03-31193. Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-10-40F Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires a one-time inspection for damage of the power feeder cables and surrounding structure, and repair if necessary. For certain airplanes, this amendment requires fabricating and installing a power feeder support bracket assembly and clamps at station Y=595.000, left side. For certain other airplanes, this amendment requires installing two power feeder support brackets and clamps at station Y=606.000, left side. This action is necessary to prevent chafing of the external ground power feeder cables against the adjacent structure, which could result in arcing and fire. This action is intended to address the identified unsafe condition.

DATES:

Effective January 27, 2004.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 27, 2004.

ADDRESSES:

The service information referenced in this AD 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 Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

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 [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10 airplanes was published in the Federal Register on September 8, 2003 (68 FR 52870). That action proposed to require a one-time inspection for damage of the power feeder cables and surrounding structure, and repair if necessary. For certain airplanes, that action proposed to require fabricating and installing a power feeder support bracket assembly and clamps at station Y=595.000, left side. For certain other airplanes, that action proposed to require installing two power feeder support brackets and clamps at station Y=606.000, left side.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comment received. The commenter supports the proposal.

Conclusion

After careful review of the available data, including the comment noted above, we have determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact

There are approximately 59 airplanes of the affected design in the worldwide fleet. The FAA estimates that 44 airplanes of U.S. registry will be affected by this AD.

It will take approximately 2 to 3 work hours per airplane to accomplish the required actions, at an average labor rate of $65 per work hour. Required parts will cost approximately $385 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $22,660 to 25,520, or $515 to $580 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this 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 adopted herein will 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 final rule does not have federalism implications under Executive Order 13132.

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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from 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 as follows:

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

§ 39.13

[Amended]

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

2003-25-13 McDonnell Douglas: Amendment 39-13396. Docket 2002-NM-08-AD.

Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-10-40F airplanes; certificated in any category; as listed in Boeing Alert Service Bulletin DC10-24A171, Revision 02, dated March 7, 2003.

Compliance: Required as indicated, unless accomplished previously.

To prevent chafing of the external ground power feeder cables against the adjacent structure, which could result in arcing and fire, accomplish the following:

Inspection

(a) Within 6 months after the effective date of this AD: Perform a general visual inspection for damage of the power feeder cables and surrounding structure, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-24A171, Revision 02, dated March 7, 2003. If any damage is found, repair it before further flight in accordance with the service bulletin. Inspections and repairs done before the effective date of this AD in accordance with Revision 01 of the service bulletin, dated November 6, 2002, are also acceptable for compliance with the requirements of this paragraph.

Note 1:

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 from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight 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.”

Bracket Installation

(b) Within 6 months after the effective date of this AD: Perform the actions specified in paragraphs (b)(1) and (b)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-24A171, Revision 02, dated March 7, 2003. Accomplishment of the actions before the effective date of this AD in accordance with Revision 01 of the service bulletin, dated November 6, 2002, is also acceptable for compliance with the requirements of this paragraph.

(1) For Group 1 and Group 3 airplanes: Fabricate and install a new power feeder support bracket assembly and clamps at station Y=595.000, left side. Bracket fabrication and installation done before the effective date of this AD in accordance with the original issue of the service bulletin, dated October 18, 2001, is also acceptable for compliance with the requirements of paragraph (b)(1) of this AD.

(2) For Group 2 airplanes: Install 2 power feeder support brackets and clamps at station Y=606.000, left side.

Alternative Methods of Compliance

(c) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance for this AD.

Incorporation by Reference

(d) Unless otherwise specified by this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin DC10-24A171, Revision 02, dated March 7, 2003. 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 Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be inspected 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; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

(e) This amendment becomes effective on January 27, 2004.

Issued in Renton, Washington, on December 11, 2003.

Kevin M. Mullin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.