AD 98-04-30 ACTIVE

This action confirms the effective date of Airworthiness Directive (AD) 98-04-30, which applies to Glaser-Dirks Flugzeugbau GmbH Model DG-500M gliders. AD 98-04-30 requires repetitively inspecting the propeller mounting plate for cracks, replacing any cracked propeller mounting plate, and modifying the bolt connections of the propeller mounting plate. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified in this AD are intended to prevent the propeller mounting plate from separating from the glider, which could result in propeller separation and possible loss of control of the glider.

Direct final rule; confirmation of effective date

98-04-30 GLASER-DIRKS FLUGZEUGBAU GMBH: Amendment 39-10342; Docket No. 97-CE-131-AD.
Applicability: Model DG-500M gliders, all serial numbers, certificated in any category.

NOTE 1: This AD applies to each glider 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 gliders 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 (e) 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 the propeller mounting plate from separating from the glider, which could result in propeller separation and possible loss of control of the glider, accomplish the following:

(a) Within the next 5 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 25 hours TIS, inspect the propeller mounting plate for cracks in accordance with the Instructions section of DG Flugzeugbau Technical Note TN 843/8, dated April 10, 1997.

(b) If any cracked propeller mounting plate is found during any inspection required by paragraph (a) of this AD, prior to further flight, replace any cracked propeller mounting plate with a new propeller mounting plate or FAA-approved propeller mounting plate in accordance with the above-referenced technical note.

(c) Within the next 5 hours TIS after the effective date of this AD, modify the bolt connections of the propeller mounting plate by inserting an aluminum plate between the propeller mounting plate and the washers of the bolt connections. Accomplish this modification in accordance with DG Flugzeugbau Technical Note TN 843/8, dated April 10, 1997.

(d) 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 glider to a location where the requirements of this AD can be accomplished.

(e) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be used if 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate.

(f) Questions or technical information related to DG Flugzeugbau Technical Note TN 843/8 dated April 10, 1997, should be directed to DG Flugzeugbau GmbH, P.O. Box 4120, 76625 Bruchsal, Germany; telephone: +49 7257-89-0; facsimile: +49 7257-8922. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City.

(g) The inspections and replacements required by this AD shall be done in accordance with DG Flugzeugbau Technical Note TN 843/8 dated April 10, 1997. 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 DG Flugzeugbau GmbH, P.O. Box 4120, 76625 Bruchsal, 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 3: The subject of this AD is addressed in German AD 97-224, dated July 31, 1997.

(h) This amendment (39-10342) becomes effective on May 15, 1998.

The FAA published this direct final rule with request for comments in the Federal Register on February 26, 1998 (63 FR 9743). The FAA uses the direct final rulemaking procedure for a non-controversial rule where the FAA anticipates that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or a written notice of intent to submit such an adverse comment, was received within the comment period, the regulation would become effective on May 15, 1998. No adverse comments were received, and thus this notice confirms that this final rule will become effective on that date.

Mr. Mike Kiesov, Aerospace Engineer, Small Airplane Directorate, Aircraft Certification Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-6934; facsimile: (816) 426-2169.