AD 97-08-02 R1

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.

Final rule; correction

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:

Models
Serial Numbers
Nimbus-2B
all serial numbers
Mini-Nimbus B
all serial numbers
Discus a and Discus b
serial numbers 1 to 446

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 unsafecondition 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 throughan 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 in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 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.

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.

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: