[Federal Register Volume 69, Number 207 (Wednesday, October 27, 2004)]
[Rules and Regulations]
[Pages 62570-62571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-23926]



[[Page 62570]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18660; Directorate Identifier 2003-NM-161-AD; 
Amendment 39-13830; AD 2004-22-02]
RIN 2120-AA64


Airworthiness Directives; Raytheon (Beech) Model MU-300-10, 400, 
400A, and 400T Series Airplanes; and Raytheon (Mitsubishi) Model Beech 
MU-300 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Raytheon (Beech) Model MU-300-10, 400, 400A, and 400T series 
airplanes; and certain Raytheon (Mitsubishi) Model Beech MU-300 
airplanes. This AD requires a one-time inspection of certain panels in 
the spoiler mixer bay for the presence of drain holes, and the addition 
of at least one new drain hole; and a one-time inspection for 
discrepancies of the sealant on the relief cutout on the aft pressure 
bulkhead, and on certain baffles; and corrective actions if necessary. 
This AD is prompted by a report of fuel leaking from components in the 
spoiler mixer bay of several Raytheon (Beech) Model 400A series 
airplanes. We are issuing this AD to prevent the accumulation of fuel 
and/or fuel vapor in the spoiler mixer bay and/or the aft fuselage 
compartment, which could result in a fire in the airplane.

DATES: This AD becomes effective December 1, 2004.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of 
December 1, 2004.

ADDRESSES: For service information identified in this AD, contact 
Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 
67201-0085. You can examine this information 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW, room PL-401, 
on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:
    Technical information: Jeff Pretz, Aerospace Engineer, Airframe 
Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 1801 
Airport Road, Propulsion 100, Mid-Continent Airport, Wichita, Kansas 
67209; telephone (316) 946-4153; fax (316) 946-4107.
    Plain language information: Marcia Walters, <a href="/cdn-cgi/l/email-protection#2e434f5c4d474f00594f425a4b5c5d6e484f4f00494158"><span class="__cf_email__" data-cfemail="b1dcd0c3d2d8d09fc6d0ddc5d4c3c2f1d7d0d09fd6dec7">[email protected]</span></a>.

Examining the Docket

    The AD docket contains the proposed AD, comments, and any final 
disposition. You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with an AD for certain Raytheon (Beech) Model MU-300-10, 400, 400A, and 
400T series airplanes; and certain Raytheon (Mitsubishi) Model Beech 
MU-300 airplanes. The proposed AD was published in the Federal Register 
on July 22, 2004 (69 FR 43783), to require a one-time inspection of 
certain panels in the spoiler mixer bay for the presence of drain 
holes, and the addition of at least one new drain hole; and a one-time 
inspection for discrepancies of the sealant on the relief cutout on the 
aft pressure bulkhead, and on certain baffles; and corrective actions 
if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Clarification of Requirements in Paragraph (f) of the Final Rule

    In paragraph (f) of the proposed AD we inadvertently referenced 
paragraphs (a)(1) and (a)(2) of the proposed AD; this is a 
typographical error. It was our intent to reference paragraphs (f)(1) 
and (f)(2). Paragraph (a) only references the comment due date and does 
not contain subparagraphs (1) and (2). Paragraph (f) of this final rule 
has been changed to correctly reference paragraphs (f)(1) and (f)(2) of 
this AD.

Costs of Compliance

    This AD will affect about 673 airplanes worldwide. The following 
table provides the estimated costs for U.S. operators to comply with 
this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                               Average                                    Number of
                                      Work      labor                          Cost per     U.S.
              Action                 hours     rate per         Parts          airplane  registered   Fleet cost
                                                 hour                                     airplanes
----------------------------------------------------------------------------------------------------------------
Inspections......................          1        $65  None...............        $65         610      $39,650
Drilling one drain hole..........          3         65  None...............        195         610      118,950
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Regulatory Findings

    We have 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

[[Page 62571]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:

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 adding the following new airworthiness 
directive:

2004-22-02 Raytheon Aircraft Company (Formerly Beech): Amendment 39-
13830. Docket No. FAA-2004-18660; Directorate Identifier 2003-NM-
161-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
1, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Raytheon (Beech) Model MU-300-10, 400, 
400A, and 400T series airplanes; and Raytheon (Mitsubishi) Model 
Beech MU-300 airplanes; certificated in any category; as listed in 
Raytheon Service Bulletin SB 53-3486, dated June, 2003.

Unsafe Condition

    (d) This AD was prompted by a report of fuel leaking from 
components in the spoiler mixer bay of several Raytheon (Beech) 
Model 400A series airplanes. We are issuing this AD to prevent the 
accumulation of fuel and/or fuel vapor in the spoiler mixer bay and/
or the aft fuselage compartment, which could result in a fire in the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspections and Corrective Actions

    (f) Within 400 flight hours or 12 months after the effective 
date of this AD, whichever occurs first, do the actions in 
paragraphs (f)(1) and (f)(2) of this AD. Do all actions in 
accordance with the Accomplishment Instructions of Raytheon Service 
Bulletin SB 53-3486, dated June 2003.
    (1) Do a one-time general visual inspection of the spoiler mixer 
bay panels to determine the presence of drain holes. Before further 
flight after doing this inspection, drill at least one new drain 
hole, and any additional drain holes needed to make a total of five, 
at the places in each mixer bay panel specified in the service 
bulletin.
    (2) Do a one-time general visual inspection for discrepancies of 
the sealant on the relief cutout on the aft pressure bulkhead, and 
of the small triangular-shaped baffles at left butt line (BL) 19.13 
and right BL 10.43. Before further flight after doing this 
inspection, do any applicable corrective actions.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Parts Installation

    (g) As of the effective date of this AD, no person may install 
on any airplane a spoiler mixer bay panel that has a part number 
listed in paragraph 3.B., ``Spares,'' of the Accomplishment 
Instructions of Raytheon Service Bulletin SB 53-3486, dated June 
2003, unless the panel has been inspected and modified in accordance 
with paragraph (f)(1) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, Wichita Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (i) You must use Raytheon Service Bulletin SB 53-3486, dated 
June 2003, to perform the actions that are required by this AD, 
unless the AD specifies otherwise. The Director of the Federal 
Register approves the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the 
service information, contact Raytheon Aircraft Company, Department 
62, P.O. Box 85, Wichita, Kansas 67201-0085. For information on the 
availability of this material at the National Archives and Records 
Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. You may view the AD docket at the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street SW, room PL-401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on October 18, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-23926 Filed 10-26-04; 8:45 am]
BILLING CODE 4910-13-P


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