[Federal Register Volume 62, Number 38 (Wednesday, February 26, 1997)]
[Proposed Rules]
[Pages 8646-8648]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-4716]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-196-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model DH 125-1A and -3A 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 Model DH 125-1A
and -3A series airplanes. This proposal would require repetitive eddy
current inspections to detect fatigue cracking of the main entry door/
frame pressing, and repair, if necessary. This proposal 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 the
proposed 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: Comments must be received by April 7, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-196-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.
The service information referenced in the proposed rule may be
obtained from Raytheon Aircraft Company, Commercial Service 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 the FAA, Wichita Aircraft Certification
Office, Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas.
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:
Comments Invited
Interested persons are invited to participate in the making of the
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
[[Page 8647]]
in this notice may be changed in light of the comments received.
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 96-NM-196-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-103, Attention: Rules
Docket No. 96-NM-196-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received several reports of fatigue cracking of the
main entry door/frame pressing of Raytheon Model DH 125-1A and -3A
series airplanes. Investigation revealed that cyclic loading of the
door frame caused the fatigue cracking. Such fatigue cracking, if not
detected and corrected in a timely manner, could cause the loss of
structural integrity of the main entry door, and lead to decompression
of the cabin.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Aircraft Service
Bulletin SB.52-48, dated June 19, 1996, which describes procedures for
eddy current inspections to detect fatigue cracking of the main entry
door/frame pressing. The service bulletin also describes procedures for
repair, if necessary.
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 repetitive eddy current inspections to detect
and correct fatigue cracking of the main entry door/frame pressing. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
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 would be affected by this proposed AD,
that it would take approximately 1 work hour per airplane to accomplish
the proposed inspections, and that the average labor rate is $60 per
work hour. Based on these figures, the cost impact of the proposed 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 proposed 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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, Raytheon Corporate Jets,
British Aerospace, Hawker Siddeley, et al.): 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, 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.
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(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 February 20, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-4716 Filed 2-25-97; 8:45 am]
BILLING CODE 4910-13-U
