Federal Register: August 27, 2001 (Volume 66, Number 166)
DOCID: FR Doc 01-21498
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 39
Docket ID: [Docket No. 99-CE-80-AD]
RIN ID: RIN 2120-AA64
NOTICE: PROPOSED RULES
ACTION: Airworthiness directives:
DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).
Airworthiness Directives; Raytheon Aircraft Company Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 Airplanes
DATES: The Federal Aviation Administration (FAA) must receive any comments on this proposed rule by October 31, 2001.
This document proposes a new airworthiness directive (AD) that would apply to certain Raytheon Aircraft Company (Raytheon) Beech Models 6590, 65A90, 65A901, 65A904, B90, C90, C90A, E90, and H90 airplanes. This proposed AD would require you to repetitively inspect the main landing gear upper torque knees and lower torque knees for evidence of fatigue cracks; and replace any torque knee with evidence of fatigue cracks. The proposed AD is the result of reports of many incidents of main landing gear torque knees cracking or breaking on the abovereferenced airplanes. The actions specified by this proposed AD are intended to detect and replace cracked main landing gear torque knees, which could result in failure of the main landing gear and consequent loss of control of the airplane during takeoff, landing, or other ground operations.
How can I be sure FAA receives my comment? If you want us to acknowledge the receipt of your comments, you must include a self addressed, stamped postcard. On the postcard, write ``Docket No. 99CE 80AD.'' We will date stamp and mail the postcard back to you. Discussion
What events have caused this proposed AD? The FAA has received reports of many incidents of fatigue cracks occurring on main landing gear torque knees. There have been at least four reports where the main landing gear separated from the airplane.
The cause of this problem is cumulative fatigue damage on the main landing gear torque knees.
What are the consequences if the condition is not corrected? This condition, if not corrected, could result in the failure of the main landing gear while the airplane is in operation with consequent loss of control of the airplane during takeoff, landing, or other ground operations.
Relevant Service Information
Is there service information that applies to this subject? Raytheon has issued these service bulletins:
Service Bulletin SB 323134, Revision 1, Revised: July 1999; and Service Bulletin SB 323116, issued October 1999.
What are the provisions of this service bulletin? The service bulletins include procedures for:
Repetitively inspecting the main landing gear upper and lower torque knees for fatigue cracks; and
replacing any torque knees with fatigue cracks.
The FAA's Determination and an Explanation of the Provisions of the Proposed AD
What has FAA decided? After examining the circumstances and
reviewing all available information related to the incidents described above, we have determined that:
The unsafe condition referenced in this document exists or could develop on other Raytheon Beech Models 6590, 65A90, 65A901, 65A90 4, B90, C90, C90A, E90, and H90 airplanes of the same type design; the actions specified in the previouslyreferenced service
information should be accomplished on the affected airplanes; and AD action should be taken in order to correct this unsafe condition.
What would the proposed AD require? This proposed AD would require you to incorporate the actions in the previously referenced service bulletins.
How many airplanes does this proposed AD impact? We estimate that this proposed AD would affect 2,124 airplanes in the U.S. registry.
What is the cost impact of this proposed AD on owners/operators of
the affected airplanes? We estimate the following costs to inspect the landing gear torque knees:
Total cost Labor cost Parts cost for each Total cost on U.S. airplane airplane operators 20 workhours x $60 per hour = $1200. $50 per airplane........... $1,250 $1,250 x 2,124 = $2,655,000 The manufacturer will also allow warranty credit to the extent noted in the service bulletin. [[Page 44989]]
These costs only take into account the costs of the initial inspection. We have no way of determining the number of repetitive inspections each owner/operator will incur over the life of the affected airplane.
We estimate the following costs to do any necessary torque knee
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of airplanes that may need such replacement:
Labor cost Parts cost Total cost per airplane 8 workhours x $60 per hour = $480. $3,286 per airplane.......... $3,766 per airplane. Regulatory Impact
Does this proposed AD impact various entities? The regulations proposed would not have a substantial direct effect 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, it is determined that this proposed rule would not have federalism implications under Executive Order 13132.
Does this proposed AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this proposed 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.
The Proposed Amendment
Accordingly, under 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 39AIRWORTHINESS 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. FAA amends Sec. 39.13 by adding a new airworthiness directive (AD) to read as follows:
Raytheon Aircraft Company: Docket No. 99CE80AD.
(a) What airplanes are affected by this AD? This AD affects the following Beech airplane models and serial numbers that are certificated in any category:
Model Serial numbers 6590, 65A90, B90, C90, and C90A......... LJ1 through LJ1559. 65A901.................................. LM1 through LM141. 65A904.................................. LU1 through LU16. E90....................................... LW1 through LW347. H90...................................... LL1 through LL61. (b) Who must comply with this AD? Anyone who wishes to operate any of the above airplane models must comply with this AD.
(c) What problem does this AD address? The actions specified by this AD are intended to detect and replace cracked main landing gear torque knees, which could result in failure of the main landing gear with consequent loss of control of the airplane during takeoff, landing, or other ground operations.
(d) What must I do to address this problem? To address this problem, you must do the following actions:
Actions Compliance times Procedures (1) Inspect the main landing Inspect within the Do the action gear upper torque knee and next 100 hours time following the lower torque knee for inservice (TIS) Accomplishment fatigue cracks. after the effective Instructions date of this AD, paragraph of and thereafter at Raytheon Mandatory intervals not to Service Bulletin SB exceed 1,000 hours 323134, Revision TIS. 1, Revised: July 1999, and the applicable airplane maintenance manual. (2) If fatigue cracks are Before further Do the action found in the main landing flight after the following the gear torque knees during inspection. Accomplishment any inspection required by Instructions this AD, replace the paragraph of cracked torque knees. Raytheon Mandatory Service Bulletin SB 323116, Issued: October 1999, and the applicable airplane maintenance manual. (3) When both the left and You may replace all Do the action right main landing gear torque knees at any following the upper and lower torque time, except for Accomplishment knees are replaced with new those torque knees Instructions upper torque knees (part that are found with paragraph of number 5081003212) and evidence of fatigue Raytheon Mandatory new lower torque knees cracks. Such torque Service Bulletin SB (part number 5081029525), knees must be 323116, Issued: the repetitive inspection replaced before October 1999, and requirement of this AD is further flight, as the applicable no longer required. required by airplane paragraph (d)(2) of maintenance manual. this AD.
(e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Your alternative method of compliance provides an equivalent level of safety; and
(2) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Send your request through an
FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.
Note: This AD applies to each airplane identified in paragraph
(a) of this AD, 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 you have not eliminated the unsafe condition, specific actions you propose to address it.
(f) Where can I get information about any alreadyapproved alternative methods of compliance? Contact Steven E. Potter, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946 4124; facsimile: (316) 9464407.
(g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.
(h) How do I get copies of the documents referenced in this AD? You can get copies from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 672010085; telephone: (800) 4295372 or (316) 676 3140; or on the Internet at http://www.raytheon.com/rac/servinfo/32 3134r1.pdf and http://www.raytheon.com/rac/servinfo/323116.pdf. These files are in Adobe Portable Document Format. The Acrobat Reader is available at http://www.adobe.com/. You can look at copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri.
Issued in Kansas City, Missouri, on August 17, 2001. Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 0121498 Filed 82401; 8:45 am] BILLING CODE 491013U
FOR FURTHER INFORMATION CONTACT
Mr. Steven E. Potter, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 9464124; facsimile: (316) 9464407.