AD Amdt-39-10560

[Federal Register Volume 63, Number 107 (Thursday, June 4, 1998)]
[Rules and Regulations]
[Pages 30373-30375]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-14617]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-102-AD; Amendment 39-10560; AD 98-12-03]
RIN 2120-AA64


Airworthiness Directives; Alexander Schleicher Segelflugzeugbau 
Models ASW-19 and ASK 21 Sailplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Alexander Schleicher Segelflugzeugbau (Alexander 
Schleicher) Models ASW-19 and ASK 21 sailplanes. This AD requires: 
modifying the rudder surface panels; replacing the airbrake bellcrank; 
and modifying the rear canopy hinge structure. 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 loss of the canopy caused by design deficiency, 
airbrake failure caused by cracking, and rudder panel flutter caused by 
high density altitude conditions, all of which could result in reduced 
sailplane controllability.

DATES: Effective July 14, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 14, 1998.

ADDRESSES: 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

[[Page 30374]]

Aviation Administration (FAA), Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 97-CE-102-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. J. Mike Kiesov, Project Officer, 
Sailplanes/Gliders, Small Airplane Directorate, Aircraft Certification 
Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; 
telephone: (816) 426-6934; facsimile: (816) 426-2169.

SUPPLEMENTARY INFORMATION:

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 certain Alexander 
Schleicher Model ASW-19 and ASK 21 sailplanes was published in the 
Federal Register as a notice of proposed rulemaking (NPRM) on March 17, 
1998 (63 FR 13013). The NPRM proposed to require modifying the 
sailplanes' rudder panel by stiffening the rudder panel, reinforcing 
the rear canopy hinge, and replacing the airbrake bellcrank. 
Accomplishment of the proposed actions as specified in the NPRM would 
be in accordance with Alexander Schleicher ASW 19 Technical Note 2, 
dated September 6, 1976, and Alexander Schleicher ASK 21 Technical Note 
20, dated October 16, 1987.
    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

    The compliance time of this AD is presented in calendar time 
instead of hours time-in-service (TIS) because of the typical usage of 
the affected gliders. For example, an operator of an affected glider 
may only utilize the glider 50 hours TIS in a year, while another 
operator may utilize an affected glider 50 hours TIS in one month. 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 gliders in a reasonable time period.

Cost Impact

    The FAA estimates that 5 sailplanes in the U.S. registry will be 
affected by the rudder panel portion of this AD, that it will take 
approximately 10 workhours per sailplane to accomplish the rudder panel 
portion of this AD, and that the average labor rate is approximately 
$60 an hour. Parts cost approximately $50 per sailplane. Based on these 
figures, the total cost impact of the rudder panel portion of this AD 
on U.S. operators is estimated to be $3,250, or $650 per sailplane.
    The FAA estimates that 30 sailplanes in the U.S. registry will be 
affected by the airbrake bellcrank portion of this AD, that it will 
take approximately 6 workhours per sailplane to accomplish the rudder 
panel portion of this AD, and that the average labor rate is 
approximately $60 an hour. Parts cost approximately $200 per sailplane. 
Based on these figures, the total cost impact of the airbrake bellcrank 
portion of this AD on U.S. operators is estimated to be $16,800, or 
$560 per sailplane.
    The FAA estimates that 30 sailplanes in the U.S. registry will be 
affected by the rear canopy hinge portion of this AD, that it will take 
approximately 11 workhours per sailplane to accomplish the rear canopy 
hinge portion of this AD, and that the average labor rate is 
approximately $60 an hour. Parts cost approximately $15 per sailplane. 
Based on these figures, the total cost impact of the rear canopy hinge 
portion proposed AD on U.S. operators is estimated to be $20,250, or 
$675 per sailplane.

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.
    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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

98-12-03  Alexander Schleicher Segelflugzeugbau: Amendment 39-10560; 
Docket No. 97-CE-102-AD.

    Applicability: Model ASW-19 sailplanes (serial numbers 19019 
through 19037, 19040, and 19042 through 19044), and Model ASK 21 
sailplanes (serial numbers 21001 through 21345), 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 (c) 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 loss of the canopy caused by design deficiency, 
airbrake failure caused by cracking, and rudder panel flutter caused 
by high density altitude conditions, all of which

[[Page 30375]]

could result in reduced sailplane controllability, accomplish the 
following:
    (a) Within the next 3 calendar months after the effective date 
of this AD, accomplish the following:
    (1) For Alexander Schleicher Model ASW-19 sailplanes, modify the 
rudder panel in accordance with the Instructions section in 
Alexander Schleicher ASW 19 Technical Note No. 2, dated September 6, 
1976.
    (2) For Alexander Schleicher Model ASK 21 sailplanes, replace 
the airbrake bellcrank with an airbrake bellcrank of improved design 
in accordance with the Action section, paragraphs 3.1, 3.2, and 3.3 
in Alexander Schleicher ASW 21 Technical Note No. 20, dated October 
16, 1987.
    (3) For Alexander Schleicher Model ASK 21 sailplanes, modify the 
rear canopy hinge in accordance with the Action section, paragraph 
4.2, in Alexander Schleicher ASW 21 Technical Note No. 20, dated 
October 16, 1987.
    (b) 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.
    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the 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.

    (d) Questions or technical information related to the service 
information referenced in this AD, should be directed to Alexander 
Schleicher Segelflugzeugbau, 6416 Poppenhausen, Wasserkuppe, Federal 
Republic of Germany. 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.
    (e) The modifications and replacement required by this AD shall 
be done in accordance with Alexander Schleicher ASW 19 Technical 
Note 2, dated September 6, 1976, and Alexander Schleicher ASK 21 
Technical Note 20, dated October 16, 1987. 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, Wasserkuppe, 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 3: The subject of this AD is addressed in German AD No. 76-
258, dated September 3, 1976, for the rudder panel condition; and 
German AD No. 88-2, dated January 1, 1988, for the airbrake 
bellcrank and the rear canopy hinge conditions.

    (f) This amendment becomes effective on July 14, 1998.

    Issued in Kansas City, Missouri, on May 22, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-14617 Filed 6-3-98; 8:45 am]
BILLING CODE 4910-13-U