[Federal Register Volume 72, Number 6 (Wednesday, January 10, 2007)]
[Rules and Regulations]
[Pages 1143-1146]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-22536]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25089; Directorate Identifier 2006-NM-091-AD; 
Amendment 39-14873; AD 2007-01-02]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain McDonnell Douglas Model MD-11 and -11F 
airplanes. That AD currently requires an initial general visual 
inspection of the power feeder cables of the integrated drive generator 
(IDG) and the fuel feed lines of engine pylons 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 new AD requires the existing actions, 
and for certain airplanes, this AD requires installation of new clamps 
on the power feeder cables of the IDG of engine pylons No. 1 and No. 3. 
This AD results from reports of IDG power feeder cables riding against 
structure and fuel lines in the No. 1 and No. 3 pylons. We are issuing 
this AD 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.

DATES: This AD becomes effective February 14, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 14, 
2007.
    On February 24, 2004 (69 FR 2657, January 20, 2004), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May 31, 
2002.

[[Page 1144]]


ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for service information 
identified in this AD.

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:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-01-17, amendment 
39-13431 (69 FR 2657, January 20, 2004). The existing AD applies to 
certain McDonnell Douglas Model MD-11 and -11F airplanes. That NPRM was 
published in the Federal Register on June 21, 2006 (71 FR 35578). That 
NPRM proposed to continue to require the existing actions, and for 
certain airplanes, the NPRM proposed to require installation of new 
clamps on the power feeder cables of the integrated drive generator 
(IDG) of engine pylons No. 1 and No. 3.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request to Incorporate by Reference Certain Service Information

    One commenter, the Modification and Replacement Parts Association 
(MARPA), states that if a service document is used as a mandatory 
element of compliance it should not simply be referenced, but should be 
incorporated into the regulatory document.
    We understand MARPA's comment concerning incorporation by 
reference. The Office of the Federal Register (OFR) requires that 
documents that are necessary to accomplish the requirements of the AD 
be incorporated by reference during the final rule phase of rulemaking. 
This final rule incorporates by reference the document necessary for 
the accomplishment of the requirements mandated by this AD. Further, we 
point out that while documents that are incorporated by reference do 
become public information, they do not lose their copyright protection. 
For that reason, we advise the public to contact the manufacturer to 
obtain copies of the referenced service information.

Request To Publish Service Information

    This same commenter, MARPA, also requests that service documents 
referenced in ADs be made available to the public by publishing the 
service documents in either the Federal Register or the Docket 
Management System (DMS). MARPA states that incorporation by reference 
was authorized to reduce the volume of material published in the 
Federal Register. MARPA contends that, with service information readily 
available in electronic formats, it is no longer necessary to have the 
high concern for brevity.
    In regard to the commenter's request that service documents be made 
available to the public by publication in the Federal Register, we 
acknowledge that incorporation by reference was authorized to reduce 
the volume of material published in the Federal Register and the Code 
of Federal Regulations. However, as specified in the Federal Register 
Document Drafting Handbook, the Director of the OFR decides when an 
agency may incorporate material by reference. As the commenter is 
aware, the OFR files documents for public inspection on the workday 
before the date of publication of the rule at its office in Washington, 
DC. As stated in the Federal Register Document Drafting Handbook, when 
documents are filed for public inspection, anyone may inspect or copy 
file documents during the OFR's hours of business. Further questions 
regarding publication of documents in the Federal Register or 
incorporation by reference should be directed to the OFR.
    In regards to the commenter's request to post service bulletins on 
the Department of Transportation's DMS, we are currently in the process 
of reviewing issues surrounding the posting of service bulletins on the 
DMS as part of an AD docket. Once we have thoroughly examined all 
aspects of this issue and have made a final determination, we will 
consider whether our current practice needs to be revised. No change to 
the final rule is necessary in response to this comment.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 195 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 98 Model MD-11 and -11F 
airplanes of U.S. registry.
    The inspections that are required by AD 2004-01-17 and retained in 
this AD take about 1 work hour per airplane, at an average labor rate 
of $80 per work hour. Based on these figures, the estimated cost of the 
currently required actions is $80 per airplane, per inspection cycle.
    The new required inspection will take about 1 work hour per 
airplane, at an average labor rate of $80 per work hour. Based on these 
figures, the estimated cost of the new inspections required in this AD 
for U.S. operators is $7,840, or $80 per airplane, per inspection 
cycle.
    The new required terminating action will take approximately 4 work 
hours per airplane to accomplish, at an average labor rate of $80 per 
work hour. The vendor states that it will supply the parts at no cost 
to the operator. Based on these figures, the estimated cost of the 
terminating action specified in this AD for U.S. operators is $31,360, 
or $320 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation

[[Page 1145]]

is within the scope of that authority because it addresses an unsafe 
condition that is likely to exist or develop on products identified in 
this rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13431 (69 FR 2657, January 20, 2004) and by 
adding the following new airworthiness directive (AD):

2007-01-02 McDonnell Douglas: Amendment 39-14873. Docket No. FAA 
2006-25089; Directorate Identifier 2006-NM-091-AD.

Effective Date

    (a) This AD becomes effective February 14, 2007.

Affected ADs

    (b) This AD supersedes AD 2004-01-17.

Applicability

    (c) This AD applies to McDonnell Douglas Model MD-11 and -11F 
airplanes, as identified in Boeing Alert Service Bulletin MD11-
54A011, Revision 3, dated November 9, 2005; certificated in any 
category.

Unsafe Condition

    (d) This AD results from reports of integrated drive generator 
(IDG) power feeder cables riding against structure and fuel lines in 
the No. 1 and No. 3 pylons. We are issuing this AD 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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2004-01-17

    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 Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May 
31, 2002. The service bulletin specifies string tie P/N 190L0F21G/A; 
the correct P/N is 109 LOF 21G/A.

Initial Inspection

    (f) Within 30 days after February 24, 2004 (the effective date 
of AD 2004-01-17), do a general visual inspection of the power 
feeder cables of the IDG and the fuel feed lines of engine pylons 
No. 1 and No. 3 on the wings for proper clearance and damage, per 
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May 
31, 2002; or Boeing Alert Service Bulletin MD11-54A011, Revision 3, 
dated November 9, 2005.

    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 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 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: Proper Clearance and No Damage

    (g) If proper clearance exists and no damage is detected during 
any inspection required by paragraph (f) of this AD, do the 
action(s) specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin 
MD11-54A011, Revision 3, dated November 9, 2005.
    (1) For Group 1 and Group 2 airplanes identified in the service 
bulletin: Repeat the inspection required by paragraph (f) of this AD 
every 6 months until the modification required by paragraph (g)(2) 
or (g)(3) of this AD, as applicable, has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after February 24, 2004, 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 February 24, 2004, replace the existing 
fairlead with a new clamp, and install new tape.

Condition 2: Improper Clearance and No Damage

    (h) If improper clearance exists and no damage is detected 
during any inspection required by paragraph (f) of this AD, do the 
action(s) specified in paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin 
MD11-54A011, Revision 3, dated November 9, 2005.
    (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 (f) of this AD every 6 months until 
the modification required by paragraph (h)(2) or (h)(3) of this AD, 
as applicable, has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after February 24, 2004, 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 February 24, 2004, replace the existing 
fairlead with a new clamp, and install new tape.

Condition 3: Improper Clearance and Damage Detected

    (i) If improper clearance exists and any damage is detected 
during any inspection required by paragraph (f) of this AD, do the 
action(s) specified in paragraphs (i)(1), (i)(2), and (i)(3) of this 
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin 
MD11-54A011, Revision 3, dated November 9, 2005.
    (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 fuel feed lines; and repeat the inspection required by 
paragraph (f) of this AD every 6 months until the modification 
required by paragraph (i)(2) or (i)(3) of this AD, as applicable, 
has been done.
    (2) For Group 1 airplanes identified in the service bulletin: 
Within 18 months after February 24, 2004, 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.

[[Page 1146]]

    (3) For Group 2 airplanes identified in the service bulletin: 
Within 18 months after February 24, 2004, replace the existing 
fairlead with a new clamp, and install new tape.

New Requirements of This AD

General Visual Inspection

    (j) For airplanes identified as Group 1, configurations 3 and 4, 
and Group 2, configuration 2, in Boeing Alert Service Bulletin (ASB) 
MD11-54A011, Revision 3, dated November 9, 2005: Within 30 days 
after the effective date of this AD, do a general visual inspection 
for proper clearance and damage of the power feeder cables of the 
IDG and the fuel feed lines of engine pylons No. 1 and No. 3 on the 
wings, in accordance with the Accomplishment Instructions of Boeing 
ASB MD11-54A011, Revision 3, dated November 9, 2005.

Condition 1: Proper Clearance and No Damage

    (k) For airplanes identified as Group 1, configurations 3 and 4, 
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3, 
dated November 9, 2005: If proper clearance exists and no damage is 
detected during any inspection required by paragraph (j) of this AD, 
do the actions specified in paragraphs (k)(1), (k)(2), and (k)(3) of 
this AD, as applicable, in accordance with the Accomplishment 
Instructions of Boeing ASB MD11-54A011, Revision 3, dated November 
9, 2005. Accomplishment of the actions specified in paragraph (k)(2) 
or (k)(3) of this AD, as applicable, terminates the inspection 
requirements of paragraph (k)(1) of this AD.
    (1) For Group 1 airplanes, configurations 3 and 4, and Group 2, 
configuration 2: Repeat the inspection required by paragraph (j) of 
this AD thereafter at intervals not to exceed 6 months, until the 
actions specified in paragraph (k)(2) or (k)(3) of this AD, as 
applicable, are accomplished.
    (2) For Group 1 airplanes, configuration 3: Within 18 months 
after the effective date of this AD, install IDG harness support 
brackets and modify the IDG power feeder cable installations.
    (3) For Group 1 airplanes, configuration 4, and Group 2, 
configuration 2: Within 18 months after the effective date of this 
AD, modify the IDG power feeder cable installations.

Condition 2: Improper Clearance and No Damage

    (l) For airplanes identified as Group 1, configurations 3 and 4, 
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3, 
dated November 9, 2005: If improper clearance exists and no damage 
is detected during any inspection required by paragraph (j) of this 
AD, do the actions specified in paragraphs (l)(1), (l)(2), and 
(l)(3) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of Boeing ASB MD11-54A011, Revision 3, 
dated November 9, 2005. Accomplishment of the actions specified in 
paragraph (l)(2) or (l)(3) of this AD, as applicable, terminates the 
repetitive inspections required in paragraph (l)(1) of this AD.
    (1) Before further flight, reposition the cables. Repeat the 
inspection required by paragraph (j) of this AD thereafter at 
intervals not to exceed 6 months, until the actions specified by 
paragraph (l)(2) or (l)(3) of this AD, as applicable, are 
accomplished.
    (2) For Group 1 airplanes, configuration 3: Within 18 months 
after the effective date of this AD, install IDG harness support 
brackets and modify the IDG power feeder cable installations.
    (3) For Group 1 airplanes, configuration 4, and Group 2 
airplanes, configuration 2: Within 18 months after the effective 
date of this AD, modify the IDG power feeder cable installations.

Condition 3: Improper Clearance and Damage Detected

    (m) For airplanes identified as Group 1, configurations 3 and 4, 
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3, 
dated November 9, 2005: If improper clearance exists and there is 
any damage to the cables, structure, or fuel feed line, do the 
actions specified in paragraphs (m)(1), (m)(2), and (m)(3) of this 
AD, as applicable, in accordance with the Accomplishment 
Instructions of Boeing ASB MD11-54A011, Revision 3, dated November 
9, 2005. Accomplishment of the actions specified in paragraph (m)(2) 
or (m)(3) of this AD, as applicable, terminates the repetitive 
inspection requirements of paragraph (m)(1) of this AD.
    (1) Before further flight, reposition cables and repair damage 
or replace damaged cables or fuel feed lines with new or serviceable 
cables or fuel feed lines. Repeat the inspection required by 
paragraph (j) of this AD thereafter at intervals not to exceed 6 
months, until the actions specified by paragraph (m)(2) or (m)(3) of 
this AD, as applicable, are accomplished.
    (2) For Group 1 airplanes, configuration 3: Within 18 months 
after the effective date of this AD, install IDG harness support 
brackets, and modify the IDG power feeder cable installations.
    (3) For Group 1 airplanes, configuration 4, and Group 2 
airplanes, configuration 2: Within 18 months after the effective 
date of this AD: Modify the IDG power feeder cable installations.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, FAA, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously in accordance with AD 2004-01-17, 
are not approved as AMOCs with this AD.
    (4) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, and the approval must specifically 
refer to this AD.

Material Incorporated by Reference

    (o) You must use Boeing Alert Service Bulletin MD11-54A011, 
Revision 02, dated May 31, 2002, or Boeing Alert Service Bulletin 
MD11-54A011, Revision 3, dated November 9, 2005, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin MD11-
54A011, Revision 3, dated November 9, 2005, in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) On February 24, 2004 (69 FR 2657, January 20, 2004), the 
Director of the Federal Register approved the incorporation by 
reference of Boeing Alert Service Bulletin MD11-54A011, Revision 02, 
dated May 31, 2002.
    (3) Contact Boeing Commercial Airplanes, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of 
this service information. You may review copies at the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street, SW., Room PL-401, Nassif Building, Washington, DC; on the 
Internet at http://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-22536 Filed 1-9-07; 8:45 am]
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