[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