81 FR 7967 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 31 (February 17, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 31 (February 17, 2016)
| Page Range | 7967-7971 | |
| FR Document | 2016-02232 |
[Federal Register Volume 81, Number 31 (Wednesday, February 17, 2016)] [Rules and Regulations] [Pages 7967-7971] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-02232] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0249; Directorate Identifier 2014-NM-174-AD; Amendment 39-18393; AD 2016-03-06] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-18-05 for The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9- 50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes; equipped with a center wing fuel tank and Boeing original equipment manufacturer-installed auxiliary fuel tanks. AD 2012-18-05 required adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. Since we issued AD 2012-18-05, we have determined that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. This new AD allows certain actions as optional methods of compliance. This AD was prompted by our determination that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. 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. DATES: This AD is effective March 23, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 23, 2016. ADDRESSES: For service information identified in this final rule, 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-2015-0249. 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- 0249; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: S[eacute]rj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5254; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR [[Page 7968]] part 39 to supersede AD 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012). AD 2012-18-05 applied to The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD- 87), MD-88, and MD-90-30 airplanes; equipped with a center wing fuel tank and Boeing original equipment manufacturer-installed auxiliary fuel tanks. The NPRM published in the Federal Register on March 26, 2015 (80 FR 15947). The NPRM was prompted by our determination that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. The NPRM proposed to allow certain actions as optional methods of compliance. We are issuing this AD to correct the unsafe condition on these products. Explanation of Revised Service Information The NPRM (80 FR 15947, March 26, 2015) specified Boeing Service Bulletin MD80-28-228, dated September 27, 2013; and Boeing Service Bulletin MD90-28-013, dated September 27, 2013; as the appropriate sources of service information for the required actions. Since the NPRM was published, both service bulletins have been revised and this AD now specifies Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015; and Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015, as the source of appropriate service information for the required actions. Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015; and Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015; both clarify the required actions and require enlarging holes and identifying a bracket. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 15947, March 26, 2015) and the FAA's response to each comment. Support for the Comment Delta Air Lines supported the comments made by Boeing, which are discussed in the following paragraphs. Request To Revise the Applicability Boeing requested that we revise paragraph (c) of the proposed AD (80 FR 15947, March 26, 2015). Boeing explained that the proposed AD should apply to the airplanes identified in paragraphs (c)(6) through (c)(8) of the proposed AD if they are equipped with center wing fuel tanks, and to airplanes identified in paragraphs (c)(1) through (c)(8) of the proposed AD if they are equipped with original equipment manufacturer-installed auxiliary fuel tanks. Boeing reasoned that DC-9 center wing fuel tanks are not affected by the proposed AD, and that the ``fuel system reviews conducted by the manufacturer'' (i.e., Boeing's SFAR 88 system safety assessments (SSA)) cited in paragraph (e) of the proposed AD concluded that center wing fuel tanks on Model DC-9 airplanes identified as paragraphs (c)(1) through (c)(5) of the proposed AD do not require the corrective actions cited in the NPRM. For airplanes with a CWT identified in paragraphs (c)(1) through (c)(5) of the proposed AD, the existing design features offer adequate protection relative to a pump running in an empty fuel tank and new design features added to the center tank fuel boost pump container address types of electrical faults cited in the NPRM. Boeing expressed that the FAA had previously concurred with the related Boeing SSA findings and approved Boeing Service Bulletin DC9- 28-216, dated March 18, 2008, mandated by FAA AD 2009-03-03, Amendment 39-15804 (74 FR 8150, February 24, 2009), as corrective action for the electrical arc burn-through. We agree to revise the applicability of this AD for the reasons stated by the commenter. We have revised paragraph (c) of this AD accordingly. Request To Clarify Certain Optional Requirements Boeing requested that we revise paragraph (h)(1)(i) of the proposed AD (80 FR 15947, March 26, 2015) by adding the phrase, ``and change fuel pump system wiring'' after ``install ground fault interrupter (GFI) relays.'' Boeing reasoned that in addition to providing procedures for installing GFI relays, Boeing Service Bulletin MD80-28- 228, dated September 27, 2013, also incorporates wiring changes to accommodate the GFI's operation and revises low pressure indication system wiring for center wing and auxiliary fuel tank fuel pumps. The low pressure indication system wiring changes are required to address the potential of fuel pumps running for prolonged periods in empty tanks. Boeing also requested that we revise paragraph (h)(2) of the proposed AD (80 FR 15947, March 26, 2015) by removing the phrase, ``install brackets and mod block rails, and'' and adding the phrase, ``and change fuel pump system wiring.'' Boeing reasoned that while Boeing Service Bulletin MD90-28-013, dated September 27, 2013, does specify installation of brackets and rails, as does Boeing Service Bulletin MD80-28-228, dated September 27, 2013, the primary changes that will address the unsafe condition are the GFI relay and wiring changes defined in Boeing Service Bulletin MD90-28-013, dated September 27, 2013. Boeing expressed that the brackets and rails can be omitted from the text of the NPRM, as they are referenced in the service information. Also, in addition to providing procedures for installing GFI relays, Boeing Service Bulletin MD90-28-013, dated September 27, 2013, also incorporates wiring changes to accommodate the GFI's operation and revises low pressure indication system wiring for center wing and auxiliary fuel tank fuel pumps. Boeing stated that the low pressure indication system wiring changes are required to address the potential of fuel pumps running for prolonged periods in empty tanks. For the reasons stated by the commenter, we agree to revise paragraphs (h)(1)(i) and (h)(2) of this AD by incorporating the requested changes. As stated earlier, since the NPRM was published, both service bulletins have been revised and this AD now specifies Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015; and Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015, as the appropriate sources of service information for the required actions. Request To Revise to the Latest Service Information Delta requested that we revise paragraph (h)(3) of the proposed AD (80 FR 15947, March 26, 2015) to include the latest service information. Delta noted that the proposed AD would require the incorporation of ``Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitations Instructions (ALIs), and short-term extensions specified in Appendixes B, C, and D of Boeing Special Compliance Item Report MDC-92K9145, Revision M'' into the maintenance and inspection program. Delta noted, however, that the referenced report has been revised to Revision N, dated June 13, 2014, and it recommends that the restriction to Revision M be removed from the final rule. For the reasons stated by the commenter, we have revised this AD to refer to the latest service information. [[Page 7969]] Request for Credit for Previously Accomplished Installations Delta requested that we revise paragraph (k) of the proposed AD (80 FR 15947, March 26, 2015) to permit credit for previously accomplished installations for paragraph (h)(1)(i) or (h)(2) of the proposed AD. Delta reasoned that paragraph (h)(1)(i) of the proposed AD provides for the installation of GFI relays on Model MD-80 series airplanes (Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 airplanes) using the procedures in Boeing Service Bulletin MD80-28-228, dated September 27, 2013. And similarly, paragraph (h)(2) of the proposed AD provides for the installation of GFI relays on MD- 90-30 airplanes in accordance with Boeing Service Bulletin MD9028-013, dated September 27, 2013. Delta explained that it has completed installation of GFI relays using the procedures in these two service bulletins on a portion of its fleet, and noted that there is no practical way to re-accomplish such modifications after the effective date of the final rule. For the reasons given by the commenter, and the addition of the latest service information, we have provided credit for the applicable actions specified in paragraph (k) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 15947, March 26, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 15947, March 26, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015; and Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015. The service information describes procedures for installing GFI relays that change fuel pump system wiring, installing a low fuel pressure indication system, and enlarging holes and identifying a bracket. We have also reviewed Boeing Twinjet Special Compliance Item Report MDC-92K9145, Revision N, dated June 13, 2014, including Appendices A through D. This service information details special compliance items (SCIs), critical design configuration control limitations (CDCCLs), airworthiness limitation instructions (ALIs), short-term extensions, and associated compliance intervals. Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015, specifies prior or concurrent accomplishment of the following service information. McDonnell Douglas MD-80 Service Bulletin 28-53, Revision 1, dated April 16, 1992, which describes procedures for installing a low fuel pressure indication system. McDonnell Douglas MD-80 Service Bulletin 28-63, Revision 2, dated April 8, 1992, which describes procedures for installing a low fuel pressure indication inhibit system. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 809 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Installing design features for 50 work-hours x $85 per $35,000 $39,250 $10,322,750 airplanes with center wing and hour = $4,250. auxiliary tanks (263 airplanes), using a method approved by the FAA [retained actions from AD 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012)]. Installing design features for 35 work-hours x $85 per 17,000 19,975 10,906,350 airplanes with center wing tank (546 hour = $2,975. airplanes), using a method approved by the FAA [retained actions from AD 2012-1805, Amendment 39-17181 (77 FR 54793, September 6, 2012)]. ---------------------------------------------------------------------------------------------------------------- Estimated Costs--New Optional Actions for Installing Design Features ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- For airplanes with center wing and auxiliary 250 work-hours x $85 per hour = $69,000 $90,250 tanks, using service information specified in $21,250. paragraph (h) of this AD (including revising the maintenance/inspection program). For airplanes with center wing tank, using 110 work-hours x $85 = 9,350.... 30,000 39,350 service information specified in paragraph (h) of this AD (including revising the maintenance/inspection program). Installing the supplemental type certificate 35 work-hours x $85 per hour = 17,000 19,975 (STC) specified in paragraph (i) of this AD. $2,975. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 7970]] 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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) 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012, and adding the following new AD: 2016-03-06 The Boeing Company: Amendment 39-18393; Docket No. FAA- 2015-0249; Directorate Identifier 2014-NM-174-AD. (a) Effective Date This AD is effective March 23, 2016. (b) Affected ADs This AD replaces AD 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, that are identified in paragraphs (c)(6) through (c)(8) of this AD and equipped with center wing fuel tanks; and those identified in paragraphs (c)(1) through (c)(8) of this AD that are equipped with Boeing original equipment manufacturer-installed auxiliary fuel tanks. For airplanes on which the auxiliary fuel tanks are removed, the actions specified for the auxiliary fuel tanks are not required. (1) Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9- 15F airplanes. (2) Model DC-9-21 airplanes. (3) Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC 9 34F, and DC 9 32F (C-9A, C 9B) airplanes. (4) Model DC-9-41 airplanes. (5) Model DC-9-51 airplanes. (6) Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes. (7) Model MD-88 airplanes. (8) Model MD-90-30 airplanes. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by fuel system reviews 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 New Compliance Time This paragraph restates the actions required by paragraph (g) of AD 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012), with a new compliance time. Except as provided by paragraphs (h) and (i) of this AD: As of 42 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) and (g)(2) 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. (1) Each electrically powered fuel pump installed in the center wing tank or auxiliary fuel tank must have a protective device installed to detect electrical faults that can cause arcing and burn through the fuel pump housing. 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 as the result of detection of an electrical fault, the device must stay latched off until the fault is cleared through maintenance action and verified that the pump and the electrical power feed are safe for operation. (2) Additional design features must be installed to detect when any center wing tank or auxiliary fuel tank pump is running in an empty fuel tank. The prospective pump shutoff system must shut off each pump no later than 60 seconds after the fuel tank is emptied. The pump shutoff system design must preclude undetected running of a fuel pump in an empty tank, after the pump was commanded off manually or automatically. (h) New Optional Methods of Compliance For Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC- 9-87 (MD-87), and Model MD-88 airplanes; and Model MD-90-30 airplanes: 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 Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 airplanes: Do the applicable actions specified in paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of this AD. (i) For all airplanes identified in paragraph (h)(1) of this AD: Within the compliance time specified in paragraph (g) of this AD, install ground fault interrupter (GFI) relays and change fuel pump system wiring, in accordance with the Accomplishment Instructions of Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015. (ii) For airplanes identified in McDonnell Douglas MD-80 Service Bulletin 28-53, Revision 1, dated April 16, 1992: Prior to or concurrently with accomplishing the action specified in paragraph (h)(1)(i) of this AD, install a low fuel pressure indication system, in accordance with the Accomplishment Instructions of McDonnell Douglas MD-80 Service Bulletin 28-53, Revision 1, dated April 16, 1992. (iii) For airplanes identified in McDonnell Douglas MD-80 Service Bulletin 28-63, Revision 2, dated April 8, 1992: Prior to or concurrently with accomplishing the action specified in paragraph (h)(1)(i) of this AD, install a low fuel pressure indication inhibition system, in accordance with the Accomplishment Instructions of McDonnell Douglas MD-80 Service Bulletin 28-63, Revision 2, dated April 8, 1992. (2) For Model MD-90-30 airplanes: Within the compliance time specified in paragraph (g) of this AD, install GFI relays and change fuel pump system wiring, in accordance with the Accomplishment Instructions of Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015. (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 [[Page 7971]] applicable, to incorporate the Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitation Instructions (ALIs), and Short-Term Extensions specified in Appendices B, C, and D of Boeing Twinjet Special Compliance Item Report MDC-92K9145, Revision N, dated June 13, 2014. The initial compliance time for accomplishing the actions specified in the ALIs is at the later of the times in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Doing the revision of the maintenance or inspection program, as applicable, required by this paragraph terminates the requirements in paragraphs (g) and (h) of AD 2008-11-15, Amendment 3915538 (73 FR 30746, May 29, 2008). (i) At the applicable time specified in Appendix C of Boeing Twinjet Special Compliance Item Report MDC-92K9145, Revision N, dated June 13, 2014, except as provided by Appendix D of Boeing Twinjet Special Compliance Item Report MDC-92K9145, Revision N, dated June 13, 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) New Optional Universal Fault Interrupter (UFI) Installation In lieu of doing the requirements of paragraph (g) of this AD, within the compliance time specified in paragraph (g) of this AD install a TDG Aerospace Inc. UFI using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Note 1 to paragraph (i) of this AD: TDG Aerospace STC ST02502LA (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ 4d132827a425d7de86257cd3004dfc02/$FILE/ST02502LA.pdf) provides additional guidance for installing the TDG UFI. (j) No Alternative Actions, Intervals, and CDCCLs After the maintenance or inspection program, as applicable, has been revised as required 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 (l) of this AD. (k) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraphs (h)(1)(ii) and (h)(1)(iii) of this AD, if those actions were performed before the effective date of this AD using any of the service information specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, which are not incorporated by reference in this AD. (i) McDonnell Douglas MD-80 Service Bulletin 28-53, dated April 8, 1991. (ii) McDonnell Douglas MD-80 Service Bulletin 28-63, dated, June 14, 1991. (iii) McDonnell Douglas MD-80 Service Bulletin 28-63, Revision 1, dated July 19, 1991. (2) This paragraph provides credit for the actions specified in paragraphs (h)(1)(i) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin MD80-28-228, dated September 27, 2013; or Boeing Service Bulletin MD90-28-013, dated September 27, 2013, which are not incorporated by reference in this AD. (l) 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 (m)(1) of this AD. Information may be emailed to: [email protected]. (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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2012-18-05, Amendment 39-17181 (77 FR 54793, September 6, 2012), are approved as AMOCs for the corresponding provisions of this AD. (m) Related Information (1) For more information about this AD, contact S[eacute]rj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5254; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Service Bulletin MD80-28-228, Revision 1, dated August 27, 2015. (ii) Boeing Service Bulletin MD90-28-013, Revision 1, dated August 27, 2015. (iii) Boeing Twinjet Special Compliance Item Report MDC-92K9145, Revision N, dated June 13, 2014, including Appendices A through D. (iv) McDonnell Douglas MD-80 Service Bulletin 28-53, Revision 1, dated April 16, 1992. (v) McDonnell Douglas MD-80 Service Bulletin 28-63, Revision 2, dated April 8, 1992. (3) For Boeing 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. (4) You may view this service information at 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on January 25, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-02232 Filed 2-16-16; 8:45 am] BILLING CODE 4910-13-P
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change to the type certificate to include of the fuselage. For the angular compliance. This AD was prompted by
another model incorporating the same acceleration conditions, zero rolling our determination that it is necessary to
novel or unusual design feature, these velocity may be assumed in the absence clarify the actions for airplanes on
special conditions would apply to that of a rational time-history investigation which the auxiliary fuel tanks are
model as well. of the maneuver. removed. We are issuing this AD to
2. At VA, sudden movement of the reduce the potential of ignition sources
Conclusion
cockpit roll control up to the limit is inside fuel tanks, which, in combination
This action affects only certain novel assumed. The position of the cockpit with flammable fuel vapors, could result
or unusual design features on one model roll control must be maintained until a in fuel tank explosions and consequent
of airplane. It is not a rule of general steady roll rate is achieved, and then loss of the airplane.
applicability. must be returned suddenly to the DATES: This AD is effective March 23,
The substance of these special neutral position. 2016.
conditions has been subjected to the 3. At VC, the cockpit roll control must The Director of the Federal Register
notice and comment period in several be moved suddenly and maintained so approved the incorporation by reference
prior instances and has been derived as to achieve a roll rate not less than of certain publications listed in this AD
without substantive change from those that obtained in special condition 2, as of March 23, 2016.
previously issued. It is unlikely that above. ADDRESSES: For service information
prior public comment would result in a 4. At VD, the cockpit roll control must identified in this final rule, contact
significant change from the substance be moved suddenly and maintained so Boeing Commercial Airplanes,
contained herein. Therefore, because a as to achieve a roll rate not less than Attention: Data & Services Management,
delay would significantly affect the one-third of that obtained in special 3855 Lakewood Boulevard, MC D800–
certification of the airplane, which is condition 2, above. 0019, Long Beach, CA 90846–0001;
imminent, the FAA has determined that Issued in Renton, Washington, on February telephone 206–544–5000, extension 2;
prior public notice and comment are 4, 2016. fax 206–766–5683; Internet https://
unnecessary and impracticable, and Michael Kaszycki, www.myboeingfleet.com. You may view
good cause exists for adopting these this referenced service information at
Acting Manager, Transport Airplane
special conditions upon publication in Directorate, Aircraft Certification Service. the FAA, Transport Airplane
the Federal Register. The FAA is Directorate, 1601 Lind Avenue SW.,
[FR Doc. 2016–03212 Filed 2–16–16; 8:45 am]
requesting comments to allow interested Renton, WA. For information on the
BILLING CODE 4910–13–P
persons to submit views that may not availability of this material at the FAA,
have been submitted in response to the call 425–227–1221. It is also available
prior opportunities for comment on the Internet at http://
DEPARTMENT OF TRANSPORTATION
described above. www.regulations.gov by searching for
List of Subjects in 14 CFR Part 25 Federal Aviation Administration and locating Docket No. FAA–2015–
0249.
Aircraft, Aviation safety, Reporting 14 CFR Part 39
and recordkeeping requirements. Examining the AD Docket
[Docket No. FAA–2015–0249; Directorate
■ The authority citation for these Identifier 2014–NM–174–AD; Amendment
You may examine the AD docket on
special conditions is as follows: 39–18393; AD 2016–03–06] the Internet at http://
Authority: 49 U.S.C. 106(g), 40113, 44701, www.regulations.gov by searching for
RIN 2120–AA64 and locating Docket No. FAA–2015–
44702, 44704.
0249; or in person at the Docket
The Special Conditions Airworthiness Directives; The Boeing Management Facility between 9 a.m.
Company Airplanes and 5 p.m., Monday through Friday,
■ Accordingly, pursuant to the authority
delegated to me by the Administrator, AGENCY: Federal Aviation except Federal holidays. The AD docket
the following special conditions are Administration (FAA), DOT. contains this AD, the regulatory
issued as part of the type certification ACTION: Final rule.
evaluation, any comments received, and
basis for Dassault Aviation Model other information. The address for the
Falcon 5X airplanes. SUMMARY: We are superseding Docket Office (phone: 800–647–5527) is
In lieu of compliance to § 25.349(a), Airworthiness Directive (AD) 2012–18– Docket Management Facility, U.S.
the following conditions, speeds, and 05 for The Boeing Company Model DC– Department of Transportation, Docket
cockpit roll-control motions (except as 9–10, DC–9–20, DC–9–30, DC–9–40, and Operations, M–30, West Building
the motions may be limited by pilot DC–9–50 series airplanes; and Model Ground Floor, Room W12–140, 1200
effort) must be considered in DC–9–81 (MD–81), DC–9–82 (MD–82), New Jersey Avenue SE., Washington,
combination with an airplane load DC–9–83 (MD–83), DC–9–87 (MD–87), DC 20590.
factor of zero, and of two-thirds of the MD–88, and MD–90–30 airplanes; FOR FURTHER INFORMATION CONTACT: Sérj
positive maneuvering factor used in equipped with a center wing fuel tank Harutunian, Aerospace Engineer,
design. In determining the resulting and Boeing original equipment Propulsion Branch, ANM–140L, FAA,
control-surface deflections, the torsional manufacturer-installed auxiliary fuel Los Angeles Aircraft Certification Office
flexibility of the wing must be tanks. AD 2012–18–05 required adding (ACO), 3960 Paramount Boulevard,
asabaliauskas on DSK5VPTVN1PROD with RULES
considered in accordance with design features to detect electrical faults Lakewood, CA 90712–4137; phone:
§ 25.301(b). and to detect a pump running in an 562–627–5254; fax: 562–627–5210;
1. Conditions corresponding to steady empty fuel tank. Since we issued AD email: serj.harutunian@faa.gov.
rolling velocities must be investigated. 2012–18–05, we have determined that it SUPPLEMENTARY INFORMATION:
In addition, conditions corresponding to is necessary to clarify the actions for
maximum angular acceleration must be airplanes on which the auxiliary fuel Discussion
investigated for airplanes with engines tanks are removed. This new AD allows We issued a notice of proposed
or other weight concentrations outboard certain actions as optional methods of rulemaking (NPRM) to amend 14 CFR
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![Federal Register / Vol. 81, No. 31 / Wednesday, February 17, 2016 / Rules and Regulations 7969
Request for Credit for Previously Conclusion MDC–92K9145, Revision N, dated June
Accomplished Installations We reviewed the relevant data, 13, 2014, including Appendices A
considered the comments received, and through D. This service information
Delta requested that we revise details special compliance items (SCIs),
paragraph (k) of the proposed AD (80 FR determined that air safety and the
public interest require adopting this AD critical design configuration control
15947, March 26, 2015) to permit credit limitations (CDCCLs), airworthiness
for previously accomplished with the changes described previously.
We have determined that these minor limitation instructions (ALIs), short-
installations for paragraph (h)(1)(i) or term extensions, and associated
(h)(2) of the proposed AD. Delta changes:
reasoned that paragraph (h)(1)(i) of the • Are consistent with the intent that compliance intervals.
proposed AD provides for the was proposed in the NPRM (80 FR Boeing Service Bulletin MD80–28–
installation of GFI relays on Model MD– 15947, March 26, 2015) for correcting 228, Revision 1, dated August 27, 2015,
80 series airplanes (Model DC–9–81 the unsafe condition; and specifies prior or concurrent
• Do not add any additional burden accomplishment of the following service
(MD–81), DC–9–82 (MD–82), DC–9–83
upon the public than was already information.
(MD–83), DC–9–87 (MD–87), and Model
MD–88 airplanes) using the procedures
proposed in the NPRM (80 FR 15947, • McDonnell Douglas MD–80 Service
March 26, 2015). Bulletin 28–53, Revision 1, dated April
in Boeing Service Bulletin MD80–28– We also determined that these
228, dated September 27, 2013. And 16, 1992, which describes procedures
changes will not increase the economic for installing a low fuel pressure
similarly, paragraph (h)(2) of the burden on any operator or increase the
proposed AD provides for the indication system.
scope of this AD. • McDonnell Douglas MD–80 Service
installation of GFI relays on MD–90–30
airplanes in accordance with Boeing Related Service Information Under 1 Bulletin 28–63, Revision 2, dated April
Service Bulletin MD9028–013, dated CFR Part 51 8, 1992, which describes procedures for
September 27, 2013. Delta explained We reviewed Boeing Service Bulletin installing a low fuel pressure indication
that it has completed installation of GFI MD80–28–228, Revision 1, dated inhibit system.
relays using the procedures in these two August 27, 2015; and Boeing Service This service information is reasonably
service bulletins on a portion of its fleet, Bulletin MD90–28–013, Revision 1, available because the interested parties
and noted that there is no practical way dated August 27, 2015. The service have access to it through their normal
to re-accomplish such modifications information describes procedures for course of business or by the means
after the effective date of the final rule. installing GFI relays that change fuel identified in the ADDRESSES section.
For the reasons given by the pump system wiring, installing a low Costs of Compliance
commenter, and the addition of the fuel pressure indication system, and
latest service information, we have enlarging holes and identifying a We estimate that this AD affects 809
provided credit for the applicable bracket. airplanes of U.S. registry.
actions specified in paragraph (k) of this We have also reviewed Boeing We estimate the following costs to
AD. Twinjet Special Compliance Item Report comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Installing design features for airplanes with center wing and 50 work-hours × $85 per hour $35,000 $39,250 $10,322,750
auxiliary tanks (263 airplanes), using a method approved = $4,250.
by the FAA [retained actions from AD 2012–18–05,
Amendment 39–17181 (77 FR 54793, September 6,
2012)].
Installing design features for airplanes with center wing tank 35 work-hours × $85 per hour 17,000 19,975 10,906,350
(546 airplanes), using a method approved by the FAA [re- = $2,975.
tained actions from AD 2012–1805, Amendment 39–
17181 (77 FR 54793, September 6, 2012)].
ESTIMATED COSTS—NEW OPTIONAL ACTIONS FOR INSTALLING DESIGN FEATURES
Cost per
Action Labor cost Parts cost product
For airplanes with center wing and auxiliary tanks, using service infor- 250 work-hours × $85 per hour = $69,000 $90,250
mation specified in paragraph (h) of this AD (including revising the $21,250.
maintenance/inspection program).
For airplanes with center wing tank, using service information specified 110 work-hours × $85 = 9,350 ........ 30,000 39,350
in paragraph (h) of this AD (including revising the maintenance/in-
spection program).
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Installing the supplemental type certificate (STC) specified in paragraph 35 work-hours × $85 per hour = 17,000 19,975
(i) of this AD. $2,975.
Authority for This Rulemaking rules on aviation safety. Subtitle I, Aviation Programs, describes in more
Title 49 of the United States Code Section 106, describes the authority of detail the scope of the Agency’s
specifies the FAA’s authority to issue the FAA Administrator. Subtitle VII, authority.
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![7970 Federal Register / Vol. 81, No. 31 / Wednesday, February 17, 2016 / Rules and Regulations
We are issuing this rulemaking under (a) Effective Date housing. The same device must shut off the
the authority described in Subtitle VII, This AD is effective March 23, 2016. pump by automatically removing electrical
Part A, Subpart III, Section 44701, power from the pump when such faults are
(b) Affected ADs detected. When a fuel pump is shut off as the
‘‘General requirements.’’ Under that result of detection of an electrical fault, the
section, Congress charges the FAA with This AD replaces AD 2012–18–05,
Amendment 39–17181 (77 FR 54793, device must stay latched off until the fault is
promoting safe flight of civil aircraft in September 6, 2012). cleared through maintenance action and
air commerce by prescribing regulations verified that the pump and the electrical
for practices, methods, and procedures (c) Applicability power feed are safe for operation.
the Administrator finds necessary for This AD applies to The Boeing Company (2) Additional design features must be
safety in air commerce. This regulation airplanes, certificated in any category, that installed to detect when any center wing tank
is within the scope of that authority are identified in paragraphs (c)(6) through or auxiliary fuel tank pump is running in an
(c)(8) of this AD and equipped with center empty fuel tank. The prospective pump
because it addresses an unsafe condition
wing fuel tanks; and those identified in shutoff system must shut off each pump no
that is likely to exist or develop on paragraphs (c)(1) through (c)(8) of this AD later than 60 seconds after the fuel tank is
products identified in this rulemaking that are equipped with Boeing original emptied. The pump shutoff system design
action. equipment manufacturer-installed auxiliary must preclude undetected running of a fuel
fuel tanks. For airplanes on which the pump in an empty tank, after the pump was
Regulatory Findings auxiliary fuel tanks are removed, the actions commanded off manually or automatically.
We have determined that this AD will specified for the auxiliary fuel tanks are not
required. (h) New Optional Methods of Compliance
not have federalism implications under
Executive Order 13132. This AD will (1) Model DC–9–11, DC–9–12, DC–9–13, For Model DC–9–81 (MD–81), DC–9–82
not have a substantial direct effect on DC–9–14, DC–9–15, and DC–9–15F airplanes. (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–
(2) Model DC–9–21 airplanes. 87), and Model MD–88 airplanes; and Model
the States, on the relationship between (3) Model DC–9–31, DC–9–32, DC–9–32 MD–90–30 airplanes: In lieu of doing the
the national government and the States, (VC–9C), DC–9–32F, DC–9–33F, DC–9–34, requirements of paragraph (g) of this AD, do
or on the distribution of power and DC 9 34F, and DC 9 32F (C–9A, C 9B) the applicable actions specified in
responsibilities among the various airplanes. paragraphs (h)(1), (h)(2), and (h)(3) of this
levels of government. (4) Model DC–9–41 airplanes. AD.
For the reasons discussed above, I (5) Model DC–9–51 airplanes. (1) For Model DC–9–81 (MD–81), DC–9–82
certify that this AD: (6) Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–
(1) Is not a ‘‘significant regulatory (MD–82), DC–9–83 (MD–83), and DC–9–87 87), and Model MD–88 airplanes: Do the
action’’ under Executive Order 12866, (MD–87) airplanes. applicable actions specified in paragraphs
(7) Model MD–88 airplanes. (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of this AD.
(2) Is not a ‘‘significant rule’’ under (8) Model MD–90–30 airplanes. (i) For all airplanes identified in paragraph
DOT Regulatory Policies and Procedures (h)(1) of this AD: Within the compliance time
(44 FR 11034, February 26, 1979), (d) Subject
specified in paragraph (g) of this AD, install
(3) Will not affect intrastate aviation Air Transport Association (ATA) of ground fault interrupter (GFI) relays and
in Alaska, and America Code 28, Fuel. change fuel pump system wiring, in
(4) Will not have a significant (e) Unsafe Condition accordance with the Accomplishment
economic impact, positive or negative, Instructions of Boeing Service Bulletin
This AD was prompted by fuel system MD80–28–228, Revision 1, dated August 27,
on a substantial number of small entities reviews conducted by the manufacturer. We
under the criteria of the Regulatory 2015.
are issuing this AD to reduce the potential of (ii) For airplanes identified in McDonnell
Flexibility Act. ignition sources inside fuel tanks, which, in Douglas MD–80 Service Bulletin 28–53,
List of Subjects in 14 CFR Part 39 combination with flammable fuel vapors,
Revision 1, dated April 16, 1992: Prior to or
could result in fuel tank explosions and
concurrently with accomplishing the action
Air transportation, Aircraft, Aviation consequent loss of the airplane.
specified in paragraph (h)(1)(i) of this AD,
safety, Incorporation by reference, (f) Compliance install a low fuel pressure indication system,
Safety. in accordance with the Accomplishment
Comply with this AD within the
Adoption of the Amendment compliance times specified, unless already Instructions of McDonnell Douglas MD–80
done. Service Bulletin 28–53, Revision 1, dated
Accordingly, under the authority April 16, 1992.
delegated to me by the Administrator, (g) Retained Criteria for Operation, With (iii) For airplanes identified in McDonnell
the FAA amends 14 CFR part 39 as New Compliance Time Douglas MD–80 Service Bulletin 28–63,
follows: This paragraph restates the actions Revision 2, dated April 8, 1992: Prior to or
required by paragraph (g) of AD 2012–18–05, concurrently with accomplishing the action
PART 39—AIRWORTHINESS Amendment 39–17181 (77 FR 54793, specified in paragraph (h)(1)(i) of this AD,
DIRECTIVES September 6, 2012), with a new compliance install a low fuel pressure indication
time. Except as provided by paragraphs (h) inhibition system, in accordance with the
■ 1. The authority citation for part 39 and (i) of this AD: As of 42 months after the Accomplishment Instructions of McDonnell
continues to read as follows: effective date of this AD, no person may Douglas MD–80 Service Bulletin 28–63,
operate any airplane affected by this AD Revision 2, dated April 8, 1992.
Authority: 49 U.S.C. 106(g), 40113, 44701. unless an amended type certificate or (2) For Model MD–90–30 airplanes: Within
supplemental type certificate that the compliance time specified in paragraph
§ 39.13 [Amended] (g) of this AD, install GFI relays and change
incorporates the design features and
■ 2. The FAA amends § 39.13 by requirements described in paragraphs (g)(1) fuel pump system wiring, in accordance with
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removing Airworthiness Directive (AD) and (g)(2) of this AD has been approved by the Accomplishment Instructions of Boeing
2012–18–05, Amendment 39–17181 (77 the Manager, Los Angeles Aircraft Service Bulletin MD90–28–013, Revision 1,
Certification Office (ACO), FAA, and those dated August 27, 2015.
FR 54793, September 6, 2012, and
design features are installed on the airplane. (3) For all airplanes: Within 30 days after
adding the following new AD: (1) Each electrically powered fuel pump accomplishing the actions required by
2016–03–06 The Boeing Company: installed in the center wing tank or auxiliary paragraph (h)(1) or (h)(2) of this AD or within
Amendment 39–18393; Docket No. fuel tank must have a protective device 30 days after the effective date of this AD,
FAA–2015–0249; Directorate Identifier installed to detect electrical faults that can whichever occurs later, revise the
2014–NM–174–AD. cause arcing and burn through the fuel pump maintenance or inspection program, as
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![Federal Register / Vol. 81, No. 31 / Wednesday, February 17, 2016 / Rules and Regulations 7971
applicable, to incorporate the Critical Design (h)(2) of this AD, if those actions were (iv) McDonnell Douglas MD–80 Service
Configuration Control Limitations (CDCCLs), performed before the effective date of this AD Bulletin 28–53, Revision 1, dated April 16,
Airworthiness Limitation Instructions (ALIs), using Boeing Service Bulletin MD80–28–228, 1992.
and Short-Term Extensions specified in dated September 27, 2013; or Boeing Service (v) McDonnell Douglas MD–80 Service
Appendices B, C, and D of Boeing Twinjet Bulletin MD90–28–013, dated September 27, Bulletin 28–63, Revision 2, dated April 8,
Special Compliance Item Report MDC– 2013, which are not incorporated by 1992.
92K9145, Revision N, dated June 13, 2014. reference in this AD. (3) For Boeing service information
The initial compliance time for identified in this AD, contact Boeing
accomplishing the actions specified in the (l) Alternative Methods of Compliance Commercial Airplanes, Attention: Data &
ALIs is at the later of the times in paragraphs (AMOCs) Services Management, 3855 Lakewood
(h)(3)(i) and (h)(3)(ii) of this AD. Doing the (1) The Manager, Los Angeles Aircraft Boulevard, MC D800–0019, Long Beach, CA
revision of the maintenance or inspection Certification Office (ACO), FAA, has the 90846–0001; telephone 206–544–5000,
program, as applicable, required by this authority to approve AMOCs for this AD, if extension 2; fax 206–766–5683; Internet
paragraph terminates the requirements in requested using the procedures found in 14 https://www.myboeingfleet.com.
paragraphs (g) and (h) of AD 2008–11–15, (4) You may view this service information
CFR 39.19. In accordance with 14 CFR 39.19,
Amendment 3915538 (73 FR 30746, May 29, at FAA, Transport Airplane Directorate, 1601
send your request to your principal inspector
2008). Lind Avenue SW., Renton, WA. For
(i) At the applicable time specified in or local Flight Standards District Office, as
appropriate. If sending information directly information on the availability of this
Appendix C of Boeing Twinjet Special material at the FAA, call 425–227–1221.
Compliance Item Report MDC–92K9145, to the manager of the ACO, send it to the
attention of the person identified in (5) You may view this service information
Revision N, dated June 13, 2014, except as that is incorporated by reference at the
provided by Appendix D of Boeing Twinjet paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOC- National Archives and Records
Special Compliance Item Report MDC–
Requests@faa.gov. Administration (NARA). For information on
92K9145, Revision N, dated June 13, 2014.
(2) Before using any approved AMOC, the availability of this material at NARA, call
(ii) Within 30 days after accomplishing the
notify your appropriate principal inspector, 202–741–6030, or go to: http://
actions required by paragraph (h)(1) or (h)(2)
or lacking a principal inspector, the manager www.archives.gov/federal-register/cfr/ibr-
of this AD, or within 30 days after the
effective date of this AD, whichever occurs of the local flight standards district office/ locations.html.
later. certificate holding district office. Issued in Renton, Washington, on January
(3) An AMOC that provides an acceptable 25, 2016.
(i) New Optional Universal Fault Interrupter
(UFI) Installation level of safety may be used for any repair, Michael Kaszycki,
modification, or alteration required by this Acting Manager, Transport Airplane
In lieu of doing the requirements of AD if it is approved by the Boeing
paragraph (g) of this AD, within the Directorate, Aircraft Certification Service.
Commercial Airplanes Organization
compliance time specified in paragraph (g) of Designation Authorization (ODA) that has
[FR Doc. 2016–02232 Filed 2–16–16; 8:45 am]
this AD install a TDG Aerospace Inc. UFI been authorized by the Manager, Los Angeles BILLING CODE 4910–13–P
using a method approved in accordance with ACO, to make those findings. To be
the procedures specified in paragraph (l) of
approved, the repair method, modification
this AD. DEPARTMENT OF TRANSPORTATION
deviation, or alteration deviation must meet
Note 1 to paragraph (i) of this AD: TDG the certification basis of the airplane and the
Aerospace STC ST02502LA (http:// approval must specifically refer to this AD. Federal Aviation Administration
rgl.faa.gov/Regulatory_and_Guidance_ (4) AMOCs approved for AD 2012–18–05,
Library/rgstc.nsf/0/ Amendment 39–17181 (77 FR 54793, 14 CFR Part 71
4d132827a425d7de86257cd3004dfc02/
September 6, 2012), are approved as AMOCs
$FILE/ST02502LA.pdf) provides additional [Docket No. FAA–2015–3361; Airspace
for the corresponding provisions of this AD.
guidance for installing the TDG UFI. Docket No. 15–AEA–4]
(m) Related Information
(j) No Alternative Actions, Intervals, and RIN 2120–AA66
CDCCLs (1) For more information about this AD,
contact Sérj Harutunian, Aerospace Engineer,
After the maintenance or inspection Propulsion Branch, ANM–140L, FAA, Los Amendment of Air Traffic Service
program, as applicable, has been revised as Angeles ACO, 3960 Paramount Boulevard, (ATS) Routes; Northeast United States
required by paragraph (h)(3) of this AD, no Lakewood, CA 90712–4137; phone: 562–627–
alternative actions (e.g., inspections), AGENCY: Federal Aviation
5254; fax: 562–627–5210; email:
intervals, or CDCCLs may be used unless the
serj.harutunian@faa.gov.
Administration (FAA), DOT.
actions, intervals, or CDCCLs are approved as ACTION: Final rule.
(2) Service information identified in this
an alternative method of compliance (AMOC)
in accordance with the procedures specified AD that is not incorporated by reference is
available at the addresses specified in SUMMARY: This action modifies jet routes
in paragraph (l) of this AD.
paragraphs (n)(3) and (n)(4) of this AD. J–6, J–97, and J–222, and VOR Federal
(k) Credit for Previous Actions airways V–196, and V–489, in the
(n) Material Incorporated by Reference
(1) This paragraph provides credit for the northeastern United States due to the
actions specified in paragraphs (h)(1)(ii) and (1) The Director of the Federal Register planned decommissioning of the
(h)(1)(iii) of this AD, if those actions were approved the incorporation by reference Plattsburgh, NY, VORTAC facility.
performed before the effective date of this AD (IBR) of the service information listed in this
These route changes enhance the safety
using any of the service information specified paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51. and management of airspace within the
in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of National Airspace System.
this AD, which are not incorporated by (2) You must use this service information
reference in this AD. as applicable to do the actions required by DATES: Effective date 0901 UTC, March
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(i) McDonnell Douglas MD–80 Service this AD, unless the AD specifies otherwise. 31, 2016. The Director of the Federal
Bulletin 28–53, dated April 8, 1991. (i) Boeing Service Bulletin MD80–28–228, Register approves this incorporation by
(ii) McDonnell Douglas MD–80 Service Revision 1, dated August 27, 2015. reference action under 1 CFR part 51,
Bulletin 28–63, dated, June 14, 1991. (ii) Boeing Service Bulletin MD90–28–013, subject to the annual revision of FAA
(iii) McDonnell Douglas MD–80 Service Revision 1, dated August 27, 2015.
(iii) Boeing Twinjet Special Compliance
Order 7400.9 and publication of
Bulletin 28–63, Revision 1, dated July 19,
1991. Item Report MDC–92K9145, Revision N, conforming amendments.
(2) This paragraph provides credit for the dated June 13, 2014, including Appendices A ADDRESSES: FAA Order 7400.9Z,
actions specified in paragraphs (h)(1)(i) and through D. Airspace Designations and Reporting
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Document Created: 2016-02-17 01:16:55
Document Modified: 2016-02-17 01:16:55
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective March 23, 2016. | |
| Contact | S[eacute]rj Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5254; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 7967 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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