[Federal Register Volume 65, Number 93 (Friday, May 12, 2000)]
[Rules and Regulations]
[Pages 30538-30539]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 00-11549]



[[Page 30538]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-372-AD; Amendment 39-11721; AD 2000-09-12]
RIN 2120-AA64


Airworthiness Directives; Raytheon (Beech) Model 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 400A and 400T series 
airplanes, that requires replacement of temperature switch assemblies 
of the wing ice protection system with new, improved parts. This 
amendment is prompted by reports of electrical continuity problems with 
solder joints on the temperature switches of the wing ice protection 
system. The actions specified by this AD are intended to prevent 
detachment or breakage of wires in the temperature switch assemblies of 
the wing ice protection system. Such detachment or breakage of wires 
could result in the flightcrew not being advised of an over-temperature 
situation on the leading edge of the wing, which could result in 
structural damage to the wing.

DATES: Effective June 16, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 16, 2000.

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, Small 
Airplane Directorate, 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: Philip Petty, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane 
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
946-4139; 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 
400A and 400T series airplanes was published in the Federal Register on 
January 12, 2000 (65 FR 1836). That action proposed to require 
replacement of temperature switch assemblies of the wing ice protection 
system with new, improved parts.

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 404 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 366 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 30 work 
hours per airplane to accomplish the required replacement, and that the 
average labor rate is $60 per work hour. Required parts will be 
provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $658,800, or $1,800 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.

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 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:

    2000-09-12  Raytheon Aircraft Company (Formerly Beech): 
Amendment 39-11721. Docket 99-NM-372-AD.

    Applicability: Model 400A series airplanes, having serial 
numbers RK-01 through RK-188 inclusive; Model 400T (T-1A) series 
airplanes, having serial numbers TT-01 through TT-180 inclusive; and 
Model 400T (TX) series airplanes, having serial numbers TX-01 
through TX-09 inclusive; 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 (c) 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.

[[Page 30539]]

    To prevent detachment or breakage of wires in the temperature 
switch assemblies of the wing ice protection system, which could 
result in the flightcrew not being advised of an over-temperature 
situation on the leading edge of the wing, and consequent structural 
damage to the wing, accomplish the following:

Replacement

    (a) At the next scheduled inspection, but no later than 200 
flight hours after the effective date of this AD, replace 
temperature switch assemblies of the wing ice protection system with 
new, improved temperature switch assemblies, in accordance with 
Raytheon Service Bulletin 30-3008, Revision 1, dated August 1999.

    Note 2: Replacements accomplished prior to the effective date of 
this AD in accordance with Raytheon Service Bulletin 30-3008, dated 
March 1999, are considered acceptable for compliance with the 
applicable action specified in this AD.

Spares

    (b) As of the effective date of this AD, no person shall 
install, on any airplane, a temperature switch assembly having a 
part number listed in the ``Old Part Number'' column of the table in 
2.D. of Raytheon Service Bulletin 30-3008, Revision 1, dated August 
1999.

Alternative Methods of Compliance

    (c) 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 Permits

    (d) 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

    (e) The replacement shall be done in accordance with Raytheon 
Service Bulletin 30-3008, Revision 1, dated August 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, Small Airplane Directorate, 
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.
    (f) This amendment becomes effective on June 16, 2000.

    Issued in Renton, Washington, on May 3, 2000.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-11549 Filed 5-11-00; 8:45 am]
BILLING CODE 4910-13-P