[Federal Register Volume 60, Number 140 (Friday, July 21, 1995)]
[Proposed Rules]
[Pages 37606-37608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-18030]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-42-AD]
Airworthiness Directives; Raytheon Corporate Jets Model Hawker
1000 and BAe 125-1000A 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 Hawker 1000
and BAe 125-1000A series airplanes. This proposal would require an
inspection to detect damage to an electrical cable loom (wire bundle).
This proposal would also require tying back the loom with a cable tie
to the cable loom support bracket, and repair, if necessary. This
proposal is prompted by a report indicating that damage had occurred to
the electrical cable loom. The actions specified by the proposed AD are
intended to prevent incorrect fault displays in the cockpit and
possible electrical systems failures, as a result of damage to the
electrical cable loom.
DATES: Comments must be received by August 31, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-42-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 Corporate Jets, Inc., Customer Support
Department, Adams Field, P.O. Box 3356, Little Rock, Arkansas 72203.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; 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-42-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-52-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 Raytheon Model Hawker 1000 and
BAe 125-1000A series airplanes. The CAA advises that it has received a
report of chafing damage to a certain electrical cable loom (wire
bundle) behind the right-hand throttle box cover. Investigation has
revealed that the chafing damage was caused by the flap selector spring
strut when it was moved to the ``lift dump'' position. This condition,
if not corrected, could result in incorrect fault displays in the
cockpit and possible failure of the electrical systems.
Raytheon has issued Service Bulletin SB 24-313, dated December 19,
1994, which describes procedures for a one-time detailed visual
inspection to detect chafing damage of the electrical cable loom
located behind the right-hand throttle box cover. The service bulletin
also describes verifying that the arrangement of the cable loom is
correct, and provides procedures for tying back the loom with a cable
tie to the cable loom support bracket, if no damaged cable is found.
The CAA classified this service bulletin as mandatory in order to
assure the continued airworthiness of these airplanes in the United
Kingdom.
This airplane model is manufactured in the United Kingdom and is
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 registered
in the United States, the proposed AD would require a one-time detailed
visual inspection to detect chafing damage of a certain electrical
cable loom located behind the right-hand throttle box cover. The
proposed AD would also require tying back the loom with a cable tie to
the cable loom support bracket, if no damaged cable is found. The
actions would be required to be accomplished in accordance with the
service bulletin described previously. If any cable loom is damaged,
the repair actions would be required to be accomplished in accordance
with a method approved by the FAA.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that
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provides for such approvals. A note has been included in this notice to
clarify this long-standing requirement.
The FAA estimates that 19 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
total cost impact of the proposed AD on U.S. operators is estimated to
be $1,140, or $60 per airplane.
The total 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.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Raytheon Corporate Jets, Inc. (Formerly de Havilland; Hawker
Siddeley; British Aerospace, plc): Docket 95-NM-42-AD.
Applicability: Model Hawker 1000 and BAe 125-1000A series
airplanes; as listed in Raytheon Service Bulletin SB 24-313, dated
December 19, 1994; 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 use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent incorrect fault displays in the cockpit and possible
electrical systems failures, accomplish the following:
(a) Within 6 months after the effective date of this AD, perform
a detailed visual inspection to detect chafing damage of the
electrical cable loom (wire bundle) behind the right-hand throttle
box cover, and perform continuity and insulation checks and system
functional tests, in accordance with Raytheon Service Bulletin SB
24-313, dated December 19, 1994.
(1) If no damage is found, prior to further flight, verify that
the arrangement of the cable loom is correct and, using a cable tie,
tie back the loom to the cable loom support bracket, in accordance
with the service bulletin.
(2) If any damage is found, prior to further flight, repair the
damaged loom, 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,
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 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 July 17, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-18030 Filed 7-20-95; 8:45 am]
BILLING CODE 4910-13-U
