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 McDonnell Douglas Model 717-200 airplanes. This proposal would require inspection of the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=+/− 7.234 for material defects, and corrective action, if necessary. This action is necessary to detect material defects in the inboard ends of the outer skin panels of the horizontal stabilizer, which could lead to cracks and an associated loss of strength in the attachments, and consequent reduced structural integrity of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
Comments must be received by November 3, 2003.
Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2002-NM-213-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: firstname.lastname@example.org. Comments sent via fax or the Internet must contain “Docket No. 2002-NM-213-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 or 2000 or ASCII text.
The service information referenced in the proposed rule may be obtained from Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Maureen Moreland, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5238; fax (562) 627-5210.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 2002-NM-213-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. 2002-NM-213-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
The FAA has received a report indicating that the manufacturer of the horizontal stabilizer failed to ultrasonically inspect the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=+/−7.234 for material defects during manufacture of certain McDonnell Douglas 717-200 airplanes. Undetected defects in the material in the inboard ends of the outer skin panels of the horizontal stabilizer could lead to cracks and an associated loss of strength in the attachments. Cracks in the inboard ends of the outer skin panels of the horizontal stabilizer and an associated loss of strength in the attachments could lead to reduced structural integrity of the horizontal stabilizer.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Service Bulletin 717-55-0005, dated June 27, 2002. The service bulletin describes procedures for performing an ultrasonic inspection of the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=+/−7.234 for material defects, and for contacting Boeing for repair instructions. 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
Although the service bulletin specifies that operators may contact the manufacturer for disposition of certain defect conditions, this proposed AD would require operators to repair those conditions per a method approved by Start Printed Page 54691the FAA, or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Los Angeles Aircraft Certification Office, to make such findings.
Operators should note that, although the service bulletin does not list a grace period in the compliance times, this proposed AD adds a grace period to the compliance times. The FAA finds that such a grace period will keep airplanes from being grounded unnecessarily.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's airworthiness directives system. The regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance (AMOCs). Because we have now included this material in part 39, only the office authorized to approve AMOCs is identified in each individual AD.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several years to calculate AD costs to operators. To account for various inflationary costs in the airline industry, we find it necessary to increase the labor rate used in these calculations from $60 per work hour to $65 per work hour. The cost impact information, below, reflects this increase in the specified hourly labor rate.
There are approximately 56 airplanes of the affected design in the worldwide fleet. The FAA estimates that 41 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 4 work hours per airplane to accomplish the proposed inspection, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $10,660, or $260 per airplane.
The cost impact figures discussed above are 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. Manufacturer warranty remedies may be available for labor costs associated with this proposed AD. As a result, the costs attributable to the proposed AD may be less than stated above.
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 39
- Air transportation
- Aviation safety
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:
2. Section 39.13 is amended by adding the following new airworthiness directive:
McDonnell Douglas: Docket 2002-NM-213-AD.
Applicability: Model 717-200 airplanes, as listed in Boeing Service Bulletin 717-55-0005, dated June 27, 2002; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To detect material defects in the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=+/−7.234, which could lead to cracks and an associated loss of strength in the attachments, and consequent reduced structural integrity of the horizontal stabilizer, accomplish the following:
(a) Prior to the accumulation of 10,000 total flight cycles, or within 15 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection of the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=+/−7.234 for material defects, per the Accomplishment Instructions of Boeing Service Bulletin 717-55-0005, dated June 27, 2002.
(b) If any defects are found during the inspection required by paragraph (a) of this AD, and the service bulletin specifies contacting Boeing for appropriate action: Before further flight, repair per a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Los Angeles ACO, to make such findings. For a repair method to be approved, as required by this paragraph, the approval letter must specifically refer to this AD.
Alternative Methods of Compliance
(c) In accordance with 14 CFR 39.19, the Manager, Los Angeles ACO, FAA, is authorized to approve alternative methods of compliance for this AD.Start Signature
Issued in Renton, Washington, on September 12, 2003.
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-23833 Filed 9-17-03; 8:45 am]
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