[Federal Register Volume 63, Number 94 (Friday, May 15, 1998)]
[Rules and Regulations]
[Pages 26964-26965]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-12625]
[[Page 26964]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-48-AD; Amendment 39-10524; AD 98-10-12]
RIN 2120-AA64
Airworthiness Directives; REVO, Incorporated Models Colonial C-2,
Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 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 all REVO, Incorporated (REVO) Models Colonial C-2, Lake LA-
4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. This action
requires measuring for a clearance of \5/32\ of an inch between the
attachment fitting and the horizontal stabilizer rear beam, and a
clearance of \1/16\ of an inch between the attachment fitting and the
stabilizer skin. If either area does not meet these minimum
measurements, this AD requires removing the affected horizontal tail
half from the airplane and inspecting the attachment fitting for any
evidence of fretting, cracking, or corrosion. If cracks, fretting, or
corrosion are present, the attachment fitting must be replaced with a
new fitting, and the stabilizer skin must be trimmed to provide a
positive clearance for the fitting. This action is prompted by an
incident report of an airplane losing control during flight after the
attachment fitting to the horizontal stabilizer fractured. The actions
specified by this AD are intended to prevent fatigue cracks to the
horizontal and vertical stabilizer attachment fitting, which could
result in loss of control of the airplane.
DATES: Effective June 8, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 8, 1998.
Comments for inclusion in the Rules Docket must be received on or
before July 8, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-48-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
REVO, Incorporated, 50 Airport Road, Laconia Airport, Laconia, New
Hampshire, 03246. This information may also be examined at the Federal
Aviation Administration (FAA), Central Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-CE-48-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106; or at the Office of the
Federal Register, 800 North Capitol Street, NW, suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Mr. Richard B. Noll, Aerospace
Engineer, FAA, Aircraft Certification Office, 12 New England Executive
Park, Burlington, Massachusetts 01803, telephone: (781) 238-7160;
facsimile: (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA recently received a report of loss of control on a REVO,
Incorporated Lake LA-4 series airplane during flight. The report
indicated that during climb-out following take-off, the pilot heard a
loud bang, and the airplane pitched over into a vertical dive, with
loss of elevator control. During the pilot's efforts to regain control,
another loud bang was heard and sufficient control was regained to
manage a safe landing. Further investigation of the incident and
inspection of the subject airplane revealed interference between the
horizontal stabilizer skin and the attachment fitting. This
interference caused fretting, which led to fatigue cracking and
associated corrosion of the attachment fitting. The fracture of the
attachment fitting resulted in loss of directional control of the
airplane.
Relevant Service Information
REVO has issued Service Bulletin B-78, dated April 3, 1998,
applicable to Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P,
and Lake LA-4-200 airplanes, which specifies procedures for:
--Measuring the gap between the horizontal stabilizer rear beam and the
attachment fitting for a clearance of \5/32\ of an inch,
--If the gap between the stabilizer rear beam and the attachment
fitting is less than \5/32\-inch, removing the fitting and visually
inspect for cracks, fretting, or corrosion,
--If cracks, fretting, or corrosion is present, replacing the
attachment fitting with a new fitting,
--Measuring the gap between the attachment fitting and the horizontal
stabilizer skin for a clearance of \1/16\ of an inch, and
--If the clearance between the horizontal stabilizer skin and the
attachment fitting is less than \1/16\ of an inch, but the other
measurement is at or greater than \5/32\ of an inch, trimming the
stabilizer skin to provide at least \1/16\ of an inch clearance.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
relevant service information, the FAA has determined that AD action
should be taken to prevent fatigue cracks in the horizontal stabilizer
attachment fitting, which if not detected and corrected, could result
in loss of control of the airplane.
Explanation of the Provisions of the AD
Since an unsafe condition has been identified that is likely to
exist or develop in other REVO Colonial C-2, Lake LA-4, Lake LA-4A,
Lake LA-4P, Lake LA-4-200 airplanes of the same type design, this AD
requires measuring the gap between the horizontal stabilizer rear beam
and the attachment fitting for correct clearance, and measuring the gap
between the attachment fitting and the horizontal stabilizer skin for
correct clearance. If the gap between the stabilizer rear beam and the
attachment fitting is not the correct clearance, the action requires
removing the horizontal tail half to gain access to the fitting, and
visually inspecting for cracks, fretting, or corrosion. If cracks,
fretting, or corrosion are present, the action requires replacing the
attachment fitting with a new fitting. If the clearance between the
horizontal stabilizer skin and the attachment fitting is not the
correct clearance, but the other measurement is correct, the action
requires trimming the stabilizer skin to provide acceptable clearance.
The actions are to be done in accordance with the instructions in REVO
Service Bulletin B-78, dated April 3, 1998.
Determination of the Effective Date of the AD
Since a situation exists (loss of directional control of the
airplane) that requires the immediate adoption of this regulation, it
is found that notice and opportunity for public prior comment hereon
are impracticable, and that good cause exists for making this amendment
effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and, thus, was not
preceded by notice and opportunity to comment, comments are invited on
this rule. Interested persons
[[Page 26965]]
are invited to comment on this rule by submitting such written data,
views, or arguments as they may desire. Communications should identify
the Rules Docket number and be submitted in triplicate to the address
specified above. All communications received on or before the closing
date for comments will be considered, and this rule may be amended in
light of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-CE-48-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has 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, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
98-10-12 Revo, Incorporated: Amendment 39-10524; Docket No. 98-CE-
48-AD.
Applicability: Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake
LA-4P, and Lake LA-4-200 airplanes, all serial numbers, certificated
in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, 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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required within the next 25 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent fatigue cracks in the horizontal and vertical
stabilizer attachment fitting, which could result in loss of control
of the airplane, accomplish the following:
(a) Measure the gap between the horizontal stabilizer rear beam
and the attachment fitting for a clearance of \5/32\ of an inch in
accordance with the PROCEDURE section in REVO Service Bulletin B-78,
dated April 3, 1998.
(1) If the gap between the stabilizer rear beam and the
attachment fitting is less than \5/32\-inch, prior to further
flight, remove the fitting and visually inspect or inspect using a
dye penetrant method for cracks, fretting, or corrosion in
accordance with the INSPECTION AND REPAIR section in REVO Service
Bulletin B-78, dated April 3, 1998.
(2) If any crack, fretting, or corrosion is present, prior to
further flight, replace the attachment fitting with a new fitting in
accordance with the INSPECTION AND REPAIR section in REVO Service
Bulletin B-78, dated April 3, 1998.
(b) Measure the gap between the attachment fitting and the
horizontal stabilizer skin for a clearance of \1/16\ of an inch in
accordance with the PROCEDURE section in REVO Service Bulletin B-78,
dated April 3, 1998.
(c) If the clearance between the horizontal stabilizer skin and
the attachment fitting is less than \1/16\ of an inch, but the
measurement required in paragraph (a) of this AD is at or greater
than \5/32\ of an inch, prior to further flight, trim the stabilizer
skin to provide at least \1/16\-inch clearance in accordance with
the PROCEDURE section in REVO Service Bulletin B-78, dated April 3,
1998.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Boston Aircraft Certification Office, 12
New England Executive Park, Burlington, Massachusetts 01803. The
request shall be forwarded through an appropriate FAA Maintenance
Inspector, who may add comments and then send it to the Manager,
Boston ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Boston ACO.
(f) The inspection, modification, and replacement required by
this AD shall be done in accordance with REVO Service Bulletin B-78,
dated April 3, 1998. This incorporation by reference was approved by
the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be obtained from REVO,
Incorporated, 50 Airport Road, Laconia Airport, Laconia, New
Hampshire, 03246. Copies may be inspected at the FAA, Central
Region, Office of the Regional Counsel, Room 1558, 601 E. 12th
Street, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
(g) This amendment becomes effective on June 8, 1998.
Issued in Kansas City, Missouri, on May 1, 1998.
Michael Gallagher,
Manager, Small Aircraft Directorate, Aircraft Certification Service.
[FR Doc. 98-12625 Filed 5-14-98; 8:45 am]
BILLING CODE 4910-13-U
