[Federal Register Volume 61, Number 168 (Wednesday, August 28, 1996)]
[Rules and Regulations]
[Pages 44157-44160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-21746]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-CE-36-AD; Amendment 39-9726; AD 96-18-02]
RIN 2120-AA64
Airworthiness Directives; American Champion Aircraft Corporation
Models 8KCAB, 8GCBC, 7GCBC, 7ECA, 7GCAA, and 7KCAB Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes Airworthiness Directive (AD) 96-03-
11, which currently requires the following on American Champion
Aircraft Corporation (American Champion) Models 8KCAB, 8GCBC, 7GCBC,
and 7ECA airplanes that are equipped with metal spar wings: inspecting
(one-time) the wing front strut attach fittings for cracks, scratches,
or surface deformities; replacing any wing front strut attach fitting
with cracks, scratches, or surface deformities; and reporting the
inspection results to the Federal Aviation Administration (FAA). This
action results from reports submitted as a requirement of the existing
AD that reference 24 fittings with cracks, scratches, or surface
deformities on 7 different airplanes, and the FAA's determination that
improved wing front strut attach fittings (developed by American
Champion) are not susceptible to cracks, scratches, or surface
deformities. This action requires installing removable inspection hole
covers for the wing front strut attach fittings, and replacing the wing
front strut attach fittings with fittings of improved design. The
action also provides the provision of repetitively inspecting the wing
front strut attach fittings (provided no cracks, scratches, or surface
deformities are found) if parts have been ordered but are not
available. The actions specified by this AD are intended to prevent
structural failure of a wing caused by cracked wing front strut attach
fittings, which, if not detected and corrected, could result in loss of
control of the airplane.
DATES: Effective September 20, 1996.
The incorporation by reference of American Champion Service Letter
409, Revision A, dated April 22, 1996; American Champion Service Letter
410, dated May 6, 1996; American Champion Service Letter 411, dated May
6, 1996; American Champion Service Letter 412, dated May 6, 1996;
American Champion Service Letter 413, dated May 6, 1996, American
Champion Service Letter 414, Revision A, dated June 25, 1996; and
American Champion Service Letter 415, Revision A, dated June 25, 1996,
is approved by the Director of the Federal Register as of September 20,
1996.
The incorporation by reference of American Champion Service Letter
408, dated January 24, 1996, was previously approved as of February 26,
1991 (61 FR 5501, February 13, 1996) by the Director of the Federal
Register.
Comments for inclusion in the Rules Docket must be received on or
before October 25, 1996.
ADDRESSES: Submit comments in triplicate to the FAA, Central Region,
Office of the Assistant Chief Counsel, Attention: Rules Docket 96-CE-
36-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 No. 96-CE-36-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 Avenue, Des
Plaines, Illinois 60018; telephone (847) 294-7697; facsimile (847) 294-
7834.
SUPPLEMENTARY INFORMATION:
Events Leading to This Action
On January 31, 1996, the FAA issued AD 96-03-11, Amendment 39-9598
(61 FR 5501, February 13, 1996), to require the following on American
Champion Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that are
equipped with metal spar wings:
--Inspecting (one-time) the wing front strut attach fittings for
cracks, scratches, or surface deformities;
--Replacing any wing front strut attach fitting with cracks, scratches,
or surface deformities; and
--Reporting the inspection results to the FAA.
AD 96-03-11 resulted from an investigation of an American Champion
Model 8KCAB airplane accident that revealed fatigue cracking of the
wing front strut attach fittings. The design of the wing and fuselage
structure of this airplane 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. On the airplane involved in
the accident that resulted in AD 96-03-11, the forward fitting
fractured through the transition area (approximately in the center of
the fitting length), causing the fitting to separate. This wing front
strut attach 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 indicated that these fatigue
cracks formed in scratches and surface deformities that resulted during
the manufacturing process, and existed prior to the accident.
After that accident and prior to issuing AD 96-03-11, the FAA and
American Champion inspected another Model 8KCAB airplane and found
[[Page 44158]]
fatigue cracks on two of the four wing front strut attach fittings.
These fatigue cracks also originated from scratches and surface
deformities in the wing front strut attach fitting. In addition, an
evaluation of new uninstalled wing front strut attach fittings revealed
these scratches and surface deformities. American Champion Models
8GCBC, 7GCBC, and 7ECA airplanes incorporate this same design fitting,
and thus were included in the Applicability section of AD 96-03-11.
The results of the inspections required by AD 96-03-11 revealed 24
wing front strut attach fittings with cracks, scratches, or surface
deformities. These cracked and scratched fittings were from 7 different
affected airplanes that had between 103 to 666 total hours time-in-
service.
Improved Design Parts and Service Information
American Champion has designed improved wing front strut attach
fittings, part number (P/N) 3-1691 and P/N 3-1692, which, when
manufactured according to design specifications, will not contain the
surface deformities and scratches found on the existing design
fittings. After extensive analysis, these fittings have proven to not
have the cracking susceptibility of those currently in service. The
following presents service information that American Champion has
issued that relates to this issue:
American Champion Service Letter (SL) 408, dated January
24, 1996, and American Champion SL 409, Revision A, dated April 22,
1996, which specify procedures for accessing and inspecting wing front
strut attach fittings, part number (P/N) 3-1632-1 and P/N 3-1632-2; and
P/N 3-1646L and 3-1646R, respectively.
American Champion SL 410, dated May 6, 1996, which
includes procedures for installing removable inspection hole covers for
the wing front strut attach fittings on Model 8KCAB airplanes that have
complied with American Champion SL 408;
American Champion SL 411, dated May 6, 1996, which
includes procedures for installing removable inspection hole covers for
the wing front strut attach fittings on Model 8KCAB airplanes that have
not complied with American Champion SL 408;
American Champion SL 412, dated May 6, 1996, which
specifies procedures for installing removable inspection hole covers
for the wing front strut attach fittings on Models 7ECA, 7GCAA, 7GCBC,
and 8GCBC airplanes that have complied with American Champion SL 409;
American Champion SL 413, dated May 6, 1996, which
specifies procedures for installing removable inspection hole covers
for wing front strut attach fittings on Models 7ECA, 7GCAA, 7GCBC, and
8GCBC airplanes that have not complied with American Champion SL 409.
American Champion SL 414, Revision A, dated June 25, 1996,
which specifies procedures for replacing the wing front strut attach
fittings on Model 8KCAB airplanes with improved wing front strut attach
fittings, P/N 3-1691, and also includes procedures for inspecting the
wing front strut attach fittings on these airplanes; and
American Champion SL 415, Revision A, dated June 25, 1996,
which specifies procedures for replacing the wing front strut attach
fittings on Models 8GCBC, 7ECA, 7GCAA, 7GCBC, and 7KCAB airplanes with
improved wing front strut attach fittings, P/N 3-1692, and also
includes procedures for inspecting the wing front strut attach fittings
on these airplanes.
FAA's Determination
After examining the circumstances and reviewing all available
information related to the events described above, the FAA has
determined that (1) The wing front strut attach fittings on American
Champion Models 8KCAB, 8GCBC, 7ECA, 7GCAA, 7GCBC, and 7KCAB airplanes
should incorporate P/N 3-1691 and 3-1692, as applicable; and (2) AD
action should be taken in order to prevent structural failure of a wing
caused by cracked wing front strut attach fittings, which, if not
detected and corrected, could result in loss of control of the
airplane.
In addition, based on results of an in-depth analysis of the
existing wing front strut attach fittings, the FAA has determined that
if the fittings were not replaced with the improved design fittings,
repetitive inspections would need to be performed at intervals not to
exceed 20 hours TIS. Allowing repetitive inspections of these airplanes
over a long period of time goes against FAA policy, which states that
if a modification exists for critical structure that could eliminate or
reduce the number of short-term inspections, the modification should be
incorporated. The FAA makes short-term allowances on this policy to
account for parts availability provided analysis shows that an
acceptable level of safety can be maintained through a short-term
repetitive inspection program.
The Provisions of the Required AD Action
Since an unsafe condition has been identified that is likely to
exist or develop in other American Champion Models 8GCBC, 7ECA, 7GCAA,
7GCBC, and 7KCAB airplanes of the same type design, this AD supersedes
AD 96-03-11 with a new AD that requires installing removable inspection
hole covers for the wing front strut attach fittings, and replacing the
wing front strut attach fittings with P/N 3-1691 (Model 8KCAB) or P/N
3-1692 (Models 8GCBC, 7ECA, 7GCAA, 7GCBC, and 7KCAB) wing front strut
attach fittings, as applicable. The FAA is including a provision of
repetitively inspecting the wing front strut attach fittings (provided
no cracks, scratches, or surface deformities are found) if parts have
been ordered but are not available. Accomplishment of these actions is
in accordance with the service information previously referenced.
Since a situation exists (structural failure of the wing caused by
a cracked wing front strut attach fitting) that requires the immediate
adoption of this regulation, it is found that notice and opportunity
for prior public 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
[[Page 44159]]
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-36-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 removing AD 96-03-11, Amendment 39-
9598 (61 FR 5501, February 13, 1996), and by adding a new airworthiness
directive (AD) to read as follows:
96-18-02 American Champion Aircraft Corporation: Amendment 39-9726;
Docket No. 96-CE-36-AD. Supersedes AD 96-03-11, Amendment 39-9598.
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 768-96;
--Model 8KCAB airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number (P/N) 7-1521 (installed
in accordance with American Champion Service Kit 403);
--Model 8GCBC airplanes, serial numbers 361-91 through 377-96;
--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 1215-96;
--Model 7GCBC airplanes, all serial numbers, that are equipped with
metal spar wings, wing assembly part number 7-1545;
--Model 7ECA airplanes, serial numbers 1355-95 through 1358-96; and
--Models 7ECA, 7GCCA, and 7KCAB 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 (f) 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 20 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent structural failure of a wing assembly caused by
cracked wing front strut attach fittings, which, if not detected and
corrected, could result in loss of control of the airplane,
accomplish the following:
(a) Install removable inspection hole openings for the wing
front strut attach fittings in accordance with one of the following,
as applicable:
(1) American Champion Service Letter (SL) 410, dated May 6,
1996, for Model 8KCAB airplanes that have complied with American
Champion SL 408, dated January 24, 1996;
(2) American Champion SL 411, dated May 6, 1996, for Model 8KCAB
airplanes that have not complied with American Champion SL 408,
dated January 24, 1996;
(3) American Champion SL 412, dated May 6, 1996, for Models
7ECA, 7GCAA, 7GCBC, and 8GCBC airplanes that have complied with
American Champion SL 409, Revision A, dated April 22, 1996; and
(4) American Champion SL 413, dated May 6, 1996, for Models
7ECA, 7GCAA, 7GCBC, and 8GCBC airplanes that have not complied with
American Champion SL 409, Revision A, dated April 22, 1996.
Note 2: American Champion SL 408 and American Champion SL 409,
when complied with, incorporate permanent inspection holes for
access to the wing front strut attach fittings, P/N 3-1632-1 and P/N
3-1632-2; and P/N 3-1646L and 3-1646R, respectively.
(b) Replace the wing front strut attach fittings with P/N 3-1691
(Model 8KCAB) or P/N 3-1692 (Models 8GCBC, 7ECA, 7GCAA, 7GCBC, and
7KCAB) wing front strut attach fittings, as applicable.
Accomplishment of these actions is required in accordance with the
instructions in American Champion SL 414, Revision A, dated June 25,
1996; or American Champion SL 415, Revision A, dated June 25, 1996,
as applicable.
(c) If the improved design wing front strut attach fittings
referenced in paragraph (b) have been ordered from the manufacturer,
but are not available, repetitively inspect the wing front strut
attach fittings for cracks, scratches, or surface deformities at
intervals not to exceed 20 hours TIS in accordance with the
instructions in American Champion SL 408, dated January 24, 1996, or
American Champion SL 409, Revision A, dated April 22, 1996, as
applicable. Figure 3 of these service letters depicts the
crosshatched areas of the fittings that must be inspected. These
service letters also specify both a visual inspection and the choice
of either a dye penetrant, Zyglo test, ultrasonic, or x-ray
inspection.
(d) The repetitive inspections allowed in paragraph (c) of this
AD may be continued until one of the following occurs at which time
the replacement required by paragraph (b) of this AD must be
accomplished prior to further flight:
(1) Cracks, scratches, or surface deformities are found on a
wing front strut attach fitting;
(2) Parts become available from the American Champion Aircraft
Corporation; or
(3) Six repetitive inspection intervals are accomplished (120
hours TIS).
(e) 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.
(f) An alternative method of compliance or adjustment of the
initial or repetitive compliance time that provides an equivalent
level of safety may be approved by the Manager, Chicago Aircraft
Certification Office (ACO), 2300 E. Devon Avenue, Des Plaines,
Illinois 60018. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Chicago ACO. Alternative methods of
compliance approved in accordance with AD 96-03-11 (superseded by
this action), are not considered approved as alternative methods of
compliance for this AD.
[[Page 44160]]
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Chicago ACO.
(g) The incorporation of certain documents referenced in this AD
is as follows:
(1) The installations required by this AD shall be done in
accordance with American Champion Service Letter 410, dated May 6,
1996; American Champion Service Letter 411, dated May 6, 1996;
American Champion Service Letter 412, dated May 6, 1996; or American
Champion Service Letter 413, dated May 6, 1996, as applicable. 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.
(2) The replacements required by this AD shall be accomplished
in accordance with American Champion Service Letter 414, Revision A,
dated June 25, 1996; or American Champion Service Letter 415,
Revision A, dated June 25, 1996, as applicable. 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.
(3) The inspections (if parts are not available) required by
this AD shall be accomplished in accordance with American Champion
Service Letter 408, dated January 24, 1996, or American Champion
Service Letter 409, Revision A, dated April 22, 1996.
(i) The incorporation by reference of American Champion Service
Letter 408 reference was previously approved as of February 26, 1996
(61 FR 5501, February 13, 1996) by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(ii) The incorporation by reference of American Champion Service
Letter 409 was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(4) Copies may be obtained from the 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., suite 700, Washington, DC.
(h) This amendment (39-9726) supersedes AD 96-03-11, Amendment
39-9598.
(i) This amendment (39-9726) becomes effective on September 20,
1996.
Issued in Kansas City, Missouri, on August 20, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-21746 Filed 8-27-96; 8:45 am]
BILLING CODE 4910-13-U
