Airworthiness Directives; Raytheon Model Hawker 1000 Series Airplanes

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