[Federal Register Volume 62, Number 141 (Wednesday, July 23, 1997)]
[Proposed Rules]
[Pages 39492-39494]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-19263]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-13-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Models 1900,
1900C, and 1900D 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 certain Raytheon Aircraft Company (Raytheon)
Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech
Models 1900, 1900C, and 1900D) airplanes. The proposed AD would require
lubricating the main landing gear actuator rod ends and eventually
replacing these rod ends with Teflon-lined rod ends. The proposed AD is
the result of in-flight separations of the rod end that attaches the
actuator to the arm of the main landing gear drag brace assembly on two
of the affected airplanes caused by excessive friction in the rod end
bearing. The actions specified by the proposed AD are intended to
prevent actuator rod end failure caused by excessive friction in the
rod end bearing, which could result in the inability to lower the main
landing gear or result in landing gear collapse during landing.
DATES: Comments must be received on or before September 26, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-CE-13-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 the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information also may be examined at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT: Mr. Steve Potter, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4124;
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
[[Page 39493]]
must submit a self-addressed, stamped postcard on which the following
statement is made: ``Comments to Docket No. 97-CE-13-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 Assistant Chief Counsel,
Attention: Rules Docket No. 97-CE-13-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received reports of in-flight separations of the rod
end that attaches the actuator to the arm of the main landing gear drag
brace assembly on two Raytheon 1900 series airplanes. These separations
occurred in the threaded shank end of the rod end. The dry film
lubricant deteriorated in the rod end, which caused excessive friction
in the rod end bearing. The airplanes involved in the referenced
incidents were equipped with Raytheon part number (P/N) 114-380041-11
(Frisby P/N 30150) main landing gear actuators. This condition, if not
corrected in a timely manner, could result in the inability to lower
the main landing gear or result in landing gear collapse during
landing.
Relevant Service Information
Raytheon has issued Mandatory Service Bulletin No. 2730, Issued:
November, 1996, which includes procedures for replacing the rod ends of
the P/N 114-380041-11 main landing gear actuators with Teflon-lined
main landing gear actuator rod ends, P/N M81935/1-8K. When the P/N
M81935/1-8K main landing gear actuator rod ends are installed, the P/N
114-380041-11 main landing gear actuator is re-identified as P/N 114-
380041-13.
Raytheon Safety Communique 1900-28, dated October 25, 1996,
includes procedures for lubricating the P/N 114-380041-11 main landing
gear actuators for those airplanes without Teflon-lined main landing
gear actuator rod ends installed.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
service information previously referenced, the FAA has determined that
AD action should be taken to prevent actuator rod end failure caused by
excessive friction in the rod end bearing, which could result in the
inability to lower the main landing gear or result in landing gear
collapse during landing.
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 1900, 1900C, and 1900D
airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D
airplanes) of the same type design that are equipped with at least one
P/N 114-380041-11 (or FAA-approved equivalent part number) main landing
gear actuator, the FAA is proposing an AD. The proposed AD would
require lubricating the actuator rod ends of the P/N 114-380041-11 (or
FAA-approved equivalent part number) main landing gear actuators in
accordance with Raytheon Safety Communique 1900-128, dated October 25,
1996. The proposed AD would also require eventually replacing the rod
ends of the P/N 114-380041-11 (or FAA-approved equivalent part number)
main landing gear actuators with Teflon-lined rod ends, P/N M81935/1-8K
(or FAA-approved equivalent part number). Accomplishment of this
proposed replacement would be in accordance with Raytheon Mandatory
Service Bulletin No. 2730, Issued: November, 1996.
Raytheon Models 1900, 1900C, and 1900D airplanes could have main
landing gear actuators installed that have Parts Manufacturer Approval
(PMA). For those airplanes having PMA parts that are equivalent (PMA by
equivalency) to those referenced in the proposed AD, the phrase ``or
FAA-approved equivalent part number'' means that the proposed actions,
if followed by a final rule, would also apply to airplanes with PMA by
equivalency actuators installed.
Cost Impact
The FAA estimates that 507 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 4
workhours per airplane (2 workhours per actuator with 2 actuators per
airplane) to accomplish the proposed modification, and that the average
labor rate is approximately $60 an hour. Parts cost approximately $233
per airplane. Based on these figures, the total cost impact of the
proposed AD on U.S. operators is estimated to be $239,811. These
figures are based on the presumption that no owner/operator of the
affected airplanes has incorporated the proposed modification.
Raytheon has informed the FAA that approximately 609 actuator rod
ends have been shipped from the Raytheon Aircraft Authorized Service
Center. This is enough to equip approximately 300 of the affected
airplanes (two main landing gear actuators per airplane). Presuming
that these actuator rod ends were incorporated on the affected
airplanes (two per airplane), this would reduce the cost impact of the
proposed AD by $141,900 from $239,811 to $97,911.
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-13-AD.
Applicability: The following model and serial number airplanes,
certificated in any category, that are equipped with at least one
[[Page 39494]]
part number (P/N) 114-380041-11 (or FAA-approved equivalent part
number) main landing gear actuator:
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Model Serial Numbers
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1900.................................. UA-2 and UA-3.
1900C................................. UB-1 through UB-74, and UC-1
through UC-174.
1900C (C-12J)......................... UD-1 through UD-6.
1900D................................. UE-1 through UE-249 and UE-252.
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Note 1: The airplanes affected by this AD could have main
landing gear actuators installed that have Parts Manufacturer
Approval (PMA). For those airplanes having PMA parts that are
equivalent (PMA by equivalency) to those referenced in the proposed
AD, the phrase ``or FAA-approved equivalent part number'' means that
this AD applies to airplanes with PMA by equivalency main landing
gear actuators installed.
Note 2: 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 (e) 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 in the body of this AD, unless
already accomplished.
To prevent actuator rod end failure caused by excessive friction
in the rod end bearing, which could result in the inability to lower
the main landing gear or result in landing gear collapse during
landing, accomplish the following:
(a) Upon accumulating 1,200 hours time-in-service (TIS) on each
P/N 114-380041-11 (or FAA-approved equivalent part number) main
landing gear actuator or within the next 100 hours TIS after the
effective date of this AD, whichever occurs later, lubricate the
actuator rod ends in accordance with Raythe on Safety Communication
1900-28, dated October 25, 1996.
(1) This lubrication is not needed on airplanes that have P/N
M81935/1-8K (or FAA-approved equivalent part number) main landing
gear actuator rod ends installed, as required by paragraph (b) of
this AD.
(2) Installing the P/N M81935/1-8K (or FAA-approved equivalent
part number) main landing gear actuator rod ends may be accomplished
at any time prior to the next 600 hours TIS, at which time they must
be installed (see paragraph (b) of this AD).
(b) Within the next 600 hours TIS after the effective date of
this AD, install Teflon-lined main landing gear actuator rod ends,
P/N M81935/1-8K (or FAA-approved equivalent part number), in
accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon
Mandatory Service Bulletin No. 2730, Issued: November, 1996.
(c) As of the effective date of this AD, no person may install a
P/N 114-380041-11(or FAA-approved equivalent part number) main
landing gear actuator without replacing the rod ends with P/N
M81935/1-8K (or FAA-approved equivalent part number). Installing
these Teflon-lined rod ends re-identifies the main landing gear
actuator as P/N 114-380041-13.
(d) 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.
(e) 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
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, 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 ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(f) 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
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on July 16, 1997.
Carolanne L. Cabrini,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-19263 Filed 7-22-97; 8:45 am]
BILLING CODE 4910-13-U