[Federal Register: September 20, 2004 (Volume 69, Number 181)]
[Proposed Rules]
[Page 56175-56181]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20se04-11]
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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:
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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
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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.
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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