Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-11F Airplanes, 47900-47902 [E9-22580]

Download as PDF 47900 Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules Corrective Action for Forward Side Inspection (l) If any crack or fracture is found during any inspection required by paragraph (k) of this AD, and Boeing Alert Service Bulletin 747–54A2224, Revision 1, dated November 16, 2006, specifies to contact Boeing for appropriate action: Before further flight, repair the crack or fracture using a method approved in accordance with the procedures specified in paragraph (q) of this AD. Credit for Inspections Done According to Boeing 747 Fleet Team Digest (m) Detailed and HFEC inspections done before January 29, 2007, in accordance with Boeing 747 Fleet Team Digest 747–FTD–54– 06002, dated June 29, 2006; or October 16, 2006; are acceptable for compliance with the initial inspection required by paragraph (k) of this AD. New Requirements of This AD erowe on DSK5CLS3C1PROD with PROPOSALS-1 Inspection and Corrective Actions (n) At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–54A2230, dated October 30, 2008; except that where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD: Do an open-hole high frequency eddy current (HFEC) inspection for cracking of the of the forward side of the front spar chord assembly on the inboard and outboard struts; and, for airplanes on which the cap skin doubler is not installed, install the cap skin doubler; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2230, dated October 30, 2008. (o) If any crack is found during the inspection required by paragraph (n) of this AD: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (q) of this AD. (p) Doing all applicable actions required by paragraphs (n) and (o) of this AD terminates the repetitive forward side detailed and HFEC inspection requirements of paragraph (k) of this AD. All aft side inspection requirements of this AD remain in effect. Alternative Methods of Compliance (AMOCs) (q)(1) The Manager, Seattle 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: Ken Paoletti, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6434; fax (425) 917–6590. Or, e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. (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), VerDate Nov<24>2008 15:09 Sep 17, 2009 Jkt 217001 as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) 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, Seattle 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. (4) AMOCs approved previously in accordance with AD 2007–01–15, are approved as AMOCs for the corresponding provisions of this AD. Issued in Renton, Washington, on September 11, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–22577 Filed 9–17–09; 8:45 am] BILLING CODE 4910–13–P 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). 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 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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 https://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 dse.boecom@boeing.com; 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 https:// 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 E:\FR\FM\18SEP1.SGM 18SEP1 Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules 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. Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5262; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited 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. 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 https:// 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. 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. 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 FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe 47901 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 Corresponding requirement in this proposed AD Requirement in AD 99–25–14 Paragraph (a) ............ paragraph (g). 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 Action erowe on DSK5CLS3C1PROD with PROPOSALS-1 Inspection (required by AD 99–25–14). Modification (new proposed action). Jkt 217001 $80 $80 16 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 15:09 Sep 17, 2009 Cost per airplane Parts 1 Authority for This Rulemaking VerDate Nov<24>2008 Average labor rate per hour Work hours 80 1,248 $80, per inspection cycle. $2,528 .................... 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Number of U.S.-registered airplanes 9 9 Fleet cost $720, per inspection cycle. $22,752. 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 E:\FR\FM\18SEP1.SGM 18SEP1 47902 Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules products identified in this rulemaking action. Boeing Alert Service Bulletin MD11–28A140, dated November 6, 2008. 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. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing amendment 39–11457 (64 FR 69389, December 13, 1999) and adding the following new AD: erowe on DSK5CLS3C1PROD with PROPOSALS-1 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. Applicability (c) This AD applies to McDonnell Douglas Model MD–11 and MD–11F airplanes, certificated in any category, as identified in 15:09 Sep 17, 2009 Jkt 217001 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 Affected ADs (b) This AD supersedes AD 99–25–14. VerDate Nov<24>2008 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. 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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 DEPARTMENT OF TRANSPORTATION Office of the Secretary 14 CFR Part 382 [Docket No. OST–2009–0093] Nondiscrimination on the Basis of Disability in Air Travel AGENCY: Office of the Secretary (OST), DOT. ACTION: Request for comments on petition for rulemaking. SUMMARY: An advocacy group representing users of psychiatric service dogs has petitioned the Department to eliminate a provision of the Department of Transportation’s Air Carrier Access regulation. The provision in question permits air carriers to require documentation and 48 hours’ advance notice for users of psychiatric service animals. In this document, the Department is seeking comment on the group’s petition and related questions. This document is not a notice of proposed rulemaking. The Department has not decided whether to grant the petition by initiating rulemaking action or to deny the petition and retain the provisions without change. The Department will publish a document in E:\FR\FM\18SEP1.SGM 18SEP1

Agencies

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


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

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).

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

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 https://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 
dse.boecom@boeing.com; 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 https://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 https://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
------------------------------------------------------------------------
                                             Corresponding  requirement
        Requirement in AD  99-25-14             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  paragraph (g).
------------------------------------------------------------------------

     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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                 Number of U.S.-
                Action                   Work hours     Average labor       Parts          Cost per airplane       registered           Fleet cost
                                                        rate per hour                                               airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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]
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