[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:

------------------------------------------------------------------------
                 Model                           Serial Numbers         
------------------------------------------------------------------------
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. 
------------------------------------------------------------------------

    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