Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes, 23988-23990 [E8-9566]

Download as PDF 23988 Federal Register / Vol. 73, No. 85 / Thursday, May 1, 2008 / Proposed Rules including the authority to buy and sell participation interests in such loans;’’ c. Amend paragraph (d) by deleting the semicolon at the end of the sentence and replacing it with the phrase: ‘‘, including the authority to buy and sell participation interests in such loans;’’ d. Redesignate paragraphs (e) through (r) as paragraphs (g) through (t), respectively, and add new paragraphs (e) and (f). e. Under the newly redesignated paragraphs (h), (j) and (l) add new paragraphs (h)(7), (j)(4), and (l)(4) through (l)(6); f. Amend the newly redesignated paragraph (p) by deleting the semicolon at the end of the sentence and replacing it with the phrase: ‘‘, including the authority to buy and sell participation interests in such loans;’’ The revisions read as follows: § 712.5 What activities and services are preapproved for CUSOs? * * * * * (b) * * * (11) Employee leasing services * * * * * (e) Credit card loan origination; (f) Payroll processing services; * * * * * (h) * * * (7) Business counseling and consultant services; * * * * * (j) * * * (4) Real estate settlement services; * * * * * (l) * * * (4) Real estate settlement services; (5) Purchase and servicing of nonperforming loans; and (6) Referral and processing of loan applications for members whose loan applications have been turned down by the credit union; § 712.7 PART 741—REQUIREMENTS FOR INSURANCE 1. The authority citation for part 741 continues to read as follows: Authority: 12 U.S.C. 1757, 1766, 1781– 1790, and 1790d. rfrederick on PROD1PC67 with PROPOSALS 2. Add a new § 741.222 to read as follows: § 741.222 Credit Union Service Organizations. (a) Any credit union that is insured pursuant to Title II of the Act must adhere to the requirements in § 712.3(d)(3) and § 712.4 of this chapter concerning agreements between credit unions and their credit union service Jkt 214001 BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0492; Directorate Identifier 2008–CE–023–AD] RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). 6. Remove and reserve § 712.7. 15:14 Apr 30, 2008 [FR Doc. E8–9457 Filed 4–30–08; 8:45 am] AGENCY: [Removed and Reserved] VerDate Aug<31>2005 organizations (CUSOs) and the requirement to maintain separate corporate identities. For purposes of this section, a CUSO is any entity in which a credit union has an ownership interest or to which a credit union has extended a loan and that is engaged primarily in providing products or services to credit unions or credit union members, or, in the case of checking and currency services, including check cashing services, sale of negotiable checks, money orders, and electronic transaction services, including international and domestic electronic fund transfers, to persons eligible for membership in any credit union having a loan, investment or contract with the entity. (b) This section shall have no preemptive effect with respect to the laws or rules of any state providing for access to CUSO books and records or CUSO examination by credit union regulatory authorities. (c) The effective date for compliance with this section is [INSERT DATE THAT IS 180 DAYS FOLLOWING PUBLICATION OF THE FINAL RULE IN THE FEDERAL REGISTER]. SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (HBC) Model 390 airplanes. This proposed AD would require you to remove the current preformed packing, elbow fitting, and jam nut from the left and right hydraulic pump pressure output port and replace with new parts. This proposed AD would also require you to install a hydraulic pump case drain check valve. This proposed AD results from nine occurrences of hydraulic fluid leaking from the engine hydraulic pump output fitting as a result of an improperly PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 installed elbow connecting the output port to the pulse dampener hose. We are proposing this AD to prevent hydraulic fluid leaks from the left and right hydraulic fluid pump and to prevent the flow of hydraulic fluid into the engine compartment. The loss of hydraulic fluid can result in loss of airplane hydraulic system pressure and the consequent loss of hydraulic system functions including gear extension/ retraction, spoiler functions, and antiskid braking system actuation. The inability of the hydraulic installation to isolate flow of hydraulic fluid could result in a hazardous amount of flammable fluid in the corresponding engine compartment. These conditions, if not corrected, could result in loss of system functions and/or fire in the engine compartment. DATES: We must receive comments on this proposed AD by June 30, 2008. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676–5034; fax: (316) 676–6614. FOR FURTHER INFORMATION CONTACT: Anthony Flores, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4174; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2008–0492; Directorate Identifier 2008–CE–023–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of E:\FR\FM\01MYP1.SGM 01MYP1 23989 Federal Register / Vol. 73, No. 85 / Thursday, May 1, 2008 / Proposed Rules 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:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion We have received information of nine occurrences of hydraulic fluid leaking from the engine hydraulic pump output fitting on HBC Model 390 airplanes. During installation of the elbow fitting, the preformed packing was installed on the fitting threads, which caused the fitting threads to damage the preformed packing when the fitting was tightened. The loss of hydraulic fluid can result in loss of airplane hydraulic system pressure and the consequent loss of hydraulic system functions including gear extension/retraction, spoiler functions, and anti-skid braking system actuation. The current hydraulic system installation lacks the means of shutting off the flow of hydraulic fluid between the left and right engine hydraulic pump case drain return lines. The installation of check valves would allow flow from the hydraulic pump case drain to the reservoir and prevent flow back through the hydraulic pump case drain lines. This installation would reduce the volume of hydraulic fluid loss into the engine compartment in the event of a leak in the left or right engine hydraulic system. The inability of the hydraulic installation to isolate flow of hydraulic fluid could result in a hazardous amount of flammable fluid in the corresponding engine compartment. These conditions, if not corrected, could result in loss of system functions and/or fire in the engine compartment. Relevant Service Information We have reviewed Hawker Beechcraft Mandatory Service Bulletin SB 29–3869, dated January 2008; and Hawker Beechcraft Mandatory Service Bulletin SB 29–3851, dated January 2008. The service information describes procedures for: Labor cost • Removing the current preformed packing, elbow fitting, and jam nut from the left and right hydraulic pump pressure output port and replacing with new parts; and • Installing a hydraulic pump case drain check valve. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would require you to remove the current preformed packing, elbow fitting, and jam nut from the left and right hydraulic pump pressure output port and replace with new parts. This proposed AD would also require you to install a hydraulic pump case drain check valve. Costs of Compliance We estimate that this proposed AD would affect 182 airplanes in the U.S. registry. We estimate the following costs to do the proposed modifications: Parts cost Hydraulic pressure output fitting assembly: 8 work-hours × $80 per hour = $640 ..................... Hydraulic Pump Case Drain Check Valve: 16 work-hours × $80 per hour = $1,280 ................. rfrederick on PROD1PC67 with PROPOSALS HBC will provide warranty credit as specified in Hawker Beechcraft Mandatory Service Bulletin SB 29–3869, dated January 2008; and Hawker Beechcraft Mandatory Service Bulletin SB 29–3851, dated January 2008. 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. VerDate Aug<31>2005 15:14 Apr 30, 2008 Jkt 214001 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. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 $100 4,353 Total cost per airplane Total cost on U.S. operators $740 5,633 $134,680 1,025,206 regulatory evaluation, any comments received, and other information on the Internet at https://www.regulations.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) 647–5527) 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, 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. E:\FR\FM\01MYP1.SGM 01MYP1 23990 § 39.13 Federal Register / Vol. 73, No. 85 / Thursday, May 1, 2008 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Hawker Beechcraft Corporation: Docket No. FAA–2008–0492; Directorate Identifier 2008–CE–023–AD. Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by June 30, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Model 390 airplanes, serial numbers RB–4 through RB–224, that are certificated in any category. Unsafe Condition (d) This AD results from nine occurrences of hydraulic fluid leaking from the engine hydraulic pump output fitting as a result of an improperly installed elbow connecting the output port to the pulse dampener hose. We are issuing this AD to prevent hydraulic fluid leaking from the left and right hydraulic fluid pump and to prevent the flow of hydraulic fluid into the engine compartment. The loss of hydraulic fluid can result in loss of airplane hydraulic system pressure and the consequent loss of hydraulic system functions including gear extension/ retraction, spoiler functions, and anti-skid braking system actuation. The inability of the hydraulic installation to isolate flow of hydraulic fluid could result in a hazardous amount of flammable fluid in the corresponding engine compartment. These conditions, if not corrected, could result in loss of system functions and/or fire in the engine compartment. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Remove current preformed packing (part number (P/N) MS28778–6), elbow fitting (P/N MS21908J6), and jam nut (P/N AN924–6J) from the left and right hydraulic pump pressure output port and install new preformed packing (P/N MS28778–6), union (P/N MS21902J6), and swivel fitting (P/N NAS1762J0606) in the left and right hydraulic pressure pump output port. (2) Install hydraulic pump case drain check valve Kit No. 390–5803–0001. Within the next 200 hours time-in-service (TIS) after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first. Follow Hawker Beechcraft Mandatory Service Bulletin SB 29–3869, dated January 2008. Within the next 200 hours TIS after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first. Hawker Beechcraft Mandatory Service Bulletin SB 29–3851, dated January 2008. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Anthony Flores, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4174; fax: (316) 946–4107. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Federal Aviation Administration Related Information rfrederick on PROD1PC67 with PROPOSALS (g) To get copies of the service information referenced in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676– 5034; fax: (316) 676–6614. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12– 140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at https://www.regulations.gov. Issued in Kansas City, Missouri, on April 24, 2008. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–9566 Filed 4–30–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:14 Apr 30, 2008 Jkt 214001 14 CFR Part 39 [Docket No. FAA–2008–0178; Directorate Identifier 2007–NM–366–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: We are revising an earlier NPRM for the products listed above. This action revises the earlier NPRM by expanding the scope. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [inspections of various fuel system components such as shields, harnesses, sleeves, and sealant] are required PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by May 21, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The E:\FR\FM\01MYP1.SGM 01MYP1

Agencies

[Federal Register Volume 73, Number 85 (Thursday, May 1, 2008)]
[Proposed Rules]
[Pages 23988-23990]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-9566]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0492; Directorate Identifier 2008-CE-023-AD]
RIN 2120-AA64


Airworthiness Directives; Hawker Beechcraft Corporation Model 390 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Hawker Beechcraft Corporation (HBC) Model 390 airplanes. This 
proposed AD would require you to remove the current preformed packing, 
elbow fitting, and jam nut from the left and right hydraulic pump 
pressure output port and replace with new parts. This proposed AD would 
also require you to install a hydraulic pump case drain check valve. 
This proposed AD results from nine occurrences of hydraulic fluid 
leaking from the engine hydraulic pump output fitting as a result of an 
improperly installed elbow connecting the output port to the pulse 
dampener hose. We are proposing this AD to prevent hydraulic fluid 
leaks from the left and right hydraulic fluid pump and to prevent the 
flow of hydraulic fluid into the engine compartment. The loss of 
hydraulic fluid can result in loss of airplane hydraulic system 
pressure and the consequent loss of hydraulic system functions 
including gear extension/retraction, spoiler functions, and anti-skid 
braking system actuation. The inability of the hydraulic installation 
to isolate flow of hydraulic fluid could result in a hazardous amount 
of flammable fluid in the corresponding engine compartment. These 
conditions, if not corrected, could result in loss of system functions 
and/or fire in the engine compartment.

DATES: We must receive comments on this proposed AD by June 30, 2008.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 
67201; telephone: (316) 676-5034; fax: (316) 676-6614.

FOR FURTHER INFORMATION CONTACT: Anthony Flores, Aerospace Engineer, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4174; fax: (316) 946-4107.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2008-0492; Directorate Identifier 2008-CE-023-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of

[[Page 23989]]

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://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    We have received information of nine occurrences of hydraulic fluid 
leaking from the engine hydraulic pump output fitting on HBC Model 390 
airplanes. During installation of the elbow fitting, the preformed 
packing was installed on the fitting threads, which caused the fitting 
threads to damage the preformed packing when the fitting was tightened. 
The loss of hydraulic fluid can result in loss of airplane hydraulic 
system pressure and the consequent loss of hydraulic system functions 
including gear extension/retraction, spoiler functions, and anti-skid 
braking system actuation.
    The current hydraulic system installation lacks the means of 
shutting off the flow of hydraulic fluid between the left and right 
engine hydraulic pump case drain return lines. The installation of 
check valves would allow flow from the hydraulic pump case drain to the 
reservoir and prevent flow back through the hydraulic pump case drain 
lines. This installation would reduce the volume of hydraulic fluid 
loss into the engine compartment in the event of a leak in the left or 
right engine hydraulic system. The inability of the hydraulic 
installation to isolate flow of hydraulic fluid could result in a 
hazardous amount of flammable fluid in the corresponding engine 
compartment.
    These conditions, if not corrected, could result in loss of system 
functions and/or fire in the engine compartment.

Relevant Service Information

    We have reviewed Hawker Beechcraft Mandatory Service Bulletin SB 
29-3869, dated January 2008; and Hawker Beechcraft Mandatory Service 
Bulletin SB 29-3851, dated January 2008.
    The service information describes procedures for:
     Removing the current preformed packing, elbow fitting, and 
jam nut from the left and right hydraulic pump pressure output port and 
replacing with new parts; and
     Installing a hydraulic pump case drain check valve.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would require you to remove the current preformed packing, elbow 
fitting, and jam nut from the left and right hydraulic pump pressure 
output port and replace with new parts. This proposed AD would also 
require you to install a hydraulic pump case drain check valve.

Costs of Compliance

    We estimate that this proposed AD would affect 182 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed modifications:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                           Labor cost                               Parts cost       airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Hydraulic pressure output fitting assembly: 8 work-hours x $80              $100            $740        $134,680
 per hour = $640................................................
Hydraulic Pump Case Drain Check Valve: 16 work-hours x $80 per             4,353           5,633       1,025,206
 hour = $1,280..................................................
----------------------------------------------------------------------------------------------------------------

    HBC will provide warranty credit as specified in Hawker Beechcraft 
Mandatory Service Bulletin SB 29-3869, dated January 2008; and Hawker 
Beechcraft Mandatory Service Bulletin SB 29-3851, dated January 2008.

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.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at https://www.regulations.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) 647-5527) 
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, 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.

[[Page 23990]]

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Hawker Beechcraft Corporation: Docket No. FAA-2008-0492; Directorate 
Identifier 2008-CE-023-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 30, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 390 airplanes, serial numbers RB-4 
through RB-224, that are certificated in any category.

Unsafe Condition

    (d) This AD results from nine occurrences of hydraulic fluid 
leaking from the engine hydraulic pump output fitting as a result of 
an improperly installed elbow connecting the output port to the 
pulse dampener hose. We are issuing this AD to prevent hydraulic 
fluid leaking from the left and right hydraulic fluid pump and to 
prevent the flow of hydraulic fluid into the engine compartment. The 
loss of hydraulic fluid can result in loss of airplane hydraulic 
system pressure and the consequent loss of hydraulic system 
functions including gear extension/retraction, spoiler functions, 
and anti-skid braking system actuation. The inability of the 
hydraulic installation to isolate flow of hydraulic fluid could 
result in a hazardous amount of flammable fluid in the corresponding 
engine compartment. These conditions, if not corrected, could result 
in loss of system functions and/or fire in the engine compartment.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Remove current preformed  Within the next 200   Follow Hawker
 packing (part number (P/N)    hours time-in-        Beechcraft
 MS28778-6), elbow fitting     service (TIS) after   Mandatory Service
 (P/N MS21908J6), and jam      the effective date    Bulletin SB 29-
 nut (P/N AN924-6J) from the   of this AD or         3869, dated January
 left and right hydraulic      within the next 6     2008.
 pump pressure output port     months after the
 and install new preformed     effective date of
 packing (P/N MS28778-6),      this AD, whichever
 union (P/N MS21902J6), and    occurs first.
 swivel fitting (P/N
 NAS1762J0606) in the left
 and right hydraulic
 pressure pump output port.
(2) Install hydraulic pump    Within the next 200   Hawker Beechcraft
 case drain check valve Kit    hours TIS after the   Mandatory Service
 No. 390-5803-0001.            effective date of     Bulletin SB 29-
                               this AD or within     3851, dated January
                               the next 6 months     2008.
                               after the effective
                               date of this AD,
                               whichever occurs
                               first.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Anthony Flores, Aerospace Engineer, Wichita ACO, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4174; 
fax: (316) 946-4107. Before using any approved AMOC on any airplane 
to which the AMOC applies, notify your appropriate principal 
inspector (PI) in the FAA Flight Standards District Office (FSDO), 
or lacking a PI, your local FSDO.

Related Information

    (g) To get copies of the service information referenced in this 
AD, contact Hawker Beechcraft Corporation, 9709 East Central, 
Wichita, Kansas 67201; telephone: (316) 676-5034; fax: (316) 676-
6614. To view the AD docket, go to U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or 
on the Internet at https://www.regulations.gov.

    Issued in Kansas City, Missouri, on April 24, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-9566 Filed 4-30-08; 8:45 am]
BILLING CODE 4910-13-P
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