[Federal Register Volume 63, Number 44 (Friday, March 6, 1998)]
[Rules and Regulations]
[Pages 11114-11115]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-5588]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-196-AD; Amendment 39-10377; AD 98-05-16]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH 125-1A and -3A 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 Model DH 125-1A and -3A series 
airplanes, that requires repetitive eddy current inspections to detect 
fatigue cracking of the main entry door/frame pressing, and repair, if 
necessary. This amendment is prompted by reports of fatigue cracking of 
the main entry door/frame pressing due to cyclic loading of the door 
frame. The actions specified by this AD are intended to detect and 
correct such fatigue cracking, which could lead to the loss of 
structural integrity of the main entry door, and, consequently, result 
in decompression of the cabin.

DATES: Effective April 10, 1998. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of April 10, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Technical Services--Beech, 
Hawker Customer 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: Larry Engler, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4122; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

[[Page 11115]]

Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Raytheon Model DH 125-1A 
and -3A series airplanes was published in the Federal Register on 
February 26, 1997 (62 FR 8646). That action proposed to require 
repetitive eddy current inspections to detect fatigue cracking of the 
main entry door/frame pressing, and repair, if necessary.

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 143 Raytheon Model DH 125 series airplanes 
of the affected design in the worldwide fleet. The FAA estimates that 
56 airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 1 work hour per airplane to accomplish the required 
inspections, and that the average labor rate is $60 per work hour. 
Based on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $3,360, or $60 per airplane, per inspection.
    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 substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

98-05-16  Raytheon Aircraft Company (Formerly Beech, Raytheon 
Corporate Jets, British Aerospace, Hawker Siddeley, et al.): 
Amendment 39-10377. Docket 96-NM-196-AD.

    Applicability: Model DH 125-1A and -3A series airplanes; 
equipped with a main entry door having part numbers 25FC3559A, 
25FC3559A/B, or 25FC3559A/C; and on which Raytheon Modification 
251429 has not been accomplished; 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 detect and correct fatigue cracking of the main entry door/
frame pressing area, which could result in loss of structural 
integrity of the door and consequent decompression of the cabin, 
accomplish the following:
    (a) Within the next 150 landings or 90 days after the effective 
date of this AD, whichever occurs earlier, perform an eddy current 
inspection to detect fatigue cracking of the main entry door/frame 
pressing, in accordance with Raytheon Aircraft Service Bulletin 
SB.52-48, including Appendix A, dated June 19, 1996.
    (1) If no cracking is detected during the inspection, repeat the 
inspection thereafter at intervals not to exceed 1,000 flight hours.
    (2) If any cracking is detected during the inspection, prior to 
further flight, repair the cracking in accordance with the service 
bulletin.
    (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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (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.
    (d) The actions shall be done in accordance with Raytheon 
Aircraft Service Bulletin, SB.52-48, including Appendix A, dated 
June 19, 1996. 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, Technical Services--Beech, Hawker Customer 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.
    (e) This amendment becomes effective on April 10, 1998.

    Issued in Renton, Washington, on February 26, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-5588 Filed 3-5-98; 8:45 am]
BILLING CODE 4910-13-P