AD 97-26-15 ACTIVE

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 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.

Final rule

97-26-15 RAYTHEON AIRCRAFT COMPANY (formerly Beech Aircraft Corporation): 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 identifiedin 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 Communiqu 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 Communiqu 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.

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 Communiqu 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 Communiqu 1900-128
The commenter states that Raytheon Safety Communiqu 1900-128 was incorrectly referenced in the proposed AD as Raytheon Safety Communiqu 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 FAAhas 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 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 asfollows:
Authority: 49 USC 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

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.

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.