62570 Federal Register / Vol. 69, No. 207 / Wednesday, October 27, 2004 / Rules and Regulations 

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.

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, marcia.walters@faa.gov.

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

Action Work 

hours 

Average

labor

rate per 

hour 

Parts Cost per

airplane 

Number 

of

U.S.

registered 

airplanes 

Fleet cost 

Inspections ................................................................. 1 $65 None ................................ $65 610 $39,650 

Drilling one drain hole ................................................ 3 65 None ................................ 195 610 118,950 

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 

Federal Register / Vol. 69, No. 207 / Wednesday, October 27, 2004 / Rules and Regulations 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

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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.

§ 39.13 [Amended]

■ 2. The FAA amends § 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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NE–43–AD; Amendment 

39–13835; AD 2004–22–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80C2 

Turbofan Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF6–80C2 turbofan engines with certain 

part number (P/N) high pressure turbine 

stage 2 nozzle guide vanes (HPT S2 

NGVs) installed. This AD requires flex 

borescope inspections of HPT S2 NGVs 

installed in CF6–80C2 turbofan engines. 

This AD results from an uncontained 

engine failure due to HPT S2 NGV 

distress. We are issuing this AD to 

prevent blade separation from HPT S2 

NGV distress, which could result in an 

uncontained engine failure.

DATES: This AD becomes effective 

December 1, 2004. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of December 1, 2004.

ADDRESSES: You can get the service 

information identified in this AD from 

General Electric Company via Lockheed 

Martin Technology Services, 10525 

Chester Road, suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400; fax 

(513) 672–8422. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; 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: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.