[Federal Register Volume 63, Number 27 (Tuesday, February 10, 1998)]
[Rules and Regulations]
[Pages 6629-6633]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3130]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-35-AD; Amendment 39-10213; AD 97-24-06]
RIN 2120-AA64


Airworthiness Directives; Glasflugel Models Standard Libelle and 
Standard Libelle 201 B 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 Glasflugel Models Standard Libelle and Standard Libelle 201 
B sailplanes. This action requires inspecting the aileron operating 
lever's actuating shaft welded seams for cracks; modifying or replacing 
the actuating shaft, if cracked; and, if no cracks are found, 
eventually modifying or

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replacing the shaft. Cracks found in the welded seams of the actuating 
shaft prompted this action. The actions specified by this AD are 
intended to prevent cracks in the aileron operating lever's actuating 
shaft welded seams, which, if not detected and corrected, could cause 
loss of control of the sailplane.

DATES: Effective March 13, 1998.

ADDRESSES: Service information that pertains to this AD may be obtained 
from Glasflugel, c/o H. Streifeneder, Glasfaser-Flugzeug Service GmbH, 
Hofener Weg, D-72582 Grabenstetten, Germany. This information may also 
be examined at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket 96-CE-
35-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr. J. Mike Kiesov, Project Officer, 
Sailplanes, FAA, Small Airplane Directorate, 1201 Walnut, suite 900, 
Kansas City, Missouri 64106; telephone (816) 426-6932, 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 Glasflugel Models 
Standard Libelle and Standard Libelle 201 B Sailplanes was published in 
the Federal Register on December 10, 1996 (61 FR 65006). The action 
proposed to require inspecting the aileron operating lever's actuating 
shaft welded seams for cracks. If cracks are found, the proposal 
specifies repairing and modifying, or replacing the actuating shaft. If 
no cracks are found, the actuating shaft would be modified or replaced 
at a later time. Accomplishment of these actions was proposed in 
accordance with the Glasfaser-Flugzeug-Service GmbH Technical Note (TN) 
201-33, dated March 4, 1996. Based upon the difficulty in obtaining the 
above-referenced technical note for U.S. operators of the affected 
airplanes, the FAA is revising the proposal to include an AD appendix 
which incorporates the Accomplishment Instructions and Figures of the 
Glasfaser-Flugzeug GbmH Technical Note TN 201-33, dated March 4, 1996.
    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 including the referenced service information, 
the FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed, except for the addition of the 
appendix described above and minor editorial corrections.

Cost Impact

    The FAA estimates that 108 sailplanes in the U.S. registry will be 
affected by this AD; that it will take approximately 4 workhours per 
sailplane to accomplish the inspection, repair and modification; or 
that it will take 3 workhours per sailplane to inspect and replace the 
lever shaft; and that the average labor rate is estimated to be 
approximately $60 an hour. Material cost for the modification is 
approximately $10 per sailplane, and a replacement shaft part costs 
$140 per sailplane. Based on these figures, the total cost impact of 
this AD on U.S. operators is estimated to be $27,000 ($250 per 
sailplane) if all shafts are modified, or $34,560 ($320 per sailplane) 
if all shafts are replaced. This figure is based on the presumption 
that no affected sailplane owner/operator has accomplished the 
inspection or modification.

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, 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:

97-24-06.  Glasflugel: Amendment 39-10213; Docket No. 96-CE-35-AD.

    Applicability: Models Standard Libelle and Standard Libelle 201 
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 (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 cracks in the aileron operating lever's actuating 
shaft welded seams, which, if not detected and corrected, could 
cause loss of control of the sailplane, accomplish the following:
    (a) Within the next 30 calendar days after the effective date of 
this AD, inspect for cracks in the paint of the aileron operating 
lever's actuating shaft welded seams using a magnifying glass (2x 
minimum) and a flashlight, and if there are cracks in the paint, 
then prior to further flight, remove the actuating shaft and perform 
a dye-penetrant inspection for cracks in accordance with Method 1 in 
the Accomplishment Instructions section and Figure 1 of the Appendix 
to this AD.
    (1) If cracks are seen in the actuating shaft, prior to further 
flight, either:
    (i) Repair any cracked welded seams, and modify the shaft in 
accordance with Method 2 of the Accomplishment Instructions and 
Figure 2 in the Appendix of this AD; or,
    (ii) Remove and replace the shaft with a new Glasflugel 
reinforced shaft in accordance

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with Figure 1 and Method 3 in the Accomplishment Instructions in the 
Appendix of this AD.
    (2) If no cracks are found, within the next 8 calendar months 
after the inspection required by paragraph (a) of this AD, either:
    (i) Modify the aileron operating lever's shaft in accordance 
with Method 2 of the Accomplishment Instructions in the Appendix of 
this AD; or,
    (ii) Remove and replace the shaft with a new Glasflugel 
reinforced shaft in accordance with Method 3 in the Accomplishment 
Instructions and Figure 1 in the Appendix of this AD.

    Note 2: The FAA recommends that the shafts be finished with 
zinc-chromate primer and paint with a grayish-green shade.

    (b) After completing any action described in paragraph (a) or 
any sub-paragraph of (a) in this AD, prior to further flight, check 
and adjust the aileron deflection range in accordance with the 
``Remarks'' paragraph in the Accomplishment Instructions in the 
Appendix of this AD.
    (c) Accomplishing all of the actions specified in the 
Accomplishment Instructions section of Glasfaser-Flugzeug Service 
GmbH Technical Note 201-33, dated March 4, 1996, incorporates the 
intent of this AD. No further action is required.
    (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 sailplane to a location where 
the requirements of this AD can be accomplished.
    (e) 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, 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.

    (f) Information related to this AD may be examined at the FAA, 
Central Region, Office of the Regional Counsel, Room 1558, 601 E. 
12th Street, Kansas City, Missouri.

Appendix to AD 97-24-06--Aileron Actuating Shaft

Accomplishment Instructions

    Method 1:

    Note: The term ``WIG-inert protective atmosphere welding 
system'' used within the Appendix text has the U.S. equivalent of 
Tungsten Inert Gas (TIG) welding system.

    Using a magnifying glass (2x minimum) and a flashlight, inspect 
the aileron actuating shaft in the fuselage (see Figure 1) near the 
welding seams for cracks in the paint. If there is any cracked paint 
on the actuating shaft, prior to further flight, remove the 
actuating shaft and inspect for cracks in the shaft and welding 
seams using a dye-penetrant method. If there are no cracks or any 
other damage, flying operation can continue until the accumulation 
of 8 calendar months after the initial inspection required by this 
AD, at which time Method 2 or Method 3 shall be accomplished. If 
cracks are found, prior to further flight, accomplish Method 2 or 
Method 3.

    Note: In Figure 2, the doubler has physical dimensions of: 90 mm 
 x  12 mm  x  1 mm, with the ends having a radius of 6 mm.

Appendix to AD 97-24-06--Aileron Actuating Shaft

    Method 2:
    Remove all paint. Weld (grove welding) all cracks. Weld the 
joints with the WIG-inert protective atmosphere welding system 
(wolfram inert gas welding system) with welding material 1.7734.2. 
Weld the plates (position 7) to the actuating shaft according to 
Figure 2. Finish the actuating shaft with primer and paint (paint 
type RAL 7003). Reinstall the aileron actuating shaft.

    Note: Method 2 in the Appendix refers to welding material 
1.7734.2. The FAA and the LBA were unable to determine the U.S. 
equivalent to this material. The recommended options would be to 
order the original part from the manufacturer, order the welding 
material from the manufacturer, or order welding material 1.7734.2 
from Germany, Italy or France.

    Method 3: 
    As an alternative to Method 2, replace the original actuating 
shaft with a new reinforced shaft according to Figure 1.
    Mass and balance: Not Affected.

Appendix to AD 97-24-06--Aileron Actuating Shaft

Remarks

    For rigging and derigging procedures, refer to the flight 
manual, page E12. After accomplishing repairs according to Method 2, 
or replacement of the actuating shaft according to Method 3, the 
aileron deflections must be checked. Plates, welding material, and 
spare parts as mentioned are available from the manufacturer.
BILLING CODE 4910-13-P

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[GRAPHIC] [TIFF OMITTED] TR10FE98.002



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[GRAPHIC] [TIFF OMITTED] TR10FE98.003


    (g) This amendment (39-10213) becomes effective on March 13, 
1998.

    Issued in Kansas City, Missouri, on February 2, 1998.
Carolanne L. Cabrini,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-3130 Filed 2-9-98; 8:45 am]
BILLING CODE 4910-13-C