Airworthiness Directives; Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT Sailplanes, 47714-47717 [E6-13440]
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47714
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
TABLE 3.—ACTIONS, COMPLIANCE, AND PROCEDURES FOR GROUP 2 AIRPLANES—Continued
Actions
Compliance
(iv) T206 only: Union at the aft vertical
cooling baffle to the fuel injector servo.
(v) Fuel injector servo to fuel flow transducer.
(vi) Fuel flow transducer to fuel manifold
valve.
(vii) Fuel injector servo return to firewall fitting.
(2) If any incorrect torque values are found during the inspection required by paragraph
(f)(1) of this AD, clean and dry the threads of
all fittings, and tighten the hose end fittings to
the correct torque values as defined in Table
4.
(g) Use the following table for the correct
torque values to tighten the hose end fittings
Procedures
Before further flight after the inspection re- Follow Cessna Service Bulletin No. SB06–71–
quired by paragraph (f)(1) of this AD, in
02, dated June 19, 2006.
which any incorrect torque values are found.
as required in paragraphs (e)(2) and (f)(2) of
this AD:
TABLE 4.—TORQUE VALUES FOR HOSE END FITTINGS
Correct torque in inch-pounds
Flare hex sizes in fractions of an inch
Hose size
Minimum
¥4
¥6
¥8
⁄
................................................................................................................................................
..............................................................................................................................................
7⁄8 .................................................................................................................................................
9 16
⁄
11 16
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, ATTN: Jeff
Janusz, Aerospace Engineer, FAA, Wichita
ACO, 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–4148;
facsimile: (316) 946–4107, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
rwilkins on PROD1PC63 with RULES
Material Incorporated by Reference
(i) You must do the actions required by this
AD following the instructions in Cessna
Service Bulletin No. SB06–71–02, dated June
19, 2006. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact The
Cessna Aircraft Company, Product Support,
P.O. Box 7706, Wichita, Kansas 67277–7706;
telephone: (316) 517–5800; facsimile: (316)
942–9006. To review copies of this service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, go to: https://www.archives
.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–25262; Directorate Identifier 2006–CE–
39–AD.
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
Issued in Kansas City, Missouri, on August
9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–13442 Filed 8–17–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24641; Directorate
Identifier 2006–CE–27–AD; Amendment 39–
14724; AD 2006–17–03]
RIN 2120–AA64
Airworthiness Directives; Stemme
GmbH & Co. KG Models S10, S10–V,
and S10–VT Sailplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Stemme GmbH & Co. KG (Stemme)
Models S10, S10–V, and S10–VT
sailplanes. This AD requires you to
inspect the connection between the
aileron push-rod and the connecting
shaft to determine if a safety washer is
installed. If there is no safety washer
installed, this AD requires you to
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135
270
450
Maximum
150
300
500
modify the aileron control assembly.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by the airworthiness
authority for Germany. We are issuing
this AD to prevent a loose bearing in the
aileron control lever, which could result
in separation of the aileron control
system. Separation of the aileron control
system could lead to loss of aileron
control.
DATES: This AD becomes effective on
September 22, 2006.
As of September 22, 2006, the
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulation.
ADDRESSES: To get the service
information identified in this AD,
contact STEMME AG, Flugplatzstrabe F
2, Nr. 7, D–15344 Strausberg, Germany;
telephone: + 49.33.41/36 12–0;
facsimile: + 49.33.41/36 12–30; e-mail:
P.Ellwanger@stemme.de.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–24641; Directorate Identifier
2006–CE–27–AD.
FOR FURTHER INFORMATION CONTACT:
Gregory A. Davison, Aerospace
E:\FR\FM\18AUR1.SGM
18AUR1
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
Engineer, ACE–112, Small Airplane
Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4130; facsimile: (816) 329–
4090.
SUPPLEMENTARY INFORMATION:
Discussion
On May 24, 2006, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Stemme Models S10, S10–V, and
S10–VT sailplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on June 2, 2006 (71 FR 31980). The
NPRM proposed to require you to
inspect the joint between the aileron
control rod, part number (P/N) 10SQ–
RMB, and the connecting shaft, P/N
10SQ–RMW, to determine if a safety
washer is installed. If a safety washer is
not installed, the NPRM proposed to
require you to modify this area by
replacing the joint bolt (P/N LN9037–
06042), installing a safety washer (P/N
D440–06), and installing washer (P/N
10M–282).
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
Labor cost
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD will affect
105 sailplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Parts cost
1 work-hour × $80 per hour = $80 .......................................................................................
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
inspection. We have no way of
Total cost per
sailplane
N/A
$80
Parts cost
2 work-hours × $80 per hour = $160 ...............................................................................................................
rwilkins on PROD1PC63 with RULES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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.
We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2006–24641;
Directorate Identifier 2006–CE–27–AD’’
in your request.
Total cost on U.S.
operators
105 × $80 =
$8,400
determining the number of sailplanes
that may need this replacement:
Labor cost
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106 describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this AD.
47715
$30
Total cost per sailplane
$160 + $30 = $190
Adoption of the Amendment
Accordingly, under 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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by adding a
new AD to read as follows:
2006–17–03 Stemme GmbH & Co. KG:
Amendment 39–14724; Docket No.
FAA–2006–24641; Directorate Identifier
2006–CE–27–AD.
Effective Date
(a) This AD becomes effective on
September 22, 2006.
List of Subjects in 14 CFR Part 39
Affected ADs
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(b) None.
(c) This AD affects the following sailplane
models and serial numbers that are
certificated in any category:
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18AUR1
47716
Model
S10 ..........
S10–V ......
S10–VT ....
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
Unsafe Condition
Serial Nos.
10–03 through 10–56.
14–001 through 14–030 (including all converted versions 14–
003M through 14–056M).
11–001 through 11–089.
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Germany. We are issuing this AD to prevent
a loose bearing in the aileron control lever,
which could result in separation of the
aileron control system. Separation of the
aileron control system could lead to loss of
aileron control.
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect the joint between the aileron control
rod, part number (P/N) 10SQ–RMB (or FAAapproved equivalent part number), and the
connecting shaft, P/N 10SQ–RMW (or FAA–
approved equivalent part number), to determine if a safety washer, P/N DIN 440–06 (or
FAA-approved equivalent part number), is installed.
(2) If after the inspection required in paragraph
(e)(1) of this AD, you can positively determine that a safety washer, P/N DIN 440–06
(or FAA-approved equivalent part number), is
installed between the joint in the aileron control rod and the connecting shaft, no further
action is required.
(3) If after the inspection required in paragraph
(e)(1) of this AD, you cannot positively determine that a safety washer is installed between the joint in the aileron control rod and
the connecting shaft, do the following.
(i) Install a safety washer, P/N DIN 440–06
(or FAA-approved equivalent part number);
(ii) Replace the existing bolt with bolt, P/N
LN9037–06042 (or FAA-approved equivalent part number), from the modification
kit; and
(iii) Install washer, P/N 10M–282 (or FAAapproved equivalent part number)
(4) 14 CFR 21.303 allows for replacement parts
through parts manufacturer approval (PMA).
The phrase ‘‘or FAA-approved equivalent part
number’’ in this AD is intended to signify
those parts that are PMA parts approved
through identicality to the design of the part
under the type certificate and replacement
parts to correct the unsafe condition under
PMA (other than identicality). If parts are installed that are identical to the unsafe parts,
then the corrective actions of the AD affect
these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may
also be installed provided they meet current
airworthiness standards, which include those
actions cited in this AD.
Within the next 20 hours time-in-service after
September 22, 2006 (the effective date of
this AD).
Follow Stemme Service Bulletin Document
Number: A31–10–069, Am.-Index 01.a,
dated September 10, 2004
Not applicable ..................................................
Not applicable
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Stemme Service Bulletin Document
Number: A31–10–069, Am.-Index 01.a,
dated September 10, 2004.
Not applicable ..................................................
Not applicable.
rwilkins on PROD1PC63 with RULES
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Standards Office, Small
Airplane Directorate, FAA, ATTN: Gregory
A. Davison, Aerospace Engineer, ACE–112,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; facsimile: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) German AD Number D–2004–443, dated
September 27, 2004, addresses the subject of
this AD.
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
Material Incorporated by Reference
(h) You must do the actions required by
this AD following the instructions in Stemme
Service Bulletin Document Number: A31–
10–069, Am.-Index 01.a, dated September 10,
2004. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact
STEMME AG, Flugplatzstrabe F 2, Nr. 7, D–
15344 Strausberg, Germany; telephone: +
49.33.41 / 36 12–0; facsimile: + 49.33.41 / 36
12–30. To review copies of this service
information, go to the National Archives and
Records Administration (NARA). For
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information on the availability of this
material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–24641; Directorate Identifier 2006–CE–
27–AD.
E:\FR\FM\18AUR1.SGM
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Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
Issued in Kansas City, Missouri, on August
9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–13440 Filed 8–17–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004–NE–05–AD; Amendment
39–14706; AD 2006–16–06]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
GE CF6–80 series turbofan engines with
certain stage 1 high-pressure turbine
(HPT) rotor disks. That AD currently
requires an initial inspection as a
qualification for the mandatory rework
procedures for certain disks, and
repetitive inspections only for certain
disks for which the rework procedures
were not required. That action also
requires reworking certain disks before
further flight, and removes certain CF6–
80E1 series disks from service. This AD
requires the same actions but shortens
the compliance schedule for HPT disks
that have not been previously inspected
using AD 2004–04–07, which this AD
supersedes. This AD results from a
recent report of an uncontained failure
of a stage 1 HPT disk. We are issuing
this AD to detect and prevent cracks in
the bottoms of the dovetail slots that
could propagate to failure of the disk
and cause an uncontained engine
failure.
Effective September 5, 2006. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of September 5, 2006. The
Director of the Federal Register
previously approved the incorporation
by reference of certain other
publications listed in the regulations as
of March 12, 2004 (69 FR 8801,
February 26, 2004).
We must receive any comments on
this AD by October 17, 2006.
rwilkins on PROD1PC63 with RULES
DATES:
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
Use one of the following
addresses to submit comments on this
ad:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2004–NE–
05–AD, 12 New England Executive Park,
Burlington, MA 01803.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
Contact General Electric Company via
Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati,
Ohio 45215, telephone (513) 672–8400,
fax (513) 672–8422, for the service
information identified in this AD.
You may examine the AD docket, by
appointment, at the FAA, New England
Region, Office of the Regional Counsel,
12 New England Executive Park,
Burlington, MA. You may examine the
service information, by appointment, at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone: (781) 238–7176, fax:
(781) 238–7199.
On
February 13, 2004, we issued AD 2004–
04–07, Amendment 39–13488 (69 FR
38; February 26, 2004). That AD
requires an initial inspection as a
qualification for the mandatory rework
procedures for certain disks, and
repetitive inspections only for certain
disks for which the rework procedures
were not required. That action also
requires reworking certain disks before
further flight. That AD was the result of
the manufacturer’s investigation and
development of a rework procedure to
chamfer the aft breakedge of the dovetail
slot bottom to reduce stresses. That
condition, if not corrected, could result
in cracks in the bottoms of the dovetail
slots that could propagate to failure of
the disk and cause an uncontained
engine failure.
SUPPLEMENTARY INFORMATION:
Actions Since AD 2004–04–07 Was
Issued
Since AD 2004–04–07 was issued, a
CF6–80A turbofan engine, installed on a
Boeing 767 airplane, experienced an
uncontained stage 1 HPT disk failure on
June 2, 2006. The disk failure resulted
in a fire and significant damage to the
airplane. The event occurred during an
on-ground maintenance operation.
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47717
Relevant Service Information
We reviewed and approved the
technical contents of the following GE
Service Bulletins (SBs) and Alert
Service Bulletin (ASB) that describe
procedures for removing, inspecting,
and reworking certain stage 1 HPT rotor
disks:
• SB No. CF6–80E1 S/B 72–0251,
dated January 22, 2004;
• SB No. CF6–80A S/B 72–0779,
Revision 1, dated January 22, 2004;
• SB No. CF6–80A S/B 72–0788,
Revision 3, dated July 20, 2006;
• SB No. CF6–80A S/B 72–0822,
dated July 20, 2006;
• ASB No. CF6–80C2 S/B 72–A1026,
Revision 2, dated January 22, 2004;
• SB No. CF6–80C2 S/B 72–1089,
Revision 3, dated July 20, 2006;
• SB No. CF6–80C2 S/B 72–1217,
dated July 20, 2006.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other GE CF6–80 series turbofan
engines of the same type design. This
AD requires rework of the dovetail slot
bottom of certain stage 1 rotor disks.
The disks must pass an inspection to
qualify for the rework. This AD also
requires removal from service of certain
disks for which the rework procedures
were not previously required. This AD
also tightens the compliance schedule
for HPT disks that have not been
previously inspected using AD 2004–
04–07. Operators must use the
compliance schedule carried forward
from AD 2004–04–07 or the new
compliance schedule below, whichever
occurs first:
• For stage 1 HPT rotor disks with
9,000 or more cycles-since-new (CSN)
on the effective date of this AD, within
250 cycles-in-service (CIS) after the
effective date of this AD, or by March
31, 2007, whichever occurs first.
• For stage 1 HPT rotor disks with
6,900 or more but fewer than 9,000 CSN
on the effective date of this AD, within
500 CIS after the effective date of this
AD, or before accumulating 9,250 CSN,
or by December 31, 2007, whichever
occurs first.
• For stage 1 HPT rotor disk with
fewer than 6,900 CSN on the effective
date of this AD, before accumulating
7,400 CSN, or by December 31, 2008,
whichever occurs first.
This AD also removes from service
certain CF6–80E1 series disks. You must
use the service information described
previously to perform the actions
required by this AD.
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]]>Agencies
[Federal Register Volume 71, Number 160 (Friday, August 18, 2006)]
[Rules and Regulations]
[Pages 47714-47717]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13440]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24641; Directorate Identifier 2006-CE-27-AD;
Amendment 39-14724; AD 2006-17-03]
RIN 2120-AA64
Airworthiness Directives; Stemme GmbH & Co. KG Models S10, S10-V,
and S10-VT Sailplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Stemme GmbH & Co. KG (Stemme) Models S10, S10-V, and S10-VT sailplanes.
This AD requires you to inspect the connection between the aileron
push-rod and the connecting shaft to determine if a safety washer is
installed. If there is no safety washer installed, this AD requires you
to modify the aileron control assembly. This AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Germany. We are issuing this AD to prevent a loose
bearing in the aileron control lever, which could result in separation
of the aileron control system. Separation of the aileron control system
could lead to loss of aileron control.
DATES: This AD becomes effective on September 22, 2006.
As of September 22, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact STEMME AG, Flugplatzstra[beta]e F 2, Nr. 7, D-15344 Strausberg,
Germany; telephone: + 49.33.41/36 12-0; facsimile: + 49.33.41/36 12-30;
e-mail: P.Ellwanger@stemme.de.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-24641; Directorate
Identifier 2006-CE-27-AD.
FOR FURTHER INFORMATION CONTACT: Gregory A. Davison, Aerospace
[[Page 47715]]
Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile:
(816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
On May 24, 2006, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Stemme Models S10, S10-V, and S10-VT sailplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on June 2, 2006 (71 FR 31980). The NPRM
proposed to require you to inspect the joint between the aileron
control rod, part number (P/N) 10SQ-RMB, and the connecting shaft, P/N
10SQ-RMW, to determine if a safety washer is installed. If a safety
washer is not installed, the NPRM proposed to require you to modify
this area by replacing the joint bolt (P/N LN9037-06042), installing a
safety washer (P/N D440-06), and installing washer (P/N 10M-282).
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD will affect 105 sailplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost sailplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80.......... N/A $80 105 x $80 = $8,400
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. We have
no way of determining the number of sailplanes that may need this
replacement:
------------------------------------------------------------------------
Labor cost Parts cost Total cost per sailplane
------------------------------------------------------------------------
2 work-hours x $80 per hour = $30 $160 + $30 = $190
$160.
------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106 describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2006-24641; Directorate Identifier 2006-CE-27-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under 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
0
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]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2006-17-03 Stemme GmbH & Co. KG: Amendment 39-14724; Docket No. FAA-
2006-24641; Directorate Identifier 2006-CE-27-AD.
Effective Date
(a) This AD becomes effective on September 22, 2006.
Affected ADs
(b) None.
(c) This AD affects the following sailplane models and serial
numbers that are certificated in any category:
[[Page 47716]]
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
S10............................... 10-03 through 10-56.
S10-V............................. 14-001 through 14-030 (including all
converted versions 14-003M through
14-056M).
S10-VT............................ 11-001 through 11-089.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Germany. We are issuing this AD to prevent a loose bearing in the
aileron control lever, which could result in separation of the
aileron control system. Separation of the aileron control system
could lead to loss of aileron control.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the joint Within the next 20 Follow Stemme
between the aileron control hours time-in- Service Bulletin
rod, part number (P/N) 10SQ- service after Document Number:
RMB (or FAA-approved September 22, 2006 A31-10-069, Am.-
equivalent part number), (the effective date Index 01.a, dated
and the connecting shaft, P/ of this AD). September 10, 2004
N 10SQ-RMW (or FAA-approved
equivalent part number), to
determine if a safety
washer, P/N DIN 440-06 (or
FAA-approved equivalent
part number), is installed.
(2) If after the inspection Not applicable...... Not applicable
required in paragraph
(e)(1) of this AD, you can
positively determine that a
safety washer, P/N DIN 440-
06 (or FAA-approved
equivalent part number), is
installed between the joint
in the aileron control rod
and the connecting shaft,
no further action is
required.
(3) If after the inspection Before further Follow Stemme
required in paragraph flight after the Service Bulletin
(e)(1) of this AD, you inspection required Document Number:
cannot positively determine in paragraph (e)(1) A31-10-069, Am.-
that a safety washer is of this AD. Index 01.a, dated
installed between the joint September 10, 2004.
in the aileron control rod
and the connecting shaft,
do the following.
(i) Install a safety
washer, P/N DIN 440-06
(or FAA-approved
equivalent part
number);
(ii) Replace the
existing bolt with
bolt, P/N LN9037-06042
(or FAA-approved
equivalent part
number), from the
modification kit; and
(iii) Install washer, P/
N 10M-282 (or FAA-
approved equivalent
part number)
(4) 14 CFR 21.303 allows for Not applicable...... Not applicable.
replacement parts through
parts manufacturer approval
(PMA). The phrase ``or FAA-
approved equivalent part
number'' in this AD is
intended to signify those
parts that are PMA parts
approved through
identicality to the design
of the part under the type
certificate and replacement
parts to correct the unsafe
condition under PMA (other
than identicality). If
parts are installed that
are identical to the unsafe
parts, then the corrective
actions of the AD affect
these parts also. In
addition, equivalent
replacement parts to
correct the unsafe
condition under PMA (other
than identicality) may also
be installed provided they
meet current airworthiness
standards, which include
those actions cited in this
AD.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Office, Small Airplane Directorate,
FAA, ATTN: Gregory A. Davison, Aerospace Engineer, ACE-112, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4130; facsimile: (816) 329-4090, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) German AD Number D-2004-443, dated September 27, 2004,
addresses the subject of this AD.
Material Incorporated by Reference
(h) You must do the actions required by this AD following the
instructions in Stemme Service Bulletin Document Number: A31-10-069,
Am.-Index 01.a, dated September 10, 2004. The Director of the
Federal Register approved the incorporation by reference of this
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. To get a copy of this service information, contact STEMME AG,
Flugplatzstra[beta]e F 2, Nr. 7, D-15344 Strausberg, Germany;
telephone: + 49.33.41 / 36 12-0; facsimile: + 49.33.41 / 36 12-30.
To review copies of this service information, go to the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030. To view the AD docket,
go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-24641; Directorate
Identifier 2006-CE-27-AD.
[[Page 47717]]
Issued in Kansas City, Missouri, on August 9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,Aircraft Certification
Service.
[FR Doc. E6-13440 Filed 8-17-06; 8:45 am]
BILLING CODE 4910-13-P
