[Federal Register Volume 65, Number 240 (Wednesday, December 13, 2000)]
[Rules and Regulations]
[Pages 77782-77783]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-31316]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-60-AD; Amendment 39-12038; AD 2000-25-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Raytheon (Beech) Model MU-300, MU-300-10, 400, 
400A, and 400T series airplanes, that requires a one-time inspection to 
detect hydraulic fluid leakage from the B-nut area, which attaches a 
hydraulic tube to the anti-skid valve assembly, and corrective actions, 
if necessary; and installation of an additional support for the 
hydraulic tube. This amendment is intended to prevent an asymmetric 
braking condition and a longer stopping distance due to sudden loss of 
normal braking to the left wheel. Such loss of normal braking could 
result in the airplane overrunning the runway surface. This action is 
intended to address the identified unsafe condition.

DATES: Effective January 17, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 17, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Manager Service Engineering, 
Beechjet/Premier Technical Support Department, P.O. Box 85, Wichita, 
Kansas 67201-0085. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul C. DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209, telephone (316) 946-4142; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Raytheon (Beech) Model MU-
300, MU-300-10, 400, 400A, and 400T series airplanes was published in 
the Federal Register on August 10, 2000 (65 FR 48945). That action 
proposed to require a one-time inspection to detect hydraulic fluid 
leakage from the B-nut area, which attaches a hydraulic tube to the 
anti-skid valve assembly, and corrective actions, if necessary; and 
installation of an additional support for the hydraulic tube.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 567 series airplanes of the affected design 
in the worldwide fleet. The FAA estimates that 522 airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 2 
work hours per airplane to accomplish the required actions, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $31 per airplane. Based on these figures, the cost impact 
of the AD on U.S. operators is estimated to be $78,822, or $151 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions. Additionally, the manufacturer has indicated 
the warranty remedies may be available to defer the cost of the 
replacement parts also associated with accomplishing this actions 
required by this AD.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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 under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy

[[Page 77783]]

of it may be obtained from the Rules Docket at the location provided 
under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-25-04  Raytheon Aircraft Company (Formerly Beech): Amendment 
39-12038. Docket 2000-NM-60-AD.

    Applicability: Model MU-300, MU-300-10, 400, 400A, and 400T 
series airplanes; as listed in Raytheon Aircraft Service Bulletin SB 
32-3300, dated December 1999; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Required as indicated, unless accomplished previously.
    To prevent an asymmetric braking condition and a longer stopping 
distance due to sudden loss of normal braking to the left wheel, 
which could result in the airplane overrunning the runway surface, 
accomplish the following:

General Visual Inspection

    (a) Within 200 flight hours after the effective date of this AD, 
perform a one-time general visual inspection to detect hydraulic 
fluid leakage from the B-nut area, which attaches a hydraulic tube 
to the anti-skid valve assembly, in accordance with Raytheon 
Aircraft Service Bulletin SB 32-3300, dated December 1999.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

    (1) If no leakage is found, prior to further flight, install an 
additional support (i.e., new nutplate, clamp, and screw) for the 
hydraulic tube; in accordance with the service bulletin.
    (2) If any leakage is found, prior to further flight, replace 
the hydraulic tube with a new or serviceable hydraulic tube, and 
install an additional support (i.e., new nutplate, clamp, and screw) 
for the hydraulic tube; in accordance with the service bulletin.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Wichita Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

Special Flight Permit

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Raytheon 
Aircraft Service Bulletin SB 32-3300, dated December 1999. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Raytheon Aircraft Company, Manager 
Service Engineering, Beechjet/Premier Technical Support Department, 
P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Wichita Aircraft Certification 
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on January 17, 2001.

    Issued in Renton, Washington, on December 4, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-31316 Filed 12-12-00; 8:45 am]
BILLING CODE 4910-13-P