[Federal Register Volume 73, Number 85 (Thursday, May 1, 2008)]
[Proposed Rules]
[Pages 23988-23990]
From the Federal Register Online via the Government Publishing 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 http://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 http://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 http://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 http://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