[Federal Register Volume 75, Number 214 (Friday, November 5, 2010)]
[Proposed Rules]
[Pages 68246-68249]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-28092]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1044; Directorate Identifier 2010-NM-033-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Corporation Model DC-
10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), 
DC-10-40, DC-10-40F; Model MD-10-10F, MD-10-30F, 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 all Model DC-10-10, DC-10-10F, DC-10-15, 
DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-
10F, MD-10-30F, MD-11, and MD-11F airplanes. The existing AD currently 
requires an inspection to determine if a certain fuel pump housing 
electrical connector is installed. The existing AD also requires a 
revision to the FAA-approved airplane flight manual (AFM) to advise the 
flightcrew of the appropriate procedures for disabling certain fuel 
pump electrical circuits following failure of a fuel pump housing 
electrical connector if applicable. The existing AD also requires the 
deactivation of certain fuel tanks or fuel pumps and the installation 
of placards if applicable. The existing AD allows the optional 
replacement of the fuel pump housing electrical connectors with new, 
improved parts, which would

[[Page 68247]]

terminate the AFM revisions, deactivation of certain fuel tanks and 
fuel pumps, and placard installation. This proposed AD would instead 
require replacing the fuel pump housing electrical connector assembly 
with a new part and doing repetitive inspections for continuity, 
resistance, and insulation resistance, and doing corrective actions if 
necessary. This proposed AD results from reports of failures of a 
certain fuel pump housing electrical connector. We are proposing this 
AD to detect and correct insulation resistance degradation and arcing 
in the potted backside of the electrical connector assembly of the fuel 
boost/transfer pump housing, which could compromise its performance and 
cause an ignition source in the fuel tank, resulting in a fuel tank 
explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by December 20, 
2010.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 
<a href="/cdn-cgi/l/email-protection#234750460d414c46404c4e63414c464a4d440d404c4e"><span class="__cf_email__" data-cfemail="325641571c505d57515d5f72505d575b5c551c515d5f">[email protected]</span></a>; 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.

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: Philip Kush, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5263; 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-2010-1044; 
Directorate Identifier 2010-NM-033-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 July 13, 2007, we issued AD 2007-15-05, Amendment 39-15134 (72 
FR 40216, July 24, 2007), for all Model DC-10-10, DC-10-10F, DC-10-15, 
DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-
10F, MD-10-30F, MD-11, and MD-11F airplanes. That AD requires an 
inspection to determine if a certain fuel pump housing electrical 
connector is installed, and a revision to the FAA-approved airplane 
flight manual (AFM) to advise the flightcrew of the appropriate 
procedures for disabling certain fuel pump electrical circuits 
following failure of a fuel pump housing electrical connector if 
applicable. That AD also requires the deactivation of certain fuel 
tanks or fuel pumps and the installation of placards if applicable. 
That AD allows the optional replacement of the fuel pump housing 
electrical connectors with new, improved parts, which would terminate 
the AFM revisions, deactivation of certain fuel tanks and fuel pumps, 
and placard installation. That AD resulted from a report of two 
failures of the fuel pump housing electrical connector. We issued that 
AD to prevent continued arcing following a short circuit of the fuel 
pump housing electrical connector, which could damage the conduit that 
protects the power lead inside the fuel tank; this condition could 
create an ignition source inside the fuel tank, which, in combination 
with flammable fuel vapors, could result in a fuel tank explosion and 
consequent loss of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2007-15-05, operators have reported failures of 
fuel pump housing electrical connector assemblies having part number 
(P/N) 60-84355-1. The installation of P/N 60-84355-1 was required in AD 
2007-15-05, but due to reported failures of that part, it needs to be 
replaced with a new fuel pump housing electrical connector assembly 
having part number (P/N) 60-84351. Inspecting the fuel boost/transfer 
pump housing electrical connector assembly and fuel boost/transfer 
pump, and replacing any fuel pump electrical connector assembly having 
P/N 60-84355-1 with one having P/N 60-84351, as required based on 
inspection results, will minimize the possibility of a potential 
ignition source in the fuel tanks and potential fuel tank explosion. If 
not corrected, insulation resistance degradation and arcing in the 
potted backside of the electrical connector assembly of the fuel boost/
transfer pump housing could compromise the performance of the 
electrical connector assembly of the fuel boost/transfer pump housing 
and result in a failure that could introduce an ignition source into 
the fuel tank and cause a fuel tank explosion. The requirements of AD 
2007-15-05 do not adequately address the identified unsafe condition.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin MD11-28A143, dated 
December 2, 2009; and Boeing Alert Service Bulletin DC10-28A261, dated 
December 1, 2009. The service bulletins describe procedures for 
replacing the fuel pump housing electrical connector assembly having P/
N 60-84355-1 with new or serviceable fuel pump housing electrical 
connector assembly having P/N 60-84351; and doing repetitive 
inspections for continuity, resistance, and insulation resistance; and 
doing corrective actions if necessary. Corrective actions include 
replacing the fuel boost/transfer pump and replacing

[[Page 68248]]

any fuel pump electrical connector assembly having P/N 60-84355-1 with 
one having P/N 60-84351.

Explanation of Change to This Proposed AD

    We have removed the ``Service Bulletin Reference'' paragraph from 
this proposed AD. That paragraph was identified as paragraph (f) in the 
existing AD. Instead, we have provided the full service bulletin 
citations throughout this proposed AD. We have re-identified the 
paragraphs accordingly.

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 2007-15-05. This proposed AD would instead require 
accomplishing the actions described previously in accordance with 
Boeing Alert Service Bulletin MD11-28A143, dated December 2, 2009; and 
Boeing Alert Service Bulletin DC10-28A261, dated December 1, 2009.

Costs of Compliance

    There are about 281 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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                      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......................  Between 20 and 36               $85  $0......................  Between $1,700 and              281  Between $477,700
                                   per inspection                                                 $3,060 per                           and $859,860 per
                                   cycle.                                                         inspection cycle.                    inspection cycle.
Replacement.....................  Up to 44...........              85  Up to $4,478............  Up to $8,218.......             281  Up to $2,309,258.
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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 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 39-15134 (72 FR 
40216, July 24, 2007) and adding the following new AD:

McDonnell Douglas Corporation: Docket No. FAA-2010-1044; Directorate 
Identifier 2010-NM-033-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
20, 2010.

Affected ADs

    (b) This AD supersedes AD 2007-15-05, Amendment 39-15134.

Applicability

    (c) This AD applies to all McDonnell Douglas Corporation Model 
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-
10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F 
airplanes, certificated in any category.

Subject

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

Unsafe Condition

    (e) This AD results from reports of failures of the fuel pump 
housing electrical connector. The Federal Aviation Administration is 
issuing this AD to detect and correct insulation resistance 
degradation and arcing in the potted backside of the electrical 
connector assembly of the fuel boost/transfer pump housing, which 
could compromise its performance and cause an ignition source in the 
fuel tank, resulting in a fuel tank explosion and consequent loss of 
the airplane.

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.

Inspection and Change

    (g) Within 10 months after the effective date of this AD, do the 
actions in paragraph (g)(1) or (g)(2) of this AD, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
DC10-28A261, dated December 1, 2009; or Boeing Alert Service 
Bulletin MD11-28A143, dated December 2, 2009; as applicable.

[[Page 68249]]

    (1) Replace the fuel pump electrical connector assembly having 
part number (P/N) 60-84355-1 with new P/N 60-84351; or
    (2) Do the actions required by paragraphs (g)(2)(i) and 
(g)(2)(ii) of this AD.
    (i) Using a digital multi-meter, do a continuity, resistance, 
and insulation resistance inspection from the terminal strip through 
the fuel boost/transfer pump; and all applicable corrective actions 
specified in the service bulletin. Do all applicable corrective 
actions before further flight.
    (ii) Except as required by paragraph (i) of this AD, within 12 
months after accomplishing the inspection required by paragraph 
(g)(2)(i) of this AD: Replace the fuel pump electrical connector 
assembly having part number (P/N) 60-84355-1 with a new fuel pump 
electrical connector assembly having P/N 60-84351.
    (h) Before further flight after installing the new fuel pump 
electrical connector assembly, insert the applicable Interim 
Operating Procedure regarding abnormal operations for failure of the 
fuel pump housing electrical connector into the Procedures section 
of the applicable airplane flight manual, in accordance with the 
applicable bulletin identified in Table 1 of this AD.

                                               Table 1--Bulletins
----------------------------------------------------------------------------------------------------------------
            Bulletin--                    Dated--                                To the--
----------------------------------------------------------------------------------------------------------------
Boeing DC-10 Operations Bulletin   January 25, 2010....  Boeing DC-10 Flight Crew Operating Manual (FCOM).
 2-001B.
Boeing MD-10 FCOM Advisory         January 25, 2010....  Boeing MD-10 FCOM.
 Bulletin 2-01B.
Boeing MD-11 FCOM Advisory         January 25, 2010....  Boeing MD-11 FCOM.
 Bulletin 2-05C.
----------------------------------------------------------------------------------------------------------------

Repetitive Inspections

    (i) Within 18 months after replacing the fuel pump electrical 
connector assembly as required by paragraph (g) of this AD, do a 
continuity, resistance, and insulation resistance inspection from 
the terminal strip through the fuel boost/transfer pump, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin DC10-28A261, dated December 1, 2009; or Boeing 
Alert Service Bulletin MD11-28A143, dated December 2, 2009; as 
applicable. Do all applicable corrective actions before further 
flight in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin DC10-28A261, dated December 1, 2009; or 
Boeing Alert Service Bulletin MD11-28A143, dated December 2, 2009; 
as applicable. Repeat the inspections thereafter at intervals not to 
exceed 18 months.

Alternative Methods of Compliance (AMOCs)

    (j)(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: Philip Kush, Aerospace Engineer, Propulsion 
Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5263; 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 October 21, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-28092 Filed 11-4-10; 8:45 am]
BILLING CODE 4910-13-P


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