[Federal Register Volume 63, Number 156 (Thursday, August 13, 1998)]
[Proposed Rules]
[Pages 43338-43340]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21720]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-305-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model BAe.125, DH.125, BH.125,
and HS.125 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise an existing airworthiness
directive (AD), applicable to certain Raytheon Model BAe.125, DH.125,
BH.125, and HS.125 series airplanes, that currently requires inspection
of the elevator mass balance side plate assembly and spigot for
corrosion, and repair, if necessary; application of corrosion
protection treatment; and installation of corrosion resistant Monel
rivets in the elevator balance weight structure. That AD was prompted
by reports of corrosion on the elevator mass balance side plate
assembly and the balance weight spigot. The actions specified by that
AD are intended to prevent such corrosion damage, which could lead to
displacement of the side plate and consequent control surface
interference and jamming of flight controls. This action would limit
the applicability of the existing AD.
DATES: Comments must be received by September 28, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-305-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 Raytheon Aircraft Company, Manager Service Engineering,
Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Mark Quam, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2145; 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 97-NM-305-AD.'' The postcard will be date stamped and
returned to the commenter.
[[Page 43339]]
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. 97-NM-305-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On August 7, 1989, the FAA issued AD 89-18-07, amendment 39-6297
(54 FR 33874, August 17, 1989), applicable to certain Raytheon Model
BAe.125, DH.125, BH.125, and HS.125 series airplanes, to require
inspection of the elevator mass balance side plate assembly and spigot
for corrosion, and repair, if necessary; the application of corrosion
protection treatment; and installation of corrosion resistant Monel
rivets in the elevator balance weight structure. That action was
prompted by reports of corrosion on the elevator mass balance side
plate assembly and the balance weight spigot. The requirements of that
AD are intended to prevent such corrosion, which could lead to
displacement of the side plate and consequent control surface
interference and jamming of flight controls.
Actions Since Issuance of Previous Rule
Since the issuance of AD 89-18-07, the FAA has reviewed and
approved Revision 3 of British Aerospace Service Bulletin S.B. 27-142,
dated November 13, 1989. This revised service bulletin is essentially
identical to Revision 2 of the service bulletin, which was referenced
in AD 89-18-07 as the appropriate source of service information. The
only relevant change is a revised effectivity listing that includes the
statement, ``up to and including series 700.''
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would revise AD 89-18-07. It would continue to require
inspection of the elevator mass balance side plate assembly and spigot
for corrosion, and repair, if necessary; application of corrosion
protection treatment; and installation of corrosion resistant Monel
rivets in the elevator balance weight structure. The proposed AD also
would limit the applicability of the existing AD. The actions would be
required to be accomplished in accordance with the service bulletin
described previously.
Cost Impact
Since this proposed AD would merely delete airplanes from the
applicability of the rule, it would add no additional costs, and would
require no additional work to be performed by affected operators. The
current costs associated with this amendment are reiterated in their
entirety (as follows) for the convenience of affected operators:
The FAA estimates that 346 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 10 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
cost impact of the proposed AD on U.S. operators is estimated to be
$207,600, or $600 per airplane.
The 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.
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 39-6297 (54 FR
33874, August 17, 1989), and by adding a new airworthiness directive
(AD), to read as follows:
Raytheon Aircraft Company (Formerly Beech, Raytheon Corporate Jets,
British Aerospace, Hawker Siddeley, et al.): Docket 97-NM-305-AD.
Revises AD 89-18-07, Amendment 39-6297.
Applicability: Model BAe.125, DH.125, BH.125, and HS.125 series
airplanes; up to and including series 700; 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 request approval for an
alternative method of compliance in accordance with paragraph (b) 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.
Note 2: Raytheon (Beech) Model DH.125-400B, BH.125-400B and -
600B, HS.125-600B and -700B, and BAe 125-800B series airplanes are
similar in design to the airplanes that are subject to the
requirements of this AD, and, therefore, also may be subject to the
unsafe condition addressed by this AD. However, as of the effective
date of this AD, those models are not type certificated for
operation in the United States. Airworthiness authorities of
countries in which those models are approved for operation should
consider adopting corrective action, applicable to these models,
that is similar to the corrective action required by this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent control surface interference and jamming of flight
controls, accomplish the following:
(a) Within 3 years since the date of airplane manufacture, or
within 60 days after September 21, 1989 (the effective date of AD
89-18-07, amendment 39-6297), whichever occurs later, accomplish the
following:
(1) Inspect the elevator mass balance weight side plate assembly
and balance weight spigot for corrosion, in accordance with British
Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987,
or Revision 3, dated November 13, 1989. Any corrosion detected
during this inspection must be repaired prior to further flight, in
accordance with the service bulletin.
[[Page 43340]]
(2) Apply corrosion protection treatment and install Monel
rivets, part number MS9318-052, or British Standard Specification
SP88-304 rivets, in the elevator balance weight structure, in
accordance with British Aerospace Service Bulletin 27-142, Revision
2, dated June 10, 1987, or Revision 3, dated November 13, 1989.
(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 3: 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 August 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-21720 Filed 8-12-98; 8:45 am]
BILLING CODE 4910-13-P