Airworthiness Directives; Raytheon Aircraft Company Model 390 Airplanes

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Final rule; request for comments.

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to inspect the hydraulic tube/hose assemblies, the engine fuel feed tube assemblies, and the engine wire harnesses for proper clearance and damage (as applicable). If improper clearance or damage is found on any assembly, you must replace and/or modify the affected assembly. This AD is the result of reports of loss of the hydraulic system functions during different operations caused by improper clearance between certain components. This resulted in damage to the tubing in the hydraulic system assemblies. Analysis shows a similar condition on the engine fuel feed assemblies. We are issuing this AD to detect, correct, and prevent such damage or improper clearance in the affected areas, which could result in failure of one or more of these systems. These failures could lead to loss of hydraulic system operations, engine shutdown, and false readings for fuel pressure, oil pressure, and other oil indications. These conditions could consequently result in reduced or loss of control of the airplane.

DATES:

This AD becomes effective on August 23, 2004.

As of August 23, 2004, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.

We must receive any comments on this AD by October 4, 2004.

ADDRESSES:

Use one of the following to submit comments on this AD:

• DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
• Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
• Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
• Fax: 1-202-493-2251.
• Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

You may get the service information identified in this AD from Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140.

You may view the comments to this AD in the AD docket on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT:

James P. Galstad, Aerospace Engineer, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4135; facsimile: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

What events have caused this AD? Raytheon received reports of loss of hydraulic pressure on two Model 390 airplanes. One of the affected airplanes experienced a complete loss of normal hydraulic system pressure during flight. The other affected airplane experienced a loss of hydraulic pressure during ground operations.

Inspections of these airplanes revealed improper clearance between the hydraulic tube/hose assemblies and the engine inlet heat exhaust duct. Improper clearance between these two components resulted in chafing of the hydraulic tube assemblies. The chafing created a hole in the engine hydraulic tube and allowed hydraulic fluid to leak out. Loss of hydraulic fluid pressure resulted in the consequent loss of normal brake function, spoiler system, and normal landing gear operation.

Further inspections also revealed the following:

—Improper clearance between the left-hand (LH) and the right-hand (RH) engine fuel feed tube assemblies and the Hydro Mechanical Unit/Electronic Control Unit (HMU/ECU) interface electrical connectors; and

—Improper clearance between the engine wire harness and the engine lube oil cooler.

The analysis shows that the bend dimension of the LH engine fuel feed tube assembly was improperly defined during the production of some airplanes. This improperly-defined bend dimension allows for interference with the HMU/ECU interface electrical connectors. In addition, torquing the RH engine fuel feed tube assembly could cause interference with the HMU/ECU interface electrical connectors. Redesigned LH and RH tube assemblies are available for those airplanes found to have the improper clearance between the two components.

What is the potential impact if FAA took no action? These conditions, if not detected, corrected, and prevented, could cause the hydraulic tube/hose assemblies, the engine fuel feed tube assemblies, and the engine wire harnesses assembly to fail. These failures could eventually lead to reduced or loss of control of the airplane.

Is there service information that applies to this subject? Raytheon has issued the following:

—Mandatory Service Bulletin Premier SB 71-3648, Issued: November, 2003, which includes procedures for inspecting the hydraulic tube/hose assemblies and all adjacent components for proper clearance and damage and replacing any damaged parts and doing modifications if improper clearance is found; and

—Mandatory Service Bulletin Beechcraft SB 71-3659, Rev. 1, Revised: May, 2004, which includes procedures for inspecting the engine fuel feed tube assemblies for proper clearance and damage and replacing any damaged parts and doing modifications if improper clearance is found.

FAA's Determination and Requirements of the AD

What has FAA decided? We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design.

Since the unsafe condition described previously is likely to exist or develop on other Raytheon Model 390 airplanes of the same type design, we are issuing this AD to detect, correct, and prevent damage to the tubing in the hydraulic system assembly, the engine fuel feed tube assemblies, and the engine wire harness, caused by improper clearance and chafing, which could result in failure of these systems. These failures could lead to loss of hydraulic system operations, engine shutdown, nacelle fire, and false readings for fuel pressure, oil pressure, and other oil indications. These conditions could consequently lead to reduced or loss of control of the airplane.

What does this AD require? This AD requires you to incorporate the actions in the previously-referenced service bulletins.

In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket.

How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.

Comments Invited

Will I have the opportunity to comment before you issue the rule? This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include “Docket No. FAA-2004-18580; Directorate Identifier 2004-CE-12-AD” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us through a nonwritten communication, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.

Regulatory Findings

Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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.

Will this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this AD:

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. 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.

We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “Docket FAA-2004-18580; Directorate Identifier 2004-CE-12-AD” in your request.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

Adoption of the Amendment

Accordingly, under 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.