Federal Aviation Administration, DOT.
Notice of proposed rulemaking (NPRM).
This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Boeing Model 707 and 720 series airplanes. This proposal would require installation of a new support structure for the trailing edge beam and main landing gear uplock mechanism. This action is necessary to prevent cracking in the frame and adjacent structure near the attach bolt of the main landing gear uplock mechanism, which could lead to compromised structural integrity. This action is intended to address the identified unsafe condition.
Comments must be received by September 10, 2001.
Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-381-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to (425) 227-1232. Comments may also be sent via the Internet using the following address: email@example.com. Comments sent via fax or the Internet must contain “Docket No. 2000-NM-381-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.
The service information referenced in the proposed rule may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Duong Tran, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2773; fax (425) 227-1181.End Further Info End Preamble Start Supplemental Information
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 shall 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 action may be changed in light of the comments received.
Submit comments using the following format:
- Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
- For each issue, state what specific change to the proposed AD is being requested.
- Include justification (e.g., reasons or data) for each request.
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 summarizing 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 action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2000-NM-381-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, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-381-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
The FAA has received reports indicating that cracks have been discovered in station 900 frame and its adjacent structure, near the attach bolt of the main landing gear (MLG) uplock mechanism. These cracks were caused by flexure of the wing, imposing Start Printed Page 38584bending loads on the frame, in addition to the normal tension loads. This cracking condition, if not corrected, could result in compromised structural integrity of the MLG.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Service Bulletin 2411, Revision 2, dated April 29, 1968, which describes procedures for, among other things, the installation of a new support structure for the trailing edge beam and main landing gear uplock mechanism. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to exist or develop on other products of this same type design, the proposed AD would require accomplishment of the actions specified in the service bulletin described previously, except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that this proposed AD would mandate the preventative modification described in Part III—Modification Data of the Accomplishment Instructions of Boeing Service Bulletin 2411, Revision 2, dated April 29, 1968, prior to the accumulation of 20,000 total flight cycles, or within 24 months from the effective date of the AD, whichever occurs later. (Incorporation of the specified preventative modification is recommended in the service bulletin “at the next major overhaul,” except for repair.)
The proposed AD also differs from the service bulletin in that it would not require the repetitive inspections to detect cracks in the support structure for the trailing edge beam and main landing gear uplock. The decision to mandate the preventative modification of the main landing gear uplock mechanism is based on the FAA's determination that long-term continued operational safety will be better assured by design changes to remove the source of the problem, rather than by repetitive inspections. Long-term inspections may not provide the degree of safety assurance necessary for the transport airplane fleet. This, coupled with a better understanding of the human factors associated with numerous continual inspections, has led the FAA to consider placing less emphasis on inspections and more emphasis on design improvements. The proposed preventative modification requirement is consistent with these findings.
There are approximately 84 airplanes of the affected design in the worldwide fleet. The FAA estimates that 10 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 80 work hours per airplane to accomplish the proposed modification, and that the average labor rate is $60 per work hour. Required parts would cost approximately $15,000 per airplane. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $198,000, or $19,800 per airplane.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this proposed AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
The regulations proposed herein 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 proposal would not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this proposed regulation (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the 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 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.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
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:Start Part
PART 39—AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:End Part
2. Section 39.13 is amended by adding the following new airworthiness directive:
Boeing: Docket 2000-NM-381-AD.
Applicability: Model 707 and 720 series airplanes, certificated in any category, as listed in Boeing Service Bulletin 2411, Revision 2, dated April 29, 1968.
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 (b) 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, unless accomplished previously.
To prevent cracking in the frame and adjacent structure near the attach bolt of the main landing gear (MLG) uplock mechanism, which could lead to compromised structural integrity of the MLG, accomplish the following:
(a) Prior to the accumulation of 20,000 flight cycles, or within 24 months from the effective date of this AD, whichever occurs later, install a new support structure for the MLG uplock mechanism in accordance with Part III—Modification Data of the Accomplishment Instructions of Boeing Service Bulletin 2411, Revision 2, dated April 29, 1968.
Alternative Methods of Compliance
(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Start Printed Page 38585Inspector, who may add comments and then send it to the Manager, Seattle ACO.
Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.
Special Flight Permits
(c) Special flight permits may be issued in accordance with §§ 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.Start Signature
Issued in Renton, Washington, on July 18, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-18437 Filed 7-24-01; 8:45 am]
BILLING CODE 4910-13-P