Airworthiness Directives; Tiger Aircraft LLC Models AA-5, AA-5A, AA-5B, and AG-5B Airplanes, 48857-48859 [05-16260]
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Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations
Issued in Renton, Washington, on June 21,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12841 Filed 8–19–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20968; Directorate
Identifier 94–CE–15–AD; Amendment 39–
14222; AD 95–19–15 R1]
RIN 2120–AA64
Airworthiness Directives; Tiger Aircraft
LLC Models AA–5, AA–5A, AA–5B, and
AG–5B Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is revising
Airworthiness Directive (AD) 95–19–15
for all Tiger Aircraft LLC (Type
Certificate A16EA formerly held by
American General Aircraft Corporation
and Grumman American Aviation
Corporation) Models AA–5, AA–5A,
AA–5B, and AG–5B airplanes. AD 95–
19–15 currently requires you to inspect
the wing attach shoulder bolts for
fretting, scoring, wear, or enlarged or
elongated mounting holes (known as
damage from hereon); replace any
damaged parts; repair any damaged
areas; inspect the wing spar at the center
spar clearance gap for excessive
clearance; and shim the spar if excessive
clearance is found. That AD was written
to apply to all serial numbers of all
models. A design change was made in
this area beginning with serial number
10175 of the Model AG–5B airplanes.
Therefore, the action should not apply
to Model AG–5B airplanes with a serial
number of 10175 or higher. This AD
retains all the actions of AD 95–19–15
for all airplanes originally affected, but
cuts off the applicability for the Model
AG–5B airplanes at serial number
10174. We are issuing this AD to
continue to prevent wing attach
shoulder bolt failure, which, if not
detected and corrected, could lead to
structural damage of the wing/fuselage
to the point of failure.
DATES: This AD becomes effective on
October 3, 2005.
As of October 3, 2005, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
SUMMARY:
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16:02 Aug 19, 2005
Jkt 205001
To get the service
information identified in this AD,
contact Tiger Aircraft LLC, 226 Pilot
Way, Martinsburg, WV 25401.
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–2005–20968; Directorate Identifier
94–CE–15–AD.
FOR FURTHER INFORMATION CONTACT:
Richard Beckwith, Aerospace Engineer,
New York Aircraft Certification Office
(ACO), 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone: 516–
794–5531; facsimile: 516–794–5531.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Discussion
What events have caused this AD?
The FAA has received four reports
(three in England and one in the United
States) of wing attach shoulder bolt
failure on Tiger Aircraft LLC (Type
Certificate A16EA formerly held by
American General Aircraft Corporation
(AGAC) and Grumman American
Aviation Corporation (GAAC)) Models
AA–5, AA–5A, AA–5B, and AG–5B
airplanes. Investigation reveals that
excessive wing to center spar clearance
could have contributed to the bolt
failures; however, in each of the four
instances, the bolts failed before
reaching the service life of 7,250 hours
time-in-service (TIS). The FAA has
determined that, to assure the safety of
these airplanes, the established service
life of these bolts needed review. Our
review of service life on Tiger Aircraft
LLC (Type Certificate A16EA formerly
held by AGAC and GAAC) Models AA–
5, AA–5A, AA–5B, and AG–5B
airplanes caused us to issue AD 95–19–
15, Amendment 39–9377 (60 FR 48628,
September 20, 1995). AD 95–19–15
currently requires the following on
Tiger Aircraft LLC (Type Certificate
A16EA formerly held by AGAC and
GAAC) Models AA–5, AA–5A, AA–5B,
and AG–5B airplanes, all serial
numbers:
—Inspect the wing attach shoulder bolts
for fretting, scoring, wear, or enlarged
or elongated mounting holes (known
as damage from hereon), and replace
any damaged parts and repairing any
damaged areas;
—Inspect the wing spar at the center
spar clearance gap for excessive
clearance; and
—Shim the spar if excessive clearance is
found.
AD 95–19–15 was written to apply to
all serial numbers of all models. A
PO 00000
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Fmt 4700
Sfmt 4700
48857
design change was made in this area
beginning with serial number 10175 of
the Model AG–5B airplanes. Therefore,
FAA determined that the action should
not apply to Model AG–5B airplanes
with a serial number of 10175 or higher.
Has FAA taken any action to this
point? 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 all Tiger
Aircraft LLC (Type Certificate A16EA
formerly held by American General
Aircraft Corporation and Grumman
American Aviation Corporation) Models
AA–5, AA–5A, AA–5B, and AG–5B
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on May
19, 2005 (70 FR 28854). The NPRM
proposed to retain all the actions of AD
95–19–15 for all airplanes originally
affected, but proposed to cut off the
applicability for the Model AG–5B
airplanes at serial number 10174.
Comments
Was the public invited to comment?
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: Type Certificate
Data Sheet (TCDS) Number (No.) Is
Referenced Incorrectly in the NPRM
What is the commenter’s concern? A
letter from Tiger Aircraft LLC notes that
the TCDS No. A16EH in the NPRM is
referenced incorrectly. The TCDS
should be No. A16EA.
What is FAA’s response to the
concern? We concur. We will correct all
reference in the final rule of the TCDS
to No. A16EA.
Comment Issue No. 2: Manufacturer’s
Contact Information Is Incorrect in the
NPRM
What is the commenter’s concern?
The commenter from Tiger Aircraft LLC
requests that FAA change the contact
information to that for Tiger Aircraft
LLC. American General Aircraft
Corporation is out of business.
What is FAA’s response to the
concern? The FAA concurs. We will
change the contact information in the
final rule to show Tiger Aircraft LLC.
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
the changes discussed above and minor
editorial corrections. We have
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48858
Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations
determined that these changes and
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.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Labor cost
Parts cost
10 work hours × $65 = $650 .......................................................
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
3,700 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to do this inspection:
Not included ..
We have no way of determining the
number of airplanes that may need this
replacement of any damaged bolts or
repair as a result of the inspection.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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
Will this AD impact various entities?
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.
Will this AD involve a significant rule
or regulatory action? 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
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16:02 Aug 19, 2005
Jkt 205001
Total cost per airplane
$650
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–2005–20968;
Directorate Identifier 94–CE–15–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
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]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
95–19–15, Amendment 39–9377 (60 FR
48628, September 20, 1995), and by
adding a new AD to read as follows:
I
95–19–15 R1 Tiger Aircraft LLC: (Type
Certificate A16EA formerly held by
American General Aircraft Corporation
and Grumman American Aviation
Corporation): Amendment 39–14222;
Docket No. FAA–2005–20968;
Directorate Identifier 94–CE–15–AD.
PO 00000
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Fmt 4700
Sfmt 4700
Total cost on U.S. operators
3,700 × $650 = $2,405,000
When Does This AD Become Effective?
(a) This AD becomes effective on October
3, 2005.
What Other ADs Are Affected By This
Action?
(b) This AD revises AD 95–19–15,
Amendment 39–9377.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
Model
Serial numbers
AA–5 ............
AA–5A ..........
AA–5B ..........
AG–5B ..........
All Serial Numbers.
All Serial Numbers.
All Serial Numbers.
99998, 10000 through 10174.
What Is the Unsafe Condition Presented in
This AD?
(d) AD 95–19–15 currently requires you to
inspect the wing attach shoulder bolts for
fretting, scoring, wear, or enlarged or
elongated mounting holes (known as damage
from hereon); replace any damaged parts;
repair any damaged areas; inspect the wing
spar at the center spar clearance gap for
excessive clearance; and shim the spar if
excessive clearance is found. That AD was
written to apply to all serial numbers of all
models. A design change was made in this
area beginning with serial number 10175 of
the Model AG–5B airplanes. Therefore, the
action should not apply to Model AG–5B
airplanes with a serial number of 10175 or
higher. This AD retains all the actions of AD
95–19–15 for all airplanes originally affected,
but cuts off the applicability for the Model
AG–5B airplanes at serial number 10174. We
are issuing this AD to continue to prevent
wing attach shoulder bolt failure, which, if
not detected and corrected, could lead to
structural damage of the wing/fuselage to the
point of failure.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following, unless already done:
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Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations
48859
Actions
Compliance
Procedures
(1) Inspect any inboard wing attach shoulder
bolt for:
Within the next 100 hours aircraft time-inservice (TIS) after November 17, 1995 (the
effective date of AD 95–19–15, unless already done
Follow American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 2005.
Before further flight after the inspection required by paragraph (e)(1) of this AD
Follow American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 2005.
Within the next 100 hours aircraft time-inservice (TIS) after November 17, 1995 (the
effective date of AD 95–19–15), unless already done
Before further flight after the inspection required by paragraph (e)(3) of this AD
Follow American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 2005.
Before further flight after the inspections required by paragraphs (e)(1) and (e)(3) of
this AD
As of October 3, 2005 (the effective date of
this AD)
Follow American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 2005.
Not Applicable.
(i) Fretting, scoring, or wear (removal of
the cad plating) to the shoulder of the
bolt
(ii) A smooth machined area between the
threads and the shoulder bevel of the
shoulder bolt profile
(2) Replace any inboard wing attach shoulder
bolt with wear (removal of the cad plating
from the shoulder of the bolt) or if the threads
contact the shoulder of the bolt found during
the inspections required in paragraph (e)(1)
of this AD
(3) Inspect the mounting holes in the wing spar
and the center section spar for enlargement
or elongation that exceeds the specified dimension
(4) Ream and bush any mounting hole that exceeds the specified dimension found during
the inspection required by paragraph (e)(3) of
this AD
(5) Inspect the wing spar at the center spar
clearance gap for excessive clearance, and
shim the spar if excessive clearance is found
(6) Do not install any wing attach shoulder bolt
that has wear resulting in removal of the cad
plating from the shoulder of the bolt or if the
threads contact the shoulder bevel of the
shoulder bolt profile
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, New York Aircraft Certification
Office (ACO), FAA. For information on any
already approved alternative methods of
compliance, contact Richard Beckwith,
Aerospace Engineer, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone: 516–794–5531; facsimile:
516–794–5531.
Does This AD Incorporate Any Material by
Reference?
(g) You must do the actions required by
this AD following the instructions in
American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 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 Tiger Aircraft LLC, 226
Pilot Way, Martinsburg, WV 25401. 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
VerDate jul<14>2003
16:02 Aug 19, 2005
Jkt 205001
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–
2005–20968; Directorate Identifier 94–CE–
15–AD.
Issued in Kansas City, Missouri, on August
11, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–16260 Filed 8–19–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2005–21608; Airspace
Docket No. 05–ACE–18]
Modification of Class E Airspace;
McCook, NE
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; confirmation of
effective date.
AGENCY:
Follow American General Aircraft Corporation
Service Bulletin No. SB–185–A, Revision A,
dated January 10, 2005
DATES:
Effective 0901 UTC, October 27,
2005.
FOR FURTHER INFORMATION CONTACT:
Brenda Mumper, Air Traffic Division,
Airspace Branch, ACE–520A, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; telephone:
(816) 329–2524.
The FAA
published this direct final rule with a
request for comments in the Federal
Register on June 28, 2005 (70 FR 37029).
The FAA uses the direct final
rulemaking procedure for a noncontroversial rule where the FAA
believes that there will be no adverse
public comment. This direct final rule
advised the public that no adverse
comments were anticipated, and that
unless a written adverse comment, or a
written notice of intent to submit such
an adverse comment, were received
within the comment period, the
regulation would become effective on
October 27, 2005. No adverse comments
were received, and thus this notice
confirms that this direct final rule will
become effective on that date.
SUPPLEMENTARY INFORMATION:
SUMMARY: This document confirms the
effective date of the direct final rule
which revises Class E airspace at
McCook, NE.
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]]>Agencies
[Federal Register Volume 70, Number 161 (Monday, August 22, 2005)]
[Rules and Regulations]
[Pages 48857-48859]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16260]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20968; Directorate Identifier 94-CE-15-AD;
Amendment 39-14222; AD 95-19-15 R1]
RIN 2120-AA64
Airworthiness Directives; Tiger Aircraft LLC Models AA-5, AA-5A,
AA-5B, and AG-5B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising Airworthiness Directive (AD) 95-19-15 for
all Tiger Aircraft LLC (Type Certificate A16EA formerly held by
American General Aircraft Corporation and Grumman American Aviation
Corporation) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. AD 95-19-
15 currently requires you to inspect the wing attach shoulder bolts for
fretting, scoring, wear, or enlarged or elongated mounting holes (known
as damage from hereon); replace any damaged parts; repair any damaged
areas; inspect the wing spar at the center spar clearance gap for
excessive clearance; and shim the spar if excessive clearance is found.
That AD was written to apply to all serial numbers of all models. A
design change was made in this area beginning with serial number 10175
of the Model AG-5B airplanes. Therefore, the action should not apply to
Model AG-5B airplanes with a serial number of 10175 or higher. This AD
retains all the actions of AD 95-19-15 for all airplanes originally
affected, but cuts off the applicability for the Model AG-5B airplanes
at serial number 10174. We are issuing this AD to continue to prevent
wing attach shoulder bolt failure, which, if not detected and
corrected, could lead to structural damage of the wing/fuselage to the
point of failure.
DATES: This AD becomes effective on October 3, 2005.
As of October 3, 2005, 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 Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401.
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-2005-20968; Directorate
Identifier 94-CE-15-AD.
FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer,
New York Aircraft Certification Office (ACO), 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile: 516-
794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The FAA has received four reports
(three in England and one in the United States) of wing attach shoulder
bolt failure on Tiger Aircraft LLC (Type Certificate A16EA formerly
held by American General Aircraft Corporation (AGAC) and Grumman
American Aviation Corporation (GAAC)) Models AA-5, AA-5A, AA-5B, and
AG-5B airplanes. Investigation reveals that excessive wing to center
spar clearance could have contributed to the bolt failures; however, in
each of the four instances, the bolts failed before reaching the
service life of 7,250 hours time-in-service (TIS). The FAA has
determined that, to assure the safety of these airplanes, the
established service life of these bolts needed review. Our review of
service life on Tiger Aircraft LLC (Type Certificate A16EA formerly
held by AGAC and GAAC) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes
caused us to issue AD 95-19-15, Amendment 39-9377 (60 FR 48628,
September 20, 1995). AD 95-19-15 currently requires the following on
Tiger Aircraft LLC (Type Certificate A16EA formerly held by AGAC and
GAAC) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes, all serial
numbers:
--Inspect the wing attach shoulder bolts for fretting, scoring, wear,
or enlarged or elongated mounting holes (known as damage from hereon),
and replace any damaged parts and repairing any damaged areas;
--Inspect the wing spar at the center spar clearance gap for excessive
clearance; and
--Shim the spar if excessive clearance is found.
AD 95-19-15 was written to apply to all serial numbers of all
models. A design change was made in this area beginning with serial
number 10175 of the Model AG-5B airplanes. Therefore, FAA determined
that the action should not apply to Model AG-5B airplanes with a serial
number of 10175 or higher.
Has FAA taken any action to this point? 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 all Tiger Aircraft LLC (Type
Certificate A16EA formerly held by American General Aircraft
Corporation and Grumman American Aviation Corporation) Models AA-5, AA-
5A, AA-5B, and AG-5B airplanes. This proposal was published in the
Federal Register as a notice of proposed rulemaking (NPRM) on May 19,
2005 (70 FR 28854). The NPRM proposed to retain all the actions of AD
95-19-15 for all airplanes originally affected, but proposed to cut off
the applicability for the Model AG-5B airplanes at serial number 10174.
Comments
Was the public invited to comment? 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: Type Certificate Data Sheet (TCDS) Number (No.) Is
Referenced Incorrectly in the NPRM
What is the commenter's concern? A letter from Tiger Aircraft LLC
notes that the TCDS No. A16EH in the NPRM is referenced incorrectly.
The TCDS should be No. A16EA.
What is FAA's response to the concern? We concur. We will correct
all reference in the final rule of the TCDS to No. A16EA.
Comment Issue No. 2: Manufacturer's Contact Information Is Incorrect in
the NPRM
What is the commenter's concern? The commenter from Tiger Aircraft
LLC requests that FAA change the contact information to that for Tiger
Aircraft LLC. American General Aircraft Corporation is out of business.
What is FAA's response to the concern? The FAA concurs. We will
change the contact information in the final rule to show Tiger Aircraft
LLC.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
[[Page 48858]]
determined that these changes and 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.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 3,700 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do this
inspection:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
10 work hours x $65 = $650............... Not included.................. $650 3,700 x $650 = $2,405,000
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have no way of determining the number of airplanes that may need
this replacement of any damaged bolts or repair as a result of the
inspection.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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-2005-20968; Directorate Identifier 94-CE-15-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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
95-19-15, Amendment 39-9377 (60 FR 48628, September 20, 1995), and by
adding a new AD to read as follows:
95-19-15 R1 Tiger Aircraft LLC: (Type Certificate A16EA formerly
held by American General Aircraft Corporation and Grumman American
Aviation Corporation): Amendment 39-14222; Docket No. FAA-2005-
20968; Directorate Identifier 94-CE-15-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on October 3, 2005.
What Other ADs Are Affected By This Action?
(b) This AD revises AD 95-19-15, Amendment 39-9377.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial numbers
------------------------------------------------------------------------
AA-5........................... All Serial Numbers.
AA-5A.......................... All Serial Numbers.
AA-5B.......................... All Serial Numbers.
AG-5B.......................... 99998, 10000 through 10174.
------------------------------------------------------------------------
What Is the Unsafe Condition Presented in This AD?
(d) AD 95-19-15 currently requires you to inspect the wing
attach shoulder bolts for fretting, scoring, wear, or enlarged or
elongated mounting holes (known as damage from hereon); replace any
damaged parts; repair any damaged areas; inspect the wing spar at
the center spar clearance gap for excessive clearance; and shim the
spar if excessive clearance is found. That AD was written to apply
to all serial numbers of all models. A design change was made in
this area beginning with serial number 10175 of the Model AG-5B
airplanes. Therefore, the action should not apply to Model AG-5B
airplanes with a serial number of 10175 or higher. This AD retains
all the actions of AD 95-19-15 for all airplanes originally
affected, but cuts off the applicability for the Model AG-5B
airplanes at serial number 10174. We are issuing this AD to continue
to prevent wing attach shoulder bolt failure, which, if not detected
and corrected, could lead to structural damage of the wing/fuselage
to the point of failure.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following, unless
already done:
[[Page 48859]]
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect any inboard wing Within the next 100 Follow American
attach shoulder bolt for: hours aircraft time- General Aircraft
in-service (TIS) Corporation Service
after November 17, Bulletin No. SB-185-
1995 (the effective A, Revision A,
date of AD 95-19- dated January 10,
15, unless already 2005.
done
(i) Fretting, scoring,
or wear (removal of the
cad plating) to the
shoulder of the bolt
(ii) A smooth machined
area between the
threads and the
shoulder bevel of the
shoulder bolt profile
(2) Replace any inboard wing Before further Follow American
attach shoulder bolt with flight after the General Aircraft
wear (removal of the cad inspection required Corporation Service
plating from the shoulder by paragraph (e)(1) Bulletin No. SB-185-
of the bolt) or if the of this AD A, Revision A,
threads contact the dated January 10,
shoulder of the bolt found 2005.
during the inspections
required in paragraph
(e)(1) of this AD
(3) Inspect the mounting Within the next 100 Follow American
holes in the wing spar and hours aircraft time- General Aircraft
the center section spar for in-service (TIS) Corporation Service
enlargement or elongation after November 17, Bulletin No. SB-185-
that exceeds the specified 1995 (the effective A, Revision A,
dimension date of AD 95-19- dated January 10,
15), unless already 2005.
done
(4) Ream and bush any Before further Follow American
mounting hole that exceeds flight after the General Aircraft
the specified dimension inspection required Corporation Service
found during the inspection by paragraph (e)(3) Bulletin No. SB-185-
required by paragraph of this AD A, Revision A,
(e)(3) of this AD dated January 10,
2005
(5) Inspect the wing spar at Before further Follow American
the center spar clearance flight after the General Aircraft
gap for excessive inspections Corporation Service
clearance, and shim the required by Bulletin No. SB-185-
spar if excessive clearance paragraphs (e)(1) A, Revision A,
is found and (e)(3) of this dated January 10,
AD 2005.
(6) Do not install any wing As of October 3, Not Applicable.
attach shoulder bolt that 2005 (the effective
has wear resulting in date of this AD)
removal of the cad plating
from the shoulder of the
bolt or if the threads
contact the shoulder bevel
of the shoulder bolt
profile
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, New York Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact Richard
Beckwith, Aerospace Engineer, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile:
516-794-5531.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in American General Aircraft Corporation Service
Bulletin No. SB-185-A, Revision A, dated January 10, 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 Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401. 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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-20968; Directorate
Identifier 94-CE-15-AD.
Issued in Kansas City, Missouri, on August 11, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-16260 Filed 8-19-05; 8:45 am]
BILLING CODE 4910-13-P
