Airworthiness Directives; Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B Airplanes, 2070-2072 [05-606]
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Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules
perform any applicable related investigative
and corrective actions (which may include
inspections for damage to surrounding
structure caused by the broken bracket, and
corrective actions for any damage that is
found), in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the Direction Generale
de l’Aviation Civile (DGAC) (or its delegated
agent).
Alternative Methods of Compliance
(AMOCs)
(k) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Related Information
(l) French airworthiness directives F–
2004–140 and F–2004–141, both dated
August 18, 2004, also address the subject of
this AD.
Issued in Renton, Washington, on
December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–612 Filed 1–11–05; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19897; Directorate
Identifier 2004–CE–45–AD]
RIN 2120–AA64
Airworthiness Directives; Eagle
Aircraft (Malaysia) Sdn. Bhd. Model
Eagle 150B Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Eagle Aircraft (Malaysia) Sdn.
Bhd. Model Eagle 150B airplanes. This
proposed AD would require you to
modify or replace the co-pilot rudder
pedal assembly. This proposed AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the airworthiness authority for
Malaysia. We are issuing this proposed
AD to prevent binding of the co-pilot
rudder pedal assembly due to premature
wear of the bushing, which could result
in loss of co-pilot rudder and brake
control. This failure could result in loss
of control of the airplane.
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17:43 Jan 11, 2005
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We must receive any comments
on this proposed AD by February 11,
2005.
ADDRESSES: Use one of the following to
submit comments on this proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
To get the service information
identified in this proposed AD, contact
Eagle Aircraft (Malaysia) Sdn. Bhd., P.O.
Box 1028, Pejabat Pos Besar, Melanka,
Malaysia, 75150; telephone: 011 (606)
317–4105; facsimile: 011 (606) 317–
7213.
To view the comments to this
proposed AD, go to https://dms.dot.gov.
This is docket number FAA–2004–
19897.
FOR FURTHER INFORMATION CONTACT: Karl
Schletzbaum, Aerospace Engineer,
Small Airplane Directorate, ACE–112,
901 Locust, Rm 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4146; facsimile: (816) 329–4149.
SUPPLEMENTARY INFORMATION:
DATES:
Comments Invited
How do I comment on this proposed
AD? We invite you to submit any
written relevant data, views, or
arguments regarding this proposal. Send
your comments to an address listed
under ADDRESSES. Include the docket
number, ‘‘FAA–2004–19897; Directorate
Identifier 2004–CE–45–AD’’ at the
beginning of your comments. We will
post all comments we receive, without
change, to https://dms.dot.gov, including
any personal information you provide.
We will also post a report summarizing
each substantive verbal contact with
FAA personnel concerning this
proposed rulemaking. Using the search
function of our docket Web site, anyone
can find and read the comments
received into any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). This is
docket number FAA–2004–19897. You
PO 00000
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may review the DOT’s complete Privacy
Act Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Are there any specific portions of this
proposed AD I should pay attention to?
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this proposed AD. If you contact us
through a nonwritten communication
and that contact relates to a substantive
part of this proposed AD, we will
summarize the contact and place the
summary in the docket. We will
consider all comments received by the
closing date and may amend this
proposed AD in light of those comments
and contacts.
Docket Information
Where can I go to view the docket
information? You may view the AD
docket that contains the proposal, any
comments received, and any final
disposition in person at the DMS Docket
Offices between 9 a.m. and 5 p.m.
(eastern standard time), Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5227) is located on the plaza level
of the Department of Transportation
NASSIF Building at the street address
stated in ADDRESSES. You may also view
the AD docket on the Internet at http:/
/dms.dot.gov. The comments will be
available in the AD docket shortly after
the DMS receives them.
Discussion
What events have caused this
proposed AD? The Department of Civil
Aviation, Malaysia (DCA), which is the
airworthiness authority for Malaysia,
recently notified FAA that an unsafe
condition may exist on certain Eagle
Aircraft Sdn. Bhd. Model Eagle 150B
airplanes. The DCA reports two
incidents of the co-pilot rudder pedal
assembly, part number (P/N) 2720D07–
02, binding and becoming inoperable
during flight.
Investigation revealed that the two
incidents resulted from premature wear
of the bushing, P/N 2720D08–39, in the
co-pilot rudder pedal assembly.
Premature wear of the bushing allowed
it to slide out of the housing resulting
in excessive play between the co-pilot
rudder pedal assembly and the shaft.
That condition caused the co-pilot
rudder control pushrod pivot, P/N
2720D08–31/04, to bind with the copilot pivot arms, P/N 2720D08–42.
Stronger material is now used to
manufacture the bushing and it has also
been improved by including side
stoppers.
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Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules
What is the potential impact if FAA
took no action? If not corrected, binding
of the co-pilot rudder pedal assembly
could result in loss of co-pilot rudder
and brake control. This failure could
result in loss of control of the airplane.
Is there service information that
applies to this subject? Eagle Aircraft
Sdn. Bhd. has issued Mandatory Service
Bulletin SB 1095, dated September 9,
2003; Optional Service Bulletin SB
1096, dated September 9, 2003; and
Optional Service Bulletin SB 1097,
dated September 9, 2003.
What are the provisions of this service
information? Eagle Aircraft Mandatory
Service Bulletin SB 1095, dated
September 9, 2003, includes procedures
for disengaging and removing the copilot rudder pedal assembly, part
number (P/N) 2720D07–02.
Eagle Aircraft Optional Service
Bulletin SB 1096, dated September 9,
2003, includes procedures for modifying
the existing co-pilot rudder pedal
assembly, P/N 2720D07–02, from a
welded to a bolted design to allow
individual parts replacement within the
assembly and includes instructions for
incorporating rudder control stoppers.
Eagle Aircraft Optional Service
Bulletin SB 1097, dated September 9,
2003, includes procedures for replacing
the existing co-pilot rudder pedal
assembly, P/N 2720D07–02, with a new
bolted design co-pilot rudder pedal
assembly, P/N 2720D07–10.
What action did the DCA take? The
DCA classified these service bulletins as
mandatory and issued Malaysian CAM
AD 002–10–2004, Issue date: October
30, 2004, to ensure the continued
airworthiness of these airplanes in
Malaysia.
Did the DCA inform the United States
under the bilateral airworthiness
agreement? These Eagle 150B airplanes
are manufactured in Malaysia and are
type-certificated for operation in the
United States under the provisions of
section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement.
Under this bilateral airworthiness
agreement, the DCA has kept us
informed of the situation described
above.
FAA’s Determination and Requirements
of This Proposed AD
What has FAA decided? We have
examined the DCA’s findings, reviewed
all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
Since the unsafe condition described
previously is likely to exist or develop
on other Eagle 150B airplanes of the
same type design that are registered in
the United States, we are proposing AD
action to prevent binding of the co-pilot
rudder pedal assembly due to premature
wear of the bushing, which could result
in loss of co-pilot rudder and brake
control. This failure could result in loss
of control of the airplane.
What would this proposed AD
require? This proposed AD would
require you to modify or replace the copilot rudder pedal assembly.
How does the revision to 14 CFR part
39 affect this proposed AD? On July 10,
2002, we published a new version of 14
CFR part 39 (67 FR 47997, July 22,
2002), which governs 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 would this
proposed AD impact? We estimate that
this proposed AD affects 13 airplanes in
the U.S. registry.
What would be the cost impact of this
proposed AD on owners/operators of the
affected airplanes? We estimate the
following costs to accomplish this
proposed modification:
Total cost per
airplane
Labor hours
Parts cost
4 work hours × $65 per hour = $260. Eagle Aircraft has
agreed to reimburse for the cost of labor.
Eagle Aircraft has agreed to provide the parts without cost ....
Not applicable.
We estimate the following costs to
accomplish the proposed replacements:
Labor cost
Parts cost
Total cost per
airplane
3 work hours × $65 per hour = $195 ......................................................................................................................
$1,440
$1,635
Regulatory Findings
Would this proposed AD impact
various entities? We have determined
that this proposed AD would not have
federalism implications under Executive
Order 13132. This proposed AD would
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.
Would this proposed AD involve a
significant rule or regulatory action? For
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17:43 Jan 11, 2005
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the reasons discussed above, I certify
that this proposed 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 proposed AD and
placed it in the AD Docket. You may get
a copy of this summary by sending a
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request to us at the address listed under
Include ‘‘AD Docket FAA–
2004–19897; Directorate Identifier
2004–CE–45–AD’’ in your request.
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
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Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Eagle Aircraft (Malaysia) SdN. BhD.: Docket
No. FAA–2004–19897; Directorate
Identifier 2004–CE–45–AD
When Is the Last Date I Can Submit
Comments on This Proposed AD?
(a) We must receive comments on this
proposed airworthiness directive (AD) by
February 11, 2005.
What Other ADs Are Affected by This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model Eagle 150B
airplanes, manufacturer serial numbers
(MSN) 016 through 042, that are:
(1) Equipped with a co-pilot rudder pedal
assembly welded design, part number (P/N)
2720D07–02; and
(2) Certificated in any category.
What Is the Unsafe Condition Presented in
This AD?
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Malaysia. We are issuing this AD to prevent
binding of the co-pilot rudder pedal assembly
due to premature wear of the bushing, which
could result in loss of co-pilot rudder and
brake control. This failure could result in loss
of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Inspect the co-pilot rudder pedal assembly
welded design, part number (P/N) 2720D07–
02, for cracks.
(i) If cracks are found, replace the assembly
with a new bolted design co-pilot rudder
pedal assembly, P/N 2720D07–10.
(ii) If no cracks are found, either:
(A) Modify P/N 2720D07–02 by replacing the
rudder control bushing with a new P/N
2720D08–39 and installing a rudder control
stopper, P/N 2720D08–44; or
(B) Replace P/N 2720D07–02 with a new
bolted design co-pilot rudder pedal assembly,
P/N 2720D07–10.
(2) Do not install a co-pilot rudder pedal assembly, P/N 2720D07–02, unless it has been
inspected and modified as required in paragraphs (e)(1) and (e)(1)(ii)(A) of this AD.
Inspect within 30 days after the effective date
of this AD. If cracks are found during the inspection, before further flight replace the
rudder pedal assembly. If no cracks are
found during the inspection, before further
flight, modify or replace the rudder pedal
assembly.
To inspect and modify the rudder pedal assembly, follow Eagle Aircraft Optional Service Bulletin SB 1096, dated September 16,
2003. To replace the rudder pedal assembly, follow Eagle Aircraft Optional Service
Bulletin SB 1097, dated September 16,
2003.
As of the effective date of this AD ...................
Not applicable.
May I Request an Alternative Method of
Compliance?
‘‘WARNING: CO-PILOT RUDDER PEDAL
IS NON-FUNCTIONAL.’’
DEPARTMENT OF COMMERCE
(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 Karl Schletzbaum,
Aerospace Engineer, Small Airplane
Directorate, ACE–112, 901 Locust, Rm 301,
Kansas City, Missouri, 64106; telephone:
(816) 329–4146; facsimile: (816) 329–4149.
Is There Other Information That Relates to
This Subject?
What if I Need To Fly the Airplane To
Another Location to Comply With This AD?
(g) The FAA can issue a special flight
permit under sections 21.197 and 21.199 of
the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate your airplane
to a location where you can accomplish the
requirements of this AD provided that the
following is adhered to:
(1) Remove the co-pilot rudder pedal
assembly, P/N 2720D07–02, from installation
following Eagle Aircraft Mandatory Service
Bulletin SB 1095, dated September 16, 2003;
and
(2) Install a temporary placard in a visible
place on the instrument panel that has the
following wording:
VerDate jul<14>2003
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(h) Malaysia CAM AD 002–10–2004, Issue
date: October 30, 2004, also addresses the
subject of this AD.
May I Get Copies of the Documents
Referenced in This AD?
(i) To get copies of the documents
referenced in this AD, contact Eagle Aircraft,
P.O. Box 1028, Pejabat Pos Besar, Melaka,
Malaysia, 75150; telephone: 011 (606) 317–
4105; facsimile: 011 (606) 317–7213. 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, or on the
Internet at https://dms.dot.gov. This is docket
number FAA–2004–19897.
Issued in Kansas City, Missouri, on January
5, 2005.
William J. Timberlake,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–606 Filed 1–11–05; 8:45 am]
BILLING CODE 4910–13–P
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Bureau of the Census
15 CFR Part 30
[Docket Number 041029301–4301–01]
RIN 0607–AA44
Requirement for Reporting the
Kimberley Process Certificate Number
for Exports (Reexports) of Rough
Diamonds
Bureau of the Census,
Commerce Department.
ACTION: Notice of proposed rulemaking
and request for comments.
AGENCY:
SUMMARY: The U.S. Census Bureau
(Census Bureau) proposes to amend the
Foreign Trade Statistics Regulations
(FTSR) to incorporate the requirement
for reporting the Kimberley Process
Certificate (KPC) number for the exports
(reexports) of rough diamonds filed
through the Automated Export System
(AES) in accordance with the Clean
Diamond Trade Act. This rule would
serve to carry out the purposes of
Executive Order 13312 of July 29, 2003,
which implemented the Clean Diamond
Trade Act and the Kimberley Process
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]]>Agencies
[Federal Register Volume 70, Number 8 (Wednesday, January 12, 2005)]
[Proposed Rules]
[Pages 2070-2072]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-606]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19897; Directorate Identifier 2004-CE-45-AD]
RIN 2120-AA64
Airworthiness Directives; Eagle Aircraft (Malaysia) Sdn. Bhd.
Model Eagle 150B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B
airplanes. This proposed AD would require you to modify or replace the
co-pilot rudder pedal assembly. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Malaysia. We are issuing this proposed AD to prevent
binding of the co-pilot rudder pedal assembly due to premature wear of
the bushing, which could result in loss of co-pilot rudder and brake
control. This failure could result in loss of control of the airplane.
DATES: We must receive any comments on this proposed AD by February 11,
2005.
ADDRESSES: Use one of the following to submit comments on this proposed
AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
To get the service information identified in this proposed AD,
contact Eagle Aircraft (Malaysia) Sdn. Bhd., P.O. Box 1028, Pejabat Pos
Besar, Melanka, Malaysia, 75150; telephone: 011 (606) 317-4105;
facsimile: 011 (606) 317-7213.
To view the comments to this proposed AD, go to https://dms.dot.gov.
This is docket number FAA-2004-19897.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
Small Airplane Directorate, ACE-112, 901 Locust, Rm 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4149.
SUPPLEMENTARY INFORMATION:
Comments Invited
How do I comment on this proposed AD? We invite you to submit any
written relevant data, views, or arguments regarding this proposal.
Send your comments to an address listed under ADDRESSES. Include the
docket number, ``FAA-2004-19897; Directorate Identifier 2004-CE-45-AD''
at the beginning of your comments. We will post all comments we
receive, without change, to https://dms.dot.gov, including any personal
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this proposed
rulemaking. Using the search function of our docket Web site, anyone
can find and read the comments received into any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
This is docket number FAA-2004-19897. You may review the DOT's complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78), or you may visit https://dms.dot.gov.
Are there any specific portions of this proposed AD I should pay
attention to? We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed AD. If you contact us through a nonwritten communication and
that contact relates to a substantive part of this proposed AD, we will
summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend this
proposed AD in light of those comments and contacts.
Docket Information
Where can I go to view the docket information? You may view the AD
docket that contains the proposal, any comments received, and any final
disposition in person at the DMS Docket Offices between 9 a.m. and 5
p.m. (eastern standard time), Monday through Friday, except Federal
holidays. The Docket Office (telephone 1-800-647-5227) is located on
the plaza level of the Department of Transportation NASSIF Building at
the street address stated in ADDRESSES. You may also view the AD docket
on the Internet at https://dms.dot.gov. The comments will be available
in the AD docket shortly after the DMS receives them.
Discussion
What events have caused this proposed AD? The Department of Civil
Aviation, Malaysia (DCA), which is the airworthiness authority for
Malaysia, recently notified FAA that an unsafe condition may exist on
certain Eagle Aircraft Sdn. Bhd. Model Eagle 150B airplanes. The DCA
reports two incidents of the co-pilot rudder pedal assembly, part
number (P/N) 2720D07-02, binding and becoming inoperable during flight.
Investigation revealed that the two incidents resulted from
premature wear of the bushing, P/N 2720D08-39, in the co-pilot rudder
pedal assembly. Premature wear of the bushing allowed it to slide out
of the housing resulting in excessive play between the co-pilot rudder
pedal assembly and the shaft. That condition caused the co-pilot rudder
control pushrod pivot, P/N 2720D08-31/04, to bind with the co-pilot
pivot arms, P/N 2720D08-42.
Stronger material is now used to manufacture the bushing and it has
also been improved by including side stoppers.
[[Page 2071]]
What is the potential impact if FAA took no action? If not
corrected, binding of the co-pilot rudder pedal assembly could result
in loss of co-pilot rudder and brake control. This failure could result
in loss of control of the airplane.
Is there service information that applies to this subject? Eagle
Aircraft Sdn. Bhd. has issued Mandatory Service Bulletin SB 1095, dated
September 9, 2003; Optional Service Bulletin SB 1096, dated September
9, 2003; and Optional Service Bulletin SB 1097, dated September 9,
2003.
What are the provisions of this service information? Eagle Aircraft
Mandatory Service Bulletin SB 1095, dated September 9, 2003, includes
procedures for disengaging and removing the co-pilot rudder pedal
assembly, part number (P/N) 2720D07-02.
Eagle Aircraft Optional Service Bulletin SB 1096, dated September
9, 2003, includes procedures for modifying the existing co-pilot rudder
pedal assembly, P/N 2720D07-02, from a welded to a bolted design to
allow individual parts replacement within the assembly and includes
instructions for incorporating rudder control stoppers.
Eagle Aircraft Optional Service Bulletin SB 1097, dated September
9, 2003, includes procedures for replacing the existing co-pilot rudder
pedal assembly, P/N 2720D07-02, with a new bolted design co-pilot
rudder pedal assembly, P/N 2720D07-10.
What action did the DCA take? The DCA classified these service
bulletins as mandatory and issued Malaysian CAM AD 002-10-2004, Issue
date: October 30, 2004, to ensure the continued airworthiness of these
airplanes in Malaysia.
Did the DCA inform the United States under the bilateral
airworthiness agreement? These Eagle 150B airplanes are manufactured in
Malaysia and are type-certificated for operation in the United States
under the provisions of section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness
agreement.
Under this bilateral airworthiness agreement, the DCA has kept us
informed of the situation described above.
FAA's Determination and Requirements of This Proposed AD
What has FAA decided? We have examined the DCA's findings, reviewed
all available information, and determined that AD action is necessary
for products of this type design that are certificated for operation in
the United States.
Since the unsafe condition described previously is likely to exist
or develop on other Eagle 150B airplanes of the same type design that
are registered in the United States, we are proposing AD action to
prevent binding of the co-pilot rudder pedal assembly due to premature
wear of the bushing, which could result in loss of co-pilot rudder and
brake control. This failure could result in loss of control of the
airplane.
What would this proposed AD require? This proposed AD would require
you to modify or replace the co-pilot rudder pedal assembly.
How does the revision to 14 CFR part 39 affect this proposed AD? On
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that
this proposed AD affects 13 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
accomplish this proposed modification:
------------------------------------------------------------------------
Total cost per
Labor hours Parts cost airplane
------------------------------------------------------------------------
4 work hours x $65 per hour = Eagle Aircraft Not applicable.
$260. Eagle Aircraft has has agreed to
agreed to reimburse for the provide the
cost of labor. parts without
cost.
------------------------------------------------------------------------
We estimate the following costs to accomplish the proposed
replacements:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
3 work hours x $65 per hour = $195.... $1,440 $1,635
------------------------------------------------------------------------
Regulatory Findings
Would this proposed AD impact various entities? We have determined
that this proposed AD would not have federalism implications under
Executive Order 13132. This proposed AD would 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.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this proposed
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 proposed 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
``AD Docket FAA-2004-19897; Directorate Identifier 2004-CE-45-AD'' in
your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:
[[Page 2072]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Eagle Aircraft (Malaysia) SdN. BhD.: Docket No. FAA-2004-19897;
Directorate Identifier 2004-CE-45-AD
When Is the Last Date I Can Submit Comments on This Proposed AD?
(a) We must receive comments on this proposed airworthiness
directive (AD) by February 11, 2005.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model Eagle 150B airplanes, manufacturer
serial numbers (MSN) 016 through 042, that are:
(1) Equipped with a co-pilot rudder pedal assembly welded
design, part number (P/N) 2720D07-02; and
(2) Certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Malaysia. We are issuing this AD to prevent binding of the co-pilot
rudder pedal assembly due to premature wear of the bushing, which
could result in loss of co-pilot rudder and brake control. This
failure could result in loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the co-pilot rudder Inspect within 30 To inspect and
pedal assembly welded design, days after the modify the rudder
part number (P/N) 2720D07-02, effective date of pedal assembly,
for cracks. this AD. If follow Eagle
(i) If cracks are found, replace cracks are found Aircraft Optional
the assembly with a new bolted during the Service Bulletin
design co-pilot rudder pedal inspection, SB 1096, dated
assembly, P/N 2720D07-10.. before further September 16,
(ii) If no cracks are found, flight replace 2003. To replace
either:. the rudder pedal the rudder pedal
(A) Modify P/N 2720D07-02 by assembly. If no assembly, follow
replacing the rudder control cracks are found Eagle Aircraft
bushing with a new P/N 2720D08- during the Optional Service
39 and installing a rudder inspection, Bulletin SB 1097,
control stopper, P/N 2720D08- before further dated September
44; or. flight, modify or 16, 2003.
(B) Replace P/N 2720D07-02 with replace the
a new bolted design co-pilot rudder pedal
rudder pedal assembly, P/N assembly.
2720D07-10..
(2) Do not install a co-pilot As of the Not applicable.
rudder pedal assembly, P/N effective date of
2720D07-02, unless it has been this AD.
inspected and modified as
required in paragraphs (e)(1)
and (e)(1)(ii)(A) of this AD.
------------------------------------------------------------------------
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 Karl Schletzbaum,
Aerospace Engineer, Small Airplane Directorate, ACE-112, 901 Locust,
Rm 301, Kansas City, Missouri, 64106; telephone: (816) 329-4146;
facsimile: (816) 329-4149.
What if I Need To Fly the Airplane To Another Location to Comply With
This AD?
(g) The FAA can issue a special flight permit under sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate your airplane to a location where you can
accomplish the requirements of this AD provided that the following
is adhered to:
(1) Remove the co-pilot rudder pedal assembly, P/N 2720D07-02,
from installation following Eagle Aircraft Mandatory Service
Bulletin SB 1095, dated September 16, 2003; and
(2) Install a temporary placard in a visible place on the
instrument panel that has the following wording:
``WARNING: CO-PILOT RUDDER PEDAL IS NON-FUNCTIONAL.''
Is There Other Information That Relates to This Subject?
(h) Malaysia CAM AD 002-10-2004, Issue date: October 30, 2004,
also addresses the subject of this AD.
May I Get Copies of the Documents Referenced in This AD?
(i) To get copies of the documents referenced in this AD,
contact Eagle Aircraft, P.O. Box 1028, Pejabat Pos Besar, Melaka,
Malaysia, 75150; telephone: 011 (606) 317-4105; facsimile: 011 (606)
317-7213. 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, or on the
Internet at https://dms.dot.gov. This is docket number FAA-2004-
19897.
Issued in Kansas City, Missouri, on January 5, 2005.
William J. Timberlake,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-606 Filed 1-11-05; 8:45 am]
BILLING CODE 4910-13-P
