[Federal Register Volume 63, Number 66 (Tuesday, April 7, 1998)]
[Rules and Regulations]
[Pages 16883-16884]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-8582]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-19-AD; Amendment 39-10439; AD 97-08-02 R1]
RIN 2120-AA64
Airworthiness Directives; Schempp-Hirth K.G. Models Nimbus-2B,
Mini-Nimbus B, Discus a, and Discus b Sailplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This document clarifies information in an existing
airworthiness directive (AD) that applies to certain Schempp-Hirth K.G.
(Schempp-Hirth) Models Standard-Cirrus, Nimbus-2, Nimbus-2B, Mini-
Nimbus HS-7, Mini-Nimbus B, Discus a, and Discus b sailplanes. That AD
currently requires accomplishing a load test of the elevator control
system, and replacing the elevator vertical actuating tube either
immediately or at a certain time period depending on the results of the
load test. The actions specified in that AD are intended to prevent
corrosion in the elevator caused by water entering the elevator control
rod, which could result in elevator failure and consequent loss of
control of the sailplane. The Schempp-Hirth Models Nimbus 2, Mini-
Nimbus HS-7, and Standard Cirrus sailplanes are not equipped with
elevator control systems, and should not be affected by the current AD.
This action eliminates all reference to the Shempp-Hirth Models Nimbus
2, Mini-Nimbus HS-7, and Standard Cirrus sailplanes in the current AD.
DATES: Effective April 17, 1998.
The incorporation by reference of certain publications listed in
the regulations was approved previously by the Director of the Federal
Register as of May 30, 1997 (62 FR 16667, April 8, 1997).
FOR FURTHER INFORMATION CONTACT: Mr. J. Mike Kiesov, Project Officer,
FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City,
Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169.
SUPPLEMENTARY INFORMATION: On April 1, 1997, the Federal Aviation
Administration (FAA) issued AD 97-08-02, Amendment 39-9990 (62 FR
16667, April 8, 1997), which applies to certain Schempp-Hirth Models
Standard-Cirrus, Nimbus-2, Nimbus-2B, Mini-Nimbus HS-7, Mini-Nimbus B,
Discus a, and Discus b sailplanes. That AD requires accomplishing a
load test of the elevator control system, and replacing the elevator
vertical actuating tube either immediately or at a certain time period
depending on the results of the load test.
Accomplishment of the test and replacement is required in
accordance with Schempp-Hirth Technical Note No. 278-33, 286-28, 295-
22, 328-10, 349-16, 360-9, 373-5, dated November 19, 1992, and the
Appendix to this technical note.
AD 97-08-02 resulted from reported incidents of corrosion found in
the elevator because of water entering the elevator control rod. The
actions required by that AD are intended to prevent corrosion in the
elevator caused by water entering the elevator control rod, which could
result in elevator failure and consequent loss of control of the
sailplane.
Need for the Correction
The FAA inadvertently included the Schempp-Hirth Models Nimbus 2,
Mini-Nimbus HS-7, and Standard Cirrus sailplanes in the Applicability
of AD 97-08-02. These sailplane models are not equipped with elevator
control systems, and should not be affected by the current AD.
Correction of Publication
This document eliminates from the Applicability of AD 97-08-02
those sailplanes that are not equipped with elevator control systems.
The AD is being reprinted in its entirely for the convenience of
affected operators.
Since this action only clarifies the FAA's original intent, it has
no adverse economic impact and imposes no additional burden on any
person. Therefore, the FAA has determined that notice and public
procedures are unnecessary.
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.
[[Page 16884]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing AD 97-08-02, Amendment 39-
9990 (62 FR 16667, April 8, 1997), and by adding a new airworthiness
directive (AD) to read as follows:
97-08-02 R1 Schempp-Hirth K.G.: Amendment 39-10439; Docket No. 96-
CE-19-AD. Revises AD 97-08-02, Amendment 39-9990.
Applicability: The following sailplane models and serial
numbers, certificated in any category:
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Models Serial numbers
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Nimbus-2B................................. All serial numbers.
Mini-Nimbus B............................. All serial numbers.
Discus a and Discus b..................... Serial numbers 1 to 446.
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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 prevent corrosion in the elevator caused by water entering
the elevator control rod, which could result in elevator failure and
consequent loss of control of the sailplane, accomplish the
following:
(a) Prior to further flight after May 30, 1997 (the effective
date of AD 97-08-02), accomplish a load test of the elevator control
system in accordance with Schempp-Hirth Technical Note No. 278-33,
286-28, 295-22, 328-10, 349-16, 360-9, 373-5, dated November 19,
1992, and the Appendix to this technical note.
Note 2: Sections 61.107(d)(1) and 61.127(d)(1) of the Federal
Aviation Regulations (14 CFR 61.107(d)(1) and 14 CFR 61.127(d)(1))
give the authorization for glider/sailplane operators to disassemble
and reassemble the elevator control system (for storage purposes
between flights). The ``prior to further flight after the effective
date of this AD'' compliance time in paragraph (a) of this AD was
established to coincide with the next reassembly of the elevator
control system.
(b) If any discrepancies are found during the load test required
by paragraph (a) of this AD, prior to further flight, replace the
elevator vertical actuating tube in accordance with Schempp-Hirth
Technical Note No. 278-33, 286-28, 295-22, 328-10, 349-16, 360-9,
373-5, dated November 19, 1992, and the Appendix to this technical
note.
(c) Within the next 6 calendar months after May 30, 1997 (the
effective date of AD 97-08-02) or prior to further flight after May
30, 1997 (the effective date of AD 97-08-02), whichever occurs
later, unless already accomplished (performing the actions in
paragraph (b) of this AD), replace the elevator vertical actuating
tube in accordance with Schempp-Hirth Technical Note No. 278-33,
286-28, 295-22, 328-10, 349-16, 360-9, 373-5, dated November 19,
1992, and the Appendix to this technical note.
(d) The elevator control system load test as required by
paragraph (a) of this AD may be performed by the sailplane owner/
operator holding at least a private pilot certificate as authorized
by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7),
and must be entered into the aircraft records showing compliance
with this AD in accordance with section 43.9 of the Federal Aviation
Regulations (14 CFR 43.9).
(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 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, FAA, 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) The load test and replacement required by this AD shall be
done in accordance with Schempp-Hirth Technical Note No. 278-33,
286-28, 295-22, 328-10, 349-16, 360-9, 373-5, dated November 19,
1992, and the Appendix to this technical note. This incorporation by
reference was approved previously by the Director of the Federal
Register as of May 30, 1997 (62 FR 16667, April 8, 1997). Copies may
be obtained from Schempp-Hirth Flugzeugbau GmbH, Krebenstrasse 25,
Postfach 1443, D-73230 Kircheim/Teck, 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.
(h) This amendment becomes effective on April 17, 1998.
Issued in Kansas City, Missouri, on March 25, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-8582 Filed 4-6-98; 8:45 am]
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