[Federal Register Volume 69, Number 75 (Monday, April 19, 2004)]
[Rules and Regulations]
[Pages 20818-20819]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-8539]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-292-AD; Amendment 39-13573; AD 2004-08-04]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model MD-11 and MD-11F 
airplanes, that requires repetitive inspections of the transfer pipe 
assembly installation for the tail tank for damage and cracks, and 
corrective action, if necessary. This action is necessary to detect and 
correct damage and cracks to the transfer pipe assembly installation 
for the tail tank, which could result in fuel leakage and possible 
ignition. This action is intended to address the identified unsafe 
condition.

DATES: Effective May 24, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 24, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, 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: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; 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 certain McDonnell Douglas Model 
MD-11 and MD-11F airplanes was published in the Federal Register on 
November 28, 2003 (68 FR 66768). That action proposed to require 
repetitive inspections of the transfer pipe assembly installation for 
the tail tank for damage and cracks, and corrective action, if 
necessary.

Comments

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

[[Page 20819]]

Conclusion

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

Interim Action

    This AD is considered to be interim action. The manufacturer has 
advised that it currently is developing Service Bulletin MD11-28-111 
that will address the unsafe condition addressed by this AD. Once this 
new service bulletin is developed, approved, and available, the FAA may 
consider additional rulemaking.

Cost Impact

    There are approximately 187 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 60 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 2 work 
hours per airplane to accomplish the required inspection, and that the 
average labor rate is $65 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $7,800, or 
$130 per airplane, per inspection cycle.
    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. Manufacturer warranty remedies may be available 
for labor costs associated with this AD. As a result, the costs 
attributable to the 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 adding the following new airworthiness 
directive:

2004-08-04 McDonnell Douglas: Amendment 39-13573. Docket 2002-NM-
292-AD.

    Applicability: Model MD-11 and MD-11F airplanes, as listed in 
McDonnell Douglas Alert Service Bulletin MD11-28A110, dated May 2, 
2000; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct damage and cracks to the transfer pipe 
assembly installation for the tail tank, which could result in fuel 
leakage and possible ignition, accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-28A110, dated May 2, 2000. Although the service 
bulletin referenced in this AD specifies to submit certain 
information to the manufacturer, this AD does not include such a 
requirement.

Initial Inspection

    (b) Within 700 flight hours from the effective date of this AD, 
perform a general visual inspection to detect any damage and 
cracking on the transfer pipe assembly installation for the tail 
tank, in accordance with the service bulletin.

    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.''

Condition 1 (No Damage/Cracking)

    (c) If no damage or cracking to the transfer pipe assembly 
installation for the tail tank is found during the inspection 
required by paragraph (b) of this AD, repeat that inspection 
thereafter at intervals not to exceed 700 flight hours.

Condition 2 (Damage/Cracking found)

    (d) If any damage or cracking to the transfer pipe assembly 
installation for the tail tank is found during the inspection 
required by paragraph (b) of this AD, before further flight, repair 
and/or replace any damaged or cracked part with a servicable part, 
per the service bulletin. Repeat that inspection thereafter at 
intervals not to exceed 700 flight hours.

Alternative Methods of Compliance

    (e) 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.

Incorporation by Reference

    (f) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-28A110, dated May 2, 2000. 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 Airplanes, 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

    (g) This amendment becomes effective on May 24, 2004.

    Issued in Renton, Washington, on April 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-8539 Filed 4-16-04; 8:45 am]
BILLING CODE 4910-13-P