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

[Federal Register Volume 68, Number 233 (Thursday, December 4, 2003)]
[Rules and Regulations]
[Pages 67796-67798]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30110]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-70-AD; Amendment 39-13378; AD 2003-24-09]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell

[[Page 67797]]

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 amendment revises the applicability of the existing AD by adding 
certain airplanes and removing certain other airplanes. The actions 
specified by this 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: Effective January 8, 2004.
    The incorporation by reference of Boeing Alert Service Bulletin 
MD11-24A157, Revision 01, dated March 11, 2003, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
January 8, 2004.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-24A157, dated August 10, 2000, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of September 26, 2001 (66 FR 44043, August 22, 2001).

ADDRESSES: The service information referenced in this AD 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 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2001-17-08, 
amendment 39-12399 (66 FR 44043, August 22, 2001), which is applicable 
to certain McDonnell Douglas Model MD-11 series airplanes, was 
published in the Federal Register on August 15, 2003 (68 FR 48835). The 
action proposed to continue 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 also proposed to 
revise the applicability of the existing AD by adding certain airplanes 
and removing certain other airplanes.

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.

Conclusion

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

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 
will be affected by this 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 
required by this AD will take approximately 5 work hours per airplane 
to accomplish, at an average labor rate of $65 per work hour. Required 
parts will cost approximately $673 per airplane. Based on these 
figures, the cost impact of the 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 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 AD, subject to warranty 
conditions. Manufacturer warranty remedies may also 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 removing amendment 39-12399 (66 FR 
44043, August 22, 2001), and by adding a new airworthiness directive 
(AD),

[[Page 67798]]

amendment 39-13378, to read as follows:

2003-24-09 McDonnell Douglas: Amendment 39-13378. 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
------------------------------------------------------------------------
           Airplanes--             Compliance time--  Service bulletin--
------------------------------------------------------------------------
(1) For Group 1 airplanes listed  Within 6 months     McDonnell Douglas
 in Boeing Alert Service           after September     Alert Service
 Bulletin MD11-24A157, Revision    26, 2001 (the       Bulletin MD11-
 01, dated March 11, 2003.         effective date of   24A157, dated
                                   AD 2001-17-08,      August 10, 2000.
                                   amendment 39-
                                   12399).
(2) For Group 2 airplanes listed  Within 6 months     Boeing Alert
 in Boeing Alert Service           after the           Service Bulletin
 Bulletin MD11-24A157, Revision    effective date of   MD11-24A157,
 01, dated March 11, 2003.         this AD.            Revision 01,
                                                       dated March 11,
                                                       2003.
------------------------------------------------------------------------


    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)

    (3) 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)

    (4) 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.

Incorporation by Reference

    (c) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-24A157, dated August 10, 2000; 
or Boeing Alert Service Bulletin MD11-24A157, Revision 01, dated 
March 11, 2003; as applicable.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin MD11-24A157, Revision 01, dated March 11, 2003, is approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-24A157, dated August 10, 2000, was approved 
previously by the Director of the Federal Register as of September 
26, 2001 (66 FR 44043, August 22, 2001).
    (3) Copies 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). 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

    (d) This amendment becomes effective on January 8, 2004.

    Issued in Renton, Washington, on November 26, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-30110 Filed 12-3-03; 8:45 am]
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