[Federal Register Volume 69, Number 181 (Monday, September 20, 2004)]
[Proposed Rules]
[Pages 56175-56181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21052]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18744; Directorate Identifier 2004-CE-24-AD]
RIN 2120-AA64


Airworthiness Directives; Great Lakes Aircraft Company, LLC, 
Models 2T-1A-1 and 2T-1A-2 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 79-
20-08, which applies to all Great Lakes Aircraft Company, LLC, (Great 
Lakes) Models 2T-1A-1 and 2T-1A-2 airplanes with a Lycoming IO-360-B1F6 
or AIO-360-B1G6 engine installed. AD 79-20-08 currently requires you to 
inspect the engine induction system and the alternate air door for any 
signs of damage and repairing or replacing any damaged components. AD 
79-20-08 also requires you to inspect the induction system for the 
presence of a drain fitting. If the drain fitting is blocked, 
restricted, or does not exist, AD 79-20-08 requires you to clear the 
fitting or drill a hole in the elbow at the fitting location. This 
proposed AD is the result of the FAA inadvertently omitting Lycoming 
engine AEIO-360-B1G6 from the applicability section of AD 79-20-08. 
Consequently, this proposed AD would retain the actions required in AD 
79-20-08 and add Lycoming engine AEIO-360-B1G6 to the applicability 
section. We are issuing this proposed AD to prevent the aircraft 
induction system from becoming blocked or restricted, which could 
result in engine failure. This failure could lead to loss of control of 
the airplane.

DATES: We must receive any comments on this proposed AD by November 16, 
2004.

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

[[Page 56176]]

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 20590-001.
     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 view the comments to this proposed AD in the AD docket on 
the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Roger Caldwell, Aerospace Engineer, 
Denver Aircraft Certification Office (ACO), Federal Aviation 
Administration (FAA), 26805 E. 68th Ave., Rm 214 Denver, CO 80249-6361; 
telephone: (303) 342-1086; facsimile: (303) 342-1088.

SUPPLEMENTARY INFORMATION:

Comments Invited

    How do I comment on this proposed AD? We invite you to submit any 
written relevant data, views, or arguments regarding this proposal. 
Send your comments to an address listed under ADDRESSES. Include the 
docket number, ``FAA-2004-18744; Directorate Identifier 2004-CE-24-AD'' 
at the beginning of your comments. We will post all comments we 
receive, without change, to http://dms.dot.gov, including any personal 
information you provide. We will also post a report summarizing each 
substantive verbal contact with FAA personnel concerning this proposed 
rulemaking. Using the search function of our docket web site, anyone 
can find and read the comments received into any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
This is docket number FAA-2004-18744. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477-78) or you may visit http://dms.dot.gov.
    Are there any specific portions of this proposed AD I should pay 
attention to? We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. If you contact us through a nonwritten communication and 
that contact relates to a substantive part of this proposed 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 this 
proposed AD in light of those comments and contacts.

Docket Information

    Where can I go to view the docket information? You may view the AD 
docket that contains the proposal, any comments received, and any final 
disposition in person at the DMS Docket Offices between 9 a.m. and 5 
p.m. (eastern standard time), Monday through Friday, except Federal 
holidays. The Docket Office (telephone 1-800-647-5227) is located on 
the plaza level of the Department of Transportation NASSIF Building at 
the street address stated in ADDRESSES. You may also view the AD docket 
on the Internet at http://dms.dot.gov. The comments will be available 
in the AD docket shortly after the DMS receives them.

Discussion

    Has FAA taken any action to this point? The alternate air source 
door on the original aircraft configuration of Great Lakes Models 2T-
1A-1 and 2T-1A-2 airplanes was operated by push-pull cable in the 
cockpit and had an induction system drain provision. Later 
modifications changed the configuration of the alternate air source 
door to automatic operation.
    All fuel-injected engines are required to have an alternate air 
source. If the primary induction air source becomes blocked or 
restricted, the lower pressure differential in the induction system 
would overcome a spring tension on the alternate air door and provide a 
secondary airflow path for the engine.
    Inspections of Lycoming engines IO-360-B1F6 and AIO-360-B1G6 
revealed instances of heat distortion, damage, and cracks in the 
alternate air door. Extensive damage to the alternate air door could 
cause pieces to break off and get sucked into the induction system 
blocking the airflow to the engine.
    Additional inspections revealed that some of the affected engines 
did not have an induction system drain to remove fluid and/or moisture 
away from the engine.
    These conditions caused us to issue AD 79-20-08. AD 79-20-08 
currently requires the following on all Great Lakes Models 2T-1A-1 and 
2T-1A-2 airplanes that have a Lycoming engine IO-360-B1F6 or AIO-360-
B1G6 installed:

--Visually inspecting the aircraft induction system drain fitting 
located in the induction elbow below the fuel injector for blockage or 
restriction;
--Clearing the blocked drain hole or drilling a hole in the elbow at 
the fitting location if the drain hole is restricted in the weld area 
or not drilled through the elbow;
--Visually inspecting the alternate air door for damage and repairing 
or replacing any damaged alternate air door; and
--Visually inspecting the aircraft induction system (including the 
filter) for cleanliness, security, and damage and repairing or 
replacing any dirty or damaged components.

    What has happened since AD 79-20-08 to initiate this proposed 
action? During a recent inspection, it was discovered that the Lycoming 
engine AEIO-360-B1G6 has the same configuration as Lycoming engines IO-
360-B1F6 and AIO-360-B1G6.
    What is the potential impact if FAA took no action? If not detected 
and corrected, blockage or restriction of the aircraft induction system 
could cause engine failure. This failure could result in loss of 
control of the airplane.

FAA's Determination and Requirements of This Proposed 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. Therefore, we are proposing 
AD action.
    What would this proposed AD require? This proposed AD would 
supersede AD 79-20-08 with a new AD that would retain the actions 
required in AD 79-20-08 and would add Lycoming engine AEIO-360-B1G6 to 
the applicability section.
    How does the revision to 14 CFR part 39 affect this proposed 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.

Costs of Compliance

    How many airplanes would this proposed AD impact? We estimate that 
this proposed AD affects 130 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish the proposed inspections of the aircraft induction system, 
the induction system drain fitting, and the alternate air door:

[[Page 56177]]



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              Labor cost                            Parts cost                  Total cost per  airplane             Total cost on U.S.  operators
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3 workhours x $65 = $195.............  Not Applicable.....................  $195............................  $195 x 130 = $25,350.
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    We estimate the following costs to accomplish any necessary repairs 
and/or replacements that would be required based on the results of this 
proposed inspections. We have no way of determining the number of 
airplanes that may need these repairs and/or replacements:

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              Labor cost                          Parts cost                    Total cost per  component
----------------------------------------------------------------------------------------------------------------
3 workhours per component x $65 = $195  Approximately $113 per          $195 + $113 = $308.
                                         component.
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    What is the difference between the cost impact of this proposed AD 
and the cost impact of AD 79-20-08? The only difference between this 
proposed AD and AD 79-20-08 is the correction to the applicability. No 
additional actions are being proposed. The FAA has determined that this 
proposed AD action does not increase the cost impact over that already 
required by AD 79-20-08.

Regulatory Findings

    Would this proposed AD impact various entities? We have determined 
that this proposed AD would not have federalism implications under 
Executive Order 13132. This proposed AD would 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.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this proposed 
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 proposed 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-24-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 79-20-08, Amendment 39-3580, and by adding a new AD to read as 
follows:

Great Lakes Aircraft Company, LLC: Docket No. FAA-2004-18744; 
Directorate Identifier 2004-CE-24-AD; Supersedes AD 79-20-08; 
Amendment 39-3580

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by November 16, 2004.

What Other ADs Are Affected by This Action?

    (b) This AD supersedes AD 79-20-08, Amendment 39-3580.

What Airplanes Are Affected by This AD?

    (c) This AD affects all Model 2T-1A-1 and 2T-1A-2 airplanes that 
have a Lycoming IO-360-B1F6, AIO-360-BIG6, or AEIO-360-BIG6 engine 
installed and that are certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of heat distortion, damage, and cracks 
found in the aircraft induction system on Lycoming IO-360-B1F6, AIO-
360-B1G6, and AEIO-360-BIG6 engines. The actions specified in this 
AD are intended to prevent the aircraft induction system from 
becoming blocked or restricted, which could result in engine 
failure. This failure could lead to loss of control of the airplane.

What Must I Do To Address This Problem?

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

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                 Actions                             Compliance                          Procedures
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(1) Perform the following:..............  For all affected airplanes:       Not applicable.
(i) Visually inspect the aircraft          Inspect within the next 25
 induction system drain fitting located    hours time-in-service (TIS)
 in the induction elbow below the fuel     after the effective date of
 injector for blockage or restriction..    this AD. Before further flight,
(ii) If the hole is blocked or             modify the blocked or
 restricted in the weld area or not        restricted aircraft induction
 drilled through the elbow, open up the    system drain fitting.
 restricted hole or drill a hole in the
 elbow at the fitting location using a
 No. 10 (.193) drill..

[[Page 56178]]

 
(2) Visually inspect the alternate air    For airplanes previously          Not applicable.
 door for distortion, heat damage, and     affected by Ad 79-20-08:
 cracks. If any damage is found, repair    Initially inspect at the next
 or fabricate a new door following         scheduled inspection required
 Figure 1, Figure 2, and Figure 3 in       by Ad 79-20-08 or within the
 this AD.                                  next 25 hours TIS after the
                                           effective date of this AD,
                                           whichever occurs later.
                                           Repetitively inspect thereafter
                                           at intervals not to exceed 100
                                           hours TIS. For airplanes not
                                           previously affected by AD 79-20-
                                           08: Inspect within the next 25
                                           hours TIS after the effective
                                           date of this AD. Repetitively
                                           inspect thereafter at intervals
                                           not to exceed 100 hours TIS.
                                           For all affected airplanes: If
                                           damage is found during any
                                           inspection, before further
                                           flight, repair or replace the
                                           damaged alternate air door.
(3) Visually inspect the aircraft         For airplanes previously          Not applicable.
 induction system for cleanliness of the   affected by AD 79-20-08:
 air filter, distortion, security, and     Initially inspect at the next
 damage from backfire or induction         scheduled inspection required
 system fire. If the air filter is         by AD 79-20-08 or within the
 dirty, if any distortion, damage, or      next 25 hours TIS after the
 lack of security is found, repair,        effective date of this AD,
 replace or modify all affected            whichever occurs later.
 components.                               Repetitively inspect thereafter
                                           at intervals not to exceed 100
                                           hours TIS. For airplanes not
                                           previously affected by AD 79-20-
                                           08: Inspect within the next 25
                                           hours TIS after the effective
                                           date of this AD. Repetitively
                                           inspect thereafter at intervals
                                           not to exceed 100 hours TIS.
                                           For all affected airplanes: If
                                           damage is found during any
                                           inspection, before further
                                           flight, repair, replace, or
                                           modify any damaged components.
----------------------------------------------------------------------------------------------------------------

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, Denver Aircraft 
Certification Office, FAA. For information on any already approved 
alternative methods of compliance, contact Roger Caldwell, Aerospace 
Engineer, Denver ACO, FAA, 26805 E. 68th Ave., Rm 214 Denver, CO 
80249-6361; telephone: (303) 342-1086; facsimile: (303) 342-1088.

May I Get Copies of the Documents Referenced in This AD?

    (g) You may view the AD docket at the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC, or on the 
Internet at http://dms.dot.gov.
BILLING CODE 4910-13-P

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    Issued in Kansas City, Missouri, on September 10, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-21052 Filed 9-17-04; 8:45 am]
BILLING CODE 4910-13-C