Airworthiness Directives; The Lancair Company Models LC40-550FG and LC42-550FG Airplanes

[Federal Register Volume 69, Number 59 (Friday, March 26, 2004)]
[Rules and Regulations]
[Pages 15657-15659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6498]



[[Page 15657]]

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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.

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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:
    <bullet<ls-thn-eq> 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.
    <bullet<ls-thn-eq> By fax: (816) 329-3771.
    <bullet<ls-thn-eq> By e-mail: [email protected]. 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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