Airworthiness Directives; McDonnell Douglas Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes, Model DC-10-40 and DC-10-40F Airplanes, and Model MD-10-30F Airplanes, 8305-8307 [E7-3171]

Download as PDF Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules paragraph (h) of this AD have been done, no alternative inspection intervals or replacement times may be approved for the PSEs and safe-life limited parts specified in Boeing 717–200 ALI, Report MDC–96K9063, Revision 5, dated February 2006. Comments Due Date (a) The FAA must receive comments on this AD action by April 12, 2007. Affected ADs (b) This AD supersedes AD 2003–17–01. Applicability (c) This AD applies to all McDonnell Douglas Model 717–200 airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to incorporate new inspections for fatigue cracking of principal structural elements (PSEs). Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to incorporate the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25–1529–1. Unsafe Condition (d) This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Los Angeles ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) 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, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on February 16, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–3170 Filed 2–23–07; 8:45 am] BILLING CODE 4910–13–P 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. DEPARTMENT OF TRANSPORTATION Restatement of Requirements of AD 2003– 17–01 14 CFR Part 39 Revising Airworthiness Limitations Section (f) Within 180 days after September 23, 2003 (the effective date of AD 2003–17–01), revise the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, Airworthiness Limitations Instructions (ALI), in accordance with Boeing Report MDC–96K9063, Revision 3, dated August 2002. (g) Except as provided by paragraph (j) of this AD: After the actions specified in paragraph (f) of this AD have been done, no alternative inspection intervals or replacement times may be approved for the PSEs and safe-life limited parts specified in Boeing Report Number MDC–96K9063, Revision 3, dated August 2002. [Docket No. FAA–2007–27340; Directorate Identifier 2006–NM–271–AD] hsrobinson on PROD1PC76 with PROPOSALS New Requirements of This AD Revising Airworthiness Limitations Section Using Revision 5 (h) Within 180 days after the effective date of this AD: Revise the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, ALI, in accordance with Boeing 717–200 ALI, Report MDC– 96K9063, Revision 5, dated February 2006. (i) Except as provided by paragraph (j) of this AD: After the actions specified in VerDate Aug<31>2005 16:00 Feb 23, 2007 Jkt 211001 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–30 and DC–10– 30F (KC–10A and KDC–10) Airplanes, Model DC–10–40 and DC–10–40F Airplanes, and Model MD–10–30F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model DC– 10–30 and DC–10–30F (KC–10A and KDC–10) airplanes, Model DC–10–40 and DC–10–40F airplanes, and Model MD–10–30F airplanes. This proposed AD would require installing bracket assemblies and jumper wires in the center main wheel well to improve the PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 8305 bonding path between the structure (wall) of the lower auxiliary fuel tank and its internal fuel pumps; measuring the electrical resistance between the fuel pump housings and the fuel tank structure; and doing corrective actions if necessary. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to detect and correct an inadequate bond between the internal fuel pump housings and the structure of the lower auxiliary fuel tank. This condition, if not corrected, could fail to meet fault current requirements and result in a potential ignition source that, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by April 12, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5262; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2007–27340; Directorate Identifier 2006–NM–271– E:\FR\FM\26FEP1.SGM 26FEP1 8306 Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. hsrobinson on PROD1PC76 with PROPOSALS Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We have received a report indicating that the electrical bond may not be adequate between the internal fuel pumps of the lower auxiliary fuel tank and the fuel tank structure (wall), on certain McDonnell Douglas Model DC– 10–30 and DC–10–30F (KC–10A and KDC–10) airplanes, Model DC–10–40 and DC–10–40F airplanes, and Model MD–10–30F airplanes. This condition, if not corrected, could fail to meet fault current requirements and result in a potential ignition source that, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane. Related Rulemaking Operators should note that the same unsafe condition exists in all McDonnell Douglas Model MD–11 and MD–11F airplanes and that we may issue a separate rulemaking to address those airplanes. Relevant Service Information We have reviewed Boeing Service Bulletin DC10–28–245, dated September 19, 2006. The service bulletin describes procedures for installing bracket assemblies and jumper wires in the center main wheel well to improve the bonding path between the lower auxiliary fuel tank and its internal fuel pumps; measuring the electrical resistance between the fuel pump housings and the fuel tank structure (wall); and doing corrective actions if necessary. Corrective actions, if any resistance measurement exceeds 2.5 milliohms, include reworking the electrical bonding between the fuel pump housings and the fuel tank structure. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Costs of Compliance There are about 242 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 178 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD, at an average labor rate of $80 per work hour. ESTIMATED COSTS Action Work hours Install bracket assemblies and jumper wires ............................... Do electrical resistance measurement ......................................... VerDate Aug<31>2005 16:00 Feb 23, 2007 Jkt 211001 PO 00000 Frm 00014 4 1 Fmt 4702 Cost per airplane Parts $1,928 ....................................... None required ........................... Sfmt 4702 E:\FR\FM\26FEP1.SGM 26FEP1 $2,248 80 Fleet cost $400,144 14,240 Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules 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. hsrobinson on PROD1PC76 with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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: VerDate Aug<31>2005 16:00 Feb 23, 2007 Jkt 211001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA–2007– 27340; Directorate Identifier 2006–NM– 271–AD. Comments Due Date (a) The FAA must receive comments on this AD action by April 12, 2007. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model DC–10–30 and DC–10–30F (KC–10A and KDC–10) airplanes, Model DC–10–40 and DC–10–40F airplanes, and Model MD– 10–30F airplanes; certificated in any category; as identified in Boeing Service Bulletin DC10–28–245, dated September 19, 2006. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct an inadequate bond between the internal fuel pump housings and the structure (wall) of the lower auxiliary fuel tank. This condition, if not corrected, could fail to meet fault current requirements and result in a potential ignition source that, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane. 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. Installation of Brackets and Jumpers, and Resistance Measurement (f) Within 60 months after the effective date of this AD, do the actions described in paragraphs (f)(1) and (f)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–245, dated September 19, 2006. (1) Install bracket assemblies and jumper wires between the structure of the lower auxiliary fuel tank and its internal fuel pumps. (2) Do an electrical resistance measurement between the fuel pump housings and structure of the lower auxiliary fuel tank. Corrective Action (g) If any resistance measurement done in accordance with paragraph (f)(2) of this AD is greater than 2.5 milliohms on either fuel pump housing: Before further flight, rework the electrical bonding between the fuel pump housings and the structure of the lower auxiliary fuel tank as needed to achieve a resistance measurement of 2.5 milliohms or less on both fuel pump housings, as described in Boeing Service Bulletin DC10– 28–245, dated September 19, 2006. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 8307 Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on February 16, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–3171 Filed 2–23–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27339; Directorate Identifier 2006–NM–280–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–10 and DC–10– 10F Airplanes, Model DC–10–15 Airplanes, Model DC–10–30 and DC– 10–30F (KC–10A and KDC–10) Airplanes, Model DC–10–40 and DC– 10–40F Airplanes, Model MD–10–10F and MD–10–30F Airplanes, and Model MD–11 and MD–11F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain transport category airplanes identified above. This proposed AD would require modifying the fuel boost pumps. This proposed AD results from a fuel boost pump found with blown thermal fuses and a fractured thrust washer. We are proposing this AD to prevent failure of the fuel boost pumps, which could lead to the potential of ignition sources inside fuel tanks. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by April 12, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. E:\FR\FM\26FEP1.SGM 26FEP1

Agencies

[Federal Register Volume 72, Number 37 (Monday, February 26, 2007)]
[Proposed Rules]
[Pages 8305-8307]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-3171]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27340; Directorate Identifier 2006-NM-271-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-30 and 
DC-10-30F (KC-10A and KDC-10) Airplanes, Model DC-10-40 and DC-10-40F 
Airplanes, and Model MD-10-30F Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas Model DC-10-30 and DC-10-30F (KC-10A and 
KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, and Model 
MD-10-30F airplanes. This proposed AD would require installing bracket 
assemblies and jumper wires in the center main wheel well to improve 
the bonding path between the structure (wall) of the lower auxiliary 
fuel tank and its internal fuel pumps; measuring the electrical 
resistance between the fuel pump housings and the fuel tank structure; 
and doing corrective actions if necessary. This proposed AD results 
from fuel system reviews conducted by the manufacturer. We are 
proposing this AD to detect and correct an inadequate bond between the 
internal fuel pump housings and the structure of the lower auxiliary 
fuel tank. This condition, if not corrected, could fail to meet fault 
current requirements and result in a potential ignition source that, in 
combination with flammable fuel vapors, could cause a fuel tank 
explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by April 12, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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 the service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-27340; Directorate Identifier 2006-NM-271-

[[Page 8306]]

AD'' at the beginning of your comments. We specifically invite comments 
on the overall regulatory, economic, environmental, and energy aspects 
of the proposed AD. We will consider all comments received by the 
closing date and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    We have received a report indicating that the electrical bond may 
not be adequate between the internal fuel pumps of the lower auxiliary 
fuel tank and the fuel tank structure (wall), on certain McDonnell 
Douglas Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes, 
Model DC-10-40 and DC-10-40F airplanes, and Model MD-10-30F airplanes. 
This condition, if not corrected, could fail to meet fault current 
requirements and result in a potential ignition source that, in 
combination with flammable fuel vapors, could cause a fuel tank 
explosion and consequent loss of the airplane.

Related Rulemaking

    Operators should note that the same unsafe condition exists in all 
McDonnell Douglas Model MD-11 and MD-11F airplanes and that we may 
issue a separate rulemaking to address those airplanes.

Relevant Service Information

    We have reviewed Boeing Service Bulletin DC10-28-245, dated 
September 19, 2006. The service bulletin describes procedures for 
installing bracket assemblies and jumper wires in the center main wheel 
well to improve the bonding path between the lower auxiliary fuel tank 
and its internal fuel pumps; measuring the electrical resistance 
between the fuel pump housings and the fuel tank structure (wall); and 
doing corrective actions if necessary. Corrective actions, if any 
resistance measurement exceeds 2.5 milliohms, include reworking the 
electrical bonding between the fuel pump housings and the fuel tank 
structure. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously.

Costs of Compliance

    There are about 242 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 178 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD, at an average labor 
rate of $80 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                       Cost per
                  Action                    Work hours             Parts               airplane     Fleet cost
----------------------------------------------------------------------------------------------------------------
Install bracket assemblies and jumper                4  $1,928.....................       $2,248        $400,144
 wires.
Do electrical resistance measurement.....            1  None required..............           80          14,240
----------------------------------------------------------------------------------------------------------------


[[Page 8307]]

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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2007-27340; Directorate Identifier 
2006-NM-271-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 12, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-10-30 and DC-
10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F 
airplanes, and Model MD-10-30F airplanes; certificated in any 
category; as identified in Boeing Service Bulletin DC10-28-245, 
dated September 19, 2006.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to detect and correct an 
inadequate bond between the internal fuel pump housings and the 
structure (wall) of the lower auxiliary fuel tank. This condition, 
if not corrected, could fail to meet fault current requirements and 
result in a potential ignition source that, in combination with 
flammable fuel vapors, could cause a fuel tank explosion and 
consequent loss of the airplane.

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.

Installation of Brackets and Jumpers, and Resistance Measurement

    (f) Within 60 months after the effective date of this AD, do the 
actions described in paragraphs (f)(1) and (f)(2) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin DC10-28-245, dated September 19, 2006.
    (1) Install bracket assemblies and jumper wires between the 
structure of the lower auxiliary fuel tank and its internal fuel 
pumps.
    (2) Do an electrical resistance measurement between the fuel 
pump housings and structure of the lower auxiliary fuel tank.

Corrective Action

    (g) If any resistance measurement done in accordance with 
paragraph (f)(2) of this AD is greater than 2.5 milliohms on either 
fuel pump housing: Before further flight, rework the electrical 
bonding between the fuel pump housings and the structure of the 
lower auxiliary fuel tank as needed to achieve a resistance 
measurement of 2.5 milliohms or less on both fuel pump housings, as 
described in Boeing Service Bulletin DC10-28-245, dated September 
19, 2006.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), 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.

    Issued in Renton, Washington, on February 16, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-3171 Filed 2-23-07; 8:45 am]
BILLING CODE 4910-13-P
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