[Federal Register Volume 62, Number 79 (Thursday, April 24, 1997)]
[Proposed Rules]
[Pages 19950-19951]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-10568]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-228-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model BAe 125-800A, and Model
Hawker 800 and Hawker 800XP Series 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 certain Raytheon Model BAe 125-
800A and -800B series airplanes, and Model Hawker 800 and Hawker 800XP
series airplanes. This proposal would require modification of the
rudder. This proposal is prompted by a report indicating that, due to
the existing design of the rudder, overbias or overbalance of the
rudder occurs during single engine handling. The actions specified by
the proposed AD are intended to prevent overbias or overbalance of the
rudder, which could result in reduced controllability of the airplane.
DATES: Comments must be received by June 2, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-228-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: Larry Engler, Aerospace Engineer,
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office,
Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4122; fax (316)
946-4407.
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 96-NM-228-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. 96-NM-228-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that, during flight
testing of a Raytheon (Beech) Model Hawker 800 series airplane, too
much rudder was being applied during single engine handling (i.e.,
rudder overbias). The results of testing also revealed that, in certain
circumstances, the rudder did not naturally return to its trimmed state
after being moved away from that position (i.e., rudder overbalance),
which causes the pilot to use pedal force to restore the rudder to the
trimmed position.
The existing design of the rudder allows, during single engine
operation, some flow separation on the ``out-of-wind'' side of the
rudder during critical combinations of rudder and sideslip angles. It
also causes control circuit friction of the rudder when the airplane is
accelerated during single engine operation. In addition, the centering
spring of the rudder does not produce consistent installation loads.
These conditions, if not corrected, could result in overbias or
overbalance of the rudder and consequent reduced controllability of the
airplane.
The rudder of Model Hawker 800 series airplanes is similar in
design to that of Model BAe 125-800A, and Model Hawker 800XP series
airplanes. Therefore, the FAA has determined that all of these models
may be subject to the same unsafe condition.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Service Bulletin SB.55-
36-25F017A&B, dated April 15, 1996, which describes procedures for
modification of the rudder. The modification involves installation of
three separation triggers that are half-round in radius (0.375 inch) on
the left- and right-hand side of the rudder just ahead of the hinge
line. The modification also involves removal of the spring strut of the
rudder and adjustment and reinstallation of it. Accomplishment of the
modification will prevent too much rudder application during rudder
bias operation.
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 require modification of the rudder. The actions would
be required to be accomplished in accordance with the service bulletin
described previously.
Cost Impact
There are approximately 295 Beech (Raytheon) Model BAe 125-800A, -
800B series airplanes, and Model Hawker 800 and Hawker 800XP series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 190 airplanes of U.S. registry would be affected by this
proposed AD, that it would take approximately 8 work hours per airplane
to accomplish the proposed actions, and that the average labor rate is
$60 per work hour. Required parts
[[Page 19951]]
would cost approximately $300 per airplane. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$148,200, or $780 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 adding the following new
airworthiness directive:
Raytheon Aircraft Company (Formerly Beech, Raytheon Corporate Jets,
British Aerospace, Hawker Siddley, et al.): Docket 96-NM-228-AD.
Applicability: Model BAe 125-800A, and Model Hawker 800 and
Hawker 800XP series airplanes; on which Raytheon Modification
25F017A&B (reference Raytheon Service Bulletin SB.55-36-25F017A&B)
has not been installed; 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 (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 Model 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 the Model
BAe 125-800B series airplanes are approved for operation should
consider adopting corrective action, applicable to those models,
that is similar to the corrective action required by this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent overbias or overbalance of the rudder, which could
result in reduced controllability of the airplane, accomplish the
following:
(a) Within 100 hours time-in-service, or within 6 months after
the effective date of this AD, whichever occurs first, modify the
rudder in accordance with Raytheon Service Bulletin SB.55-36-
25F017A&B, dated April 15, 1996.
(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, Wichita Aircraft Certification
Office (ACO), FAA, Small 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, Wichita ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(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 17, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-10568 Filed 4-23-97; 8:45 am]
BILLING CODE 4910-13-P
