AD 2002-21-05

[Federal Register Volume 67, Number 201 (Thursday, October 17, 2002)]
[Rules and Regulations]
[Pages 64039-64041]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-26371]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-40-AD; Amendment 39-12911; AD 2002-21-05]
RIN 2120-AA64


Airworthiness Directives; REVO, Incorporated Models Lake LA-4, 
Lake LA-4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain REVO, Incorporated (REVO) Models Lake LA-4, Lake LA-
4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 airplanes. This AD 
requires you to inspect the upper and lower wing spar doublers and 
angles for cracks at a certain time after the incorporation of 
Modification Kit B-79 or FAA-approved equivalent, replace any cracked 
wing spar doubler or angle, and report the results of the inspection to 
the Federal Aviation Administration (FAA). The kit modification 
consists of installing a doubler kit to give the spar an adequate 
fatigue life. This AD is the result of an incident of a crack found at 
the most outboard wing attachment fitting hole on one of the affected 
airplanes with the modification incorporated. The actions specified by 
this AD are intended to prevent wing spar failure caused by cracks in 
the wing spar doublers or angles, which could result in the wing 
separating from the airplane with consequent loss of control.

DATES: This AD becomes effective on October 23, 2002.
    The Federal Aviation Administration (FAA) must receive any comments 
on this rule on or before November 1, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2002-CE-40-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may view any 
comments at this location between 8 a.m. and 4 p.m., Monday through 
Friday, except Federal holidays. You may also send comments 
electronically to the following address: <a href="/cdn-cgi/l/email-protection#3b02167a787e160c167f5458505e4f7b5d5a5a155c544d"><span class="__cf_email__" data-cfemail="8bb2a6cac8cea6bca6cfe4e8e0eeffcbedeaeaa5ece4fd">[email&#160;protected]</span></a>. 
Comments sent electronically must contain ``Docket No. 2002-CE-40-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 text.
    You may get information related to this AD from FAA, Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2002-CE-40-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr. Richard B. Noll, Aerospace 
Engineer, FAA, Boston Aircraft Certification Office, 12 New England 
Executive Park, Burlington, Massachusetts 01803; telephone: (781) 238-
7160; facsimile: (781) 238-7170.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    The FAA has received a report of a crack at the most outboard wing 
attachment fitting bolt hole on a REVO Model Lake LA-4-200 airplane. 
This airplane had incorporated the modification from AD 2000-10-22, 
Amendment 39-11746 (65 FR 34065, May 26, 2000), which requires the 
following on REVO Models Lake LA-4, Lake LA-4A, Lake LA-4P, Lake LA-4-
200, and Lake Model 250 airplanes:

--Inspection of the left and right wing upper and lower spar doublers 
for cracks;
--Replacement of any cracked parts; and
--Incorporation of the B-79 Modification Kit or FAA-approved 
equivalent.

    This modification consists of installing a doubler kit to give the 
spar an adequate fatigue life. The repetitive inspections are no longer 
required after incorporation of this modification.
    AD 2000-10-12 was the result of reports of a fatigue crack found at 
the second most inboard wing attachment bolt hole on one of the 
affected airplanes and similar fatigue cracking on seven more of the 
affected airplanes.
    The most recent accident airplane had accumulated about 50 hours 
time-in-service (TIS) since incorporating the modification required by 
AD 2000-10-22.

What Are the Consequences if the Condition Is Not Corrected?

    This condition, if not corrected, could result in wing spar failure 
and the wing separating from the airplane with consequent loss of 
control.

The FAA's Determination and an Explanation of the Provisions of This AD

What Has FAA Decided?

    The FAA has reviewed all available information, including the 
service information referenced above; and determined that:

--The unsafe condition referenced in this document exists or could 
develop on other REVO Models Lake LA-4, Lake LA-4A, Lake LA-4P, Lake 
LA-4-200, and Lake Model 250 airplanes of the same type design;
--The affected airplanes that incorporate the modification required by 
AD 2000-10-22 should have the wing spar doublers and angles inspected 
for cracks and have any cracked parts replaced; and
--AD action should be taken in order to correct this unsafe condition.

What Does This AD Require?

    This AD requires you to accomplish the following:

--Inspect the upper and lower wing spar doublers and angles for cracks 
at a certain time after the incorporation of Modification Kit B-79 or 
FAA-approved equivalent as required by AD 2000-10-22;
--Replace any cracked wing spar doubler or angle; and
--Report the results of the inspection to FAA.

    In preparation of this rule, we contacted type clubs and aircraft 
operators to obtain technical information and information on 
operational and economic impacts. We have included, in the rulemaking 
docket, a discussion of information that may have influenced this 
action.

Will I Have the Opportunity To Comment Prior to the Issuance of the 
Rule?

    Because the unsafe condition described in this document could 
result in the wing separating from the airplane with consequent loss of 
control, we find that notice and opportunity for public prior comment 
are impracticable. Therefore, good cause exists for making this 
amendment effective in less than 30 days.

[[Page 64040]]

Comments Invited

How Do I Comment on This AD?

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, FAA invites your 
comments on the rule. You may submit whatever written data, views, or 
arguments you choose. You need to include the rule's docket number and 
submit your comments to the address specified under the caption 
ADDRESSES. We will consider all comments received on or before the 
closing date specified above. We may amend this rule in light of 
comments received. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether we need to take additional rulemaking 
action.

Are There Any Specific Portions of the AD I Should Pay Attention To?

    We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. You may view all comments we receive 
before and after the closing date of the rule in the Rules Docket. We 
will file a report in the Rules Docket that summarizes each FAA contact 
with the public that concerns the substantive parts of this AD.

How Can I Be Sure FAA Receives My Comment?

    If you want us to acknowledge the receipt of your written comments, 
you must include a self-addressed, stamped postcard. On the postcard, 
write ``Comments to Docket No. 2002-CE-40-AD.'' We will date stamp and 
mail the postcard back to you.

Regulatory Impact

Does This AD Impact Various Entities?

    These regulations 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. Therefore, FAA has determined that this 
final rule does not have federalism implications under Executive Order 
13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    We have determined that this regulation is an emergency regulation 
that must be issued immediately to correct an unsafe condition in 
aircraft, and is not a significant regulatory action under Executive 
Order 12866. It has been determined further that this action involves 
an emergency regulation under DOT Regulatory Policies and Procedures 
(44 FR 11034, February 26, 1979). If it is determined that this 
emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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.


Sec.  39.13  [Amended]

    2. FAA amends Sec.  39.13 by adding a new airworthiness directive 
(AD) to read as follows:

2002-21-05 Revo, Incorporated: Amendment 39-12911; Docket No. 2002-
CE-40-AD.

    (a) What airplanes are affected by this AD? This AD applies to 
the model and serial number airplanes in paragraph (a)(1) of this AD 
and that incorporate any of the wing spar part numbers (or FAA-
approved equivalent part numbers) specified in paragraph (a)(2) of 
this AD:
    (1) Affected Airplanes: This following model and serial number 
airplanes, certificated in any category, are affected by this AD:

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                 Model                             Serial Nos.
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Lake LA-4..............................  246 through 421, 423 through
                                          429, 445, and 446.
Lake LA-4A.............................  244 and 245.
Lake LA-4P.............................  121.
Lake LA-4-200..........................  422, 430 through 444, and all
                                          serial numbers after 446.
Lake Model 250.........................  1 through 232.
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    (2) Wing Spar Part Numbers Incorporated: The following specifies 
the part numbers of the wing spars that are installed on the 
affected airplanes:

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            Wing spar parts                         Part Nos.
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Upper Spar Cap Angles..................  2-1610-015 and 2-1610-016.
Lower Spar Cap Angles..................  2-1610-075 and 2-1610-076.
Upper Spar Doublers....................  2-1610-061 and 2-1610-081 and 2-
                                          1610-065.
Lower Spar Doublers....................  2-1610-063 and 2-1610-083.
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    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent wing spar failure caused by cracks 
in the wing spar doublers or angles, which could result in the wing 
separating from the airplane with consequent loss of control.
    (d) What must I do to address this problem? To address this 
problem, you must accomplish the following actions:

[[Page 64041]]



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                Actions                             Compliance
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(1) Inspect the wing spar doublers and   Upon accumulating 25 hours time-
 spar cap angles for cracks from the      in-service (TIS) after
 root end to the outboard of the wing     incorporating Modification B-
 attachment fittings, as follows:         79 or FAA-approved equivalent
(i) From inside the wheel well, clean     (the modification required by
 the upper and lower wing spar doublers   AD 2000-10-22) or within the
 and adjoining structure to the paint.    next 10 hours TIS after
 Use a detergent or mineral-based         October 23, 2002 (the
 solvent..                                effective date of this AD),
(ii) Use a strong light source and a 3x   whichever occurs later, unless
 magnifying glass to inspect the          already accomplished after
 exposed areas of the upper and lower     accumulating 25 hours TIS
 spar doublers and adjoining structure    after incorporating the
 for cracks. Use a mirror to inspect      modification required by AD
 the exposed edge of the spar cap angle   2000-10-22.
 behind the doubler..
(2) Replace any doubler or angle found   Prior to further flight after
 cracked during the inspection required   the inspection.
 by paragraphs (d)(1), (d)(1)(i), and
 (d)(1)(ii) of this AD. Replace with
 new parts that incorporate the same
 part numbers or FAA-approved
 equivalent part numbers.
(3) Report the results of the            Within 7 days after the the
 inspection to the FAA at the address     inspection required by this AD
 specified in paragraph (f) of this AD.   or 7 days after October 23,
 Use the inspection report that is        2002 (the effective date of
 included as Figure 1 of this AD. The     this AD), whichever occurs
 Office of Management and Budget (OMB)    later.
 approved the information collection
 requirements contained in this
 regulation under the provisions of the
 Paperwork Reduction Act of 1980 (44
 U.S.C. 3501 et seq.) and assigned OMB
 Control Number 2120-0056.
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Figure 1 to AD 2002-21-05--Inspection Report

    Report the following information to: Manager, Boston Aircraft 
Certification Office, Engine And Propeller Directorate, Aircraft 
Certification Service, Federal Aviation Administration, 12 New 
England Executive Park, Burlington, MA 01803-5299, Fax: (781) 238-
7170.

 Operator/Repair Station-----------------------------------------------
 Aircraft Model--------------------------------------------------------
 Aircraft S/N----------------------------------------------------------
 Date of Inspection----------------------------------------------------
Aircraft Time-in Service (TIS):
 Total-----------------------------------------------------------------
 Since installation of AD 2000-10-22 Kit-------------------------------

    Note: Add additional pages for the following for each part 
inspected.

 Part No.--------------------------------------------------------------
Inspection
 Pass------------------------------------------------------------------
 Fail------------------------------------------------------------------

    If a crack is found, indicate the approximate location on the 
part and the length of the crack in inches:

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Part Time-In Service (TIS) (Hours):

 Estimated-------------------------------------------------------------
 Actual----------------------------------------------------------------
 Unknown---------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Boston Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Boston ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 (e) 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Mr. Richard B. Noll, 
Aerospace Engineer, FAA, Boston Aircraft Certification Office, 12 
New England Executive Park, Burlington, Massachusetts 01803; 
telephone: (781) 238-7160; facsimile: (781) 238-7170.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) When does this amendment become effective? This amendment 
becomes effective on October 23, 2002.

    Issued in Kansas City, Missouri, on October 8, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-26371 Filed 10-16-02; 8:45 am]
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