[Federal Register Volume 68, Number 158 (Friday, August 15, 2003)]
[Proposed Rules]
[Pages 48835-48837]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-20835]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-70-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 supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 series airplanes, that currently requires performing a 
general visual inspection to detect chafing or damage of the parallel 
power feeder cables of the number 2 integrated drive generator (IDG); 
repairing any chafed cable and damaged structure; and repositioning the 
parallel power feeder cables of the number 2 IDG. This action would 
revise the applicability of the existing AD by adding certain airplanes 
and removing certain other airplanes. The actions specified by the 
proposed AD are intended to prevent chafing and arcing of the parallel 
feeder cables of the number 2 IDG, which could result in smoke and/or 
fire in the right aft galley area. This action is intended to address 
the identified unsafe condition.

DATES: Comments must be received by September 29, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-70-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. 2003-NM-70-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: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, 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 2003-NM-70-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. 2003-NM-70-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On August 14, 2001, the FAA issued AD 2001-17-08, amendment 39-
12399 (66 FR 44043, August 22, 2001), applicable to certain McDonnell 
Douglas Model MD-11 series airplanes, to require performing a general 
visual inspection to detect chafing or damage of the parallel power 
feeder cables of the number 2 integrated drive generator (IDG); 
repairing any chafed cable and damaged structure; and repositioning the 
parallel power feeder cables of the number 2 IDG. That action was 
prompted by an incident in which smoke permeated the right aft galley 
area and an electrical power generator system fault alert occurred on a 
McDonnell Douglas Model MD-11

[[Page 48836]]

airplane. The requirements of that AD are intended to prevent chafing 
and arcing of the parallel feeder cables of the number 2 IDG, which 
could result in smoke and/or fire in the right aft galley area.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the airplane manufacturer has 
informed the FAA that it inadvertently omitted 43 airplanes from the 
effectivity listing of McDonnell Douglas Alert Service Bulletin MD11-
24A157, dated August 10, 2000 (which was referenced in AD 2001-17-08 an 
appropriate source of service information for accomplishing the 
required actions) that are subject to the identified unsafe condition 
and included 24 other airplanes that are not subject to the identified 
unsafe condition.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Alert Service Bulletin MD11-
24A157, Revision 01, dated March 11, 2003, which revises the 
effectivity of the initial release of the service bulletin by adding 43 
additional airplanes and removing 24 other airplanes. The inspection, 
repositioning, and corrective actions if necessary specified in 
Revision 01 are essentially identical to those described in initial 
release of the service bulletin. No more work is necessary on airplanes 
changed per the initial release of this service bulletin. 
Accomplishment of the actions specified in the service bulletin is 
intended to adequately address 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 2001-17-08 to require performing a 
general visual inspection to detect chafing or damage of the parallel 
power feeder cables of the number 2 IDG; repairing any chafed cable and 
damaged structure; and repositioning the parallel power feeder cables 
of the number 2 IDG. The proposed AD also would revise the 
applicability of the existing AD by adding certain airplanes and 
removing certain other airplanes. The actions would be required to be 
accomplished in accordance with the applicable service bulletin 
revision described previously.

Explanation of Change to Applicability

    The applicability of AD 2001-17-08 identified the affected 
airplanes as ``Model MD-11 series airplanes, as listed in McDonnell 
Douglas Alert Service Bulletin MD11-24A157, dated August 10, 2000.'' 
Although Model MD-11F airplanes are not specifically identified by 
model name in the applicability of that AD, those airplanes are 
identified by the manufacturer's fuselage numbers in the referenced 
service bulletin. This proposed AD would identify those model 
designations as published in the most recent type certificate data 
sheet for the affected models (i.e., Model MD-11 and -11F airplanes).

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD 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, for purposes of this proposed 
AD, it is only necessary to identify the office authorized to approve 
AMOCs and previously approved AMOCs that are acceptable for compliance 
with the applicable requirements of this proposed AD. Therefore, Note 1 
and paragraph (c) of AD 2001-17-08 are not included in this proposed 
AD, and paragraph (b) of AD 2001-17-08 has been revised in this 
proposed 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 85 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 15 airplanes of U.S. registry 
would be affected by this proposed AD.
    For Group 1 airplanes listed in Boeing Alert Service Bulletin MD11-
24A157, Revision 01, dated March 11, 2003: The actions that are 
currently required by AD 2001-17-08 take approximately 4 work hours per 
airplane to accomplish, at an average labor rate of $65 per work hour. 
Based on these figures, the cost impact of the currently required 
actions on these U.S. operators is estimated to be $260 per airplane.
    For Group 2 airplanes listed in Boeing Alert Service Bulletin MD11-
24A157, Revision 01, dated March 11, 2003: The new actions that are 
proposed in this AD action would take approximately 5 work hours per 
airplane to accomplish, at an average labor rate of $65 per work hour. 
Required parts would cost approximately $673 per airplane. Based on 
these figures, the cost impact of the proposed requirements of this AD 
on these U.S. operators is estimated to be $998 per airplane.
    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. The manufacturer may 
cover the cost of replacement parts associated with this proposed AD, 
subject to warranty conditions. Manufacturer warranty remedies may also 
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

[[Page 48837]]

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 39-12399 (66 FR 
44043, August 22, 2001), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2003-NM-70-AD. Supersedes AD 2001-17-08, 
Amendment 39-12399.

    Applicability: Model MD-11 and -11F airplanes, as listed in 
Boeing Alert Service Bulletin MD11-24A157, Revision 01, dated March 
11, 2003; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing and arcing of the parallel feeder cables of 
the number 2 integrated drive generator (IDG), which could result in 
smoke and/or fire in the right aft galley area, accomplish the 
following:

Inspection

    (a) Do a general visual inspection to detect chafing or damage 
of the parallel power feeder cables of the number 2 IDG at the 
applicable time and per the applicable service bulletin specified in 
Table 1 of this AD. Table 1 is as follows:

               Table 1.--Compliance Time/Service Bulletin
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            Airplanes               Compliance Time    Service Bulletin
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For Group 1 airplanes listed in   Within 6 months     McDonnell Douglas
 Boeing Alert Service Bulletin     after September     Alert Service
 MD11-24A157, Revision 01, dated   26, 2001 (the       Bulletin MD11-
 March 11, 2003.                   effective date of   24A157, dated
                                   AD 2001-17-08,      August 10, 2000.
                                   amendment 39-
                                   12399).
For Group 2 airplanes listed in   Within 6 months     Boeing Alert
 Boeing Alert Service Bulletin     after the           Service Bulletin
 MD11-24A157, Revision 01, dated   effective date of   MD11-24A157,
 March 11, 2003.                   this AD.            Revision 01,
                                                       dated March 11,
                                                       2003.
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    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 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 (No Chafing and No Structure Damage)

    (1) If no chafing and damage is detected, before further flight, 
reposition the parallel power feeder cables of the number 2 IDG, per 
the applicable service bulletin.

Condition 2 (Chafing or Structure Damage)

    (2) If any chafing or damage is detected, before further flight, 
repair the chafed cable and damaged structure, as applicable, and 
reposition the parallel power feeder cables of the number 2 IDG, per 
the applicable service bulletin.

Alternative Methods of Compliance

    (b)(1) 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.
    (2) Alternative methods of compliance, approved previously per 
AD 2001-17-08, amendment 39-12399, are approved as alternative 
methods of compliance with the requirements of this AD.


    Issued in Renton, Washington, on August 11, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-20835 Filed 8-14-03; 8:45 am]
BILLING CODE 4910-13-P