Airworthiness Directives; Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes, 4761-4763 [05-1511]
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Federal Register / Vol. 70, No. 19 / Monday, January 31, 2005 / Rules and Regulations
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 adding
the following new airworthiness
directive (AD):
I
2005–02–07 Empresa Brasileira de
Aeronautica S.A. (EMBRAER):
Amendment 39–13952. Docket No.
FAA–2004–19526; Directorate Identifier
2004–NM–140–AD.
Effective Date
(a) This AD becomes effective March 7,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to EMBRAER Model
EMB–135BJ series airplanes, serial numbers
145462, 145495, 145505, 145528, 145625,
145637, and 145642; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by a report that
the stick pushers are not being inhibited
when the AP/PUSH/TRIM switches are
activated, which can result in reduced
controllability of the airplane if there is a
system malfunction. We are issuing this AD
to prevent reduced controllability of the
airplane if the stick pusher system
malfunctions.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Modification of Electrical Wiring
(f) Within 400 flight hours or 180 calendar
days after the effective date of this AD,
whichever is first: Modify the wiring for the
stick pusher system by accomplishing all of
the actions specified in the Accomplishment
Instructions of EMBRAER Service Bulletin
145LEG–27–0009, dated March 1, 2004.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(h) Brazilian airworthiness directive 2004–
04–02, dated May 6, 2004, also addresses the
subject of this AD.
Material Incorporated by Reference
(i) You must use EMBRAER Service
Bulletin 145LEG–27–0009, dated March 1,
2004, to perform the actions that are required
by this AD, unless the AD specifies
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16:42 Jan 28, 2005
Jkt 205001
otherwise. The Director of the Federal
Register approves the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. For
copies of the service information, contact
Empresa Brasileira de Aeronautica S.A.
(EMBRAER), P.O. Box 343—CEP 12.225, Sao
Jose dos Campos—SP, Brazil. For information
on the availability of this material at the
National Archives and Records
Administration (NARA), call (202) 741–6030,
or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_
locations.html. You may view the AD docket
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC.
4761
Federal Aviation Administration
Latrobe Regional Airport, P.O. Box 881,
Morwell, Victoria 3840, Australia;
telephone: 61 (0) 3 5172 1200; facsimile:
61 (0) 3 5172 1201. To review 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–2004–19442.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE–112,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: 816–329–
4059; facsimile: 816–329–4090.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Discussion
Issued in Renton, Washington, on January
18, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–1515 Filed 1–28–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2004–19442; Directorate
Identifier 2004–CE–31–AD; Amendment 39–
13956; AD 2005–01–11]
RIN 2120–AA64
Airworthiness Directives; Gippsland
Aeronautics Pty. Ltd. Model GA8
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Gippsland Aeronautics Pty. Ltd. Model
GA8 airplanes. This AD requires you to
inspect the pilot and co-pilot control
column wheels and aileron cable
operating arm shafts for damage and, if
damage is found, to repair the shafts or
to replace the steel shafts with bronze
shafts. We are issuing this AD to detect
and correct damage of the pilot and copilot control wheels and aileron cable
operating arm shafts. This damage could
result in the aileron controls becoming
stiff or locking, which could lead to loss
of control of the airplane.
DATES: This AD becomes effective on
March 4, 2005.
As of March 4, 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 Gippsland Aeronautics Pty. Ltd.,
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
What events have caused this AD?
The Civil Aviation Safety Authority
(CASA), which is the airworthiness
authority for Australia, recently notified
FAA that an unsafe condition may exist
on certain Gippsland Aeronautics Pty.
Ltd. Model GA8 airplanes. CASA
reports three occurrences of aileron
control stiffness and one occurrence of
aileron control locking during taxi.
Rubbing between the control wheel
shaft and the bush in the control
column may cause wear or damage to
the control wheel shaft where the shaft
connects to the control column. This
damage may lead to the aileron control
becoming stiff or locking.
What is the potential impact if FAA
took no action? Damage of the pilot and
co-pilot control wheels and aileron
cable operating arm shafts could result
in the aileron controls becoming stiff or
locking, which could lead to loss of
control of the airplane.
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 certain
Gippsland Aeronautics Pty. Ltd. Model
GA8 airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on November 8, 2004 (69 FR 64695).
The NPRM proposed to detect and
correct damage of the pilot and co-pilot
control wheels and aileron cable
operating arm shafts that could result in
E:\FR\FM\31JAR1.SGM
31JAR1
4762
Federal Register / Vol. 70, No. 19 / Monday, January 31, 2005 / Rules and Regulations
the aileron controls becoming stiff or
locking, which could lead to loss of
control of the airplane.
Comments
Was the public invited to comment?
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
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
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.
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.
Changes to 14 CFR Part 39—Effect on
the AD
How many airplanes does this AD
impact? We estimate that this AD affects
5 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 accomplish the inspection:
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.
Costs of Compliance
Labor cost
Parts cost
Total cost
per airplane
Total cost
on U.S.
operators
2 work hours × $65 per hour = $130 ..........................................................................................
N/A
$130
$650
We estimate the following costs to
accomplish any necessary replacements
that would be required based on the
results of this inspection. We have no
way of determining the number of
airplanes that may need this repair/
replacement:
Labor cost
Parts cost
Total cost
per airplane
Labor Cost per side (either pilot or co-pilot)—8 work hours × $65 per hour =
$520.
Warranty ..............................................
Per side = $520.
For both sides = $1,040.
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
VerDate jul<14>2003
16:42 Jan 28, 2005
Jkt 205001
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 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–2004–19442;
Directorate Identifier 2004–CE–31–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
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. FAA amends § 39.13 by adding a
new AD to read as follows:
I
2005–02–11 Gippsland Aeronautics Pty.
Ltd.: Amendment 39–13956; Docket No.
FAA–2004–19442; Directorate Identifier
2004–CE–31–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on March 4,
2005.
What Other ADs Are Affected by This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects model GA8 airplanes,
serial numbers GA8–00–004 through GA8–
04–056, that are certificated in any category.
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31JAR1
Federal Register / Vol. 70, No. 19 / Monday, January 31, 2005 / Rules and Regulations
What Is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of rubbing
between the control wheel shaft and the bush
in the control column, which may cause wear
or damage to the control wheel shaft where
the shaft connects to the control column.
This damage may lead to the aileron control
becoming stiff or locking. The actions
specified in this AD are intended to detect
and correct damage of the pilot and co-pilot
control wheels and aileron cable operating
arm shafts that could result in the aileron
4763
controls becoming stiff or locking, which
could lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
(1) Inspect the pilot and co-pilot control column
wheel and aileron cable operating arm shafts
for damage.
(2) If no damage is found, continue repetitive
inspections.
Perform the initial inspection within 50 hours
time-in-service (TIS) after March 4, 2005
(the effective date of this AD).
Perform repetitive inspections every 300
hours TIS until steel operating arm shafts
are replaced with bronze operating arm
shafts. Replacement of steel operating arm
shafts with bronze operating arm shafts is
terminating action for this AD on the side
that was replaced. If one steel shaft requires replacement, all of the shafts on that
side (pilot or co-pilot) must be replaced with
bronze shafts. If only one side (pilot or copilot) is replaced, repetitive inspections are
still required for the side that was not replaced.
If damage is found, repair or replace operating arm shafts prior to further flight. If airplane is repaired, repetitively inspect every
300 hours TIS after repair until replacement
of the operating arm shafts. Replacement of
the steel operating arm shafts with bronze
operating arm shafts is terminating action
for this AD. If only one side (pilot or co-pilot)
is replaced with bronze shafts, you must
still repetitively inspect the other side that
was not replaced.
Follow Gippsland Aeronautics Pty.
ice Bulletin SB–GA8–2004–11,
dated August 25, 2004.
Follow Gippsland Aeronautics Pty.
ice Bulletin SB–GA8–2004–11,
dated August 25, 2004.
As of March 4, 2005 (the effective date of this
AD).
Follow Gippsland Aeronautics Pty. Ltd. Service Bulletin SB–GA8–2004–11, Issue 2,
dated August 25, 2004.
Does This AD Incorporate Any Material by
Reference?
(h) You must do the actions required by
this AD following the instructions in
Gippsland Aeronautics Pty. Ltd. Service
Bulletin SB–GA8–2004–11, Issue 2, dated
August 25, 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 Gippsland Aeronautics
Pty. Ltd., Latrobe Regional Airport, P.O. Box
881, Morwell, Victoria 3840, Australia;
telephone: 61 (0) 3 5172 1200; facsimile: 61
(0) 3 5172 1201. 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–
2004–19442.
(3) For airplanes where damage is found:
(i) If damage can be repaired by polishing out
marks or scratches so that material removed
does not exceed 0.005 inches, repair the
shaft. You can not repair by polishing out
marks or scratches more than one time.
(ii) If damage can not be repaired by polishing
out marks or scratches so that that material
removed does not exceed 0.005 inches or
you have already repaired the damage by
polishing out marks or scratches previously,
the damed steel operating arm shaft must be
replaced with a bronze operating arm shaft.
When a shaft (pilot or co-pilot) requires replacement, you must install new bronze
shafts in all areas of the affected side
(4) As of the effective date of this AD, do not
install shafts that are not bronze on any affected Model GA8 airplane.
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, Standards Office, Small Airplane
Directorate, FAA. For information on any
already approved alternative methods of
compliance, contact Doug Rudolph,
Aerospace Engineer, Small Airplane
Directorate, ACE–112, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: 816–
329–4059; facsimile: 816–329–4090.
Is There Other Information That Relates to
This Subject?
(g) Australian Civil Aviation Safety
Authority Airworthiness Directive AD/GA8/
2, dated September 17, 2004, and Gippsland
Aeronautics Pty., Ltd., Service Bulletin SB–
GA8–2004–11, dated August 25, 2004, also
address the subject of this AD.
VerDate jul<14>2003
16:42 Jan 28, 2005
Jkt 205001
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
Procedures
Ltd. ServIssue 2,
Ltd. ServIssue 2,
Follow Gippsland Aeronautics Pty. Ltd. Service Bulletin SB–GA8–2004–11, Issue 2,
dated August 25, 2004.
Issued in Kansas City, Missouri, on January
20, 2005.
David A. Downey,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–1511 Filed 1–28–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF JUSTICE
28 CFR Part 28
[Docket No. OAG 108; A.G. Order No. 2753–
2005]
RIN 1105–AB09
DNA Sample Collection From Federal
Offenders Under the Justice for All Act
of 2004
AGENCY:
E:\FR\FM\31JAR1.SGM
Department of Justice.
31JAR1
]]>Agencies
[Federal Register Volume 70, Number 19 (Monday, January 31, 2005)]
[Rules and Regulations]
[Pages 4761-4763]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-1511]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19442; Directorate Identifier 2004-CE-31-AD;
Amendment 39-13956; AD 2005-01-11]
RIN 2120-AA64
Airworthiness Directives; Gippsland Aeronautics Pty. Ltd. Model
GA8 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Gippsland Aeronautics Pty. Ltd. Model GA8 airplanes. This AD requires
you to inspect the pilot and co-pilot control column wheels and aileron
cable operating arm shafts for damage and, if damage is found, to
repair the shafts or to replace the steel shafts with bronze shafts. We
are issuing this AD to detect and correct damage of the pilot and co-
pilot control wheels and aileron cable operating arm shafts. This
damage could result in the aileron controls becoming stiff or locking,
which could lead to loss of control of the airplane.
DATES: This AD becomes effective on March 4, 2005.
As of March 4, 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 Gippsland Aeronautics Pty. Ltd., Latrobe Regional Airport, P.O.
Box 881, Morwell, Victoria 3840, Australia; telephone: 61 (0) 3 5172
1200; facsimile: 61 (0) 3 5172 1201. To review 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-2004-19442.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE-112, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: 816-329-4059; facsimile: 816-329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Civil Aviation Safety
Authority (CASA), which is the airworthiness authority for Australia,
recently notified FAA that an unsafe condition may exist on certain
Gippsland Aeronautics Pty. Ltd. Model GA8 airplanes. CASA reports three
occurrences of aileron control stiffness and one occurrence of aileron
control locking during taxi. Rubbing between the control wheel shaft
and the bush in the control column may cause wear or damage to the
control wheel shaft where the shaft connects to the control column.
This damage may lead to the aileron control becoming stiff or locking.
What is the potential impact if FAA took no action? Damage of the
pilot and co-pilot control wheels and aileron cable operating arm
shafts could result in the aileron controls becoming stiff or locking,
which could lead to loss of control of the airplane.
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 certain Gippsland Aeronautics Pty.
Ltd. Model GA8 airplanes. This proposal was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on November 8, 2004
(69 FR 64695). The NPRM proposed to detect and correct damage of the
pilot and co-pilot control wheels and aileron cable operating arm
shafts that could result in
[[Page 4762]]
the aileron controls becoming stiff or locking, which could lead to
loss of control of the airplane.
Comments
Was the public invited to comment? 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
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 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.
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 5 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 accomplish the
inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
2 work hours x $65 per hour = $130........................... N/A $130 $650
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
replacements that would be required based on the results of this
inspection. We have no way of determining the number of airplanes that
may need this repair/replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
Labor Cost per side (either pilot or co- Warranty................... Per side = $520.
pilot)--8 work hours x $65 per hour = For both sides = $1,040.
$520.
----------------------------------------------------------------------------------------------------------------
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
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-2004-19442; Directorate Identifier 2004-CE-31-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:
2005-02-11 Gippsland Aeronautics Pty. Ltd.: Amendment 39-13956;
Docket No. FAA-2004-19442; Directorate Identifier 2004-CE-31-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on March 4, 2005.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects model GA8 airplanes, serial numbers GA8-00-
004 through GA8-04-056, that are certificated in any category.
[[Page 4763]]
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of rubbing between the control wheel
shaft and the bush in the control column, which may cause wear or
damage to the control wheel shaft where the shaft connects to the
control column. This damage may lead to the aileron control becoming
stiff or locking. The actions specified in this AD are intended to
detect and correct damage of the pilot and co-pilot control wheels
and aileron cable operating arm shafts that could result in the
aileron controls becoming stiff or locking, which could lead to loss
of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the pilot and co- Perform the Follow Gippsland
pilot control column wheel and initial Aeronautics Pty.
aileron cable operating arm inspection within Ltd. Service
shafts for damage. 50 hours time-in- Bulletin SB-GA8-
service (TIS) 2004-11, Issue 2,
after March 4, dated August 25,
2005 (the 2004.
effective date of
this AD).
(2) If no damage is found, Perform repetitive Follow Gippsland
continue repetitive inspections. inspections every Aeronautics Pty.
300 hours TIS Ltd. Service
until steel Bulletin SB-GA8-
operating arm 2004-11, Issue 2,
shafts are dated August 25,
replaced with 2004.
bronze operating
arm shafts.
Replacement of
steel operating
arm shafts with
bronze operating
arm shafts is
terminating
action for this
AD on the side
that was
replaced. If one
steel shaft
requires
replacement, all
of the shafts on
that side (pilot
or co-pilot) must
be replaced with
bronze shafts. If
only one side
(pilot or co-
pilot) is
replaced,
repetitive
inspections are
still required
for the side that
was not replaced.
(3) For airplanes where damage If damage is Follow Gippsland
is found: found, repair or Aeronautics Pty.
(i) If damage can be repaired by replace operating Ltd. Service
polishing out marks or arm shafts prior Bulletin SB-GA8-
scratches so that material to further 2004-11, Issue 2,
removed does not exceed 0.005 flight. If dated August 25,
inches, repair the shaft. You airplane is 2004.
can not repair by polishing out repaired,
marks or scratches more than repetitively
one time.. inspect every 300
(ii) If damage can not be hours TIS after
repaired by polishing out marks repair until
or scratches so that that replacement of
material removed does not the operating arm
exceed 0.005 inches or you have shafts.
already repaired the damage by Replacement of
polishing out marks or the steel
scratches previously, the damed operating arm
steel operating arm shaft must shafts with
be replaced with a bronze bronze operating
operating arm shaft. When a arm shafts is
shaft (pilot or co-pilot) terminating
requires replacement, you must action for this
install new bronze shafts in AD. If only one
all areas of the affected side. side (pilot or co-
pilot) is
replaced with
bronze shafts,
you must still
repetitively
inspect the other
side that was not
replaced.
(4) As of the effective date of As of March 4, Follow Gippsland
this AD, do not install shafts 2005 (the Aeronautics Pty.
that are not bronze on any effective date of Ltd. Service
affected Model GA8 airplane. this AD). Bulletin SB-GA8-
2004-11, Issue 2,
dated August 25,
2004.
------------------------------------------------------------------------
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, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Doug Rudolph, Aerospace
Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: 816-329-4059; facsimile:
816-329-4090.
Is There Other Information That Relates to This Subject?
(g) Australian Civil Aviation Safety Authority Airworthiness
Directive AD/GA8/2, dated September 17, 2004, and Gippsland
Aeronautics Pty., Ltd., Service Bulletin SB-GA8-2004-11, dated
August 25, 2004, also address the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Gippsland Aeronautics Pty. Ltd. Service Bulletin SB-
GA8-2004-11, Issue 2, dated August 25, 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 Gippsland
Aeronautics Pty. Ltd., Latrobe Regional Airport, P.O. Box 881,
Morwell, Victoria 3840, Australia; telephone: 61 (0) 3 5172 1200;
facsimile: 61 (0) 3 5172 1201. 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-2004-19442.
Issued in Kansas City, Missouri, on January 20, 2005.
David A. Downey,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-1511 Filed 1-28-05; 8:45 am]
BILLING CODE 4910-13-P
