AD 99-23-10

This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 1000 series airplanes, that requires 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 amendment 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 this AD are intended to prevent a short circuit due to wire chafing, which can cause a fire in the ventral fuel tank area.

Final rule.

99-23-10 RAYTHEON AIRCRAFT COMPANY (Formerly Beech): Amendment 39-11406. 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 comments and then send it to the Manager, Wichita ACO.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with thisAD, 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.

Incorporation by Reference
(f) Except as provided by paragraph (c)(2) of this AD, the actions shall be done in accordance with Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Raytheon Aircraft Company, Manager Service Engineering, Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected 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; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This amendment becomes effective on December 17, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Raytheon Model Hawker 1000 series airplanes was published in the Federal Register on August 20, 1999 (64 FR 45485). That action proposed to 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.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

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 will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the actions, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this 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 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 adopted herein will 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 final rule does not have sufficient federalism implicationsto warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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.

39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: