[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]
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