[Federal Register Volume 61, Number 49 (Tuesday, March 12, 1996)]
[Proposed Rules]
[Pages 9958-9960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-5857]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-180-AD]
Airworthiness Directives; Beech (Raytheon) Model BAe 125-1000A
and Model Hawker 1000 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 Beech (Raytheon) Model BAe
125-1000A and Model Hawker 1000 series airplanes. This proposal would
require a one-time inspection for adequate clearances between, and
damage to, the flap cables and turnbuckles, airbrakes cables and
turnbuckles, and all other flight control cables and turnbuckles at
keel subframe 15A; and various follow-on actions, if necessary. This
proposal is prompted by reports of chafing due to insufficient
clearance between the flaps turnbuckle and the subframe, and between
the airbrakes cable and the subframe. The actions specified by the
proposed AD are intended to prevent such chafing, which could result in
damage to the flaps turnbuckle and the airbrakes cable, and subsequent
fraying or seizing of the flight control cables. These conditions, if
not corrected, could result in restriction or loss of the flight
controls.
DATES: Comments must be received by April 22, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-180-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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 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 95-NM-180-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. 95-NM-180-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, recently notified the FAA that an
unsafe condition may exist on certain Beech (Raytheon) Model BAe 125-
1000A and Model Hawker 1000 series airplanes. The CAA advises that it
received reports of chafing of the flaps turnbuckle and the airbrakes
cable at keel subframe 15A. The cause of this chafing has been
attributed to insufficient clearance between the flap turnbuckle and
the subframe, and between the airbrakes cable and the subframe. Such
insufficient clearance and resultant chafing could result in damage to
the flap cables and/or turnbuckles and the airbrakes cable, and
subsequent fraying or seizing of the flight control cables. These
conditions, if not corrected, could result in restriction or loss of
the flight controls.
Raytheon Corporate Jets has issued Hawker Service Bulletin SB.27-
168, dated July 17, 1995, which describes procedures for a one-time
visual inspection for adequate clearances and/or damage of the flap
cables and turnbuckles, airbrakes cables and turnbuckles, and all other
flight control cables and turnbuckles at keel subframe 15A (left- and
right-hand side); and various follow-on actions, if necessary. (These
follow-on actions include modification, repair, and replacement of
damaged cables.) The CAA classified this service bulletin as mandatory
in order to assure the continued airworthiness of these airplanes in
the United Kingdom.
These airplane models are manufactured in the United Kingdom and
are type certificated for operation in the United States under the
provisions of section 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, the
proposed AD would require a one-time visual inspection for adequate
clearances between, and/or damage to, the flap cables and turnbuckles,
airbrakes cables and turnbuckles, and all other flight control cables
and turnbuckles at keel subframe 15A (left- and right-hand side); and
various follow-on actions, if necessary. The actions would be required
to be accomplished in accordance with the service bulletin described
previously.
The FAA estimates that 25 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour 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
$1,500, or $60 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
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action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
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:
Beech Aircraft Corporation (Formerly DeHavilland; Hawker Siddeley;
British Aerospace, PLC; Raytheon Corporate Jets, Inc.): Docket 95-
NM-180-AD.
Applicability: Model BAe 125-1000A and Model Hawker 1000 series
airplanes, as listed in Hawker Service Bulletin SB.27-168, dated
July 17, 1995; 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.
Compliance: Required as indicated, unless accomplished
previously.
To prevent restriction or loss of the flight controls due to
insufficient clearance and resultant chafing and damage to the flaps
cable and/or turnbuckle and the airbrakes cable, accomplish the
following:
(a) Within 6 months after the effective date of this AD: Perform
a one-time detailed visual inspection for adequate working
clearances and for damage of the flap, airbrakes, and other flight
control cables and turnbuckles with the structure at keel subframe
15A (left- and right-hand sides) specified in Hawker Service
Bulletin SB.27-168, dated July 17, 1995. Perform the inspection in
accordance with that service bulletin. The detailed visual
inspection for working clearances shall be conducted for each
affected flight control through its full range of travel.
(1) If all clearances are within the limits specified in the
service bulletin, and no damage is found: No further action is
required by this AD.
(2) If the clearance for the flaps controls is outside the
limits specified in the service bulletin: Prior to further flight,
accomplish Modification SB 27-168-253705B in accordance with the
service bulletin.
(3) If the clearance for the airbrakes controls is outside the
limits specified in the service bulletin: Prior to further flight,
repair in accordance with the service bulletin.
(4) If any cable is found to be damaged, and the damage exceeds
the limits defined in Chapter 20-10-31 of the Airplane Maintenance
Manual: Prior to further flight, replace the damaged cable with a
new cable in accordance with the service bulletin.
(5) If any turnbuckle, keel subframe, or polythene strip is
found to be damaged: Prior to further flight, repair in accordance
with a method approved by the Manager, Standardization Branch, ANM-
113, FAA, Transport Airplane Directorate.
(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.
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 2: 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 March 6, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-5857 Filed 3-11-96; 8:45 am]
BILLING CODE 4910-13-U
