[Federal Register Volume 68, Number 117 (Wednesday, June 18, 2003)]
[Proposed Rules]
[Pages 36520-36523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15334]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-164-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
MD-11 and -11F airplanes. This proposal would require an initial 
general visual inspection of the power feeder cables of the integrated 
drive generator (IDG) and the fuel feed lines of engine plyons No. 1 
and No. 3 on the wings for proper clearance and damage; corrective 
actions if necessary; and repetitive general visual inspections and a 
terminating action for the repetitive inspections. This action is 
necessary to prevent potential chafing of the power feeder cables of 
the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent 
arcing on the fuel lines in the engine pylons and possible fuel fire. 
This action is intended to address the identified unsafe condition.

DATES: Comments must be received by August 4, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-164-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-16-4AD'' in the subject line and need not 
be submitted

[[Page 36521]]

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; or at the FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712.

FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; 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-164-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-164-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    As part of its practice of re-examining all aspects of the service 
experience of a particular aircraft whenever an accident occurs, the 
FAA has become aware of reports indicating that the power feeder cables 
of the integrated drive generator (IDG) are riding against structure 
and fuel lines in engine pylons No. 1 and No. 3 on the wings of certain 
McDonnell Douglas Model MD-11 and -11F airplanes. The cables are routed 
too closely to the components. This condition, if not corrected, could 
result in potential chafing of the power feeder cables of the IDG in 
engine pylons No. 1 and No. 3 on the wings, and consequent arcing on 
the fuel lines in the engine pylons and possible fuel fire.

Other Related Rulemaking

    The FAA, in conjunction with Boeing and operators of Model MD-11 
and -11F airplanes, has reviewed all aspects of the service history of 
those airplanes to identify potential unsafe conditions and to take 
appropriate corrective actions. This proposed airworthiness directive 
(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.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Alert Service Bulletin MD11-
54A011, Revision 02, dated May 31, 2002. The service bulletin describes 
procedures for an initial general visual inspection of the power feeder 
cables of the IDG and the fuel feed lines of engine plyons No. 1 and 3 
on the wings for proper clearance and damage; corrective action if 
necessary; and repetitive general visual inspections and a terminating 
action for the repetitive inspections. The corrective actions include:
    [sbull] Repositioning cables with improper clearance; and
    [sbull] Repairing damage or replacing damaged cables or fuel feed 
lines with new or serviceable cables or fuel feed lines.
    The terminating action involves:
    [sbull] Installing brackets to support the IDG harness;
    [sbull] Installing new clamps on the power feeder cables of the IDG 
of engine pylons No. 1 and No. 3; and
    [sbull] Replacing the existing fairlead with a new clamp, and 
installing new tape; as applicable.
    Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.
    Boeing also has issued Information Notice MD11-54A011 R02 IN 02, 
dated July 11, 2002. The information notice informs operators of a 
typographical error for the string tie part number (P/N) specified in 
the Boeing Alert Service Bulletin MD11-54A011, Revision 02. The service 
bulletin specifies string tie P/N 190L0F21G/A; the correct P/N is 109 
LOF 21G/A.

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.

Clarification of Procedures in Service Bulletin

    Boeing has informed us that, although the service bulletin 
specifies two options (i.e., ``Option 1'' and ``Option 2'') for 
Conditions 1 through 3 findings, these actions are not optional. The 
intent is that the actions specified in Option 1 be accomplished until 
the actions specified in Option 2 are accomplished at a later time. If 
an operator elects to accomplish the actions specified in Option 2 
before the actions specified in Option 1, the actions specified in 
Option 1 do not need to be accomplished.

Changes to 14 CFR part 39/Effect on the Proposed AD

    On July 10, 2002, we 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

[[Page 36522]]

AMOCs is identified in each individual AD.

Cost Impact

    There are approximately 195 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 74 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 1 work hour per airplane to accomplish the 
proposed inspection, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be $4,440, or $60 per airplane, per 
inspection cycle.
    It would take approximately 4 work hours per airplane to accomplish 
the terminating action, at an average labor rate of $60 per work hour. 
Required parts would cost approximately $91 per airplane. Based on 
these figures, the cost impact of this terminating action is estimated 
to be $24,494, or $331 per airplane.
    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 2001-NM-164-AD.
    Applicability: Model MD-11 and -11F airplanes, as listed in 
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May 
31, 2002; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent potential chafing of the power feeder cables of the 
integrated drive generator (IDG) in engine pylons No. 1 and No. 3 on 
the wings, and consequent arcing on the fuel lines in the engine 
pylons and possible fuel fire, accomplish the following:

    Note 1:
    Boeing has issued Information Notice MD11-54A011 R02 IN 02, 
dated July 11, 2002. The information notice informs operators of a 
typographical error for the string tie part number (P/N) specified 
in the Boeing Alert Service Bulletin MD11-54A011, Revision 02. The 
service bulletin specifies string tie P/N 190L0F21G/A; the correct 
P/N is 109 LOF 21G/A.

Initial Inspection

    (a) Within 30 days after the effective date of this AD, do a 
general visual inspection of the power feeder cables of the IDG and 
the fuel feed lines of engine pylons No. 1 and 3 on the wings for 
proper clearance and damage, per Boeing Alert Service Bulletin MD11-
54A011, Revision 02, dated May 31, 2002.

    Note 2:
    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.''

Condition 1: Proper Clearance and No Damage

    (b) If proper clearance exists and no damage is detected during 
any inspection required by paragraph (a) of this AD, do the 
action(s) specified in paragraphs (b)(1), (b)(2), and (b)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002.
    (1) For Group 1 and Group 2 airplanes identified in the service 
bulletin: Repeat the inspection required by paragraph (a) of this AD 
every 6 months until the modification required by paragraph (b)(2) 
or (b)(3) of this AD, as applicable, has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, install the 
brackets to support the IDG harness, and install new clamps on the 
power feeder cables of the IDG of the No. 1 and No. 3 pylons.
    (3) For Group 2 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, replace the 
existing fairlead with a new clamp, and install new tape.

Condition 2: Improper Clearance and No Damage

    (c) If improper clearance exists and no damage is detected 
during any inspection required by paragraph (a) of this AD, do the 
action(s) specified in paragraphs (c)(1), (c)(2), and (c)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002.
    (1) For Group 1 and Group 2 airplanes identified in the service 
bulletin: Before further flight, reposition cables, and repeat the 
inspection required by paragraph (a) of this AD every 6 months until 
the modification required by paragraph (c)(2) or (c)(3) of this AD, 
as applicable, has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, install the 
brackets to support the IDG harness, and install new clamps on the 
power feeder cables of the IDG of engine pylons No. 1 and No. 3.
    (3) For Group 2 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, replace the 
existing fairlead with a new clamp, and install new tape.

Condition 3: Improper Clearance and Damage Detected

    (d) If improper clearance exists and any damage is detected 
during any inspection required by paragraph (a) of this AD, do the 
action(s) specified in paragraphs (d)(1), (d)(2), and (d)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002.
    (1) For Group 1 and Group 2 airplanes identified in the service 
bulletin: Before further flight, reposition cables; repair damage or 
replace damaged cables or fuel feed lines with new or serviceable 
cables or

[[Page 36523]]

fuel feed lines; and repeat the inspection required by paragraph (a) 
of this AD every 6 months until the modification required by 
paragraph (d)(2) or (d)(3) of this AD, as applicable, has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, install the 
brackets to support the IDG harness, and install new clamps on the 
power feeder cables of the IDG of engine pylons No. 1 and No. 3.
    (3) For Group 2 airplanes identified in the service bulletin: 
Within 18 months after the effective date of this AD, replace the 
existing fairlead with a new clamp, and install new tape.

Credit for Earlier Service Bulletin

    (e) Accomplishment of the actions specified in this AD before 
the effective date of this AD per Boeing Alert Service Bulletin 
MD11-54A011, Revision 01, dated August 22, 2002, is acceptable for 
compliance with the requirements of this AD.

Alternative Methods of Compliance

    (f) 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 June 12, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-15334 Filed 6-17-03; 8:45 am]
BILLING CODE 4910-13-U