[Federal Register Volume 63, Number 173 (Tuesday, September 8, 1998)]
[Proposed Rules]
[Pages 47440-47442]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-24064]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-217-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model Viscount 744,
745, 745D, and 810 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of 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 action would require 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 action also would limit the
applicability of the existing AD. This proposal is prompted by reports
of cracked and separated lower eye end fittings. The actions specified
by the proposed 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: Comments must be received by October 8, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-217-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 British Aerospace Regional Aircraft Limited, Chadderton
Division, Engineering Support, Greengate,
[[Page 47441]]
Middleton, Manchester M24 1SA, England. This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington.
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:
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 98-NM-217-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-114, Attention: Rules
Docket No. 98-NM-217-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On September 10, 1990, the FAA issued AD 90-20-17, amendment 39-
6744 (55 FR 38539, September 19, 1990), applicable to all British
Aerospace Model Viscount 700, 800, and 810 series airplanes, to require
repetitive visual, x-ray, ultrasonic, and dye penetrant inspections to
detect cracks and corrosion in the inboard and outboard engine nacelle
structures on the left and right wings; replacement of any cracked
fittings and mating struts; and treatment or replacement of any
corroded fittings or struts. That action was prompted by reports
indicating that nacelle lower eye end fittings had cracked and
separated due to fatigue failure or stress corrosion. The requirements
of that AD are intended to detect and correct fatigue or stress
corrosion cracking of the nacelle lower eye end fittings, which could
result in reduced structural integrity of the engine nacelle support
structures.
Actions Since Issuance of Previous Rule
Since the issuance of AD 90-20-17, the Civil Aviation Authority
(CAA), which is the airworthiness authority for the United Kingdom, has
determined that long-term continued operational safety would be better
assured by using eddy current inspections, rather than visual, x-ray,
ultrasonic, and dye penetrant inspections, to detect cracking and
corrosion in engine nacelle support structures. British Aerospace has
issued new service information to reflect this determination.
Explanation of Relevant Service Information
British Aerospace has issued 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). British
Aerospace also has issued PTL 197, Issue 3, including Appendices 1 and
2, all dated November 20, 1993 (for Model Viscount 810 series
airplanes). Those PTL's describe procedures for repetitive eddy current
inspections to detect cracking or corrosion of the eye end fittings of
the outboard engine lower support and of the bore of the taper pin
holes in the engine nacelle subframes, tubes, and fittings. The CAA
classified these PTL's as mandatory in order to assure the continued
airworthiness of these airplanes in the United Kingdom.
FAA's Conclusions
These airplane models are manufactured in the United Kingdom and
are type certificated for operation in the United States under the
provisions of Sec. 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.
Explanation of Requirements of Proposed Rule
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 supersede AD 90-20-17 to
require new repetitive eddy current 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
proposed AD also would limit the applicability of the existing AD. The
actions would be required to be accomplished in accordance with the
PTL's described previously, except as discussed below.
Differences Between Proposed Rule and Preliminary Technical
Leaflets
Operators should note that, although the PTL's specify that the
manufacturer may be contacted for disposition of repair conditions,
this proposal would require the repair of those conditions to be
accomplished in accordance with a method approved by either the FAA, or
the CAA (or its delegated agent). In light of the type of repair that
would be required to address the identified unsafe condition, and in
consonance with existing bilateral airworthiness agreements, the FAA
has determined that, for this proposed AD, a repair approved by either
the FAA or the CAA would be acceptable for compliance with this
proposed AD.
Explanation of Revisions to Applicability
The applicability of the proposed AD has been reduced to include
only 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. This change is
necessary to incorporate restrictions to the effectivity of the PTL's
that are specified in the Compliance paragraph of each PTL.
Other Relevant Rulemaking
The FAA previously has issued AD 98-12-17, amendment 39-10444 (63
FR 31347, June 9, 1998), which is applicable to all British Aerospace
Model Viscount 744, 745, 745D, and 810 series airplanes. That AD
requires repetitive inspections to detect cracking
[[Page 47442]]
and corrosion of components of the engine nacelle subframe structure;
corrective action, if any cracking or corrosion is found; and
replacement of any component that has reached its life limit with a new
or serviceable component. That AD references British Aerospace Viscount
Alert Preliminary Technical Leaflet (PTL) 500, dated January 1, 1993;
including Appendices 1 through 4 inclusive, dated November 1992, and
Appendix 5, dated October 1992; as the appropriate sources of service
information for accomplishment of the actions required by AD 98-12-17.
PTL 500 superseded and canceled British Aerospace Viscount Alert PTL
No. 122, Issue 4, and British Aerospace Viscount Alert PTL No. 258,
Issue 4, which were referenced in AD 90-20-17 as appropriate sources of
service information for accomplishment of certain actions required by
that AD. For this reason, those actions would not be mandated by this
new proposed AD.
Cost Impact
There are approximately 29 airplanes of U.S. registry that would be
affected by this proposed AD.
The new eddy current inspections that are proposed in this AD
action would 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 proposed requirements of 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 current or proposed
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 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:
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), to read as follows:
British Aerospace Regional Aircraft Limited (Formerly British
Aerospace Commercial Aircraft Limited, Vickers-Armstrongs Aircraft
Limited): 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).
(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
Secs. 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 September 1, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-24064 Filed 9-4-98; 8:45 am]
BILLING CODE 4910-13-U
