[Federal Register Volume 63, Number 219 (Friday, November 13, 1998)]
[Rules and Regulations]
[Pages 63388-63389]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30050]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-305-AD; Amendment 39-10878; AD 89-18-07 R1]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model BAe.125, DH.125, BH.125,
and HS.125 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment revises 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 amendment limits the applicability of the existing AD.
DATES: Effective December 18, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 18, 1998.
ADDRESSES: The service information referenced in this AD 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 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: 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by revising AD 89-18-07,
amendment 39-6297 (54 FR 33874, August 17, 1989), which is applicable
to certain Raytheon Model BAe.125, DH.125, BH.125, and HS.125 series
airplanes, was published in the Federal Register on August 13, 1998 (63
FR 43338). The action proposed 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 action also proposed to limit the
applicability of the existing AD.
Comments
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.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
Since the issuance of the existing AD, the FAA has reviewed the
figures it has used in calculating the economic impact of AD activity.
In order to account for various inflationary costs in the airline
industry, the FAA has determined that it is necessary to increase the
labor rate used in these calculations to $60 per work hour. The cost
impact information, below, has been revised to reflect this increase in
the specified hourly labor rate.
Because this AD merely deletes airplanes from the applicability of
the
[[Page 63389]]
rule, the AD otherwise adds no additional costs, and requires no
additional work to be performed by affected operators.
The FAA estimates that 346 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 10 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 cost impact of
the 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 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 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 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), amendment 39-10878, to read as follows:
89-18-07 R1 Raytheon Aircraft Company (Formerly Beech, Raytheon
Corporate Jets, British Aerospace, Hawker Siddeley, et al.):
Amendment 39-10878. 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.
(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.
(d) The actions shall be done in accordance with British
Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987,
or British Aerospace Service Bulletin 27-142, Revision 3, dated
November 13, 1989, which contains the following list of effective
pages:
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Revision
Page No. level shown Date shown on page
on page
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1............................. 3............ November 13, 1989.
2............................. Original..... May 15, 1987.
3............................. 2............ June 10, 1987.
4............................. 1............ May 21, 1987.
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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 Raytheon Aircraft Company, Manager
Service Engineering, Hawker Customer Support Department, P.O. Box
85, Wichita, Kansas 67201-0085. 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.
(e) This amendment becomes effective on December 18, 1998.
Issued in Renton, Washington, on November 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-30050 Filed 11-12-98; 8:45 am]
BILLING CODE 4910-13-U
