[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
