80 FR 16321 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 59 (March 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 59 (March 27, 2015)
| Page Range | 16321-16324 | |
| FR Document | 2015-06746 |
[Federal Register Volume 80, Number 59 (Friday, March 27, 2015)] [Proposed Rules] [Pages 16321-16324] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-06746] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0248; Directorate Identifier 2014-NM-143-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-08- 23, which applies to all The Boeing Company 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. AD 2013-08-23 currently requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. Since we issued AD 2013-08-23, we have determined that it is necessary to clarify the requirements for the design features and to remove a terminating action for certain inspections. This proposed AD would clarify certain requirements and remove a terminating action. This proposed AD would also provide an optional method of compliance for the proposed actions. We are proposing this AD 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. DATES: We must receive comments on this proposed AD by May 11, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above 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, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0248. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0248; 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 (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712- 4137; phone: 562-627-5254; fax: 562-627-5210; email: serj.harutunian@faa.gov. 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-2015-0248; Directorate Identifier 2014-NM-143-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 April 10, 2013, we issued AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), for all The Boeing Company 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. AD 2013- 08-23 requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. AD 2013-08-23 resulted from fuel system reviews conducted by the manufacturer. We issued AD 2013-08-23 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. Actions Since AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), Was Issued Since we issued AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), we have determined [[Page 16322]] that it is necessary to clarify the requirements for the design features and to remove a terminating action for certain inspections. In addition, The Boeing Company has issued new service information, which provides optional alternative methods of compliance for the actions required by AD 2013-08-23. Related Service Information Under 1 CFR Part 51 We reviewed the following service information, which describes procedures for changing the fuel pump control and indication system wiring: Boeing Service Bulletin DC10-28-256, dated June 24, 2014; and Boeing Service Bulletin MD11-28-137, dated June 24, 2014. We have also reviewed Appendixes B, C, and D of Boeing Special Compliance Item Report MDC-02K1003, Revision M, dated July 25, 2014, which include Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitations Instructions (ALIs), and short-term extensions. Boeing Service Bulletin MD11-28-137, dated June 24, 2014, specifies prior or concurrent accomplishment of Boeing Alert Service Bulletin MD11-28A133, dated June 5, 2014. Boeing Alert Service Bulletin MD11- 28A133, dated June 5, 2014, describes procedures for replacing the fuel pump control relays with fault current detectors and changing the fuel tank boost/transfer pump wire termination. Boeing Service Bulletin DC10-28-256, dated June 24, 2014, specifies prior or concurrent accomplishment of Boeing Alert Service Bulletin DC10-28A253, dated June 5, 2014. Boeing Alert Service Bulletin DC10- 28A253, dated June 5, 2014, describes procedures for replacing the fuel pump control relays with fault current detectors and changing the fuel tank boost/transfer pump wire termination. This service information is reasonably available; see ADDRESSES for ways to access this service information. Clarification of the Requirements for the Design Features In the introductory text of paragraph (g) of this proposed AD, we have added the text ``for the auxiliary fuel tank'' to the last sentence to clarify that, for airplanes on which Boeing-installed auxiliary fuel tanks are removed, only the actions specified in this AD for the auxiliary fuel tanks are not required. In paragraph (g)(1) of this proposed AD, we have added the text ``and each pump that is partially covered by a lowering fuel level'' and ``main tanks'' to the first sentence to clarify the pumps that must have a protective device installed. Removal of a Terminating Action for Certain Actions Paragraph (h) of AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), specifies, in part, that accomplishing the actions required by paragraph (g)(1) of that AD terminates certain inspections and tests required by paragraph (a) of AD 2002-13-10, Amendment 39- 12798 (67 FR 45053, July 8, 2002), and repetitive inspections required by paragraph (j) of AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011), for pumps affected by those ADs. However, we have determined that accomplishing the actions required by paragraph (g)(1) of AD 2013-08-23 (which is restated in paragraph (g)(1) of this proposed AD) does not terminate those actions and, therefore, we have not retained the terminating action in this proposed AD. The actions specified in paragraph (h) of this proposed AD (i.e., a new optional method of compliance in lieu of paragraph (g) of this proposed AD) would extend the compliance times for certain inspections and tests required by paragraph (a) of AD 2002-13-10, and repetitive inspections required by paragraph (j) of AD 2011-11-05, from 18-month intervals to 24-month intervals. We have added paragraph (j) to this proposed AD to specify that accomplishing the actions in paragraph (h) of this proposed AD would extend certain repetitive intervals. Revised Compliance Time We have determined that it is appropriate to allow additional time to accomplish the design features and requirements specified in this proposed AD. Therefore, we have added a compliance time ``as of 48 months after the effective date of this AD'' to paragraph (g) of this proposed AD. We have determined that this extension of the compliance time will provide an acceptable level of safety. Related AD On November 12, 2009, we issued AD 2008-06-21 R1, Amendment 39- 16100 (74 FR 61504, November 25, 2009), for all McDonnell Douglas Corporation 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. AD 2008-06-21 R1 requires revising the maintenance program or the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to incorporate inspections and CDCCLs. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would retain certain requirements of AD 2013-08- 23, Amendment 39-17441 (78 FR 24037, April 24, 2013), clarify certain requirements, and remove a certain terminating action. This proposed AD would also provide a new optional method of compliance for the actions required by AD 2013-08-23. This proposed AD specifies to revise certain operator maintenance documents to include new actions (e.g., inspections) and Critical Design Configuration Control Limitations (CDCCLs). Compliance with these actions and CDCCLs is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions 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 (k) of this proposed AD. The request should include a description of changes to the required actions and CDCCLs that will ensure the continued operational safety of the airplane. Costs of Compliance We estimate that this proposed AD affects 341 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 16323]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Installing design features using a 152 work-hours x $85 per $137,500 $150,420 $51,923,220 method approved by the FAA [retained hour = $12,920. action from AD 2013[dash]08-23, Amendment 39[dash]17441 (78 FR 24037, April 24, 2013)]. Installing design features using 98 work-hours x $85 per 109,000 117,330 40,478,850 service information specified in hour = $8,330. paragraph (h) of this proposed AD (including revising the maintenance/ inspection program) [new option of this proposed AD]. ---------------------------------------------------------------------------------------------------------------- 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. 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 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-0248; Directorate Identifier 2014-NM-143-AD. (a) Comments Due Date The FAA must receive comments on this AD action by May 11, 2015. (b) Affected ADs (1) This AD replaces AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013). (2) This AD affects AD 2008-06-21 R1, Amendment 39-16100 (74 FR 61504, November 25, 2009). (3) This AD affects AD 2002-13-10, Amendment 39-12798 (67 FR 45053, July 8, 2002). (4) This AD affects AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011). (c) Applicability This AD applies to all The Boeing Company Model airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) 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 airplanes. (2) MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by a fuel system review conducted by the manufacturer. We are issuing this AD 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Criteria for Operation, With Clarifications and New Compliance Time This paragraph restates the actions required by paragraph (g) of AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), with clarification of actions for airplanes with auxiliary fuel tanks removed, clarification of the pumps that must have a protective device installed, and a new compliance time. Except as provided by paragraph (h) of this AD: As of 48 months after the effective date of this AD, no person may operate any airplane affected by this AD unless an amended type certificate or supplemental type certificate that incorporates the design features and requirements described in paragraphs (g)(1) through (g)(4) of this AD has been approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, and those design features are installed on the airplane to meet the criteria specified in 14 CFR Section 25.981(a) and (d), at Amendment level 25-125. For airplanes on which Boeing-installed auxiliary fuel tanks are removed, the actions specified in this AD for the auxiliary fuel tanks are not required. (1) For all airplanes: Each electrically powered alternating current (AC) fuel pump installed in any fuel tank that normally empties during flight and each pump that is partially covered by a lowering fuel level--such as main tanks, center wing tanks, auxiliary fuel tanks installed by the airplane manufacturer, and tail tanks--must have a protective device installed to detect electrical faults that can cause arcing and burn through of the fuel pump housing and pump electrical connector. The same device must shut off the pump by automatically removing electrical power from the pump when such faults are detected. When a fuel pump is shut off resulting from detection of an electrical fault, the device must stay latched off, until [[Page 16324]] the fault is cleared through maintenance action and the pump is verified safe for operation. (2) For airplanes with a 2-person flight crew: Additional design features, if not originally installed by the airplane manufacturer, must be installed to meet 3 criteria: To detect a running fuel pump in a tank that is normally emptied during flight, to provide an indication to the flight crew that the tank is empty, and to automatically shut off that fuel pump. The prospective pump indication and shutoff system must automatically shut off each pump in case the flight crew does not shut off a pump running dry in an empty tank within 60 seconds after each fuel tank is emptied. An airplane flight manual supplement (AFMS) that includes flight crew manual pump shutoff procedures in the Limitations Section of the AFMS must be submitted to the Los Angeles ACO, FAA, for approval. (3) For airplanes with a 3-person flight crew: Additional design features, if not originally installed by the airplane manufacturer, must be installed to detect when a fuel pump in a tank that is normally emptied during flight is running in an empty fuel tank, and provide an indication to the flight crew that the tank is empty. The flight engineer must manually shut off each pump running dry in an empty tank within 60 seconds after the tank is emptied. The AFMS Limitations section must be revised to specify that this pump shutoff must be done by the flight engineer. (4) For all airplanes with tanks that normally empty during flight: Separate means must be provided to detect and shut off a pump that was previously commanded to be shut off automatically or manually but remained running in an empty tank during flight. (h) New Optional Method of Compliance In lieu of doing the requirements of paragraph (g) of this AD, do the applicable actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) For MD-11 and MD-11F airplanes: Do the actions specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) As of 48 months after the effective date of this AD, change the fuel pump control and indication system wiring, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD11-28-137, dated June 24, 2014. (ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(1)(i) of this AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank boost/transfer pump wire termination, in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin MD11- 28A133, dated June 5, 2014. (2) For 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, and MD-10-30F airplanes: Do the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) As of 48 months after the effective date of this AD, change the fuel pump control and indication system wiring, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10-28-256, dated June 24, 2014. (ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(2)(i) of this AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank boost/transfer pump wire termination, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10- 28A253, dated June 5, 2014. (3) For all airplanes: Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this AD, or within 30 days after the effective date of this AD, whichever occurs later, revise the maintenance or inspection program, as applicable, to incorporate the Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitations Instructions (ALIs), and short- term extensions specified in Appendix B, C, and D of Special Compliance Item (SCI) Report MDC-02K1003, Revision M, dated July 25, 2014. The initial compliance time for accomplishing the actions specified in the ALIs is at the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Revising of the maintenance or inspection program required by this paragraph terminates the requirements in paragraph (g) and (h) of AD 2008-06- 21 R1, Amendment 39-16100 (74 FR 61504, November 25, 2009). (i) At the applicable time specified in Appendix C of SCI Report MDC-02K1003, Revision M, dated July 25, 2014, except as provided by Appendix D of SCI Report MDC-02K1003, Revision M, dated July 25, 2014. (ii) Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this AD, or within 30 days after the effective date of this AD, whichever occurs later. (i) No Alternative Actions, Intervals, or CDCCLs If the option in paragraph (h)(3) of this AD is accomplished: After the maintenance or inspection program has been revised, as provided by paragraph (h)(3) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (j) Compliance Time Extension in Related ADs Accomplishment of the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable, extends the 18-month repetitive inspections and tests required by paragraph (a) of AD 2002-13-10, Amendment 39-12798 (67 FR 45053, July 8, 2002), and the 18-month repetitive inspections required by paragraph (j) of AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011), to 24- month intervals for pumps affected by those ADs, regardless if the pump is installed in a tank that normally empties, provided the remaining actions required by those two ADs have been accomplished. (k) Alternative Methods of Compliance (AMOCs) (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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that 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. (4) AMOCs approved for AD 2013-08-23, Amendment 39-17441 (78 FR 24037, April 24, 2013), are approved as AMOCs for the corresponding provisions of this AD. (l) Related Information (1) For more information about this AD, contact Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-4137; phone: 562-627-5254; fax: 562-627- 5210; email: serj.harutunian@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on February 11, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-06746 Filed 3-26-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 59 / Friday, March 27, 2015 / Proposed Rules 16321
send your request to your principal inspector 08–23 currently requires adding design regulatory evaluation, any comments
or local Flight Standards District Office, as features to detect electrical faults and to received, and other information. The
appropriate. If sending information directly detect a pump running in an empty fuel street address for the Docket Office
to the manager of the ACO, send it to the tank. Since we issued AD 2013–08–23, (phone: 800–647–5527) is in the
attention of the person identified in
we have determined that it is necessary ADDRESSES section. Comments will be
paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC- to clarify the requirements for the available in the AD docket shortly after
Requests@faa.gov. design features and to remove a receipt.
(2) Before using any approved AMOC, terminating action for certain FOR FURTHER INFORMATION CONTACT: Serj
notify your appropriate principal inspector, inspections. This proposed AD would Harutunian, Aerospace Engineer,
or lacking a principal inspector, the manager clarify certain requirements and remove Propulsion Branch, ANM–140L, FAA,
of the local flight standards district office/ a terminating action. This proposed AD Los Angeles Aircraft Certification Office
certificate holding district office. would also provide an optional method (ACO), 3960 Paramount Boulevard,
(3) AMOCs approved for AD 2005–18–18, of compliance for the proposed actions. Lakewood, California 90712–4137;
Amendment 39–14258 (70 FR 53554,
September 9, 2005), are approved as AMOCs
We are proposing this AD to reduce the phone: 562–627–5254; fax: 562–627–
for paragraph (g) of this AD. potential of ignition sources inside fuel 5210; email: serj.harutunian@faa.gov.
tanks, which, in combination with SUPPLEMENTARY INFORMATION:
(j) Related Information flammable fuel vapors, could result in
(1) For more information about this AD, fuel tank explosions and consequent Comments Invited
contact Christopher Baker, Aerospace loss of the airplane. We invite you to send any written
Engineer, Propulsion Branch, ANM–140S, relevant data, views, or arguments about
DATES: We must receive comments on
FAA, Seattle ACO, 1601 Lind Avenue SW., this proposed AD. Send your comments
Renton, WA 98057–3356; phone: 425–917– this proposed AD by May 11, 2015.
to an address listed under the
6498; fax: 425–917–6590; email: ADDRESSES: You may send comments,
ADDRESSES section. Include ‘‘Docket No.
christopher.r.baker@faa.gov. using the procedures found in 14 CFR
(2) For service information identified in FAA–2015–0248; Directorate Identifier
11.43 and 11.45, by any of the following
this AD, contact Boeing Commercial 2014–NM–143–AD’’ at the beginning of
methods:
Airplanes, Attention: Data & Services your comments. We specifically invite
• Federal eRulemaking Portal: Go to
Management, P.O. Box 3707, MC 2H–65, comments on the overall regulatory,
http://www.regulations.gov. Follow the
Seattle, WA 98124–2207; telephone 206– economic, environmental, and energy
544–5000, extension 1; fax 206–766–5680; instructions for submitting comments.
aspects of this proposed AD. We will
Internet https://www.myboeingfleet.com. You • Fax: 202–493–2251.
consider all comments received by the
may view this referenced service information • Mail: U.S. Department of
closing date and may amend this
at the FAA, Transport Airplane Directorate, Transportation, Docket Operations,
proposed AD because of those
1601 Lind Ave. SW., Renton WA. For M–30, West Building Ground Floor, comments.
information on the availability of this Room W12–140, 1200 New Jersey
material at the FAA, call 425–227–1221.
We will post all comments we
Avenue SE., Washington, DC 20590. receive, without change, to http://
Issued in Renton, Washington, on March • Hand Delivery: Deliver to Mail www.regulations.gov, including any
12, 2015. address above between 9 a.m. and 5 personal information you provide. We
Jeffrey E. Duven, p.m., Monday through Friday, except will also post a report summarizing each
Manager, Transport Airplane Directorate, Federal holidays. substantive verbal contact we receive
Aircraft Certification Service. For service information identified in about this proposed AD.
[FR Doc. 2015–06782 Filed 3–26–15; 8:45 am] this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data Discussion
BILLING CODE 4910–13–P
& Services Management, 3855 On April 10, 2013, we issued AD
Lakewood Boulevard, MC D800–0019, 2013–08–23, Amendment 39–17441 (78
DEPARTMENT OF TRANSPORTATION Long Beach, CA 90846–0001; telephone FR 24037, April 24, 2013), for all The
206–544–5000, extension 2; fax 206– Boeing Company Model DC–10–10, DC–
Federal Aviation Administration 766–5683; Internet https:// 10–10F, DC–10–15, DC–10–30, DC–10–
www.myboeingfleet.com. You may view 30F (KC–10A and KDC–10), DC–10–40,
14 CFR Part 39 this referenced service information at DC–10–40F, MD–10–10F, MD–10–30F,
[Docket No. FAA–2015–0248; Directorate the FAA, Transport Airplane MD–11, and MD–11F airplanes. AD
Identifier 2014–NM–143–AD] Directorate, 1601 Lind Avenue SW., 2013–08–23 requires adding design
Renton, WA. For information on the features to detect electrical faults and to
RIN 2120–AA64 availability of this material at the FAA, detect a pump running in an empty fuel
call 425–227–1221. It is also available tank. AD 2013–08–23 resulted from fuel
Airworthiness Directives; The Boeing
on the Internet at http:// system reviews conducted by the
Company Airplanes
www.regulations.gov by searching for manufacturer. We issued AD 2013–08–
AGENCY: Federal Aviation and locating Docket No. FAA–2015– 23 to reduce the potential of ignition
Administration (FAA), DOT. 0248. sources inside fuel tanks, which, in
ACTION: Notice of proposed rulemaking Examining the AD Docket combination with flammable fuel
vapors, could result in fuel tank
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(NPRM).
You may examine the AD docket on explosions and consequent loss of the
SUMMARY: We propose to supersede the Internet at http:// airplane.
Airworthiness Directive (AD) 2013–08– www.regulations.gov by searching for
23, which applies to all The Boeing and locating Docket No. FAA–2015– Actions Since AD 2013–08–23,
Company Model DC–10–10, DC–10– 0248; or in person at the Docket Amendment 39–17441 (78 FR 24037,
10F, DC–10–15, DC–10–30, DC–10–30F Management Facility between 9 a.m. April 24, 2013), Was Issued
(KC–10A and KDC–10), DC–10–40, DC– and 5 p.m., Monday through Friday, Since we issued AD 2013–08–23,
10–40F, MD–10–10F, MD–10–30F, MD– except Federal holidays. The AD docket Amendment 39–17441 (78 FR 24037,
11, and MD–11F airplanes. AD 2013– contains this proposed AD, the April 24, 2013), we have determined
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![Federal Register / Vol. 80, No. 59 / Friday, March 27, 2015 / Proposed Rules 16323
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Installing design features using a method approved by the 152 work-hours × $85 per $137,500 $150,420 $51,923,220
FAA [retained action from AD 2013-08–23, Amendment hour = $12,920.
39-17441 (78 FR 24037, April 24, 2013)].
Installing design features using service information specified 98 work-hours × $85 per hour 109,000 117,330 40,478,850
in paragraph (h) of this proposed AD (including revising = $8,330.
the maintenance/inspection program) [new option of this
proposed AD].
Authority for This Rulemaking List of Subjects in 14 CFR Part 39 (d) Subject
Air Transport Association (ATA) of
Title 49 of the United States Code Air transportation, Aircraft, Aviation America Code 28, Fuel.
specifies the FAA’s authority to issue safety, Incorporation by reference,
Safety. (e) Unsafe Condition
rules on aviation safety. Subtitle I,
Section 106, describes the authority of This AD was prompted by a fuel system
The Proposed Amendment review conducted by the manufacturer. We
the FAA Administrator. Subtitle VII, are issuing this AD to reduce the potential of
Aviation Programs, describes in more Accordingly, under the authority ignition sources inside fuel tanks, which, in
detail the scope of the Agency’s delegated to me by the Administrator, combination with flammable fuel vapors,
authority. the FAA proposes to amend 14 CFR part could result in fuel tank explosions and
39 as follows: consequent loss of the airplane.
We are issuing this rulemaking under
the authority described in Subtitle VII, (f) Compliance
PART 39—AIRWORTHINESS
Part A, Subpart III, Section 44701, Comply with this AD within the
DIRECTIVES
‘‘General requirements.’’ Under that compliance times specified, unless already
section, Congress charges the FAA with done.
■ 1. The authority citation for part 39
promoting safe flight of civil aircraft in (g) Retained Criteria for Operation, With
continues to read as follows:
air commerce by prescribing regulations Clarifications and New Compliance Time
for practices, methods, and procedures Authority: 49 U.S.C. 106(g), 40113, 44701. This paragraph restates the actions
the Administrator finds necessary for § 39.13 [Amended]
required by paragraph (g) of AD 2013–08–23,
safety in air commerce. This regulation Amendment 39–17441 (78 FR 24037, April
is within the scope of that authority ■ 2. The FAA amends § 39.13 by 24, 2013), with clarification of actions for
removing Airworthiness Directive (AD) airplanes with auxiliary fuel tanks removed,
because it addresses an unsafe condition clarification of the pumps that must have a
that is likely to exist or develop on 2013–08–23, Amendment 39–17441 (78
protective device installed, and a new
products identified in this rulemaking FR 24037, April 24, 2013), and adding compliance time. Except as provided by
action. the following new AD: paragraph (h) of this AD: As of 48 months
The Boeing Company: Docket No. FAA– after the effective date of this AD, no person
Regulatory Findings 2015–0248; Directorate Identifier 2014– may operate any airplane affected by this AD
NM–143–AD. unless an amended type certificate or
We have determined that this supplemental type certificate that
proposed AD would not have federalism (a) Comments Due Date incorporates the design features and
implications under Executive Order The FAA must receive comments on this requirements described in paragraphs (g)(1)
13132. This proposed AD would not AD action by May 11, 2015. through (g)(4) of this AD has been approved
have a substantial direct effect on the by the Manager, Los Angeles Aircraft
(b) Affected ADs Certification Office (ACO), FAA, and those
States, on the relationship between the design features are installed on the airplane
national Government and the States, or (1) This AD replaces AD 2013–08–23,
Amendment 39–17441 (78 FR 24037, April to meet the criteria specified in 14 CFR
on the distribution of power and Section 25.981(a) and (d), at Amendment
24, 2013).
responsibilities among the various level 25–125. For airplanes on which Boeing-
(2) This AD affects AD 2008–06–21 R1,
levels of government. installed auxiliary fuel tanks are removed,
Amendment 39–16100 (74 FR 61504,
the actions specified in this AD for the
For the reasons discussed above, I November 25, 2009). auxiliary fuel tanks are not required.
certify that the proposed regulation: (3) This AD affects AD 2002–13–10, (1) For all airplanes: Each electrically
Amendment 39–12798 (67 FR 45053, July 8, powered alternating current (AC) fuel pump
(1) Is not a ‘‘significant regulatory 2002).
action’’ under Executive Order 12866, installed in any fuel tank that normally
(4) This AD affects AD 2011–11–05, empties during flight and each pump that is
(2) Is not a ‘‘significant rule’’ under Amendment 39–16704 (76 FR 31462, June 1, partially covered by a lowering fuel level—
the DOT Regulatory Policies and 2011). such as main tanks, center wing tanks,
auxiliary fuel tanks installed by the airplane
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Procedures (44 FR 11034, February 26, (c) Applicability
1979), manufacturer, and tail tanks—must have a
This AD applies to all The Boeing protective device installed to detect electrical
(3) Will not affect intrastate aviation Company Model airplanes identified in faults that can cause arcing and burn through
in Alaska, and paragraphs (c)(1) and (c)(2) of this AD, of the fuel pump housing and pump
certificated in any category. electrical connector. The same device must
(4) Will not have a significant (1) DC–10–10, DC–10–10F, DC–10–15, DC– shut off the pump by automatically removing
economic impact, positive or negative, 10–30, DC–10–30F (KC–10A and KDC–10), electrical power from the pump when such
on a substantial number of small entities DC–10–40, DC–10–40F airplanes. faults are detected. When a fuel pump is shut
under the criteria of the Regulatory (2) MD–10–10F, MD–10–30F, MD–11, and off resulting from detection of an electrical
Flexibility Act. MD–11F airplanes. fault, the device must stay latched off, until
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![16324 Federal Register / Vol. 80, No. 59 / Friday, March 27, 2015 / Proposed Rules
the fault is cleared through maintenance the Accomplishment Instructions of Boeing (k) Alternative Methods of Compliance
action and the pump is verified safe for Service Bulletin DC10–28–256, dated June (AMOCs)
operation. 24, 2014. (1) The Manager, Los Angeles Aircraft
(2) For airplanes with a 2-person flight (ii) Prior to or concurrently with
crew: Additional design features, if not Certification Office (ACO), FAA, has the
accomplishing the actions specified in
originally installed by the airplane authority to approve AMOCs for this AD, if
paragraph (h)(2)(i) of this AD: Replace the
manufacturer, must be installed to meet 3 fuel pump control relays with fault current requested using the procedures found in 14
criteria: To detect a running fuel pump in a detectors, and change the fuel tank boost/ CFR 39.19. In accordance with 14 CFR 39.19,
tank that is normally emptied during flight, transfer pump wire termination, in send your request to your principal inspector
to provide an indication to the flight crew accordance with the Accomplishment or local Flight Standards District Office, as
that the tank is empty, and to automatically Instructions of Boeing Alert Service Bulletin appropriate. If sending information directly
shut off that fuel pump. The prospective DC10–28A253, dated June 5, 2014. to the manager of the ACO, send it to the
pump indication and shutoff system must (3) For all airplanes: Within 30 days after attention of the person identified in
automatically shut off each pump in case the accomplishing the actions required by paragraph (l)(1) of this AD. Information may
flight crew does not shut off a pump running paragraph (h)(1) or (h)(2) of this AD, or be emailed to: 9-ANM-LAACO-AMOC-
dry in an empty tank within 60 seconds after
within 30 days after the effective date of this Requests@faa.gov.
each fuel tank is emptied. An airplane flight
AD, whichever occurs later, revise the (2) Before using any approved AMOC,
manual supplement (AFMS) that includes
maintenance or inspection program, as notify your appropriate principal inspector,
flight crew manual pump shutoff procedures
applicable, to incorporate the Critical Design or lacking a principal inspector, the manager
in the Limitations Section of the AFMS must
Configuration Control Limitations (CDCCLs),
be submitted to the Los Angeles ACO, FAA, of the local flight standards district office/
Airworthiness Limitations Instructions
for approval. certificate holding district office.
(3) For airplanes with a 3-person flight (ALIs), and short-term extensions specified in
Appendix B, C, and D of Special Compliance (3) An AMOC that provides an acceptable
crew: Additional design features, if not level of safety may be used for any repair
originally installed by the airplane Item (SCI) Report MDC–02K1003, Revision
M, dated July 25, 2014. The initial required by this AD if it is approved by the
manufacturer, must be installed to detect Boeing Commercial Airplanes Organization
when a fuel pump in a tank that is normally compliance time for accomplishing the
actions specified in the ALIs is at the later Designation Authorization (ODA) that has
emptied during flight is running in an empty
fuel tank, and provide an indication to the of the times specified in paragraphs (h)(3)(i) been authorized by the Manager, Los Angeles
flight crew that the tank is empty. The flight and (h)(3)(ii) of this AD. Revising of the ACO, to make those findings. For a repair
engineer must manually shut off each pump maintenance or inspection program required method to be approved, the repair must meet
running dry in an empty tank within 60 by this paragraph terminates the the certification basis of the airplane, and the
seconds after the tank is emptied. The AFMS requirements in paragraph (g) and (h) of AD approval must specifically refer to this AD.
Limitations section must be revised to 2008–06–21 R1, Amendment 39–16100 (74 (4) AMOCs approved for AD 2013–08–23,
specify that this pump shutoff must be done FR 61504, November 25, 2009). Amendment 39–17441 (78 FR 24037, April
by the flight engineer. (i) At the applicable time specified in
24, 2013), are approved as AMOCs for the
(4) For all airplanes with tanks that Appendix C of SCI Report MDC–02K1003,
Revision M, dated July 25, 2014, except as corresponding provisions of this AD.
normally empty during flight: Separate
means must be provided to detect and shut provided by Appendix D of SCI Report MDC– (l) Related Information
off a pump that was previously commanded 02K1003, Revision M, dated July 25, 2014.
(ii) Within 30 days after accomplishing the (1) For more information about this AD,
to be shut off automatically or manually but
actions required by paragraph (h)(1) or (h)(2) contact Serj Harutunian, Aerospace Engineer,
remained running in an empty tank during
flight. of this AD, or within 30 days after the Propulsion Branch, ANM–140L, FAA, Los
effective date of this AD, whichever occurs Angeles Aircraft Certification Office (ACO),
(h) New Optional Method of Compliance later. 3960 Paramount Boulevard, Lakewood,
In lieu of doing the requirements of California 90712–4137; phone: 562–627–
(i) No Alternative Actions, Intervals, or
paragraph (g) of this AD, do the applicable 5254; fax: 562–627–5210; email:
CDCCLs
actions specified in paragraphs (h)(1), (h)(2), serj.harutunian@faa.gov.
and (h)(3) of this AD. If the option in paragraph (h)(3) of this AD (2) For service information identified in
(1) For MD–11 and MD–11F airplanes: Do is accomplished: After the maintenance or
this AD, contact Boeing Commercial
the actions specified in paragraphs (h)(1)(i) inspection program has been revised, as
Airplanes, Attention: Data & Services
and (h)(1)(ii) of this AD. provided by paragraph (h)(3) of this AD, no
alternative actions (e.g., inspections), Management, 3855 Lakewood Boulevard, MC
(i) As of 48 months after the effective date
of this AD, change the fuel pump control and intervals, or CDCCLs may be used unless the D800–0019, Long Beach, CA 90846–0001;
indication system wiring, in accordance with actions, intervals, or CDCCLs are approved as telephone 206–544–5000, extension 2; fax
the Accomplishment Instructions of Boeing an alternative method of compliance (AMOC) 206–766–5683; Internet https://
Alert Service Bulletin MD11–28–137, dated in accordance with the procedures specified www.myboeingfleet.com. You may view this
June 24, 2014. in paragraph (k) of this AD. referenced service information at the FAA,
(ii) Prior to or concurrently with Transport Airplane Directorate, 1601 Lind
(j) Compliance Time Extension in Related
accomplishing the actions specified in Avenue SW., Renton, WA. For information
ADs
paragraph (h)(1)(i) of this AD: Replace the on the availability of this material at the
fuel pump control relays with fault current Accomplishment of the actions specified in FAA, call 425–227–1221.
detectors, and change the fuel tank boost/ paragraphs (h)(1), (h)(2), and (h)(3) of this
transfer pump wire termination, in AD, as applicable, extends the 18-month Issued in Renton, Washington, on February
accordance with Accomplishment repetitive inspections and tests required by 11, 2015.
Instructions of Boeing Alert Service Bulletin paragraph (a) of AD 2002–13–10,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Jeffrey E. Duven,
MD11–28A133, dated June 5, 2014. Amendment 39–12798 (67 FR 45053, July 8,
2002), and the 18-month repetitive Manager, Transport Airplane Directorate,
(2) For Model DC–10–10, DC–10–10F, DC–
10–15, DC–10–30, DC–10–30F (KC–10A and inspections required by paragraph (j) of AD Aircraft Certification Service.
KDC–10), DC–10–40, DC–10–40F, MD–10– 2011–11–05, Amendment 39–16704 (76 FR [FR Doc. 2015–06746 Filed 3–26–15; 8:45 am]
10F, and MD–10–30F airplanes: Do the 31462, June 1, 2011), to 24-month intervals BILLING CODE 4910–13–P
actions specified in paragraphs (h)(2)(i) and for pumps affected by those ADs, regardless
(h)(2)(ii) of this AD. if the pump is installed in a tank that
(i) As of 48 months after the effective date normally empties, provided the remaining
of this AD, change the fuel pump control and actions required by those two ADs have been
indication system wiring, in accordance with accomplished.
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Document Created: 2015-12-18 11:36:11
Document Modified: 2015-12-18 11:36:11
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 11, 2015. | |
| Contact | Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712- 4137; phone: 562-627-5254; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 80 FR 16321 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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