[Federal Register Volume 68, Number 229 (Friday, November 28, 2003)]
[Proposed Rules]
[Pages 66768-66770]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29699]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-292-AD]
RIN 2120-AA64


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

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 certain McDonnell Douglas Model 
MD-11 and MD-11F airplanes. This proposal would require 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: Comments must be received by January 12, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-292-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-292-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 or 2000 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.

FOR FURTHER INFORMATION CONTACT: Samuel S. Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5338; fax (562) 627-5210.

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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2002-NM-292-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. 2002-NM-292-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

[[Page 66769]]

Discussion

    The FAA has received reports of cracks and damage to the transfer 
pipe assembly installation for the tail tank on McDonnell Douglas Model 
MD-11 airplanes. The support brackets and clamps for the refuel and 
fuel transfer lines of the tail fuel tank are being cracked and 
damaged, resulting in chafing and denting of the transfer pipe 
assembly. The cause of the cracks and damage is transient pressure 
surges that are higher than designed for the fuel transfer piping 
configuration during fuel transfer operations. This condition, if not 
corrected, could result in damage and cracks to the transfer pipe 
assembly installation for the tail tank, which could result in fuel 
leakage and possible ignition.
    The subject area on certain Model MD-11F airplanes is almost 
identical to that on the affected Model MD-11 airplanes. Therefore, 
those MD-11F airplanes may be subject to the unsafe condition revealed 
on the MD-11 airplanes.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin MD11-28A110, dated May 2, 2000, which describes procedures for 
performing repetitive inspections of the transfer pipe assembly 
installation for the tail tank for damage and cracks; and repairing 
and/or replacing any damaged or cracked part with a serviceable part.

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 service bulletin described previously. Although the service 
bulletin referenced in the proposed AD specifies to submit certain 
information to the manufacturer, the proposed AD does not include such 
a requirement.

Clarification of Service Bulletin Applicability

    The FAA points out that McDonnell Douglas Model MD-11F airplanes 
are not specifically identified in the service bulletin. However, those 
airplanes are identified by manufacturer's fuselage numbers in the 
service bulletin effectivity listing. Therefore, the FAA has revised 
the applicability in the NPRM to include Model MD-11F airplanes, in 
addition to Model MD-11 airplanes.

Interim Action

    This proposed 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 proposed 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 
would be affected by this proposed AD, that it would take approximately 
2 work hours per airplane to accomplish the proposed inspection, and 
that the average labor rate is $65 per work hour. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $7,800, or $130 per airplane, per inspection cycle.
    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. Manufacturer warranty 
remedies may be available for labor costs associated with this proposed 
AD. As a result, the costs attributable to the proposed AD may be less 
than stated above.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

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:

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.


Sec.  39.13  [Amended]

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

McDonnell Douglas: 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

[[Page 66770]]

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 serviceable 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, FAA, is authorized to approve 
alternative methods of compliance for this AD.

    Issued in Renton, Washington, on November 21, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-29699 Filed 11-26-03; 8:45 am]
BILLING CODE 4910-13-P