[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.


[[Page 8648]]


    (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