[Federal Register Volume 74, Number 180 (Friday, September 18, 2009)]
[Proposed Rules]
[Pages 47900-47902]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-22580]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0866; Directorate Identifier 2009-NM-074-AD]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas Model MD-11 
and MD-11F airplanes. The existing AD currently requires a one-time 
inspection to determine if metallic transitions are installed on wire 
harnesses of the tail tank fuel transfer pumps, and to determine if 
damaged wires are present; and repair, if necessary. This proposed AD 
would require modifying the case grounding for the alternate fuel pump 
of the tail tank, the leak detection thermal switch grounding for the 
number 2 engine, and wire braid grounding in the empennage and number 2 
engine inlet. This proposed AD would also remove one airplane from the 
applicability of the existing AD. This proposed AD results from reports 
that the wire assembly for the alternate fuel pump is missing a case 
ground wire, and the lightning protection wire braid for wire 
assemblies located in the empennage and number 2 engine inlet are 
grounded improperly. We are proposing this AD to prevent insufficient 
grounding of the fuel pump, which in combination with an electrical 
failure within the fuel pump and a compromised electrical bond could 
cause a fuel tank ignition, resulting in consequent fire or explosion.

DATES: We must receive comments on this proposed AD by November 2, 
2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
[email protected]; Internet https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221 or 425-227-1152.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification

[[Page 47901]]

Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0866; 
Directorate Identifier 2009-NM-074-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 2, 1999, we issued AD 99-25-14, amendment 39-11457 (64 
FR 69389, December 13, 1999), for certain McDonnell Douglas Model MD-11 
and MD-11F airplanes. That AD requires a one-time inspection to 
determine if metallic transitions are installed on wire harnesses of 
the tail tank fuel transfer pumps, and to determine if damaged wires 
are present; and repair, if necessary. That AD also requires repetitive 
inspections of the repaired area; and a permanent modification of the 
wire harnesses if metallic transitions are not installed, which 
terminates the repetitive inspections. That AD resulted from a report 
of chafing and damage to a wire harness of a tail tank fuel transfer 
pump. We issued that AD to prevent wire chafing and damage, which could 
result in an inoperative fuel transfer pump and/or an increased risk of 
a fire or explosion from a fuel leak.

Actions Since Existing AD Was Issued

    Since we issued AD 99-25-14, we have received reports that the wire 
assembly for the alternate fuel pump is missing a case ground wire, and 
the lightning protection wire braid for wire assemblies located in the 
empennage and number 2 engine inlet are grounded improperly. Further 
investigation revealed that the wiring of the anti-ice leak detection 
thermal switch of the number 2 engine was not included in the wire 
assembly, and that the support bracket of the leak detection thermal 
switch was not electrically bonded to the engine spar of the number 2 
engine. Insufficient grounding of the fuel pump, in combination with an 
electrical failure within the fuel pump and a compromised electrical 
bond, could cause a fuel tank ignition, resulting in consequent fire or 
explosion.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin MD11-28A140, dated 
November 6, 2008. The service bulletin describes procedures to modify 
the case grounding for the alternate fuel pump of the tail tank and the 
leak detection thermal switch grounding for the number 2 engine. The 
modification also includes modifying the wire metal braid grounding in 
the empennage and the inlet of the number 2 engine, and testing the 
leak detection thermal switch for correct operation.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 99-25-14 and would retain the requirements of the 
existing AD. This proposed AD would also require accomplishing the 
actions specified in the ``Relevant Service Information'' described 
previously.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 99-25-14. 
Since AD 99-25-14 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
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                                             Corresponding  requirement
        Requirement in AD  99-25-14             in this  proposed AD
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Paragraph (a).............................  paragraph (g).
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     In addition, we have revised the applicability of AD 99-25-14 by 
referring to Boeing Alert Service Bulletin MD11-28A140, dated November 
6, 2008, in paragraph (c) of this AD. This proposed AD would remove one 
airplane, fuselage number 450, from the applicability due to hull loss.

Costs of Compliance

    There are about 13 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
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                                                                                                                 Number of U.S.-
                Action                   Work hours     Average labor       Parts          Cost per airplane       registered           Fleet cost
                                                        rate per hour                                               airplanes
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Inspection (required by AD 99-25-14).               1             $80             $80  $80, per inspection                    9  $720, per inspection
                                                                                        cycle.                                    cycle.
Modification (new proposed action)...              16              80           1,248  $2,528..................               9  $22,752.
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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 is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on

[[Page 47902]]

products identified in this rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by removing amendment 39-11457 (64 FR 
69389, December 13, 1999) and adding the following new AD:

McDonnell Douglas: Docket No. FAA-2009-0866; Directorate Identifier 
2009-NM-074-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
2, 2009.

Affected ADs

    (b) This AD supersedes AD 99-25-14.

Applicability

    (c) This AD applies to McDonnell Douglas Model MD-11 and MD-11F 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin MD11-28A140, dated November 6, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

    (e) This AD results from reports that the wire assembly for the 
alternate fuel pump is missing a case ground wire, and the lightning 
protection wire braid for wire assemblies located in the empennage 
and number 2 engine inlet are grounded improperly. The Federal 
Aviation Administration is issuing this AD to prevent insufficient 
grounding of the fuel pump, which in combination with an electrical 
failure within the fuel pump and a compromised electrical bond could 
cause a fuel tank ignition, resulting in consequent fire or 
explosion.

Compliance

    (f) 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 99-25-14 With No Changes

Inspection and Corrective Actions

    (g) Within 30 days after January 18, 2000 (the effective date of 
AD 99-25-14), perform a one-time visual inspection of the wire 
harnesses of the tail tank fuel transfer pumps to determine if 
metallic transitions are installed, and to determine if damaged 
wires are present, in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-28A101, dated August 24, 1998 (``the service 
bulletin'').
    (1) If all metallic transitions are installed, no further action 
is required by paragraph (g) of this AD.
    (2) If metallic transitions are not installed, accomplish the 
following:
    (i) Prior to further flight, accomplish the temporary repair in 
accordance with condition 2 of the service bulletin;
    (ii) Repeat the visual inspection thereafter at intervals not to 
exceed 2 years; and
    (iii) Within 5 years after January 18, 2000, permanently modify 
the wire harnesses in accordance with McDonnell Douglas Service 
Bulletin MD11-28-102, Revision 01, dated June 23, 1999. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspection requirements of this AD.

    Note 1: Modification of the wire harnesses accomplished prior to 
January 18, 2000 (the effective date of AD 99-25-14), in accordance 
with McDonnell Douglas Service Bulletin MD11-28-102, dated January 
29, 1999, is considered acceptable for compliance with the 
modification required by paragraph (g)(2)(iii) of this AD.

New Requirements of This AD

Modification

    (h) Within 72 months after the effective date of this AD, modify 
the case grounding for the alternate fuel pump of the tail tank, the 
leak detection thermal switch grounding for the number 2 engine, and 
wire braid grounding in the empennage and number 2 engine inlet, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD11-28A140, dated November 6, 2008.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion 
Branch, ANM-140L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5262; fax (562) 
627-5210.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

    Issued in Renton, Washington, on September 11, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-22580 Filed 9-17-09; 8:45 am]
BILLING CODE 4910-13-P