Airworthiness Directives; GROB-WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes, 47702-47706 [E6-13439]
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47702
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
TABLE 3.—AFM INSERTION PAGES—Continued
Model of airplane affected
(v) MU–2B–26 ............
(vi) MU–2B–26A .........
(vii) MU–2B–35 ..........
(viii) MU–2B–36A .......
(ix) MU–2B–40 ...........
(x) MU–2B–60 ............
(xi) MU–2B–10 ...........
(xii) MU–2B–30 ..........
(xiii) MU–2B–36 .........
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
AFM,
Section
Section
Section
Section
Section
Section
Section
Section
Section
Section
Section
6,
6,
6,
6,
6,
6,
6,
6,
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6,
6,
Reissued March 25, 1986; and ....................................................................................
Revision 9, dated January 14, 1999 .............................................................................
Reissued March 25, 1986 .............................................................................................
Reissued March 25, 1986; and ....................................................................................
Revision 9, dated January 14, 1999 .............................................................................
Reissued February 28, 1986 ........................................................................................
Reissued March 25, 1986 .............................................................................................
Reissued September 24, 1985 .....................................................................................
Revision 9, dated January 14, 1999 .............................................................................
Revision 10, dated January 14, 1999 ...........................................................................
Revision 9, dated January 14, 1999 .............................................................................
Note: AFM, Section 6, Reissued March 25,
1986 (FAA-approved) TCDS A10SW. AFM,
Section 6, Revision 9 and Revision 10, dated
January 14, 1999 (JCAB-approved).
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Fort Worth Aircraft
Certification Office, FAA, ATTN: Rao
Edupuganti, Aerospace Engineer, ASW–150,
Fort Worth ACO, 2601 Meacham Blvd., Fort
Worth, Texas 76193; telephone: (817) 222–
5284; facsimile: (817) 222–5960, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
Related Information
(h) Japan Civil Aviation Bureau
Airworthiness Directive No. TCD 4889–98,
dated November 5, 1998, also addresses the
subject of this AD.
rwilkins on PROD1PC63 with RULES
Material Incorporated by Reference
(i) You must do the actions required by this
AD following the instructions in Mitsubishi
Heavy Industries, Ltd. MV–2 Service
Bulletins No. 233A, dated January 14, 1999;
and No. 095/77–002, dated July 15, 1998. 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 Mitsubishi
Heavy Industries America, Inc., 4951 Airport
Parkway, Suite 800, Addison, Texas 75001;
telephone: (972) 934–5480; facsimile: (972)
934–5488. 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–
2006–23883; Directorate Identifier 2006–CE–
12–AD.
VerDate Aug<31>2005
Page number
from AFM
Date and version of AFM
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. E6–13441 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–2006–24253; Directorate
Identifier 2006–CE–23–AD; Amendment 39–
14723; AD 2006–17–02]
RIN 2120–AA64
Airworthiness Directives; GROB–
WERKE GMBH & CO KG Model G102
ASTIR CS Sailplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA supersedes
Airworthiness Directive (AD) 84–09–05,
which applies to certain GROB–WERKE
GMBH & CO KG (previously identified
as BURKHART–GROB FLUGZEUGBAU
INDUSTRIESTRABE) Model G102
ASTIR CS sailplanes. AD 84–09–05
requires you to install a modified
spherical locking bolt and nut in the
forward horizontal stabilizer connection
to the vertical stabilizer and install new
locking pins in the aft connecting plate
for the horizontal stabilizer. Since we
issued AD 84–09–05, fatigue cracks
were found in the modified spherical
locking bolt. Consequently, this AD
requires you to replace the modified
spherical locking bolt, the retaining pins
(collar bolts), and associated hardware;
add a life limit on the spherical locking
bolt and the retaining pins; and
repetitively inspect the front and rear
horizontal stabilizer attachment. This
AD results from mandatory continuing
airworthiness information (MCAI)
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6–17 and
6–19.
6–17 and
6–18 and
6–19.
6–20 and
6–17 and
6–19 and
6–19.
6–19.
6–20.
6–18
6–18.
6–19
6–21.
6–18.
6–20.
issued by the airworthiness authority for
Germany. We are issuing this AD to
prevent cracks in the spherical locking
bolt, which could result in failure of the
horizontal stabilizer connection. This
failure could lead to loss of 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: For service information
identified in this AD, contact GROB
Luft-und Raumfahrt, Lettenbachstrasse
9, D–86874 Tussenhausen-Mattsies,
Federal Republic of Germany;
telephone: 011 49 8268 998139; fax: 011
49 8268 998200; e-mail:
productsupport@grob-aerospace.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–
0001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–24253; Directorate Identifier
2006–CE–23–AD.
FOR FURTHER INFORMATION CONTACT:
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.
SUPPLEMENTARY INFORMATION:
Discussion
On May 30, 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 GROB–WERKE GMBH & CO KG
(previously identified as BURKHART–
GROB FLUGZEUGBAU
INDUSTRIESTRABE) Model G102
ASTIR CS sailplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
E:\FR\FM\18AUR1.SGM
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Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
on June 6, 2006 (71 FR 32484). The
NPRM proposed to supersede AD 84–
09–05 with a new AD that would
require you to do the following:
• Remove the existing spherical
locking bolt, nut, retaining pins (collar
bolts), self-locking nut, and the lock
washer; and replace with a new
spherical locking bolt, P/N 102–3500.21,
that has revision letter ‘‘b’’ permanently
marked on the bottom of the bolt, a new
nut, P/N 102–3510.21, new retaining
pins (collar bolts), P/N 102–2142.46, a
new self-locking nut, P/N LN9348–M8,
and a new lock washer, P/N DIN 6797–
10,5PHR;
• Add a life limit on the new
spherical locking bolt and the retaining
pins; and
• Inspect (repetitively) the front and
rear horizontal stabilizer attachment
assembly after the initial replacements.
Comments
We provided the public the
opportunity to participate in developing
this AD. The following presents the
comments received on the proposal and
FAA’s response to each comment:
Comment Issue No. 1: Address the
Intent of the AD as It Affects Parts
Manufacturer Approval (PMA)
Alternatives to the Original Equipment
Manufacturer (OEM) Part
The Modification and Replacement
Parts Association (MARPA) provides
comments to the mandatory continuing
airworthiness information (MCAI) AD
process pertaining to how the FAA
addresses PMA parts. The commenter
would like to see the FAA more fully
address the intent of the AD as it affects
PMA alternatives to the unsafe OEM
part.
We acknowledge the need to ensure
that unsafe parts are identified and
addressed in MCAI-related ADs. For this
AD, we use the phrase ‘‘or FAAapproved equivalent part number’’ to
address the PMA issue. We are currently
examining all aspects of this issue,
including input from industry. Once we
have made a final determination, we
will consider how our policy regarding
PMA parts in ADs needs to be revised.
We consider that to delay this AD action
would be inappropriate since we have
determined that an unsafe condition
exists and that replacement of certain
parts must be accomplished to ensure
continued safety.
We have not changed the final rule
AD action based on this comment.
Labor cost
47703
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.
Differences Between This AD and the
Service Information
The service information specifies
using a 20X magnifying glass for doing
the inspections. This AD specifies using
a dye penetrant method and a 10X
magnifying glass for doing the
inspections. This difference is because
20X magnifiers are not readily available
in the field.
The requirements of this AD take
precedence over the provisions in the
service information.
Costs of Compliance
We estimate that this AD will affect
56 sailplanes in the U.S. registry.
We estimate the following costs to do
the replacements:
Parts cost
2 work-hours × $80 per hour = $160 ..........................................................................................
$253
Total cost for
each sailplane
Total cost on
U.S. operators
$413
$23,128
Total cost for
each sailplane
Total cost on
U.S. operators
$160
$8,960
We estimate the following costs to do
each inspection:
Labor cost
Parts cost
2 work-hours × $80 per hour = $160 ..........................................................................................
Not applicable
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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
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18:30 Aug 17, 2006
Jkt 208001
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:
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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–2006–24253;
E:\FR\FM\18AUR1.SGM
18AUR1
47704
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
Directorate Identifier 2006–CE–23–AD’’
in your request.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. FAA amends § 39.13 by removing
Airworthiness Directive (AD) 84–09–05,
Amendment 39–4849, and adding the
following new AD:
I
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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
2006–17–02 GROB–WERKE GMBH & CO
KG (previously identified as
BURKHART–GROB FLUGZEUGBAU
INDUSTRIESTRABE): Amendment 39–
14723; Docket No. FAA–2006–24253;
Directorate Identifier 2006–CE–23–AD.
Effective Date
(a) This AD becomes effective on
September 22, 2006.
PART 39—AIRWORTHINESS
DIRECTIVES
Affected ADs
1. The authority citation for part 39
continues to read as follows:
I
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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
cracks in the spherical locking bolt, which
could result in failure of the horizontal
stabilizer connection. This failure could lead
to loss of control.
Compliance
(e) To address this problem, you must do
the following:
Compliance
(1) Remove and replace as follows:
(i) Remove the existing retaining pins (collar bolts) and the self-locking nut and replace with new retaining pins, part numbers (P/N) 102–2142.46, and self-locking
nut, P/N LN9348–M8 (or FAA-approved
equivalent part numbers), on the T-plate;
(ii) Remove the existing spherical locking
bolt and replace with a new spherical
locking bolt, P/N 102–3500.21, that has
revision letter ‘‘b’’ permanently marked
on the bottom of the bolt (or FAA-approved equivalent part number). Return
replaced spherical locking bolts, P/N
102–3500.21, to Grob Systems, Inc., Aircraft Division, 1070 Navajo Drive,
Bluffton, Ohio 45817;
(iii) Remove the existing nut and replace
with a new nut, 102–3510.21 (or FAAapproved equivalent part number); and
(iv) Remove the existing lock washer and
replace with a new lock washer, P/N DIN
6797–10,5PHR (or FAA-approved equivalent part number)
(2) Using a dye-penetrant method along with a
minimum 10X magnifying glass, repetitively
inspect the front and rear horizontal stabilizer
attachment assembly for excessive movement, cracks, and/or damage in the spherical
locking bolt. This inspection method takes
precedence over the procedures outlined in
GROB Service Bulletin MSB306–38, dated
February 12, 2004.
(3) If, during any inspection required in paragraph (e)(2) of this AD, you find excessive
movement:
19:13 Aug 17, 2006
(c) This AD affects Model G102 ASTIR CS
sailplanes, serial numbers 1001 through
1536, that are certificated in any category.
(b) This AD supersedes 84–09–05,
Amendment 39–4849.
Actions
VerDate Aug<31>2005
Applicability
Jkt 208001
Procedures
Within the next 90 days after September 22,
2006 (the effective date of this AD), unless
already done. After doing the replacements,
the spherical locking bolt and the retaining
pins have a life limit of 10 years and must
be replaced at that time.
As specified in GROB Service Bulletin
MSB306–38/1, dated November 28, 2005,
following the Accomplishment Instructions
in GROB Service Bulletin MSB306–38,
dated February 12, 2004, and the Annual
Inspection procedures on pages 7 and 8 of
the Astir CS Maintenance Manual, Rev. 9,
dated Nov. 2005.
Initially inspect within the next 100 hours timein-service (TIS) or at the next annual inspection after the replacement required in
paragraph (e)(1) of this AD, whichever occurs first. Repetitively inspect thereafter at
12-month intervals or at intervals not to exceed 100 hours TIS, whichever occurs first.
As specified in GROB Service Bulletin
MSB306–38/1, dated November 28, 2005,
following the Accomplishment Instructions
in GROB Service Bulletin MSB306–38,
dated February 12, 2004, and the Annual
Inspection procedures on pages 7 and 8 of
the Astir CS Maintenance Manual, Rev. 9,
dated Nov. 2005.
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Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
Actions
Compliance
(i) In the front horizontal stabilizer attachment, you must replace the spherical
locking bolt with a new part.
(ii) In the rear horizontal stabilizer attachment, you must replace the retaining
pins with new parts
(iii) In the front and rear horizontal stabilizer attachment after doing the replacement(s) required in paragraph
(e)(3)(i) and (e)(3)(ii) of this AD, you
must replace the bearings in the stabilizer spar web
(4) If, during any inspection required in paragraph (e)(2) of this AD, you do not find excessive movement in the front and rear horizontal stabilizer attachment:
(i) Inspect the spherical locking bolt for
cracks and damage using a dye-penetrant method along with a minimum 10X
magnifying glass
(ii) If you find cracks or damage on the
spherical locking bolt, during the inspection required in paragraph (e)(4)(i) of this
AD, you must replace the bolt with a
new bolt
(5) Do not install any spherical locking bolt, P/N
102–3500.21 (or FAA-approved equivalent
part number), that does not have revision letter ‘‘b’’ permanently marked on the bottom of
the bolt.
(6) 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.
Procedures
Before further flight after each inspection required in paragraph (e)(2) of this AD. After
each replacement, the spherical locking bolt
and the retaining pins have a life limit of 10
years and must be replaced at that time.
As specified in GROB Service Bulletin
MSB306–38/1, dated November 28, 2005,
following the Accomplishment Instructions
in GROB Service Bulletin MSB306–38,
dated February 12, 2004, and the Annual
Inspection procedures on pages 7 and 8 of
the Astir CS Maintenance Manual, Rev. 9,
dated Nov. 2005.
Before further flight after each inspection required in paragraph (e)(2) of this AD. After
each replacement, the spherical locking bolt
and the retaining pins have a life limit of 10
years and must be replaced at that time.
As specified in GROB Service Bulletin
MSB306–38/1, dated November 28, 2005,
following the Accomplishment Instructions
in GROB Service Bulletin MSB306–38,
dated February 12, 2004, and the Annual
Inspection procedures on pages 7 and 8 of
the Astir CS Maintenance Manual, Rev. 9,
dated Nov. 2005.
As of September 22, 2006 (the effective date
of this AD).
Not applicable.
Not applicable ..................................................
Not applicable.
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 84–09–05 are
not approved for this AD.
Alternative Methods of Compliance
(AMOCs)
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Note: During ground handling, it has been
noted that a tendency exists for the ground
crew to move these gliders by using the
horizontal stabilizer as a lifting point. This
practice may facilitate damage to the
stabilizer assembly and should be avoided.
See Caution note in GROB Service Bulletin
MSB306–38, dated February 12, 2004.
Material Incorporated by Reference
(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
VerDate Aug<31>2005
19:13 Aug 17, 2006
47705
Jkt 208001
Related Information
(h) German AD Number D–2004–168,
dated March 23, 2004, also addresses the
subject of this AD.
(i) You must do the actions required by this
AD following the instructions in GROB
Service Bulletin MSB306–38, dated February
12, 2004, and GROB Service Bulletin
MSB306–38/1, dated November 28, 2005.
The Director of the Federal Register approved
the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
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and 1 CFR part 51. To get a copy of this
service information, contact GROB Luft-und
Raumfahrt, Lettenbachstrasse 9, D–86874
Tussenhausen-Mattsies, Federal Republic of
Germany; telephone: 011 49 8268 998139;
fax: 011 49 8268 998200; e-mail:
productsupport@grob-aerospace.de. 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://
E:\FR\FM\18AUR1.SGM
18AUR1
47706
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
dms.dot.gov. The docket number is FAA–
2006–24253; Directorate Identifier 2006–CE–
23–AD.
Issued in Kansas City, Missouri, on August
9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–13439 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–2006–23889; Directorate
Identifier 2005–NM–252–AD; Amendment
39–14714; AD 2006–16–14]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A318, A319, A320, and
A321 airplanes. This AD requires
inspecting to determine the part number
of the twin motor actuators, and related
investigative and corrective actions if
necessary. This AD results from a report
of a low pressure valve of the twin
motor actuator found partially open,
although the valve detection system
indicated that the valve was closed.
Investigation revealed that the locating
pin in the actuator was too short to
engage with the valve slot, resulting in
incorrect alignment of the actuator and
the drive assembly, causing the valve to
remain partially open. We are issuing
this AD to ensure that, in the event of
an engine fire, the valve actuator
functions properly to block the fuel flow
to the engine and prevent an
uncontrollable fire.
DATES: This AD becomes effective
September 22, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 22, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–5356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the street
address stated in the ADDRESSES section.
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain Airbus
Model A318, A319, A320, and A321
airplanes. That supplemental NPRM
was published in the Federal Register
on May 18, 2006 (71 FR 28825). That
supplemental NPRM proposed to
require inspecting to determine the part
number of the twin motor actuators, and
related investigative and corrective
actions if necessary. That supplemental
NPRM also proposed to revise the
original NPRM by expanding the
applicability.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment
received.
Request To Add Revised Service
Information to Applicability Section
Airbus advises that the service
bulletin specified in the supplemental
NPRM has been revised. Airbus notes
that Airbus Service Bulletin A320–28–
1122, Revision 01, including Appendix
01, dated April 11, 2006 (the original
issue of the service bulletin was
referenced in the supplemental NPRM
for accomplishing the specified actions),
changes the recommended status of the
original issue to mandatory in Revision
01.
We agree with Airbus. We have
reviewed Revision 01 of the service
bulletin and note that it does not
necessitate additional work. We have
revised paragraph (f) of the AD to reflect
Revision 01 of the service bulletin. In
addition, we have added a new
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
paragraph (g) to this AD specifying that
accomplishing the actions specified in
paragraph (f) of the AD in accordance
with the original issue of the service
bulletin is considered to be an
acceptable method of compliance.
Subsequent paragraphs of the AD have
been re-identified accordingly.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. These changes will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
This AD affects about 763 airplanes of
U.S. registry. The inspection takes about
1 work hour per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
this AD on U.S. operators is $61,040, or
$80 per airplane.
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 rulemaking
action.
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;
E:\FR\FM\18AUR1.SGM
18AUR1
]]>Agencies
[Federal Register Volume 71, Number 160 (Friday, August 18, 2006)]
[Rules and Regulations]
[Pages 47702-47706]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13439]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD;
Amendment 39-14723; AD 2006-17-02]
RIN 2120-AA64
Airworthiness Directives; GROB-WERKE GMBH & CO KG Model G102
ASTIR CS Sailplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA supersedes Airworthiness Directive (AD) 84-09-05,
which applies to certain GROB-WERKE GMBH & CO KG (previously identified
as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS
sailplanes. AD 84-09-05 requires you to install a modified spherical
locking bolt and nut in the forward horizontal stabilizer connection to
the vertical stabilizer and install new locking pins in the aft
connecting plate for the horizontal stabilizer. Since we issued AD 84-
09-05, fatigue cracks were found in the modified spherical locking
bolt. Consequently, this AD requires you to replace the modified
spherical locking bolt, the retaining pins (collar bolts), and
associated hardware; add a life limit on the spherical locking bolt and
the retaining pins; and repetitively inspect the front and rear
horizontal stabilizer attachment. This AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Germany. We are issuing this AD to prevent cracks in the
spherical locking bolt, which could result in failure of the horizontal
stabilizer connection. This failure could lead to loss of 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: For service information identified in this AD, contact GROB
Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies,
Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49
8268 998200; e-mail: productsupport@grob-aerospace.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 20590-0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-24253; Directorate
Identifier 2006-CE-23-AD.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Discussion
On May 30, 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 GROB-WERKE GMBH & CO KG (previously identified
as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS
sailplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM)
[[Page 47703]]
on June 6, 2006 (71 FR 32484). The NPRM proposed to supersede AD 84-09-
05 with a new AD that would require you to do the following:
Remove the existing spherical locking bolt, nut, retaining
pins (collar bolts), self-locking nut, and the lock washer; and replace
with a new spherical locking bolt, P/N 102-3500.21, that has revision
letter ``b'' permanently marked on the bottom of the bolt, a new nut,
P/N 102-3510.21, new retaining pins (collar bolts), P/N 102-2142.46, a
new self-locking nut, P/N LN9348-M8, and a new lock washer, P/N DIN
6797-10,5PHR;
Add a life limit on the new spherical locking bolt and the
retaining pins; and
Inspect (repetitively) the front and rear horizontal
stabilizer attachment assembly after the initial replacements.
Comments
We provided the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and FAA's response to each comment:
Comment Issue No. 1: Address the Intent of the AD as It Affects Parts
Manufacturer Approval (PMA) Alternatives to the Original Equipment
Manufacturer (OEM) Part
The Modification and Replacement Parts Association (MARPA) provides
comments to the mandatory continuing airworthiness information (MCAI)
AD process pertaining to how the FAA addresses PMA parts. The commenter
would like to see the FAA more fully address the intent of the AD as it
affects PMA alternatives to the unsafe OEM part.
We acknowledge the need to ensure that unsafe parts are identified
and addressed in MCAI-related ADs. For this AD, we use the phrase ``or
FAA-approved equivalent part number'' to address the PMA issue. We are
currently examining all aspects of this issue, including input from
industry. Once we have made a final determination, we will consider how
our policy regarding PMA parts in ADs needs to be revised. We consider
that to delay this AD action would be inappropriate since we have
determined that an unsafe condition exists and that replacement of
certain parts must be accomplished to ensure continued safety.
We have not changed the final rule AD action based on this comment.
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.
Differences Between This AD and the Service Information
The service information specifies using a 20X magnifying glass for
doing the inspections. This AD specifies using a dye penetrant method
and a 10X magnifying glass for doing the inspections. This difference
is because 20X magnifiers are not readily available in the field.
The requirements of this AD take precedence over the provisions in
the service information.
Costs of Compliance
We estimate that this AD will affect 56 sailplanes in the U.S.
registry.
We estimate the following costs to do the replacements:
----------------------------------------------------------------------------------------------------------------
Total cost for Total cost on
Labor cost Parts cost each sailplane U.S. operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $80 per hour = $160.............................. $253 $413 $23,128
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do each inspection:
----------------------------------------------------------------------------------------------------------------
Total cost for Total cost on
Labor cost Parts cost each sailplane U.S. operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $80 per hour = $160.............................. Not applicable $160 $8,960
----------------------------------------------------------------------------------------------------------------
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-2006-24253;
[[Page 47704]]
Directorate Identifier 2006-CE-23-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 removing Airworthiness Directive (AD) 84-
09-05, Amendment 39-4849, and adding the following new AD:
2006-17-02 GROB-WERKE GMBH & CO KG (previously identified as
BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE): Amendment 39-14723;
Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD.
Effective Date
(a) This AD becomes effective on September 22, 2006.
Affected ADs
(b) This AD supersedes 84-09-05, Amendment 39-4849.
Applicability
(c) This AD affects Model G102 ASTIR CS sailplanes, serial
numbers 1001 through 1536, that are certificated in any category.
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 cracks in the spherical
locking bolt, which could result in failure of the horizontal
stabilizer connection. This failure could lead to loss of control.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Remove and replace as
follows:
(i) Remove the existing Within the next 90 As specified in GROB
retaining pins (collar days after Service Bulletin
bolts) and the self- September 22, 2006 MSB306-38/1, dated
locking nut and replace (the effective date November 28, 2005,
with new retaining of this AD), unless following the
pins, part numbers (P/ already done. After Accomplishment
N) 102-2142.46, and doing the Instructions in
self-locking nut, P/N replacements, the GROB Service
LN9348-M8 (or FAA- spherical locking Bulletin MSB306-38,
approved equivalent bolt and the dated February 12,
part numbers), on the T- retaining pins have 2004, and the
plate; a life limit of 10 Annual Inspection
(ii) Remove the existing years and must be procedures on pages
spherical locking bolt replaced at that 7 and 8 of the
and replace with a new time. Astir CS
spherical locking bolt, Maintenance Manual,
P/N 102-3500.21, that Rev. 9, dated Nov.
has revision letter 2005.
``b'' permanently
marked on the bottom of
the bolt (or FAA-
approved equivalent
part number). Return
replaced spherical
locking bolts, P/N 102-
3500.21, to Grob
Systems, Inc., Aircraft
Division, 1070 Navajo
Drive, Bluffton, Ohio
45817;
(iii) Remove the
existing nut and
replace with a new nut,
102-3510.21 (or FAA-
approved equivalent
part number); and
(iv) Remove the existing
lock washer and replace
with a new lock washer,
P/N DIN 6797-10,5PHR
(or FAA-approved
equivalent part number)
(2) Using a dye-penetrant Initially inspect As specified in GROB
method along with a minimum within the next 100 Service Bulletin
10X magnifying glass, hours time-in- MSB306-38/1, dated
repetitively inspect the service (TIS) or at November 28, 2005,
front and rear horizontal the next annual following the
stabilizer attachment inspection after Accomplishment
assembly for excessive the replacement Instructions in
movement, cracks, and/or required in GROB Service
damage in the spherical paragraph (e)(1) of Bulletin MSB306-38,
locking bolt. This this AD, whichever dated February 12,
inspection method takes occurs first. 2004, and the
precedence over the Repetitively Annual Inspection
procedures outlined in GROB inspect thereafter procedures on pages
Service Bulletin MSB306-38, at 12-month 7 and 8 of the
dated February 12, 2004. intervals or at Astir CS
intervals not to Maintenance Manual,
exceed 100 hours Rev. 9, dated Nov.
TIS, whichever 2005.
occurs first.
(3) If, during any
inspection required in
paragraph (e)(2) of this
AD, you find excessive
movement:
[[Page 47705]]
(i) In the front Before further As specified in GROB
horizontal stabilizer flight after each Service Bulletin
attachment, you must inspection required MSB306-38/1, dated
replace the spherical in paragraph (e)(2) November 28, 2005,
locking bolt with a new of this AD. After following the
part. each replacement, Accomplishment
the spherical Instructions in
locking bolt and GROB Service
the retaining pins Bulletin MSB306-38,
have a life limit dated February 12,
of 10 years and 2004, and the
must be replaced at Annual Inspection
that time. procedures on pages
7 and 8 of the
Astir CS
Maintenance Manual,
Rev. 9, dated Nov.
2005.
(ii) In the rear
horizontal stabilizer
attachment, you must
replace the retaining
pins with new parts
(iii) In the front and
rear horizontal
stabilizer attachment
after doing the
replacement(s) required
in paragraph (e)(3)(i)
and (e)(3)(ii) of this
AD, you must replace
the bearings in the
stabilizer spar web
(4) If, during any
inspection required in
paragraph (e)(2) of this
AD, you do not find
excessive movement in the
front and rear horizontal
stabilizer attachment:
(i) Inspect the Before further As specified in GROB
spherical locking bolt flight after each Service Bulletin
for cracks and damage inspection required MSB306-38/1, dated
using a dye-penetrant in paragraph (e)(2) November 28, 2005,
method along with a of this AD. After following the
minimum 10X magnifying each replacement, Accomplishment
glass the spherical Instructions in
(ii) If you find cracks locking bolt and GROB Service
or damage on the the retaining pins Bulletin MSB306-38,
spherical locking bolt, have a life limit dated February 12,
during the inspection of 10 years and 2004, and the
required in paragraph must be replaced at Annual Inspection
(e)(4)(i) of this AD, that time. procedures on pages
you must replace the 7 and 8 of the
bolt with a new bolt Astir CS
Maintenance Manual,
Rev. 9, dated Nov.
2005.
(5) Do not install any As of September 22, Not applicable.
spherical locking bolt, P/N 2006 (the effective
102-3500.21 (or FAA- date of this AD).
approved equivalent part
number), that does not have
revision letter ``b''
permanently marked on the
bottom of the bolt.
(6) 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.
------------------------------------------------------------------------
Note: During ground handling, it has been noted that a tendency
exists for the ground crew to move these gliders by using the
horizontal stabilizer as a lifting point. This practice may
facilitate damage to the stabilizer assembly and should be avoided.
See Caution note in GROB Service Bulletin MSB306-38, dated February
12, 2004.
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.
(g) AMOCs approved for AD 84-09-05 are not approved for this AD.
Related Information
(h) German AD Number D-2004-168, dated March 23, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(i) You must do the actions required by this AD following the
instructions in GROB Service Bulletin MSB306-38, dated February 12,
2004, and GROB Service Bulletin MSB306-38/1, dated November 28,
2005. 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 GROB Luft-und Raumfahrt,
Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic
of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200;
e-mail: productsupport@grob-aerospace.de. 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://
[[Page 47706]]
dms.dot.gov. The docket number is FAA-2006-24253; Directorate
Identifier 2006-CE-23-AD.
Issued in Kansas City, Missouri, on August 9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-13439 Filed 8-17-06; 8:45 am]
BILLING CODE 4910-13-P
