[Federal Register Volume 63, Number 86 (Tuesday, May 5, 1998)]
[Proposed Rules]
[Pages 24756-24758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11887]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-148-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Models
A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to Raytheon Aircraft Company (Raytheon) Models
A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C
airplanes. The proposed action would require replacing the main landing
gear left and right actuator clevis assembly. Reports of main landing
gear failure on two of the affected airplanes prompted the proposed
action. The actions specified by the proposed AD are intended to
prevent failure of the actuator clevis assembly in the main landing
gear, which could result in loss
[[Page 24757]]
of control of the airplane during landing operations.
DATES: Comments must be received on or before July 10, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-148-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106. Comments may be inspected at this
location between 8 a.m. and 4 p.m., Monday through Friday, holidays
excepted.
Service information that applies to the proposed AD may be obtained
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information
also may be examined at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4146;
facsimile (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 should 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 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 that summarizes 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 No. 97-CE-148-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, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 97-CE-148-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The FAA has received two reports of failed main landing gear (MLG)
on Raytheon Models B200 and B200C airplanes. Further investigation
shows the MLG actuator clevis in these airplanes failed from fatigue
cracking in the threaded shank portion of the clevis. The MLG actuator
clevis assembly that is currently installed in these Raytheon airplanes
could also fracture causing collapse of the MLG while landing.
Relevant Service Information
Raytheon Aircraft has issued Mandatory Service Bulletin No. 2728,
Issued: June 1997, Revision No. 1, dated February 1998, which specifies
replacing the left and right MLG actuator clevis assmembly with a new
MLG actuator clevis assembly of improved design.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent failure of the
actuator clevis assembly in the main landing gear, which, if not
corrected, could result in loss of control of the airplane during
landing operations.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Raytheon Models A200CT, B200, B200C, B200CT,
200T/B200T, 300, B300, and B300C of the same type design, the proposed
AD would require replacing the left and right MLG actuator clevis
assembly with a new actuator clevis assembly of improved design.
Cost Impact
The FAA estimates that 897 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 5
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Parts cost
approximately $581 per airplane. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be
$790,257, or $881 per airplane. The manufacturer has informed the FAA
that 105 owners/operators of these airplanes have already accomplished
the proposed action; therefore, the total cost impact of the proposed
AD on U.S. operators would be reduced by $92,505 from $790,257 to
$697,752.
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 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) 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 has been placed 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 a new airworthiness directive
(AD) to read as follows:
Raytheon Aircraft Company: Docket No. 97-CE-148-AD.
Applicability: Airplane models listed below, certificated in any
category.
[[Page 24758]]
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Model Serial No.
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B200.................................... BB-1158, BB-1167, BB-1193
through BB-1263, BB-1265
through BB-1286, BB-1287, BB-
1288, BB-1290 through BB-
1300, BB-1302 through BB-
1425, BB-1427 through BB-
1447, BB-1449, BB-1450, BB-
1453, BB-1455, BB-1456, and
BB-1458 through BB-1559.
B200C................................... BL-124 through BL-140.
B200CT (FW-II).......................... FG-1 and FG-2.
200T/B200T.............................. BT-31 through BT-38.
300..................................... FA-1 through FA-230 and FF-1
through FF-19.
B300.................................... FL-1 through FL-159.
B300C................................... FM-1 through FM-9 and FN-1.
A200CT (C-12D).......................... BP-46 through BP-51.
A200CT (C-12F).......................... BP-52 through BP-63.
A200CT (RC-12K)......................... FE-1 through FE-9.
A200CT (RC-12N)......................... FE-10 through FE-24.
A200CT (RC-12P)......................... FE-25 through FE-31, FE-33,
FE-35.
A200CT (RC-12Q)......................... FE-32, FE-34, FE-36.
B200C (C-12F)........................... BP-64 through BP-71, BL-73
through BL-112, and BL-118
through BL-123.
B200C (UC-12F).......................... BU-1 through BU-10.
B200CT (RC-12F)......................... BU-11 and BU-12.
B200C (UC-12M).......................... BV-1 through BV-10.
B200C (RC-12M).......................... BV-11 and BV-12.
B200C (C-12R)........................... BW-1 through BW-29.
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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 within the next 200 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent failure of the actuator clevis rod in the main
landing gear, which could result in loss of control of the airplane
during landing operations, accomplish the following:
(a) Replace the left and right main landing gear actuator clevis
assembly with a new MLG actuator clevis assembly of improved design
in accordance with the Accomplishment Instructions section in
Raytheon Aircraft Mandatory Service Bulletin No. 2728, Issued: June,
1997, Revision No. 1, February, 1998.
(b) 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.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Wichita, Kansas 67209. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Wichita Aircraft
Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita Aircraft Certification Office.
(d) All persons affected by this directive may obtain copies of
the document referred to herein upon request to the Raytheon
Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; or may
examine this document at the FAA, Central Region, Office of the
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on April 29, 1998.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11887 Filed 5-4-98; 8:45 am]
BILLING CODE 4910-13-U