Airworthiness Directives; Raytheon (Beech) Model 400 and 400A Series Airplanes, 26877-26879 [E6-7014]
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Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2006–24697;
Directorate Identifier 2006–NM–045–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 23, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200, –200PF, and –200CB series airplanes,
certificated in any category; as identified in
Boeing Special Attention Service Bulletin
757–53–0090, dated June 2, 2005.
Unsafe Condition
(d) This AD results from a report indicating
that certain modified rivets were incorrectly
installed in some areas of the skin lap splices
during production because they were drilled
with a countersink that was too deep. We are
issuing this AD to detect and correct
premature fatigue cracking at certain skin lap
splice locations of the fuselage and
consequent rapid decompression of the
airplane.
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
No Reporting Required
(h) Although Boeing Special Attention
Service Bulletin 757–53–0090, dated June 2,
2005, recommends that inspection results be
reported to the manufacturer, this AD does
not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
Issued in Renton, Washington, on April 28,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–7007 Filed 5–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
mstockstill on PROD1PC68 with PROPOSALS
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.
14 CFR Part 39
Initial and Repetitive Inspections
(f) Do initial and repetitive detailed or high
frequency eddy current inspections for
cracking around the rivets at the upper
fastener row of the skin lap splice of the
fuselage by doing all the actions in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–53–0090, dated June 2,
2005, except as provided by paragraphs (g)
and (h) of this AD. Do the inspections at the
applicable times specified in Paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin; except
where the service bulletin specifies a
compliance time after the original release
date of the service bulletin, this AD requires
compliance after the effective date of this AD.
Airworthiness Directives; Raytheon
(Beech) Model 400 and 400A Series
Airplanes
Repair
(g) If any crack is found during any
inspection required by this AD: Before
VerDate Aug<31>2005
15:37 May 08, 2006
Jkt 208001
[Docket No. FAA–2006–24694; Directorate
Identifier 2006–NM–018–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Raytheon (Beech) Model 400 and
400A series airplanes. This proposed
AD would require, among other actions,
reviewing the airplane logbook to
determine whether certain generator
control unit (GCU) installation kits are
installed, and replacing any incorrect
GCU. This proposed AD results from
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
26877
reports of over-voltage conditions of the
direct current (DC) starter generator. We
are proposing this AD to prevent such
over-voltage conditions due to the
incompatibility between certain GCUs,
which could result in the loss of normal
electrical power, damage to some
electrical components, or blown fuses
during flight, and consequent
unrecoverable loss of some or all
essential equipment.
DATES: We must receive comments on
this proposed AD by June 23, 2006.
ADDRESSES: Use one of the following
addresses 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.
• Fax: (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.
Contact Raytheon Aircraft Company,
Department 62, P.O. Box 85, Wichita,
Kansas 67201–0085, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Philip Petty, Aerospace Engineer,
Electrical Systems and Avionics, ACE–
119W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road,
room 100, Mid-Continent Airport,
Wichita, Kansas 67209; telephone (316)
946–4139; fax (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24694; Directorate
Identifier 2006–NM–018–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
E:\FR\FM\09MYP1.SGM
09MYP1
26878
Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in 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.). You may
review 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.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
We have received reports of overvoltage conditions of the direct current
(DC) starter generator. In one case, overvoltage conditions resulted in complete
loss of the DC electrical power during
flight and loss of the primary flight
display. The cause is the
incompatibility between a Goodrich
(formerly Lucas Aerospace) DC starter
generator and a Shinko generator
control unit (GCU). This condition, if
not corrected, could result in loss of
normal electrical power, damage to
some electrical components, or blown
fuses during flight, which could result
in the unrecoverable loss of some or all
essential equipment.
mstockstill on PROD1PC68 with PROPOSALS
Relevant Service Information
We have reviewed Raytheon Service
Bulletin SB 24–3713, dated November
2005. The service bulletin describes
procedures for reviewing the airplane
logbook to determine whether a certain
GCU installation kit (Lucas Aerospace/
Goodrich) is installed and replacing any
incorrect Shinko GCU with a new Lucas
Aerospace/Goodrich GCU. For certain
findings, the service bulletin also
describes the following procedures, as
applicable:
• Inspecting to determine the part
number (P/N) of both GCUs;
• Inspecting to determine the P/N of
both current sense transformers on the
VerDate Aug<31>2005
15:37 May 08, 2006
Jkt 208001
lower inboard quadrant of the left-hand
and right-hand engine inlets;
• Replacing any incorrect GCU with a
certain new GCU; and
• Replacing any incorrect current
sense transformer with a certain new
transformer.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously except as discussed under
‘‘Difference Between the Proposed AD
and the Service Bulletin.’’
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.
For the reasons discussed above, I
certify that the proposed regulation:
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
Difference Between the Proposed AD
and the Service Bulletin
Operators should note that the
applicability of this proposed AD differs
from the Effectivity of Raytheon Service
Bulletin SB 24–3713. In addition to
airplanes on which Kit No. 128–3004–
1 P has been incorporated, this
proposed AD also affects airplanes on
which Kit No. 128–3004–3 P has been
incorporated. We have determined that
those airplanes also are subject to the
identified unsafe condition.
We have coordinated this difference
with the airplane manufacturer.
Costs of Compliance
There are about 43 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about 40
airplanes of U.S. registry. The proposed
inspection would take about 1 work
hour per airplane, at an average labor
rate of $80 per work hour. Based on
these figures, the estimated cost of the
proposed AD for U.S. operators is
$3,200, or $80 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
Regulatory Findings
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 FAA proposes to amend 14 CFR part
39 as follows:
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Raytheon Aircraft Company (Formerly
Beech): Docket No. FAA–2006–24694;
Directorate Identifier 2006–NM–018–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 23, 2006.
E:\FR\FM\09MYP1.SGM
09MYP1
Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
Affected ADs
26879
Applicability
(c) This AD applies to the airplanes
identified in Table 1 of this AD, certificated
in any category.
(b) None.
TABLE 1.—APPLICABILITY
Raytheon (Beech) model—
Serials—
On which—
(1) 400 series airplanes .......
RJ–1 through RJ–65 inclusive.
RK–1 through RK–23 inclusive.
Kit part number (P/N) 128–3004–1 P or 128–3004–3 P has been incorporated
(Lucas Aerospace/Goodrich Direct Current (DC) Starter Generator).
Kit P/N 128–3004–1 P or 128–3004–3 P has been incorporated (Lucas Aerospace/
Goodrich DC Starter Generator).
(2) 400A series airplanes .....
Unsafe Condition
(d) This AD results from reports of overvoltage conditions of the DC starter generator.
We are issuing this AD to prevent overvoltage conditions of the DC starter generator
due to the incompatibility between certain
GCUs, which could result in the loss of
normal electrical power, damage to some
electrical components, or blown fuses during
flight, and consequent unrecoverable loss of
some or all essential equipment.
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.
Service Bulletin
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Raytheon Service Bulletin SB
24–3713, dated November 2005.
Review of Logbook
(g) Within 200 flight hours or 6 months
after the effective date of this AD, whichever
occurs first, review the airplane logbook to
determine whether GCU installation kit, P/N
128–3001–1 P or 128–3001–3 P, is installed,
in accordance with the service bulletin.
Installation Kit Not Found Installed:
Replacement of Shinko GCU
(h) If no GCU installation kit, P/N 128–
3001–1 P or 128–3001–3 P, is found installed
or if the kit P/N cannot be conclusively
determined during the review required by
paragraph (g) of this AD, within 200 flight
hours or 6 months after the effective date of
this AD, whichever occurs first, replace the
Shinko GCUs with new Lucas Aerospace/
Goodrich GCUs (installation kit P/N 128–
3001–1 P or 128–3001–3 P), in accordance
with the service bulletin.
Installation Kit Found Installed: Inspections
of GCUs and Current Sense Transformers
and Replacement of Transformers as
Applicable
(i) If any GCU installation kit, P/N 128–
3001–1 P or 128–3001–3 P is found installed
during the review required by paragraph (g)
of this AD: Within 200 flight hours or 6
months after the effective date of this AD,
whichever occurs first, inspect to determine
the P/N of both GCUs, in accordance with the
service bulletin; and at the times specified in
Table 2, do the applicable action(s) in that
table.
TABLE 2.—INSPECTION AND REPLACEMENT OF CURRENT SENSE TRANSFORMERS
Then, within 200 flight hours or 6
months after the effective date of
this AD, whichever occurs first
If—
Then—
P/N
Inspect to determine the P/N of
both current sense transformers
on the lower inboard quadrant
of the left-hand and right-hand
engine inlets, in accordance
with the service bulletin.
Both current sense transformers
have P/N 45AS88801–21.
Either current sense transformer
is not identified with P/N
45AS88801–21.
(2) Either GCU does not have P/N
45AS88801–19 or –25.
Replace the GCU with a new
GCU, P/N 45AS88801–19 or
–25, and inspect to determine
the P/N of both current sense
transformers on the lower inboard quadrant of the left-hand
and right-hand engine inlets; in
accordance with the service
bulletin.
Both current sense transformers
have P/N 45AS88801–21.
Either current sense transformer
is not identified with P/N
45AS88801–21.
No further action is required by
this AD.
Within 200 flight hours or 6
months after the effective date
of this AD, whichever occurs
first, replace the current sense
transformer with a new transformer,
P/N 45AS88801–21, in accordance with the service bulletin.
No further action is required by
this AD.
Within 200 flight hours or 6
months after the effective date
of this AD, whichever occurs
first, replace the current sense
transformer with a new transformer,
P/N 45AS88801–21, in accordance with the service bulletin.
If—
mstockstill on PROD1PC68 with PROPOSALS
(1) Both GCUs have
45AS88801–19 or –25.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
VerDate Aug<31>2005
15:37 May 08, 2006
Jkt 208001
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
PO 00000
Issued in Renton, Washington, on April 28,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–7014 Filed 5–8–06; 8:45 am]
BILLING CODE 4910–13–P
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E:\FR\FM\09MYP1.SGM
09MYP1
]]>Agencies
[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Proposed Rules]
[Pages 26877-26879]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-7014]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24694; Directorate Identifier 2006-NM-018-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon (Beech) Model 400 and 400A
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Raytheon (Beech) Model 400 and 400A series airplanes. This
proposed AD would require, among other actions, reviewing the airplane
logbook to determine whether certain generator control unit (GCU)
installation kits are installed, and replacing any incorrect GCU. This
proposed AD results from reports of over-voltage conditions of the
direct current (DC) starter generator. We are proposing this AD to
prevent such over-voltage conditions due to the incompatibility between
certain GCUs, which could result in the loss of normal electrical
power, damage to some electrical components, or blown fuses during
flight, and consequent unrecoverable loss of some or all essential
equipment.
DATES: We must receive comments on this proposed AD by June 23, 2006.
ADDRESSES: Use one of the following addresses 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.
Fax: (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.
Contact Raytheon Aircraft Company, Department 62, P.O. Box 85,
Wichita, Kansas 67201-0085, for the service information identified in
this proposed AD.
FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer,
Electrical Systems and Avionics, ACE-119W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road, room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4139; fax (316)
946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24694; Directorate Identifier 2006-NM-018-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal
[[Page 26878]]
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this proposed
AD. Using the search function of that Web site, anyone can find and
read the comments in 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.). You may review 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.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
We have received reports of over-voltage conditions of the direct
current (DC) starter generator. In one case, over-voltage conditions
resulted in complete loss of the DC electrical power during flight and
loss of the primary flight display. The cause is the incompatibility
between a Goodrich (formerly Lucas Aerospace) DC starter generator and
a Shinko generator control unit (GCU). This condition, if not
corrected, could result in loss of normal electrical power, damage to
some electrical components, or blown fuses during flight, which could
result in the unrecoverable loss of some or all essential equipment.
Relevant Service Information
We have reviewed Raytheon Service Bulletin SB 24-3713, dated
November 2005. The service bulletin describes procedures for reviewing
the airplane logbook to determine whether a certain GCU installation
kit (Lucas Aerospace/Goodrich) is installed and replacing any incorrect
Shinko GCU with a new Lucas Aerospace/Goodrich GCU. For certain
findings, the service bulletin also describes the following procedures,
as applicable:
Inspecting to determine the part number (P/N) of both
GCUs;
Inspecting to determine the P/N of both current sense
transformers on the lower inboard quadrant of the left-hand and right-
hand engine inlets;
Replacing any incorrect GCU with a certain new GCU; and
Replacing any incorrect current sense transformer with a
certain new transformer.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously except as discussed under ``Difference
Between the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
Operators should note that the applicability of this proposed AD
differs from the Effectivity of Raytheon Service Bulletin SB 24-3713.
In addition to airplanes on which Kit No. 128-3004-1 P has been
incorporated, this proposed AD also affects airplanes on which Kit No.
128-3004-3 P has been incorporated. We have determined that those
airplanes also are subject to the identified unsafe condition.
We have coordinated this difference with the airplane manufacturer.
Costs of Compliance
There are about 43 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 40 airplanes of
U.S. registry. The proposed inspection would take about 1 work hour per
airplane, at an average labor rate of $80 per work hour. Based on these
figures, the estimated cost of the proposed AD for U.S. operators is
$3,200, or $80 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this 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.
For the reasons discussed above, I certify that the proposed
regulation:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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 FAA proposes to amend 14 CFR part 39 as follows:
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Raytheon Aircraft Company (Formerly Beech): Docket No. FAA-2006-
24694; Directorate Identifier 2006-NM-018-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 23,
2006.
[[Page 26879]]
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
Raytheon (Beech) model-- Serials-- On which--
----------------------------------------------------------------------------------------------------------------
(1) 400 series airplanes................ RJ-1 through RJ-65 Kit part number (P/N) 128-3004-1 P or 128-
inclusive. 3004-3 P has been incorporated (Lucas
Aerospace/Goodrich Direct Current (DC)
Starter Generator).
(2) 400A series airplanes............... RK-1 through RK-23 Kit P/N 128-3004-1 P or 128-3004-3 P has
inclusive. been incorporated (Lucas Aerospace/
Goodrich DC Starter Generator).
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of over-voltage conditions of
the DC starter generator. We are issuing this AD to prevent over-
voltage conditions of the DC starter generator due to the
incompatibility between certain GCUs, which could result in the loss
of normal electrical power, damage to some electrical components, or
blown fuses during flight, and consequent unrecoverable loss of some
or all essential equipment.
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.
Service Bulletin
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Raytheon Service Bulletin SB 24-3713,
dated November 2005.
Review of Logbook
(g) Within 200 flight hours or 6 months after the effective date
of this AD, whichever occurs first, review the airplane logbook to
determine whether GCU installation kit, P/N 128-3001-1 P or 128-
3001-3 P, is installed, in accordance with the service bulletin.
Installation Kit Not Found Installed: Replacement of Shinko GCU
(h) If no GCU installation kit, P/N 128-3001-1 P or 128-3001-3
P, is found installed or if the kit P/N cannot be conclusively
determined during the review required by paragraph (g) of this AD,
within 200 flight hours or 6 months after the effective date of this
AD, whichever occurs first, replace the Shinko GCUs with new Lucas
Aerospace/Goodrich GCUs (installation kit P/N 128-3001-1 P or 128-
3001-3 P), in accordance with the service bulletin.
Installation Kit Found Installed: Inspections of GCUs and Current Sense
Transformers and Replacement of Transformers as Applicable
(i) If any GCU installation kit, P/N 128-3001-1 P or 128-3001-3
P is found installed during the review required by paragraph (g) of
this AD: Within 200 flight hours or 6 months after the effective
date of this AD, whichever occurs first, inspect to determine the P/
N of both GCUs, in accordance with the service bulletin; and at the
times specified in Table 2, do the applicable action(s) in that
table.
Table 2.--Inspection and Replacement of Current Sense Transformers
----------------------------------------------------------------------------------------------------------------
Then, within 200 flight
hours or 6 months after
If-- the effective date of If-- Then--
this AD, whichever
occurs first
----------------------------------------------------------------------------------------------------------------
(1) Both GCUs have P/N 45AS88801-19 Inspect to determine Both current sense No further action is
or -25. the P/N of both transformers have P/N required by this AD.
current sense 45AS88801-21. Within 200 flight hours
transformers on the Either current sense or 6 months after the
lower inboard quadrant transformer is not effective date of this
of the left-hand and identified with P/N AD, whichever occurs
right-hand engine 45AS88801-21. first, replace the
inlets, in accordance current sense
with the service transformer with a new
bulletin. transformer, P/N
45AS88801-21, in
accordance with the
service bulletin.
(2) Either GCU does not have P/N Replace the GCU with a Both current sense No further action is
45AS88801-19 or -25. new GCU, P/N 45AS88801- transformers have P/N required by this AD.
19 or -25, and inspect 45AS88801-21. Within 200 flight hours
to determine the P/N Either current sense or 6 months after the
of both current sense transformer is not effective date of this
transformers on the identified with P/N AD, whichever occurs
lower inboard quadrant 45AS88801-21. first, replace the
of the left-hand and current sense
right-hand engine transformer with a new
inlets; in accordance transformer, P/N
with the service 45AS88801-21, in
bulletin. accordance with the
service bulletin.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Issued in Renton, Washington, on April 28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-7014 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P
