[Federal Register Volume 65, Number 155 (Thursday, August 10, 2000)]
[Proposed Rules]
[Pages 48945-48947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20245]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-60-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Raytheon (Beech) Model MU-
300, MU-300-10, 400, 400A, and 400T series airplanes. This proposal 
would 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. This action is 
necessary 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: Comments must be received by September 25, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-60-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-60-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule 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 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the

[[Page 48946]]

proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-60-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2000-NM-60-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report indicating that hydraulic fluid 
leakage has occurred on certain Raytheon (Beech) Model MU-300, MU-300-
10, 400, 400A, and 400T series airplanes. The existing design of the 
hydraulic tube installation for the left wheel of the landing gear 
includes an unsupported hydraulic line (tube), which is vulnerable to 
vibrations or mishandling. This unsupported hydraulic tube was found to 
have fatigue cracks around the flared end of the tube causing hydraulic 
fluid to leak from the fittings (B-nut area). Such leakage could 
progress to a sudden loss of normal braking to the left wheel resulting 
in an asymmetric braking condition and a longer stopping distance. This 
condition, if not corrected, could result in the airplane overrunning 
the runway surface.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Raytheon Aircraft Service 
Bulletin SB 32-3300, dated December 1999, which describes procedures 
for 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. The corrective actions 
involve the installation of a new or serviceable hydraulic tube if 
hydraulic fluid leakage is found. The service bulletin also describes 
procedures for the installation of an additional support for the 
hydraulic tube, which involves the installation of a new nutplate, 
clamp, and screw. Accomplishment of the actions specified in the 
service bulletin is intended to adequately address the identified 
unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously.

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 would be affected by this proposed AD, that it would take 
approximately 2 work hours per airplane to accomplish the proposed 
actions, and that the average labor rate is $60 per work hour. Required 
parts would cost approximately $31 per airplane. Based on these 
figures, the cost impact of the proposed 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 proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed 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 proposed AD.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Raytheon Aircraft Company (Formerly Beech): 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

[[Page 48947]]

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, Small Airplane Directorate. 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.

    Issued in Renton, Washington, on August 3, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-20245 Filed 8-9-00; 8:45 am]
BILLING CODE 4910-13-P