[Federal Register Volume 69, Number 58 (Thursday, March 25, 2004)]
[Proposed Rules]
[Pages 15264-15266]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6679]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-244-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe.125 Series 800A, 
800A (C-29A), and 800B Airplanes; and Model Hawker 800 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 15265]]

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Model BAe.125 series 800A, 
800A (C-29A), and 800B airplanes; and Model Hawker 800 airplanes. This 
proposal would require a one-time inspection of certain wire bundles 
for discrepancies and related corrective action. This action is 
necessary to find and fix chafing and damage to the wire bundles, which 
could result in electrical arcing and heat damage in a potential fuel 
zone and possible fire or explosion in the fuel tank. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by May 10, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-244-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-244-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Raytheon Aircraft Company, Department 62, 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, 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, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4139; fax (316) 
946-4107.

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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, 
discuss a request to change the compliance time and a request to change 
the service bulletin reference as two separate issues.
     For each issue, state what specific change to 
the proposed AD is being requested.
     Include justification (e.g., reasons or data) 
for each request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-244-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. 2003-NM-244-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports indicating that wires from the fuel 
boost pump of relays ``KT'' and ``JT'' interfered with and chafed 
against the avionics wire bundle that was routed through pressure bung 
``DD'' and the wing fuel transfer valve lever. This occurred because 
sufficient clearance was not attained during the manufacturing process. 
One incident resulted in a short circuit of the affected fuel boost 
pump wires against the radio altimeter coax cables. Chafing and damage 
to the wire bundles could result in electrical arcing and heat damage 
in a potential fuel zone, and possible fire or explosion in the fuel 
tank.

Explanation of Relevant Service Information

    We have reviewed and approved Raytheon Service Bulletin SB 24-3588, 
Revision 1, dated September 2003, which describes procedures for a one-
time inspection for discrepancies (chafing, damage, adequate 
clearance); of the wire bundles extending from relays ``JT'' and ``KT'' 
on Panel ``JA''; the wire bundle entering pressure bung ``DD''; and the 
wire bundles adjacent to relay ``KT'' and against the wing fuel 
transfer valve lever, and related corrective action. The inspection 
includes securing the wire bundles with cable ties if clearance is 
adequate (minimum clearance between wire bundles is 0.25 inch), to 
maintain adequate clearance. The related corrective action includes the 
following:
     Repairing or replacing any damaged wires, as 
applicable.
     Replacing or splicing wires to achieve adequate 
clearance if clearance is inadequate.
     If clearance is inadequate between the wire 
bundles, and the wire bundles and relay boxes: Installing P-clips to 
maintain clearance after adequate clearance is attained.
     If clearance is inadequate between the wiring 
extending from relay ``KT'' and the wing fuel transfer valve lever: 
Installing P-clips to maintain clearance after adequate clearance is 
attained.

Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

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 This Proposed AD and Service Bulletin

    The service bulletin recommends accomplishing the inspection for 
discrepancies of the wire bundles within 10 flight hours or 30 days, 
whichever is first, however; this proposed AD allows accomplishment of 
the inspection within 125 flight hours or 90 days, whichever is first. 
In developing an appropriate compliance time for this proposed AD, we 
considered not only the manufacturer's recommendation, but the degree 
of urgency associated with addressing the subject unsafe condition, the 
average

[[Page 15266]]

utilization of the affected fleet, and the time necessary to perform 
the inspection (1 hour). In light of all of these factors, we find a 
compliance time of within 125 flight hours or 90 days, whichever is 
first, represents an appropriate interval of time allowable for 
affected airplanes to continue to operate without compromising safety.
    The service bulletin refers to an ``inspection'' of certain wire 
bundles for discrepancies, but we have determined that the procedures 
in the service bulletin should be described as a ``detailed 
inspection.'' Note 1 has been included in this proposed AD to define 
this type of inspection.

Cost Impact

    There are about 184 airplanes of the affected design in the 
worldwide fleet. We estimate that 110 airplanes of U.S. registry would 
be affected by this proposed AD, that it would take about 1 work hour 
per airplane to accomplish the proposed inspection, and that the 
average labor rate is $65 per work hour. Based on these figures, the 
cost impact of the inspection proposed by this AD on U.S. operators is 
estimated to be $7,150, or $65 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 proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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: Docket 2003-NM-244-AD.

    Applicability: Model BAe.125 series 800A, 800A (C-29A), and 800B 
airplanes; and Model Hawker 800 airplanes, as listed in Raytheon 
Service Bulletin SB 24-3588, Revision 1, dated September 2003; 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix chafing and damage to certain wire bundles, 
which could result in electrical arcing and heat damage in a 
potential fuel zone and possible fire or explosion in the fuel tank, 
accomplish the following:

One-Time Inspection/Corrective Action

    (a) Within 125 flight hours or 90 days after the effective date 
of this AD, whichever is first: Do a one-time detailed inspection 
for discrepancies of the wire bundles extending from relays `JT' and 
`KT' on Panel `JA,' and the wire bundle entering pressure bung `DD'; 
and do any related corrective action; by doing all the actions per 
Part 3.A. of the Accomplishment Instructions of Raytheon Service 
Bulletin SB 24-3588, Revision 1, dated September 2003. Do any 
related corrective action before further flight.

    Note 1: For the purposes of this AD, a detailed 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.''

Inspections/Corrective Action Accomplished Per Previous Issue of 
Service Bulletin

    (b) Inspections and corrective action accomplished before the 
effective date of this AD per Raytheon Service Bulletin SB 24-3588, 
dated February 2003, are considered acceptable for compliance with 
the corresponding actions specified in this AD.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Wichita 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.

    Issued in Renton, Washington, on March 19, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6679 Filed 3-24-04; 8:45 am]
BILLING CODE 4910-13-P