[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:
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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 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
