FR Doc E8-9566

[Federal Register: May 1, 2008 (Volume 73, Number 85)]
[Proposed Rules]
[Page 23988-23990]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01my08-14]

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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).

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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:

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Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
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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..................................................
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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

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:

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Actions Compliance Procedures
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(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.
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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]

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