for Model Viscount 744, 754D,
airplanes), as applicable. If corrosion is detected during the
inspection, prior to further flight, correct the discrepancies in
accordance with the service bulletin. Thereafter, repeat the
inspection at intervals not to exceed 8 years.
(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, 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.
(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.
Issued in Renton, Washington, on April 13, 1995.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-9624 Filed 4-18-95; 8:45 am]
BILLING CODE 4910-13-U
