AD 98-18-05 ACTIVE

This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher ) Models K 8 and K 8 B sailplanes. This AD requires inspecting the canopy hood lock assembly to assure that the height of the cam is at least 2 millimeters (mm), and modifying or replacing any canopy hood lock assembly where the cam is less than 2 mm in height. 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 prevent the canopy from coming open in flight because the height of the locking cam is less than 2 mm, which could result in loss of the canopy with consequent pilot injury.

Final rule.

98-18-05 ALEXANDER SCHLEICHER SEGELFLUGZEUGBAU: Amendment 39-10721; Docket No. 98-CE-02-AD.

Applicability: Models K 8 and K 8 B sailplanes, all serial numbers, certificated in any category.

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 (d) 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 thisAD, unless already accomplished.

To prevent the canopy from coming open in flight because the height of the locking cam is less than 2 millimeters (mm), which could result in loss of the canopy with consequent pilot injury, accomplish the following:

(a) Within the next 3 calendar months after the effective date of this AD, inspect the canopy hood lock assembly to assure that the height of the cam is at least 2 mm, in accordance with Alexander Schleicher Technical Note No. 21, dated May 12, 1980.

(b) Prior to further flight after the inspection required by paragraph (a) of this AD, accomplish one of the following, if applicable:

(1) Modify (file) any canopy hood lock assembly where the cam is less than 2 mm in height, in accordance with Alexander Schleicher Technical Note No. 21, dated May 12, 1980; and apply a corrosion preventative (alodine or equivalent substitute); or

(2) Replace any canopy hood lock assembly where the cam is less than 2 mm in height, inaccordance with the applicable maintenance manual.

(c) 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.

(d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Manager, Small Airplane Directorate, Aircraft Certification Service, 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.

(e) Questions or technical information related to Alexander Schleicher Technical Note No. 21, dated May 12, 1980, should be directed to Alexander Schleicher Segelflugzeugbau, 6416 Poppenhausen, Federal Republic of Germany; telephone: 49.6658.890 or 49.6658.8920; facsimile: 49.6658.8923 or 49.6658.8940. 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.

(f) The inspection and modification required by this AD shall be done in accordance with Alexander Schleicher Technical Note No. 21, dated May 12, 1980. 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 Alexander Schleicher Segelflugzeugbau, 6416 Poppenhausen, 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 CapitolStreet, NW, suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in German AD No. 80-158, dated June 16, 1980.

(g) This amendment becomes effective on October 12, 1998.

Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Alexander Schleicher Models K 8 and K 8 B sailplanes was published in the Federal Register as a notice of proposed rulemaking (NPRM) on June 9, 1998 (63 FR 31368). The NPRM proposed to require inspecting the canopy hood lock assembly to assure that the height of the cam is at least 2 mm, and modifying or replacing any canopy hood lock assembly where the cam is less than 2 mm in height. Accomplishment of the proposed action as specified in the NPRM would be in accordance with Alexander Schleicher Technical Note No. 21, dated May 12, 1980.

The NPRM was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.

Compliance Time of This AD

Although the canopy opening will only be unsafe during flight, the condition specified in this AD is not a result of the number of times the sailplane is operated. The chance of this situation occurring is the same for a sailplane with 10 hours time-in-service (TIS) as it will be for a sailplane with 500 hours TIS. For this reason, the FAA has determined that a compliance based on calendar time should be utilized in this AD in order to assure that the unsafe condition is addressed on all sailplanes in a reasonable time period.

Cost Impact

The FAA estimates that 100 sailplanes in the U.S. registry will be affected by this AD, that it will take approximately 1 workhour per sailplane to accomplish the inspection, and that the average labor rate is $60 per work hour. No parts will be required to accomplish the modification. Parts will cost $50 per sailplane if the replacement option is chosen over the modification. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $11,000, or $110 per sailplane if the replacement option is chosen; or $6,000, or $60 per sailplane if the modification option is chosen.

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 ofgovernment. 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.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption "ADDRESSES".

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 adding a new airworthiness directive (AD) to read as follows:

Service information that applies to this AD may be obtained from Alexander Schleicher Segelflugzeugbau, 6416 Poppenhausen, Wasserkuppe, Federal Republic of Germany; telephone: 49.6658.890 or 49.6658.8920; facsimile: 49.6658.8923 or 49.6658.8940. This information may also be examined at the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-02-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.

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