[Federal Register Volume 61, Number 30 (Tuesday, February 13, 1996)]
[Rules and Regulations]
[Pages 5501-5503]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2684]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 61, No. 30 / Tuesday, February 13, 1996 /
Rules and Regulations
[[Page 5501]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-08-AD; Amendment 39-9508; AD 96-03-11]
Airworthiness Directives; American Champion Aircraft Corporation
Models 8KCAB, 8GCBC, 7GCBC, and 7ECA 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 American Champion Aircraft Corporation (American Champion)
Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that are equipped with
metal spar wings. This action requires inspecting (one time) the wing
front strut fittings for cracks or scratches, replacing any wing front
strut fittings found cracked or scratched, and reporting the inspection
results to the Federal Aviation Administration (FAA). Fatigue cracks
found on the wing front strut fittings on two Model 8KCAB airplanes
prompted this action. The actions specified by this AD are intended to
prevent structural failure of a wing assembly caused by cracked or
scratched wing front strut fittings, which, if not detected and
corrected, could result in loss of control of the airplane.
DATES: Effective February 26, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 26, 1996.
Comments for inclusion in the Rules Docket must be received on or
before April 12, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 96-CE-08-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
the American Champion Aircraft Corporation, 32032 Washington Avenue,
Rochester, Wisconsin 53167. This information may also be examined at
the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket 96-CE-08-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: Ms. Karen Forest, Aerospace Engineer,
FAA, Chicago Aircraft Certification Office, 2300 E. Devon, room 232,
Des Plaines, Illinois 60018; telephone (847) 294-7697; facsimile (847)
294-7834.
SUPPLEMENTARY INFORMATION: The FAA has received a report of an American
Champion Model 8KCAB airplane breaking apart in flight and resulting in
a fatal accident. The cause of the accident is attributed to the pilot
operating the airplane outside of its approved flight envelope during
aerobatic instruction. During the accident investigation, the National
Transportation Safety Board (NTSB), American Champion, and the FAA
examined the remains of the accident airplane, including the separated
pieces of the wing and fuselage structure. This examination revealed
fatigue cracking of the wing front strut fittings.
The design of the wing and fuselage structure is such that the
outboard ends of the wing fittings for each primary strut are bolted to
the web of the wing's front spar. One fitting is on the forward side of
the web and one is on the aft side of the web. The fittings then
transition to a wider area where the strut is attached with a bolt. In
the above-referenced accident, the forward fitting fractured through
the transition area (approximately in the center of the fitting
length), causing the fitting to separate. This wing strut fitting
transition area contains an aft leg that is assembled against the
forward face of the wing spar web and a forward leg.
Investigation of the fitting from the accident aircraft revealed
that small, sharp scratches in the forward edge of the shorter portion
of the aft leg contributed to the fatigue cracking in the wing fitting.
Metallurgical examination of the fitting indicates that these fatigue
cracks formed in scratches and surface deformities that resulted during
the manufacturing process, and existed prior to the accident.
Since the accident, the FAA and American Champion have inspected
another Model 8KCAB airplane and found fatigue cracks on two of the
four wing strut fittings. These fatigue cracks also originated from
scratches and surface deformities in the wing front strut fitting. In
addition, evaluation of new uninstalled wing front strut fittings
reveal these scratches and surface deformities.
American Champion Models 8GCBC, 7GCBC, and 7ECA airplanes
incorporate the same design fitting that the Model 8KCAB airplanes
incorporate. The fittings of these airplanes do incur lower stress
levels compared to the fittings of the Model 8KCAB airplanes; however,
the FAA does not know at what stress levels fatigue cracks will form in
the area of scratches or surface deformities of these fittings, and how
many or which fittings have scratches or surface deformities as a
result of the manufacturing process.
The FAA does know that the accident airplane had accumulated
approximately 890 hours time-in-service (TIS) and the airplane
inspected that had fatigue cracks in two of the four wing front strut
fittings had accumulated about 200 hours TIS. While a full analysis of
the fatigue crack growth on these fittings is currently taking place,
the FAA feels that the above range of hours TIS on the two aircraft
found with fatigue cracks presents an immediate unsafe condition on the
American Champion Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that
may have scratches or surface deformities on any wing front strut
fitting.
American Champion has issued Service Letter 408, dated January 24,
1996, which specifies procedures for inspecting the wing front strut
fittings for cracks or scratches. This service letter includes a figure
that depicts the crosshatched areas of the wing front strut fittings to
be inspected.
After examining the circumstances and reviewing all available
information
[[Page 5502]]
related to the incidents described above including the referenced
service letter, the FAA has determined that (1) the wing fittings of
all American Champion airplane models that incorporate metal wing spars
should be inspected to detect and correct any cracks, scratches, or
surface deformities; and (2) AD action should be taken to prevent
structural failure of a wing assembly caused by cracked or scratched
wing front strut fittings, which, if not detected and corrected, could
result in loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other American Champion Models 8KCAB, 8GCBC, 7GCBC,
and 7ECA airplanes of the same type design that are equipped with metal
spar wings, this AD requires inspecting (one-time) the wing front strut
fittings for cracks, scratches, or surface deformities, and replacing
any wing front strut fittings found with cracks, scratches, or surface
deformities. The proposed AD would also require the owners/operators of
the affected airplanes to report the results of the one-time inspection
to the FAA. The FAA will then analyze these reports to determine
whether additional rulemaking (repetitive inspections, modifications,
etc.) is necessary for these airplanes. Accomplishment of the
inspection is in accordance with American Champion Service Letter 408.
This service letter also depicts the crosshatched areas of the wing
front strut fittings to be inspected. The replacement (if necessary) is
accomplished in accordance with the applicable maintenance manual.
Since a situation exists (possible structural failure of the wing
assembly caused by cracked or scratched wing front strut fittings) 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 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. 96-CE-08-AD.'' The postcard will be date stamped and
returned to the commenter.
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 USC 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:
96-03-11 American Champion Aircraft Corporation: Amendment 39-9508;
Docket No. 96-CE-08-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category, that are equipped with metal spar
wings:
--Model 8KCAB airplanes, serial numbers 643-90 through 762-95;
--Model 8KCAB airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number 7-1521 (installed in
accordance with American Champion Service Kit 403);
--Model 8GCBC airplanes, serial numbers 361-91 through 374-95;
--Model 8GCBC airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number 7-1542;
--Model 7GCBC airplanes, serial numbers 1200-94 through 1212-95;
--Model 7GCBC airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number 7-1541;
--Model 7ECA airplanes, serial numbers 1355-95 through 1357-95; and
--Model 7ECA airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number 7-1567.
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 (d) 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 as follows:
--Within the next 50 hours time-in-service after the effective date
of this AD, unless already accomplished; and
--Upon the installation of metal spar wings, unless the replacement
wings have been inspected in accordance with this AD prior to
installation.
To prevent structural failure of a wing assembly caused by
cracked or scratched
[[Page 5503]]
wing front strut fittings, which, if not detected and corrected, could
result in loss of control of the airplane, accomplish the following:
(a) Inspect the wing front strut fittings for cracks, scratches,
or surface deformities in accordance with the instructions in
American Champion Aircraft Corporation Service Letter 408, dated
January 24, 1996. Figure 3 of Service Letter 408 depicts the
crosshatched areas of the fittings that must be inspected. This
service letter specifies both a visual inspection and the choice of
either a dye penetrant, Zyglo test, ultrasonic, or x-ray inspection.
Prior to further flight, replace any wing front strut fitting that
has any crack, scratch, or surface deformity, with a wing front
strut fitting that is found to be free of cracks, scratches, and
surface deformities. Accomplish this replacement in accordance with
the instructions in the applicable maintenance manual.
Note 2: American Champion Aircraft Corporation Service Letter
408 specifies replacing the wing strut fitting if scratches are
found that are deeper than 0.010 inch. This AD requires replacing
the wing strut fitting if any scratch is found and takes precedence
over that specified in the service letter.
Note 3: American Champion Service Letter 408 only references
wing front strut fittings, part numbers 3-1632-1 and 3-1632-2.
Certain airplanes will incorporate wing front strut fittings, part
numbers 3-1646R and 3-1646L, depending on the specific airplane
design. The design of the critical area of the strut is the same and
the inspection procedures apply to all of the above-referenced wing
front strut fitting part numbers.
(b) Send the results of the inspection required by paragraph (a)
of this AD within 10 calendar days after the inspection to the
Manager, Chicago Aircraft Certification Office (ACO), 2300 E. Devon,
room 232, Des Plaines, Illinois 60018. Include the airplane serial
number, and the condition and number of hours time-in-service of
each cracked or scratched wing front strut fitting at the time of
inspection. (Reporting approved by the Office of Management and
Budget under OMB no. 2120-0056.)
(c) 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.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Chicago ACO, at the address specified in
paragraph (b) of this AD. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Chicago ACO.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Chicago ACO.
(e) The inspections required by this AD shall be done in
accordance with American Champion Aircraft Corporation Service
Letter 408 dated January 24, 1996. 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
American Champion Aircraft Corporation, 32032 Washington Avenue,
Rochester, Wisconsin 53167. Copies may be inspected at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri, or at the Office of the
Federal Register, 800 North Capitol Street, NW., 7th Floor, suite
700, Washington, DC.
(f) This amendment (39-9508) becomes effective on February 26,
1996.
Issued in Kansas City, Missouri, on January 31, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-2684 Filed 2-12-96; 8:45 am]
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