Federal Register: December 13, 2000 (Volume 65, Number 240)
DOCID: FR Doc 00-31316
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 39
Docket ID: [Docket No. 2000-NM-60-AD; Amendment 39-12038; AD 2000-25-04]
RIN ID: RIN 2120-AA64
ACTION: Airworthiness directives:
DOCUMENT ACTION: Final rule.
Airworthiness Directives; Raytheon (Beech) Model MU-300, MU-300- 10, 400, 400A, and 400T Series Airplanes
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.
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model MU300, MU30010, 400, 400A, and 400T series airplanes, that requires a onetime inspection to detect hydraulic fluid leakage from the Bnut area, which attaches a hydraulic tube to the antiskid 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.
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, MU30010, 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 onetime inspection to detect hydraulic fluid leakage from the Bnut area, which attaches a hydraulic tube to the antiskid 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.
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.
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
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 39AIRWORTHINESS 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:
20002504 Raytheon Aircraft Company (Formerly Beech): Amendment 3912038. Docket 2000NM60AD.
Applicability: Model MU300, MU30010, 400, 400A, and 400T series airplanes; as listed in Raytheon Aircraft Service Bulletin SB 323300, 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.
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 onetime general visual inspection to detect hydraulic fluid leakage from the Bnut area, which attaches a hydraulic tube to the antiskid valve assembly, in accordance with Raytheon Aircraft Service Bulletin SB 323300, 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 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.''
(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 323300, 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 672010085. 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, MidContinent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(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. 0031316 Filed 121200; 8:45 am] BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT
Paul C. DeVore, Aerospace Engineer, Systems and Propulsion Branch, ACE116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209, telephone (316) 9464142; fax (316) 9464407.