[Federal Register Volume 64, Number 161 (Friday, August 20, 1999)]
[Proposed Rules]
[Pages 45485-45487]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21684]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-156-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon 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 Raytheon Model Hawker 1000
series airplanes. This proposal would require a visual inspection of
the PS wire bundle, shielded wires going to fuel probe ``G,'' and any
other wire or wire bundle for chafing in the forward wing spar and
forward ventral tank area; and corrective actions, if necessary. This
proposal is prompted by reports indicating that, due to improper
routing of a wire bundle, the wire bundle chafed against the forward
ventral tank transfer/crossfeed valve, which caused an electrical short
and resulted in failure of the landing light. The actions specified by
the proposed AD are intended to prevent a short circuit due to wire
chafing, which can cause a fire in the ventral fuel tank area.
DATES: Comments must be received by October 4, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-156-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; or at the FAA,
Small Airplane Directorate, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas.
FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace
Engineer,Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316)
946-4139; 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 99-NM-156-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-114, Attention: Rules
Docket No. 99-NM-156-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports of a wire bundle chafing against the
forward ventral tank transfer/crossfeed valve on Raytheon Model Hawker
1000 series airplanes. The wire insulation had worn through and caused
an electrical short, which resulted in failure of the landing light.
The cause of such chafing has been attributed to improper routing of
the PS wire bundle at fuselage station 293.47 during production, which
may allow the wire bundle to contact the forward ventral tank transfer/
crossfeed valve. This condition, if not corrected, could result in an
electrical short, which could cause a fire in the ventral fuel tank
area.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Aircraft Service
Bulletin SB 24-3201, dated October 1998. The service bulletin describes
procedures for a detailed visual inspection of the PS wire bundle,
shielded wires going to fuel probe ``G,'' and any other wire or wire
bundle for chafing in the forward wing spar and forward ventral tank
area; and corrective action, if necessary. The corrective actions
involve ensuring adequate clearance between the PS wire bundle and the
front ventral tank transfer/crossfeed valve actuator, and between the
shielded wires going to fuel probe ``G'' and the wing transfer valve
actuator; installing spiral wrap; repairing chafed wire; and replacing
chafed wire with new wire. Accomplishment of the actions specified in
the service bulletin is intended to adequately address the identified
unsafe condition.
[[Page 45486]]
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 accomplishment of the actions specified in
the service bulletin described previously, except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
repair conditions, this proposal would require the repair of those
conditions to be accomplished in accordance with a method approved by
the FAA.
Cost Impact
There are approximately 91 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 39 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
$2,340, 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 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): Docket 99-NM-156-AD.
Applicability: Model Hawker 1000 series airplanes, serial
numbers 258151, 258159, and 259003 through 259052 inclusive,
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 (d) 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 a short circuit due to wire chafing, which can cause
a fire in the ventral fuel tank area, accomplish the following:
Inspection and Modification
(a) Within 50 flight hours after the effective date of this AD,
perform a detailed visual inspection of the PS wire bundle coming
from the bung `DF' for chafing against the front ventral tank
transfer/crossfeed actuator, in accordance with Raytheon Aircraft
Service Bulletin SB 24-3201, dated October 1998.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(1) If no chafing is found, prior to further flight, ensure a
minimum 0.25-inch clearance exists between the PS wire bundle and
valve actuator; and install spiral wrap, as necessary; in accordance
with the service bulletin.
(2) If any chafing is found on a 22, 20, 16, or 14 gauge (non-
shielded) wire, prior to further flight, repair chafed wire by
splicing the damaged section using MIL-S-81824/1 splices; ensure a
minimum 0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(3) If any chafing is found on a 10 gauge wire, replace the
entire wire with a new 10 gauge wire; ensure a minimum 0.25-inch
clearance exists between the wire bundle and valve actuator; and
install spiral wrap, as necessary; in accordance with the service
bulletin.
(b) Within 50 flight hours after the effective date of this AD,
perform a detailed visual inspection of the shielded wires going to
the fuel probe ``G'' for chafing against the wing transfer valve
actuator and mounting screws, in accordance with Raytheon Aircraft
Service Bulletin SB 24-3201, dated October 1998.
(1) If no chafing is found, prior to further flight, ensure a
minimum 0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(2) If any chafing is found, prior to further flight, replace
the entire shielded wire with a new shielded wire; ensure a minimum
0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(c) Within 50 flight hours after the effective date of this AD,
perform a borescope inspection of the entire forward wing spar/
forward ventral tank area for chafing of any other wire or wire
bundle; and install spiral wrap, as necessary; in accordance with
Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998.
(1) If no chafing is found, no further action is required by
this AD.
(2) If any chafed wire or wire bundle is found, prior to further
flight, repair in accordance with a method approved by the Manager,
Wichita Aircraft Certification Office (ACO), FAA, Small Airplane
Directorate. For a repair method to be approved by the Manager,
Wichita ACO, as required by this paragraph, the Manager's approval
letter must specifically reference this AD.
Alternative Methods of Compliance
(d) 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 ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add
[[Page 45487]]
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.
Special Flight Permits
(e) 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 16, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-21684 Filed 8-19-99; 8:45 am]
BILLING CODE 4910-13-P
