[Federal Register Volume 68, Number 142 (Thursday, July 24, 2003)]
[Proposed Rules]
[Pages 43695-43698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-18795]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-163-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

[[Page 43696]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 series airplanes, that currently requires an inspection to 
detect chafing or damage of the electrical wires leading to the 
terminal strips in the center accessory compartment (CAC) area, and 
corrective actions if necessary. That AD also currently requires 
revising the wire connection stack up of certain cable terminals at the 
electrical power center bays in the CAC, and replacing certain terminal 
strips with new strips and removing applicable nameplates at electrical 
power center bays. This action would require additional actions for 
improving the terminal strips and would revise the applicability of the 
existing AD to include additional airplanes. This proposal is prompted 
by issuance of revised service information. The actions specified by 
the proposed AD are intended to prevent arcing and sparking damage to 
the power feeder cables, terminal strips, and adjacent structure, and 
consequent smoke and fire in the CAC.

DATES: Comments must be received by September 8, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-163-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. 2001-NM-163-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 for Windows 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.

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:

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 2001-NM-163-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. 2001-NM-163-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On November 22, 2000, the FAA issued airworthiness directive (AD) 
2000-24-12, amendment 39-12019 (65 FR 75615, December 4, 2000), 
applicable to certain McDonnell Douglas Model MD-11 series airplanes, 
to require an inspection to detect chafing or damage of the electrical 
wires leading to the terminal strips in the center accessory 
compartment (CAC) area, and corrective actions if necessary. That AD 
also requires revising the wire connection stack up of certain cable 
terminals at the electrical power center bays in the CAC, and replacing 
certain terminal strips with new strips and removing applicable 
nameplates at electrical power center bays. That action was prompted by 
an incident of arcing between a power feeder cable and terminal strip 
support bracket. The requirements of that AD are intended to prevent 
arcing and sparking damage to the power feeder cables, terminal strips, 
and adjacent structure, and consequent smoke and fire in the CAC.

Other Related Rulemaking

    We, in conjunction with Boeing and operators of Model MD-11 and -
11F airplanes, have reviewed all aspects of the service history of 
those airplanes to identify potential unsafe conditions and to take 
appropriate corrective actions. This proposed AD is one of a series of 
corrective actions identified during that process. We have previously 
issued several other ADs and may consider further rulemaking actions to 
address the remaining identified unsafe conditions.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2000-24-12, we have reviewed and approved 
Revision 02 of Boeing Alert Service Bulletin MD11-24A097, including 
Evaluation Form, dated December 4, 2002 (the original issue of the 
service bulletin was referenced in AD 2000-24-12 as the appropriate 
source of service information for accomplishing the required actions). 
Revision 02 provides additional terminal strip information; adds 
airplanes to the effectivity; and corrects part numbers for the 
terminal stud stack up washers, which were inadvertently called out 
incorrectly in the original issue of this service bulletin. More work 
is necessary on all airplanes changed per the original issue and 
Revision 01 of the service bulletin.
    For certain airplanes, Revision 02 of the service bulletin 
describes procedures for:
    [sbull] Revising the wire connection stack up of the cable 
terminals at the

[[Page 43697]]

electrical power center bays in the CAC, as applicable, and doing a 
one-time general visual inspection of the surrounding structure and 
electrical cables for chafing or damage;
    [sbull] Replacing terminal strips, removing the applicable 
nameplate at the electrical power center bays 1, 2, and 3 in the CAC, 
and doing a general visual inspection of the surrounding structure and 
electrical cables for arcing damage.
    For certain other airplanes, Revision 02 of the service bulletin 
also describes procedures for relocating the terminal strip, and doing 
a general visual inspection of the surrounding structure and electrical 
cables for arcing damage.
    If any chafing or damage is detected during any general visual 
inspection, Revision 02 of the service bulletin describes procedures 
for repairing or replacing the damaged or chafed component with new or 
serviceable components.
    Accomplishment of the actions specified in Revision 02 of the 
service bulletin is intended to adequately address the identified 
unsafe condition.

Explanation of Change to Applicability

    The applicability of this notice of proposed rulemaking (NRPM) 
differs from AD 2000-24-12 in that it identifies model designations as 
published in the most recent type certificate data sheet for the 
affected models, and references Revision 02 of the service bulletin, 
which includes additional airplanes that are subject to the identified 
unsafe condition.

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 supersede AD 2000-24-12 to require accomplishment of 
the applicable actions specified in Revision 02 of the service bulletin 
described previously; except as discussed below.

Differences Between Proposed AD and Service Bulletin

    Operators should note that Revision 02 of the service bulletin 
specifies to repair damage or chafed structure per the Structural 
Repair Manual (SRM). However, the SRM does not provide adequate 
procedures for repair of certain structural material. Therefore, this 
proposed AD would require the repair of damaged or chafed structure 
that is not covered in the SRM to be accomplished per a method approved 
by the FAA.
    In addition, Revision 02 of the service bulletin specifies to use 
the form located in the Appendix for reporting inspection findings to 
the airplane manufacturer. Although the service bulletin references a 
reporting requirement, such reporting is not required by this AD. The 
airplane manufacturer has also informed us that it inadvertently 
published the service bulletin without the Appendix.

Changes to 14 CFR Part 39/Effect on the 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.

Cost Impact

    There are approximately 163 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 73 
airplanes of U.S. registry would be affected by this proposed AD.
    The new actions that are proposed in this AD action would take 
approximately between 1 and 7 work hours per airplane (depending on the 
airplane configuration) to accomplish, at an average labor rate of $65 
per work hour. Required parts would cost approximately between $721 and 
$2,035 per airplane (depending on the airplane configuration). Based on 
these figures, the cost impact of the proposed requirements of this AD 
on U.S. operators is estimated to be between $786 and $2,490 per 
airplane (depending on the airplane configuration).
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
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 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 removing amendment 39-12019 (65 FR 
75615, December 4, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2001-NM-163-AD. Supersedes AD 2000-24-12, 
Amendment 39-12019.

    Applicability: Model MD-11 and -11F airplanes, as listed in 
Boeing Alert Service Bulletin MD11-24A097, Revision 02, dated 
December 4, 2002; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent arcing and sparking damage to the power feeder 
cables, terminal strips, and adjacent structure, and consequent 
smoke and fire in the center accessory compartment (CAC), accomplish 
the following:

[[Page 43698]]

Revising Wire Connection Stack Up, Inspecting, Replacing Terminal 
Strips, Removing the Nameplate, and Relocating Terminal Strips; as 
Applicable

    (a) For Groups 1 through 6 airplanes as listed in Boeing Alert 
Service Bulletin MD11-24A097, Revision 02, dated December 4, 2002: 
Within 12 months after the effective date of this AD, do the actions 
specified in paragraphs (a)(1) and (a)(2) of this AD per the service 
bulletin. Although the service bulletin references a reporting 
requirement, such reporting is not required by this AD.
    (1) Revise the wire connection stack up of the cable terminals 
at the electrical power center bays 1, 2, and 3 in the CAC, as 
applicable, and do a one-time general visual inspection of the 
surrounding structure and electrical cables for chafing or damage.

    Note: 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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

    (2) Replace the terminal strips and remove the applicable 
nameplate at the electrical power center bays 1, 2, and 3 in the 
CAC, and do a general visual inspection of the surrounding structure 
and electrical cables for arcing damage.
    (b) For Group 7 airplanes as listed in Boeing Alert Service 
Bulletin MD11-24A097, Revision 02, dated December 4, 2002: Within 12 
months after the effective date of this AD, relocate the terminal 
strip, and do a general visual inspection of the surrounding 
structure and electrical cables for arcing damage, per the service 
bulletin. Although the service bulletin references a reporting 
requirement, such reporting is not required by this AD.

Corrective Action

    (c) If any chafing or damage is detected during any general 
visual inspection required by this AD, before further flight, repair 
or replace the damaged or chafed component with new or serviceable 
components, per Boeing Alert Service Bulletin MD11-24A097, Revision 
02, dated December 4, 2002; except if the type of structural 
material that has been affected is not covered in the Structural 
Repair Manual (SRM), repair per a method approved by the Manager, 
Los Angeles Aircraft Certification Office (ACO), FAA. In addition, 
although the service bulletin references a reporting requirement, 
such reporting is not required by this AD.

Credit for Earlier Service Bulletins

    (d) Applicable actions specified in this AD accomplished before 
the effective date of this AD per McDonnell Douglas Alert Service 
Bulletin MD11-24A097, dated April 3, 2000; or Revision 01, dated 
July 12, 2001, are acceptable for compliance with the applicable 
requirements of this AD.

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 for this AD.

    Issued in Renton, Washington, on July 17, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-18795 Filed 7-23-03; 8:45 am]
BILLING CODE 4910-13-P