[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