Airworthiness Directives; McDonnell Douglas DC-10-30 Airplane

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to a single McDonnell Douglas Model DC-10-30 airplane, that requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/transfer pump connectors; and corrective actions, if necessary. This action is necessary to prevent arcing of connectors in the fuel boost/transfer pump circuit, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.

DATES:

Effective May 15, 2003.

The incorporation by reference of Boeing Alert Service Bulletin DC10-28A228, including Appendix, Revision 02, dated December 7, 2001, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 12, 2002 (67 FR 45053, July 8, 2002).

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; 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:

Philip C. Kush, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627-5263; fax (562) 627-5210.

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 a single McDonnell Douglas Model DC-10-30 airplane was published in the Federal Register on January 3, 2003 (68 FR 320). That action proposed to require repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/transfer pump connectors; and corrective actions, if necessary.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

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. However, for clarity and consistency in this final rule, we have retained the language of the NPRM regarding that material.

Interim Action

This is considered to be interim action. The manufacturer has advised that it currently is developing a modification that will address the unsafe condition addressed by this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking.

Cost Impact

This AD applies to one McDonnell Douglas Model DC-10-30 airplane and that airplane is of U.S. registry. It will take approximately 65 work hours to accomplish the required tests and inspections on that airplane, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the AD on the single U.S. operator is estimated to be $3,900, per test or inspection cycle.

The cost impact figure discussed above is based on assumptions that the operator has not yet accomplished the requirements of this AD action, and that the operator would not 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.

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

2003-07-14 McDonnell Douglas: Amendment 39-13110. Docket 2002-NM-134-AD.

Applicability: Model DC-10-30 airplane, fuselage number 0106, certificated in any category.

Note 1:

The requirements of this AD are identical to those in AD 2002-13-10, amendment 39-12798, which applies to Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and -40F airplanes, and Model MD-10-10F and -30F airplanes; as listed in Boeing Alert Service Bulletin DC10-28A228, including Appendix, Revision 01, dated July 16, 2001; and Model MD-11 and -11F airplanes, as listed in Boeing Alert Service Bulletin MD11-28A112, including Appendix, dated December 11, 2000.

Note 2:

Airplane fuel tanks on which the fuel/boost pump and wiring connector have been physically removed and the fuel tank made inoperable are not subject to the requirements of this AD.

Note 3:

This AD applies to the airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. If the airplane has 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 (c) 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 arcing of connectors of the fuel boost/transfer pump, which could result in a fire or explosion of the fuel tank, accomplish the following:

Repetitive Tests and Inspections

(a) Within 6 months after the effective date of this AD, do tests (using a digital multi-meter and Quadtech 1864 megohm meter or an equivalent megohm meter that meets current and voltage requirements, as specified in the service bulletin) for electrical continuity and resistance and a general visual inspection to detect discrepancies (e.g., damage, arcing, loose parts, wear) of the fuel boost/transfer pump (alternating current pumping unit) by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-28A228, including Appendix, Revision 02, dated December 7, 2001. Repeat the tests and inspection thereafter every 18 months. Although the service bulletin refers to a reporting requirement using the Appendix of the service bulletin, such reporting is not required.

Note 4:

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.”

Corrective Actions, If Necessary

(b) If the result of any test required by paragraph (a) of this AD is outside the limits specified in the service bulletin identified in that paragraph, or if any discrepancy is detected during any inspection required by paragraph (a) of this AD, before further flight, accomplish corrective actions (e.g., replacement of connector/wire assembly with serviceable connector/wire assembly, and replacement of the pump with a serviceable fuel boost/transfer pump), as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-28A228, including Appendix, Revision 02, dated December 7, 2001. Although the service bulletin refers to a reporting requirement using the Appendix of the service bulletin, such reporting is not required.

Alternative Methods of Compliance

(c) 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.

Note 5:

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 Permits

(d) 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.

Incorporation by Reference

(e) The actions shall be done in accordance with Boeing Alert Service Bulletin DC10-28A228, including Appendix, Revision 02, dated December 7, 2001. The incorporation by reference of that document was approved previously by the Director of the Federal Register as of August 12, 2002 (67 FR 45053, July 8, 2002). 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; 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

(f) This amendment becomes effective on May 15, 2003.