Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes

[Federal Register Volume 62, Number 244 (Friday, December 19, 1997)]
[Rules and Regulations]
[Pages 66498-66500]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-13-AD; Amendment 39-10258; AD 97-26-15]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 
1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 
1900C, and 1900D airplanes). This AD requires lubricating the main 
landing gear actuator rod ends and eventually replacing these rod ends 
with Teflon-lined rod ends. The AD results from 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 of the affected airplanes 
caused by excessive friction in the rod end bearing. The actions

[[Page 66499]]

specified by this 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: Effective January 25, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 25, 1998.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 97-CE-13-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Steven E. 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:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Raytheon 
Models 1900, 1900C, and 1900D airplanes was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on July 23, 1997 (62 
FR 39492). The NPRM proposed to 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.
    The NPRM resulted from 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 of the affected airplanes caused by excessive 
friction in the rod end bearing.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received from one commenter. No comments have been 
received regarding the FAA's estimate of the cost impact upon the 
public.

Comment No. 1: Language Change in the AD

    The commenter requests that the FAA add the following language to 
paragraph (b) of the proposed AD:

    Installation of P/N M81935/1-8K (or FAA-approved equivalent 
part) rod end constitutes terminating action to the lubricating 
requirements of provision (a) of this AD.

The commenter feels that adding this language to paragraph (b) of this 
AD will eliminate the need for the language in paragraph (a)(1) and 
(a)(2) of this AD.
    The FAA partially agrees. The FAA believes that language similar to 
that proposed by the commenter could replace paragraph (a)(1) of the 
proposed AD, which currently reads:

    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.

However, paragraph (a)(2) states that the operator may accomplish the 
installation at any time prior to 600 hours time-in-service (TIS). The 
FAA feels that this paragraph is necessary as it provides information 
and clarification necessary for persons who might want to accomplish 
the installation at a regular maintenance interval, and would prefer to 
accomplish the installation and not accomplish the lubrication 
requirements of the AD. The FAA will replace the language of paragraph 
(a)(1) with language similar to that requested by the commenter. 
Paragraph (a)(1) of the final rule has been changed accordingly.

Comment No. 2: Wrong reference to Raytheon Safety Communique 1900-128

    The commenter states that Raytheon Safety Communique 1900-128 was 
incorrectly referenced in the proposed AD as Raytheon Safety Communique 
1900-28. The commenter requests that the proposed AD be changed to 
reflect the correct reference to this service information.
    The FAA concurs and will change the final rule accordingly.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
the changes described above and minor editorial corrections. The FAA 
has determined that these changes and minor corrections will not change 
the meaning of the AD and will not add any additional burden upon the 
public than was already proposed.

Cost Impact

    The FAA estimates that 507 airplanes in the U.S. registry would be 
affected by this AD, that it would take approximately 4 workhours per 
airplane (2 workhours per actuator with 2 actuators per airplane) to 
accomplish the required installation, 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, or $473 per airplane. 
These figures are based on the presumption that no owner/operator of 
the affected airplanes has incorporated the required installation.
    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 this 
AD by $141,900 from $239,811 to $97,911.

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does

[[Page 66500]]

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) 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 final 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

97-26-15  Raytheon Aircraft Company: Amendment 39-10258; 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 
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 this 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 installation, 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 Raytheon Safety Communique 
1900-128, dated October 25, 1996.
    (1) Installation of P/N M81935/1-8K (or FAA-approved equivalent 
part number) main landing gear actuator rod ends constitutes 
terminating action to the lubricating requirements of paragraph (a) 
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) The lubrication required by this AD shall be done in 
accordance with Raytheon Safety Communique 1900-128, dated October 
25, 1996. The installation required by this AD shall be done in 
accordance with Raytheon Mandatory Service Bulletin No. 2730, 
Issued: November, 1996. This incorporation by reference was approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from the Raytheon 
Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. Copies 
may be inspected at the FAA, Central Region, Office of the Regional 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (g) This amendment (39-10258) becomes effective on January 25, 
1998.

    Issued in Kansas City, Missouri, on December 10, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-32994 Filed 12-18-97; 8:45 am]
BILLING CODE 4910-13-U

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