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Proposed Rule

Airworthiness Directives; McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F Series Airplanes; and Model MD-10-10F and MD-10-30F Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

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AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes the adoption of a new airworthiness directive (AD) that is applicable to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-10-30F series airplanes. This proposal would require an inspection of the parallel power feeder cables of the number 2 generator for chafing or structure damage; repositioning of the cables; and repair, if necessary. This action is necessary to prevent wire chafing of the parallel power feeder cables of the number 2 generator, which, if not corrected, could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the aft door panel area. This action is intended to address the identified unsafe condition.

DATES:

Comments must be received by February 19, 2002.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-121-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: 9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must contain “Docket No. 2001-NM-121-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 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.

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FOR FURTHER INFORMATION CONTACT:

Natalie Phan-Tran, Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5343; fax (562) 627-5210.

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SUPPLEMENTARY INFORMATION:

Comments Invited

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 2001-NM-121-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. 2001-NM-121-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The FAA has received a report of a fault alert of the electrical power generator system with smoke in the right aft galley area on a McDonnell Douglas Model MD-11 series airplane. The affected airplane had accumulated 28,867 total flight hours and 4,878 total flight cycles. Investigation revealed that the parallel power feeder cable of the number 2 Integrated Drive Generator (IDG) was burned through 30 percent due to chafing on the aft track of door R4. The parallel power feeder cables on Model MD-11 and DC-10 series airplanes, and Model MD-10-10F and MD-10-30F series airplanes are routed the same at the aft track of door R4. Wire chafing of the parallel power feeder cables of the number 2 generator, if not corrected, could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the aft door panel area.

Other Relevant Rulemaking

On August 14, 2001, the FAA issued AD 2001-17-08, amendment 39-12399 (66 FR 44043, August 22, 2001), which applies to certain McDonnell Douglas Model MD-11 series airplanes. That AD is intended to prevent chafing and Start Printed Page 551arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. The AD requires a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 IDG; repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG.

Explanation of Relevant Service Information

The FAA has reviewed and approved Boeing Alert Service Bulletin DC10-24A170, Revision 01, dated September 25, 2001, which describes procedures for a one-time general visual inspection of the parallel power feeder cables of the number 2 generator for chafing and structure damage; repositioning of the cables; and repair, if necessary. Accomplishment of the actions specified in the alert 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 alert service bulletin described previously.

Cost Impact

There are approximately 231 Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-10-30F series airplanes of the affected design in the worldwide fleet. The FAA estimates that 157 airplanes of U.S. registry would be affected by this proposed AD.

It would take approximately 1 work hour per airplane to accomplish the proposed inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection proposed by this AD on U.S. operators is estimated to be $9,420, or $60 per airplane.

It would take approximately 2 work hours per airplane to accomplish the proposed repositioning of cables, at an average labor rate of $60 per work hour. Required parts would cost approximately $646 per airplane. Based on these figures, the cost impact of the repositioning of cables proposed by this AD on U.S. operators is estimated to be $120,262, or $766 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.

Regulatory Impact

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.

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List of Subjects in 14 CFR Part 39

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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:

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PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

McDonnell Douglas: Docket 2001-NM-121-AD.

Applicability: Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-10-30F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin DC10-24A170, Revision 01, dated September 25, 2001.

Note 1:

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 wire chafing of the parallel power feeder cables of the number 2 generator, which, if not corrected, could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the aft door panel area, accomplish the following:

Inspection and Follow-On Actions

(a) Within 6 months after the effective date of this AD, do a one-time general visual inspection of the parallel power feeder cables of the number 2 generator for chafing and structure damage, per Boeing Alert Service Bulletin DC10-24A170, Revision 01, dated September 25, 2001.

(1) Condition 1. If no chafing or structure damage is found: At the next scheduled maintenance visit, but no later than 6 months after the effective date of this AD, reposition the cables per the alert service bulletin.

(2) Condition 2. If any chafing or structure damage is found: Prior to further flight, repair the cable and damaged adjacent structure, as applicable, and reposition the cables, per the alert service bulletin.

Note 2:

For the purposes of this AD, a general visual inspection is defined as “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

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, Los Angeles Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO.

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Note 3:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.

Special Flight Permit

(c) 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.

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Issued in Renton, Washington, on December 21, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 02-209 Filed 1-3-02; 8:45 am]

BILLING CODE 4910-13-P