Airworthiness Directives; Raytheon Aircraft Company Model 390 Airplanes, 78051-78053 [E6-22382]
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Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Rules and Regulations
or other institution in excess of that
member’s or other institution’s
minimum investment in capital stock
required under the Bank’s capital plan,
the Act, or the Finance Board’s
regulations, as applicable.
*
*
*
*
*
PART 917—POWERS AND
RESPONSIBILITIES OF BANK
BOARDS OF DIRECTORS AND
SENIOR MANAGEMENT
7. The authority citation for part 930
is revised to read as follows:
Authority: 12 U.S.C. 1422a(a)(3), 1422b(a),
1426, 1436(a), 1440, 1443, and 1446.
3. The authority citation for part 917
continues to read as follows:
§ 930.1
Authority: 12 U.S.C. 1422a(a)(3),
1422b(a)(1), 1426, 1427, 1432(a), 1436(a), and
1440.
4. Revise § 917.9 to read as follows:
§ 917.9
Dividends.
(a) A Bank’s board of directors may
declare and pay a dividend only from
previously retained earnings or current
net earnings and only in accordance
with any other applicable limitations on
dividends set forth in the Act or this
chapter. Dividends on such capital stock
shall be computed without preference.
(b) A Bank’s board of directors may
not declare or pay a dividend based on
projected or anticipated earnings and
may not declare or pay a dividend if the
par value of the Bank’s stock is impaired
or is projected to become impaired after
paying such dividend.
(c) The requirement in paragraph (a)
of this section that dividends be
computed without preference shall
cease to apply to any Bank that has
established any dividend preferences for
1 or more classes or subclasses of its
capital stock as part of its approved
capital plan, as of the date on which the
capital plan takes effect.
PART 925—MEMBERS OF THE BANKS
5. The authority citation for part 925
continues to read as follows:
I
Authority: 12 U.S.C. 1422, 1422a, 1422b,
1423, 1424, 1426, 1430, and 1442.
I
6. Revise § 925.23 to read as follows:
cprice-sewell on PROD1PC66 with RULES
§ 925.23
Excess stock.
(a) Sale of excess stock. Subject to the
restriction in paragraph (b) of this
section, a member may purchase excess
stock as long as the purchase is
approved by the member’s Bank and is
permitted by the laws under which the
member operates.
(b) Restriction. Any Bank with excess
stock greater than 1 percent of its total
assets shall not declare or pay any
dividends in the form of additional
shares of Bank stock or otherwise issue
any excess stock. A Bank shall not issue
VerDate Aug<31>2005
15:10 Dec 27, 2006
Jkt 211001
PART 930—DEFINITIONS APPLYING
TO RISK MANAGEMENT AND CAPITAL
REGULATIONS
I
I
I
excess stock, as a dividend or otherwise,
if after the issuance, the outstanding
excess stock at the Bank would be
greater than 1 percent of its total assets.
[Amended]
8. Amend § 930.1 by removing the
definition of the term ‘‘excess stock’’.
I
Dated: December 22, 2006.
By the Board of Directors of the Federal
Housing Finance Board.
Ronald A. Rosenfeld,
Chairman.
[FR Doc. E6–22325 Filed 12–27–06; 8:45 am]
BILLING CODE 6725–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25745; Directorate
Identifier 2006–CE–47–AD; Amendment 39–
14866; AD 2006–26–08]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company Model 390 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede AD 2006–02–51, which
applies to certain Raytheon Aircraft
Company Model 390 airplanes. AD
2006–02–51 currently requires you to
inspect the left engine hydraulic pump
outlet tube and the clamp; replace the
clamp at each inspection; replace the
hydraulic pump outlet tube
immediately if any problem is found;
and report the results of each inspection
or replacement to the FAA. This AD is
the result of several hydraulic pump
outlet tube failures after issuance of AD
2006–02–51, including failures on the
right engine. This AD requires you to
visually inspect the hydraulic pump
outlet tube on both engines on a
recurring basis and immediately replace
the tube if damage is found. This AD
also requires incorporation of an
Airplane Flight Manual (AFM) change
to not allow operation of an engine with
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
78051
its associated firewall hydraulic shutoff
valve closed. In addition, this AD
requires you to replace the hydraulic
pump outlet tube if an engine is
operated with its firewall hydraulic
shutoff valve closed. We are issuing this
AD to prevent failure of the hydraulic
pump outlet tube and consequent
leaking of hydraulic fluid. Such leakage
could result in a fire. There is also a risk
of loss of hydraulic system functions
including normal gear extensions, speed
brakes, roll spoilers, lift dump, and
normal brakes.
DATES: This AD becomes effective on
December 28, 2006.
The Director of the Federal Register
previously approved the incorporation
by reference of the documents listed in
this AD on February 2, 2006 (71 FR
5581, February 2, 2006).
We must receive any comments on
this AD by February 26, 2007.
ADDRESSES: Use one of the following
addresses to comment on this 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–
0001.
• 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.
To get the service information
identified in this AD, contact Raytheon
Aircraft Company, P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800)
625–7043.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2006–25745;
Directorate Identifier 2006-CE–47–AD.
FOR FURTHER INFORMATION CONTACT:
James P. Galstad, Propulsion Aerospace
Engineer, ACE 116W, Wichita Aircraft
Certification Office, 1801 Airport Road,
Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4135; fax: (316)
946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
Reports of four failures of the lefthand engine hydraulic pump outlet tube
on Raytheon Model 390 airplanes
caused us to issue AD 2006–02–51,
Amendment 39–14459 (71 FR 5581,
E:\FR\FM\28DER1.SGM
28DER1
78052
Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Rules and Regulations
February 2, 2006). AD 2006–02–51
currently requires you to do the
following:
• Inspect the hydraulic pump outlet
tube on the left engine;
• replace the clamp at each
inspection;
• replace the hydraulic pump outlet
tube immediately if any of the problems
identified in the service bulletin are
found; and
• report the results of each inspection
or replacement to the FAA.
Since issuing AD 2006–02–51, we
have received additional reports of
failures of the hydraulic pump outlet
tube, including failures on the right
engine. Since failures continue to occur
and are no longer limited to the left
engine hydraulic pump outlet tube, the
repetitive inspection interval of 50
hours time-in-service (TIS) required by
AD 2006–02–51 and procedures in AD
2006–02–51 to only inspect the left
hydraulic pump outlet tube do not
adequately address the unsafe
condition.
Failure of these hydraulic pump
outlet tubes, if not prevented, could
cause flammable fluid leakage in the
engine nacelle. Such leakage could
result in a fire. There is also a risk of
loss of hydraulic system functions
including normal gear extensions, speed
brakes, roll spoilers, lift dump, and
normal brakes.
cprice-sewell on PROD1PC66 with RULES
Relevant Service Information
Raytheon Mandatory Service Bulletin
No. SB 29–3771, dated January, 2006;
and Raytheon Safety Communique No.
267, dated January 2006, included in
AD 2006–02–51 will be retained for this
AD.
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
evaluated all the information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This AD supersedes AD
2006–02–51 and requires the following
on Raytheon Model 390 airplanes:
• Repetitive visual inspections of the
hydraulic pump outlet tube on both
engines;
• replacement of the hydraulic pump
outlet tube clamp on the left-hand
engine at each inspection;
• immediate replacement of the
hydraulic pump outlet tube if damage is
found;
• incorporation of a revision to the
Airplane Flight Manual (AFM) to not
allow operation of an engine with its
firewall hydraulic shutoff valve closed;
and
VerDate Aug<31>2005
15:10 Dec 27, 2006
Jkt 211001
• replacement of the hydraulic pump
outlet tube if an engine is operated with
the firewall hydraulic shutoff valve
closed.
This AD is considered interim action.
The FAA is working with the type
certificate holder on developing a
design change for these hydraulic pump
outlet tubes. The FAA will take future
rulemaking action to address this unsafe
condition for the long-term.
In preparing this rule, we contacted
type clubs and aircraft operators to get
technical information and information
on operational and economic impacts.
We did not receive any information
through these contacts. If received, we
would have included a discussion of
any information that may have
influenced this action in the rulemaking
docket.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and an
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments regarding this
AD. Send your comments to an address
listed under the ADDRESSES section.
Include the docket number ‘‘FAA–
2006–25745; Directorate Identifier
2006–CE–47–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the AD in light of those
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 we receive
concerning this AD.
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.
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
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 determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the AD, the regulatory
evaluation, any comments received, and
other information on the Internet at
https://dms.dot.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone (800) 647–
5227) is located at the street address
stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
E:\FR\FM\28DER1.SGM
28DER1
Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Rules and Regulations
2006–26–08 Raytheon Aircraft Company:
Amendment 39–14866; Docket No.
FAA–2006–25745; Directorate Identifier
2006–CE–47–AD.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Effective Date
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
(a) This AD becomes effective on December
28, 2006.
Affected ADs
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2006–02–51, Amendment 39–14459 (71
FR 5581, February 2, 2006), and by
adding a new AD to read as follows:
I
(b) This AD supersedes AD 2006–02–51;
Amendment 39–14459.
Applicability
(c) This AD applies to Model 390 airplanes,
all serial numbers, that are certificated in any
category:
78053
Unsafe Condition
(d) This AD is the result of several
hydraulic pump outlet tube failures after
issuance of AD 2006–02–51. We are issuing
this AD to prevent failure of the hydraulic
pump outlet tubes and consequent leaking of
hydraulic fluid. Such leakage could result in
a fire. There is also a risk of loss of hydraulic
system functions including normal gear
extensions, speed brakes, roll spoilers, lift
dump, and normal brakes.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Visually inspect the hydraulic pump outlet
tube for evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid
leakage, as follows:
(i) For the left-hand (LH) engine: Remove the
clamp, perform the inspection, and replace
the clamp with a new one as specified in
Raytheon Mandatory Service Bulletin No. SB
29–3771 after each inspection
(ii) For the right-hand (RH) engine: Perform the
inspection. Removal and replacement of the
clamps are not necessary
Initially at whichever of the following occurs
first and thereafter at intervals not to exceed 25 hours time-in-service (TIS):
(A) Within the next 25 hours TIS after December 28, 2006 (the effective date of this AD);
or
(B) At the next inspection required by AD
2006–02–51
Inspect following Raytheon Safety Communique No. 267, dated January 2006.
Raytheon Safety Communique No. 267,
dated January 2006, addresses the LH engine. Use the same inspection procedures
for the RH engine hydraulic pump outlet
tube (P/N 390–580037). Remove and replace the clamp (LH only) following
Raytheon Mandatory Service Bulletin No.
SB 29–3771, dated January 2006.
(2) Replace the hydraulic pump outlet tube,
Part Number (P/N) 390–580035 (or FAA-approved equivalent) for the LH engine or P/N
390–580037 (or FAA-approved equivalent)
for the RH engine.
Each and every time any of the following occurs:
(i) Prior to further flight after any inspection
from paragraph (e)(1) of this AD where evidence of chafing, excessive vibration, wear,
deterioration, or hydraulic fluid leakage is
found; and
(ii) Within 1 hour TIS following identification of
an intended or unintended engine operation
with the hydraulic valve closed.
Raytheon Aircraft Premier 1 Model 390 Maintenance Manual, P/N 390–590001–0015.
(3) Incorporate Raytheon Aircraft Company Part
Number 390–590001–0003C3TC6, dated
September 16, 2006 into the Airplane Flight
Manual (AFM).
Within 5 days after December 28, 2006 (the
effective date of this AD)
The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations
(14 CFR 43.7) may do the AFM changes
requirement of this AD. Make an entry into
the aircraft records showing compliance
with this portion of the AD in accordance
with section 43.9 of the Federal Aviation
Regulations (14 CFR 43.9).
Alternative Methods of Compliance
(AMOCs)
cprice-sewell on PROD1PC66 with RULES
(f) The Manager, Wichita Aircraft
Certification Office, FAA, ATTN: James P.
Galstad, Propulsion Aerospace Engineer,
ACE 116W, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946–
4135; fax: (316) 946–4107, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(g) You must use Raytheon Mandatory
Service Bulletin No. SB 29–3771, dated
January 2006; and Raytheon Safety
VerDate Aug<31>2005
15:10 Dec 27, 2006
Jkt 211001
Communique No. 267, dated January 2006, to
do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
previously approved this incorporation by
reference under 5 U.S.C. 552(a) and 1 CFR
part 51 on February 2, 2006 (71 FR 5581,
February 2, 2006).
(2) For service information identified in
this AD, contact Raytheon Aircraft Company,
P.O. Box 85, Wichita, Kansas 67201–0085;
telephone: (800) 625–7043.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
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Fmt 4700
Sfmt 4700
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, Missouri, on
December 22, 2006.
Kim Smith,
Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E6–22382 Filed 12–27–06; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\28DER1.SGM
28DER1
]]>Agencies
[Federal Register Volume 71, Number 249 (Thursday, December 28, 2006)]
[Rules and Regulations]
[Pages 78051-78053]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-22382]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25745; Directorate Identifier 2006-CE-47-AD;
Amendment 39-14866; AD 2006-26-08]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Model 390
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede AD 2006-02-51, which applies to certain Raytheon Aircraft
Company Model 390 airplanes. AD 2006-02-51 currently requires you to
inspect the left engine hydraulic pump outlet tube and the clamp;
replace the clamp at each inspection; replace the hydraulic pump outlet
tube immediately if any problem is found; and report the results of
each inspection or replacement to the FAA. This AD is the result of
several hydraulic pump outlet tube failures after issuance of AD 2006-
02-51, including failures on the right engine. This AD requires you to
visually inspect the hydraulic pump outlet tube on both engines on a
recurring basis and immediately replace the tube if damage is found.
This AD also requires incorporation of an Airplane Flight Manual (AFM)
change to not allow operation of an engine with its associated firewall
hydraulic shutoff valve closed. In addition, this AD requires you to
replace the hydraulic pump outlet tube if an engine is operated with
its firewall hydraulic shutoff valve closed. We are issuing this AD to
prevent failure of the hydraulic pump outlet tube and consequent
leaking of hydraulic fluid. Such leakage could result in a fire. There
is also a risk of loss of hydraulic system functions including normal
gear extensions, speed brakes, roll spoilers, lift dump, and normal
brakes.
DATES: This AD becomes effective on December 28, 2006.
The Director of the Federal Register previously approved the
incorporation by reference of the documents listed in this AD on
February 2, 2006 (71 FR 5581, February 2, 2006).
We must receive any comments on this AD by February 26, 2007.
ADDRESSES: Use one of the following addresses to comment on this 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 20590-0001.
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.
To get the service information identified in this AD, contact
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone: (800) 625-7043.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2006-25745; Directorate Identifier 2006-CE-47-AD.
FOR FURTHER INFORMATION CONTACT: James P. Galstad, Propulsion Aerospace
Engineer, ACE 116W, Wichita Aircraft Certification Office, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4135; fax:
(316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
Reports of four failures of the left-hand engine hydraulic pump
outlet tube on Raytheon Model 390 airplanes caused us to issue AD 2006-
02-51, Amendment 39-14459 (71 FR 5581,
[[Page 78052]]
February 2, 2006). AD 2006-02-51 currently requires you to do the
following:
Inspect the hydraulic pump outlet tube on the left engine;
replace the clamp at each inspection;
replace the hydraulic pump outlet tube immediately if any
of the problems identified in the service bulletin are found; and
report the results of each inspection or replacement to
the FAA.
Since issuing AD 2006-02-51, we have received additional reports of
failures of the hydraulic pump outlet tube, including failures on the
right engine. Since failures continue to occur and are no longer
limited to the left engine hydraulic pump outlet tube, the repetitive
inspection interval of 50 hours time-in-service (TIS) required by AD
2006-02-51 and procedures in AD 2006-02-51 to only inspect the left
hydraulic pump outlet tube do not adequately address the unsafe
condition.
Failure of these hydraulic pump outlet tubes, if not prevented,
could cause flammable fluid leakage in the engine nacelle. Such leakage
could result in a fire. There is also a risk of loss of hydraulic
system functions including normal gear extensions, speed brakes, roll
spoilers, lift dump, and normal brakes.
Relevant Service Information
Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January,
2006; and Raytheon Safety Communique No. 267, dated January 2006,
included in AD 2006-02-51 will be retained for this AD.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD
supersedes AD 2006-02-51 and requires the following on Raytheon Model
390 airplanes:
Repetitive visual inspections of the hydraulic pump outlet
tube on both engines;
replacement of the hydraulic pump outlet tube clamp on the
left-hand engine at each inspection;
immediate replacement of the hydraulic pump outlet tube if
damage is found;
incorporation of a revision to the Airplane Flight Manual
(AFM) to not allow operation of an engine with its firewall hydraulic
shutoff valve closed; and
replacement of the hydraulic pump outlet tube if an engine
is operated with the firewall hydraulic shutoff valve closed.
This AD is considered interim action. The FAA is working with the
type certificate holder on developing a design change for these
hydraulic pump outlet tubes. The FAA will take future rulemaking action
to address this unsafe condition for the long-term.
In preparing this rule, we contacted type clubs and aircraft
operators to get technical information and information on operational
and economic impacts. We did not receive any information through these
contacts. If received, we would have included a discussion of any
information that may have influenced this action in the rulemaking
docket.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2006-
25745; Directorate Identifier 2006-CE-47-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those 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 we
receive concerning this AD.
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 determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at https://dms.dot.gov; or in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located at the street address stated in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
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 FAA amends 14 CFR part 39 as follows:
[[Page 78053]]
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2006-02-51, Amendment 39-14459 (71 FR 5581, February 2, 2006), and by
adding a new AD to read as follows:
2006-26-08 Raytheon Aircraft Company: Amendment 39-14866; Docket No.
FAA-2006-25745; Directorate Identifier 2006-CE-47-AD.
Effective Date
(a) This AD becomes effective on December 28, 2006.
Affected ADs
(b) This AD supersedes AD 2006-02-51; Amendment 39-14459.
Applicability
(c) This AD applies to Model 390 airplanes, all serial numbers,
that are certificated in any category:
Unsafe Condition
(d) This AD is the result of several hydraulic pump outlet tube
failures after issuance of AD 2006-02-51. We are issuing this AD to
prevent failure of the hydraulic pump outlet tubes and consequent
leaking of hydraulic fluid. Such leakage could result in a fire.
There is also a risk of loss of hydraulic system functions including
normal gear extensions, speed brakes, roll spoilers, lift dump, and
normal brakes.
Compliance
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Visually inspect the Initially at Inspect following
hydraulic pump outlet tube whichever of the Raytheon Safety
for evidence of chafing, following occurs Communique No. 267,
excessive vibration, wear, first and dated January 2006.
deterioration, or hydraulic thereafter at Raytheon Safety
fluid leakage, as follows: intervals not to Communique No. 267,
(i) For the left-hand (LH) exceed 25 hours dated January 2006,
engine: Remove the clamp, time-in-service addresses the LH
perform the inspection, and (TIS): engine. Use the
replace the clamp with a (A) Within the next same inspection
new one as specified in 25 hours TIS after procedures for the
Raytheon Mandatory Service December 28, 2006 RH engine hydraulic
Bulletin No. SB 29-3771 (the effective date pump outlet tube (P/
after each inspection of this AD); or. N 390-580037).
(ii) For the right-hand (RH) (B) At the next Remove and replace
engine: Perform the inspection required the clamp (LH only)
inspection. Removal and by AD 2006-02-51. following Raytheon
replacement of the clamps Mandatory Service
are not necessary Bulletin No. SB 29-
3771, dated January
2006.
------------------------------------------------------------------------
(2) Replace the hydraulic Each and every time Raytheon Aircraft
pump outlet tube, Part any of the Premier 1 Model 390
Number (P/N) 390-580035 (or following occurs: Maintenance Manual,
FAA-approved equivalent) (i) Prior to further P/N 390-590001-
for the LH engine or P/N flight after any 0015.
390-580037 (or FAA-approved inspection from
equivalent) for the RH paragraph (e)(1) of
engine. this AD where
evidence of
chafing, excessive
vibration, wear,
deterioration, or
hydraulic fluid
leakage is found;
and.
(ii) Within 1 hour
TIS following
identification of
an intended or
unintended engine
operation with the
hydraulic valve
closed..
------------------------------------------------------------------------
(3) Incorporate Raytheon Within 5 days after The owner/operator
Aircraft Company Part December 28, 2006 holding at least a
Number 390-590001- (the effective date private pilot
0003C3TC6, dated September of this AD) certificate as
16, 2006 into the Airplane authorized by
Flight Manual (AFM). section 43.7 of the
Federal Aviation
Regulations (14 CFR
43.7) may do the
AFM changes
requirement of this
AD. Make an entry
into the aircraft
records showing
compliance with
this portion of the
AD in accordance
with section 43.9
of the Federal
Aviation
Regulations (14 CFR
43.9).
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office, FAA,
ATTN: James P. Galstad, Propulsion Aerospace Engineer, ACE 116W,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4135; fax: (316) 946-
4107, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(g) You must use Raytheon Mandatory Service Bulletin No. SB 29-
3771, dated January 2006; and Raytheon Safety Communique No. 267,
dated January 2006, to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register previously approved
this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part
51 on February 2, 2006 (71 FR 5581, February 2, 2006).
(2) For service information identified in this AD, contact
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone: (800) 625-7043.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on December 22, 2006.
Kim Smith,
Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E6-22382 Filed 12-27-06; 8:45 am]
BILLING CODE 4910-13-P
