[Federal Register Volume 63, Number 227 (Wednesday, November 25, 1998)]
[Rules and Regulations]
[Pages 65057-65060]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31434]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-106-AD; Amendment 39-10917; AD 98-24-30]
RIN 2120-AA64
Airworthiness Directives; Stemme GmbH & Co. KG Models S10, S10-V,
and S10-VT Sailplanes
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 certain Stemme GmbH & Co. KG (Stemme) Models S10, S10-V, and
S10-VT sailplanes. This AD requires inspecting certain areas in the
flight control system for cracks; immediately replacing any cracked
parts; and eventually replacing all longitudinal coupling with modified
coupling regardless if found cracked. This AD is the result of
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for Germany. The actions specified by this AD
are intended to detect and correct cracks in certain areas of the
flight control system, which could result in flight control system
failure with consequent reduced or loss of control of the sailplane.
DATES: Effective December 18, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 18, 1998.
Comments for inclusion in the Rules Docket must be received on or
before December 28, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket 98-CE-106-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
Stemme GmbH & Co. KG, Gustav-Meyer-Allee 25, D-13355 Berlin, Federal
Republic of Germany; telephone: 49.33.41.31.11.70; facsimile:
49.33.41.31.11.73. This information may also be examined at the Federal
Aviation Administration (FAA), Central Region, Office of the Regional
Counsel, Attention: Rules Docket 98-CE-106-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. Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City,
Missouri 64106; telephone: (816) 426-6934; facsimile: (816) 426-2169.
SUPPLEMENTARY INFORMATION:
Discussion
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for Germany, recently notified the FAA that an unsafe condition may
exist on certain Stemme Models S10, S10-V, and S10-VT sailplanes. The
LBA reports that cracks were found on the flight control longitudinal
coupling during a static load test on the elevator control system.
The cracks were such that the flight control system would have most
likely failed in a short period of operating time with reduced or loss
of control of the sailplane.
[[Page 65058]]
Other parts in the flight control system have the same type of
force intersection design and cracks could exist or develop in these
areas also. These areas are the wing flap coupling, part number (P/N)
10SW-RVW; the airbrake control coupling, P/N 10SB-RVW; the flap drive
rocker, P/N 10SW-RMW; and the flap/aileron interference shaft, P/N
10SQ-RMW.
Cracks in any of these areas, if not detected and corrected in a
timely manner, could result in flight control system failure with
consequent reduced or loss of control of the sailplane.
Relevant Service Information
Stemme has issued Service Bulletin A31-10-032, Amendment-Index
02.a, dated July 10, 1998, which specifies procedures for inspecting
the following parts for cracks:
The flight control longitudinal coupling, part number (P/
N) 10SH-RVH;
The wing flap coupling, P/N 10SW-RVW;
The airbrake control coupling, P/N 10SB-RVW;
The flap drive rocker, P/N 10SW-RMW; and
The flap/aileron interference shaft, P/N 10SQ-RMW.
This service bulletin also references Stemme Installation
Instructions A34-10-032-E, Amendment-Index 01.a, dated August 10, 1998,
which includes procedures for replacing the flight control longitudinal
coupling, with modified P/N 10SH-RVH coupling.
The LBA classified this service information as mandatory and issued
German AD 1998-323, dated July 1, 1998, in order to assure the
continued airworthiness of these sailplanes in Germany.
The FAA's Determination
These sailplane models are manufactured in Germany and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LBA has kept the FAA informed of
the situation described above.
The FAA has examined the findings of the LBA; reviewed all
available information, including the service information referenced
above; and determined that AD action is necessary for products of this
type design that are certificated for operation in the United States.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Stemme Models S10, S10-V, and S10-VT
sailplanes of the same type design registered for operation in the
United States, the FAA is taking AD action. This AD requires inspecting
the areas of the flight control system previously referenced for
cracks; immediately replacing any cracked parts; and eventually
replacing all longitudinal coupling with modified coupling regardless
if found cracked.
Accomplishment of the inspection will be required in accordance
with Stemme Service Bulletin A31-10-032, Amendment-Index 02.a, dated
July 10, 1998.
Accomplishment of the longitudinal coupling replacement will be
required in accordance with Stemme Installation Instructions A34-10-
032-E, Amendment-Index 01.a, dated August 10, 1998.
Accomplishment of the replacement of any other cracked part in the
flight control system will be required in accordance with procedures
obtained from the manufacturer through the FAA, Small Airplane
Directorate.
Possible Follow-up Action
Stemme has modified the longitudinal coupling, but has not modified
the wing flap coupling, the airbrake control coupling, the flap drive
rocker, and the flap/aileron interference shaft. If cracks are found on
parts other than the longitudinal coupling, then Stemme will develop
modified parts upon demand as quickly as possible. Operation of the
sailplane while the parts are being developed will not be allowed. The
FAA has determined that this alternative is better than operating the
sailplane with cracked parts in the flight control system.
The FAA will continue to monitor this situation, and may issue
additional AD action to require mandatory replacement of modified
flight control system parts other than the longitudinal coupling, as
these parts become available.
Compliance Time of This AD
The replacement compliance of this AD is presented in calendar time
and hours time-in-service (TIS). Cracks in the flight control system
occur because of sailplane operation; however, there is a potential for
corrosion in this area, which could enhance crack growth. For this
reason, the FAA has determined that requiring the replacement at 6
calendar months will assure the safety of the low-usage sailplanes; and
requiring the replacement at 100 hours TIS will assure the safety of
the high-usage sailplanes. The prevalent compliance time will be that
which occurs first.
Differences Between This AD, the Service Information, and the
German AD
Stemme Service Bulletin A31-10-032, Amendment-Index 02.a, dated
July 10, 1998, specifies inspecting certain areas of the flight control
system coupling prior to further flight on sailplanes with over 100
hours TIS. The German AD requires this on all sailplanes registered for
operation in Germany.
The FAA does not have the justification to require the initial
inspection prior to further flight on all sailplanes with over 100
hours TIS. The FAA is giving a grace period of 5 hours TIS for those
sailplanes that have more than 100 hours TIS on the flight control
system.
Determination of the Effective Date of the AD
Since a situation exists (possible flight control system failure)
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
[[Page 65059]]
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-106-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:
98-24-30 STEMME GMBH & Co. KG: Amendment 39-10917; Docket No. 98-
CE-106-AD.
Applicability: The following models and serial number
sailplanes, certificated in any category:
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Model Serial numbers
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S10........................... 10-03 through 10-63.
S10-V......................... 14-002 through 14-030 and transformed
S10-V sailplanes with serial numbers of
14-012M through 14-063M.
S10-VT........................ 11-001, 11-004 through 11-013, and 11-
015.
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Note 1: This AD applies to each sailplane 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 sailplanes 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 as indicated in the body of this AD, unless
already accomplished.
To detect and correct cracks in certain areas of the flight
control system, which could result in flight control system failure
with consequent reduced or loss of control of the sailplane,
accomplish the following:
(a) Upon accumulating 100 hours time-in-service (TIS) on the
flight control system or within the next 5 hours TIS after the
effective date of this AD, whichever occurs later, inspect the
following areas in the flight control system, in accordance with the
Instructions section of Stemme Service Bulletin A31-10-032,
Amendment-Index 02.a, dated July 10, 1998:
(1) The longitudinal coupling, part number (P/N) 10SH-RVH;
(2) The wing flap coupling, P/N 10SW-RVW;
(3) The airbrake control coupling, P/N 10SB-RVW;
(4) The flap drive rocker, P/N 10SW-RMW; and
(5) The flap/aileron interference shaft, P/N 10SQ-RMW.
(b) Prior to further flight after the inspection required by
paragraph (a) of this AD, replace any cracked part with a modified
part.
(1) Obtain modified parts (including installation instructions),
except for the longitudinal coupling, from the manufacturer through
the FAA, Small Airplane Directorate, at the address specified in
paragraph (e) of this AD.
(2) Obtain modified longitudinal coupling from the manufacturer
as specified in Stemme Service Bulletin A31-10-032, Amendment-Index
02.a, dated July 10, 1998; and install this modified longitudinal
coupling in accordance with Stemme Installation Instructions A34-10-
032-E, Amendment-Index 01.a, dated August 10, 1998.
Note 2: Stemme Service Bulletin A31-10-032, Amendment-Index
02.a, dated July 10, 1998, includes a return form for reporting the
findings of the crack inspection required by paragraph (a) of this
AD. The FAA encourages all owners/operators of the affected
sailplanes to have this form filled out and send it to the
manufacturer at the address specified in paragraph (g) of this AD.
(c) Within the next 6 calendar months after the effective date
of this AD or within the next 100 hours TIS after the effective date
of this AD, whichever occurs first, unless already accomplished
(compliance with the applicable part of paragraph (b) of this AD),
obtain modified longitudinal coupling from the manufacturer as
specified in Stemme Service Bulletin A31-10-032, Amendment-Index
02.a, dated July 10, 1998; and install this modified longitudinal
coupling in accordance with Stemme Installation Instructions A34-10-
032-E, Amendment-Index 01.a, dated August 10, 1998.
(d) As of the effective date of this AD, no person may install
on any affected sailplane, longitudinal coupling that has not been
modified as specified in Stemme Service Bulletin A31-10-032,
Amendment-Index 02.a, dated July 10, 1998; and installed in
accordance with Stemme Installation Instructions A34-10-032-E,
Amendment-Index 01.a, dated August 10, 1998.
(e) Special flight permits may be issued in accordance with
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the sailplane to a location where the
requirements of this AD can be accomplished.
(f) An alternative method of compliance or adjustment of the
compliance times that provides an equivalent level of safety may be
approved by the Manager, Small Airplane Directorate, 1201 Walnut,
suite 900, Kansas City, Missouri 64106. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Small Airplane
Directorate.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(g) Questions or technical information related to the service
information referenced in this AD should be directed to Stemme GmbH
& Co. KG, Gustav-Meyer-Allee 25, D-13355 Berlin, Federal Republic of
Germany; telephone: 49.33.41.31.11.70; facsimile: 49.33.41.31.11.73.
This service information may be examined at the FAA, Central Region,
Office of the Regional Counsel, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
(h) The inspection required by this AD shall be done in
accordance with Stemme
[[Page 65060]]
Service Bulletin A31-10-032, Amendment-Index 02.a, dated July 10,
1998. The longitudinal coupling replacement required by this AD
shall be done in accordance with Stemme Installation Instructions
A34-10-032-E, Amendment-Index 01.a, dated August 10, 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 Stemme GmbH & Co. KG, Gustav-Meyer-
Allee 25, D-13355 Berlin, Federal Republic of Germany. 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.
Note 4: The subject of this AD is addressed in German AD 1998-
323, dated July 1, 1998.
(i) This amendment becomes effective on December 18, 1998.
Issued in Kansas City, Missouri, on November 17, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 98-31434 Filed 11-24-98; 8:45 am]
BILLING CODE 4910-13-U