Airworthiness directives: Lancair Co.,

[Federal Register: March 26, 2004 (Volume 69, Number 59)]

[Rules and Regulations]

[Page 15657-15659]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr26mr04-2]

[[Page 15657]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-07-AD; Amendment 39-13535; AD 2004-06-09]

RIN 2120-AA64

Airworthiness Directives; The Lancair Company Models LC40-550FG and LC42-550FG 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 The Lancair Company (Lancair) Models LC40-550FG and LC42-550FG airplanes. This AD requires you to repetitively inspect the fuel pressure transducer for evidence of chafing and measure the cross section diameter (as necessary). The AD also requires you to install a compliance kit at a time dependent on the outcomes of the inspections and measurement. Installation of the kit is terminating action for the repetitive inspection requirements. This AD is the result of several reports of the fuel pressure transducer wearing through at the threads where it attached to the fuel line. We are issuing this AD to detect and correct chafing and wear of the fuel pressure transducer, which could result in failure of the transducer threaded fitting with a resulting fuel leak. These fuel leaks could lead to engine power loss or fire.

DATES: This AD becomes effective on May 3, 2004.

As of May 3, 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 June 1, 2004.

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

By mail: FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2004-CE-07-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.

By fax: (816) 329-3771.

By e-mail: 9-ACE-7-Docket@faa.gov. Comments sent electronically must contain ``Docket No. 2004-CE-07-AD'' in the subject line. If you send comments electronically as attached electronic files, the files must be formatted in Microsoft Word 97 for Windows or ASCII.

You may get the service information identified in this AD from The Lancair Company, 22550 Nelson Rd., Bend, Oregon 97701; telephone: (541) 318-1144; facsimile: (541) 318-1177.

You may view the AD docket at FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2004-CE-07-AD, 901 Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jeff Morfitt, Aerospace Engineer, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98055; telephone: 425-917-6405; facsimile: 425-917-6590.

SUPPLEMENTARY INFORMATION:

What Events Have Caused This AD?

The FAA has received several reports of wear of the fuel pressure transducer at the threads due to vibration and the consequent abrasion in the mount. There was one report of a failure of the mount with a resulting fuel leak in a Lancair Model LC40-550FG with about 370 hours time-in-service.

What Is the Potential Impact if FAA Took No Action?

This fuel leak could lead to engine power loss or fire.

Is There Service Information That Applies to This Subject?

Lancair has issued:

--Service Bulletin No. SB-04-002B, dated March 10, 2004; and --Compliance Kit Instruction No. CK-002, dated March 10, 2004.

What Are the Provisions of This Service Information?

The service information includes procedures for:

--Repetitively inspecting the fuel pressure transducer and related parts for evidence of chafing; --measuring the diameter of the transducer if chafing is found; and --installing Compliance Kit Instruction No. CK-002.

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 Lancair Models LC40-550FG and LC42-550FG airplanes of the same type design, we are issuing this AD to detect and correct chafing and wear of the fuel pressure transducer, which could result in failure of the transducer threaded fitting with a resulting fuel leak. These fuel leaks could lead to engine power loss or fire.

What Does This AD Require?

This AD requires you to incorporate the actions in the previously- referenced service bulletin.

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 ``AD Docket No. 2004-CE-07-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.

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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 ``AD Docket No. 2004-CE-07-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

0 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

0 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]

0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):

2004-06-09 The Lancair Company: Amendment 39-13535; Docket No. 2004- CE-07-AD.

When Does This AD Become Effective?

(a) This AD becomes effective on May 3, 2004.

Are Any Other ADs Affected by This Action?

(b) None.

What Airplanes Are Affected by This AD?

(c) This AD affects the following airplane models and serial numbers that are certificated in any category:

Model

Serial numbers

LC40-550FG............................... 40004 through 40079 LC42-550FG............................... 42002 through 42045

What Is the Unsafe Condition Presented in This AD?

(d) This AD is the result of several reports of that the fuel pressure transducer had worn through at the threads where it attached to the fuel line. We are issuing this AD to detect and correct chafing and wear of the fuel pressure transducer, which could result in failure of the transducer threaded fitting with a resulting fuel leak. These fuel leaks could lead to engine power loss or fire.

What Must I Do to Address This Problem?

(e) To address this problem, you must do the following:

Actions

Compliance

Procedures

(1) Inspect the fuel

Initially, unless Follow The Lancair pressure transducer, as already done within Company Model 300/ follows:

the last 25 hours 350 Mandatory (i) Visually inspect the time-in-service Service Bulletin fuel inlet of the

(TIS), inspect upon No. SB-04-002B, transducer for chafing

accumulating 100 dated March 10, (surface discontinuity or hours TIS or within 2004, and the discoloration).

5 hours TIS after applicable airplane (ii) If chafing is found, May 3, 2004 (the maintenance manual. use a caliper and measure effective date of the outside diameter of the this AD), whichever fuel inlet fitting

occurs later. (rotating the transducer Repetitively inspect while noting the minimum thereafter at cross sectional

intervals not to measurement). If the

exceed 25 hours TIS measurement is 0.370 inches until the or more and there is no modification in evidence of fuel leakage, paragraph (e)(3) of then repetitively inspect this AD is done. until you do the

The modification in modification in paragraph paragraph (e)(3) of (e)(3) of this AD.

this AD is terminating action for the repetitive inspection requirements in this AD.

(2) If the measurement of Before further

Follow The Lancair the outside diameter of the flight after the Company Model 300/ fuel inlet fitting is 0.369 inspection required 350 Mandatory inches or less, do the

in paragraph (e)(1) Service Bulletin modification in paragraph of this AD in which No. SB-04-002B, (3)(3) of this AD.

the measurement of dated March 5, 0.369 inches or 2004, The Lancair less is found.

Company Model 300/ 350 Compliance Kit Instruction No. CK- 002, dated March 10, 2004, and the applicable airplane maintenance manual.

(3) Install Compliance Kit Within 100 hours TIS Follow The Lancair CK-002.

after May 3, 2004 Company Model 300/ (the effective date 350 Compliance Kit of this AD) or

Instruction No. CK- before further

002, dated March flight if the

10, 2004, and the criteria in

applicable airplane paragraph (e)(2) of maintenance manual. this AD exists. You may do this installation before this time as terminating action for the repetitive inspection requirements.

May I Request an Alternative Method of Compliance?

(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Seattle Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Jeff Morfitt, Aerospace Engineer, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98055; telephone: 425-917-6405; facsimile: 425-917-6590.

May I Obtain a Special Flight Permit for the Initial Inspection Requirement of This AD?

(g) No. Special flight permits are not allowed for this AD. Part 39 of the Federal Aviation Regulations (14 CFR part 39) provides blanket approval of special flight permits for ADs, unless otherwise specified in the individual AD. The FAA has

[[Page 15659]]

determined that the safety issue is severe enough that the chafing in the fuel pressure transducer or fuel leaks must be corrected before further operation.

Does This AD Incorporate Any Material by Reference?

(h) You must do the actions required by this AD following the instructions in The Lancair Company Model 300/350 Mandatory Service Bulletin No. SB-04-002B, dated March 10, 2004, and The Lancair Company Model 300/350 Compliance Kit Instruction No. CK-002, dated March 10, 2004. The Director of the Federal Register approved the incorporation by reference of this service information in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from The Lancair Company, 22550 Nelson Rd., Bend, Oregon 97701; telephone: (541) 318-1144; facsimile: (541) 318-1177. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Issued in Kansas City, Missouri, on March 16, 2004. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 04-6498 Filed 3-25-04; 8:45 am]

BILLING CODE 4910-13-P

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