Airworthiness directives: McDonnell Douglas,
[Federal Register: October 17, 2003 (Volume 68, Number 201)]
[Rules and Regulations]
[Page 59709-59711]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17oc03-3]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. 2001-NM-57-AD; Amendment 39-13340; AD 2003-21-05]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
SUMMARY: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment requires a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed-through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The actions specified by this AD are intended to prevent the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit. This action is intended to address the identified unsafe condition.
DATES: Effective November 21, 2003.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 21, 2003.
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 FAA, 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: Brett Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
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Aviation Regulations (14 CFR part 39) by superseding AD 2000-03-13, amendment 39-11572 (65 FR 8028, February 17, 2000), which is applicable to certain McDonnell Douglas Model MD-11 airplanes, was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on July 24, 2003 (68 FR 43686). The action proposed to require a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed- through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The action also specified new corrective actions.
Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the supplemental NPRM 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 (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.
Cost Impact
There are approximately 193 airplanes of the affected design in the worldwide fleet. The FAA estimates that 62 airplanes of U.S. registry will be affected by this AD.
The actions that are required by this AD will take approximately 2 work hours per airplane to accomplish, at an average labor rate of $65 per work hour. Required parts will cost approximately $407 per airplane. Based on these figures, the cost impact of the requirements of this AD on U.S. operators is estimated to be $33,294, or $537 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. The manufacturer may cover the cost of replacement parts associated with this AD, subject to warranty conditions. Manufacturer warranty remedies may also be available for labor costs associated with this AD. As a result, the costs attributable to this AD may be less than stated above.
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
0 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
0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0 2. Section 39.13 is amended by removing amendment 39-11572 (65 FR 8028, February 17, 2000), and by adding a new airworthiness directive (AD), amendment 39-13340, to read as follows:
2003-21-05 McDonnell Douglas: Amendment 39-13340. Docket 2001-NM-57- AD. Supersedes AD 2000-03-13, Amendment 39-11572.
Applicability: Model MD-11 airplanes, as listed in Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002; certificated in any category.
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 (d)(1) 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 the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit, accomplish the following:
Inspection
(a) Within 1 year after the effective date of this AD, do a one- time detailed inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires, per Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002.
Note 2: For the purposes of this AD, a detailed inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror,
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magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.''
Condition 1: No Damaged or Chafed Wire
(b) If no damaged or chafed wire is detected during the detailed inspection required by paragraph (a) of this AD, before further flight, revise the wire bundle support clamp installation, per Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002.
Condition 2: Any Damaged or Chafed Wire
(c) If any damaged or chafed wire is detected during the detailed inspection required by paragraph (a) of this AD, before further flight, repair wiring, and revise the wire bundle support clamp installation, per Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002.
Alternative Methods of Compliance
(d)(1) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD.
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.
(2) Alternative methods of compliance, approved previously in accordance with AD 2000-03-13, amendment 39-11572, are approved as alternative methods of compliance with this AD.
Incorporation by Reference
(e) The actions shall be done in accordance with Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002. 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). 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; 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 November 21, 2003.
Issued in Renton, Washington, on October 9, 2003. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-26116 Filed 10-16-03; 8:45 am]
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