81 FR 79384 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 219 (November 14, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 219 (November 14, 2016)
| Page Range | 79384-79389 | |
| FR Document | 2016-25491 |
[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)] [Rules and Regulations] [Pages 79384-79389] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25491] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-7527; Directorate Identifier 2015-NM-094-AD; Amendment 39-18686; AD 2016-21-05] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. This AD requires modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. This AD also requires an inspection to identify the part number of the motor operated valve (MOV) actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire. DATES: This AD is effective December 19, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 19, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 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 [[Page 79385]] available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-7527. 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- 7527; 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: Brendan Shanley, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6492; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. The NPRM published in the Federal Register on December 23, 2015 (80 FR 79754) (``the NPRM''). The NPRM was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. The NPRM proposed to require modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. The NPRM also proposed to require an inspection to identify the part number of the MOV actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Boeing stated that it has reviewed the NPRM and concurs with the contents of the NPRM. Request To Reduce the Compliance Time One commenter, Geoffrey Barrance, requested that we reduce the compliance time in paragraph (g) of the proposed AD. Mr. Barrance stated he is concerned that the timescale proposed for implementing the required modification, 60 months after the effective date of the AD, is too long. Mr. Barrance commented that the unsafe condition is a common failure affecting the continued operation of both engines, and therefore is critical to the safe flight and landing of any airplane. We disagree with the commenter's request. It is important to note that while the commenter has indicated there is currently a common mode failure affecting the continued operation of both engines, it is more accurate to say that certain airplanes are currently in a configuration that makes them vulnerable to a single event causing a common mode failure. However, there have been no reports of any events causing this condition. This AD is intended to eliminate that condition. The compliance time is determined to be appropriate in consideration of the risk and the safety implications, the average utilization rate of the affected fleet, the practical aspects of an orderly modification of the fleet during regular maintenance periods, and the availability of required modification parts. In addition to our own criteria, we have also considered the manufacturer's safety assessment and recommendation for the compliance time. The compliance time accounts for the risk to the fleet, availability of parts, and other factors. Therefore, we have determined that the compliance time is acceptable. We have not changed this AD in this regard. Request To Remove the Concurrent Requirements All Nippon Airways (ANA), Japan Airlines (JAL), and United Airlines (UAL) requested that we remove the concurrent requirement for accomplishing Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015. JAL and ANA stated that there was no relationship between the wiring change and the actuator replacement. ANA, JAL, and UAL commented that Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, is already mandated by AD 2013-05-03, Amendment 39-17375 (78 FR 17290, March 21, 2013) (``AD 2013-05-03''), and it addressed MOV actuator part number (P/N) MA20A1001-1; therefore, it should not be a concurrent requirement. ANA also added that because the MOV actuator has been addressed, paragraphs (i)(2) and (i)(3) of the proposed AD should not be included. We partially agree with the commenters. We agree that the actions in Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, are the same actions that are required by AD 2013-05-03 in accordance with Boeing Service Bulletin 777-28A0034, Revision 2, dated September 20, 2010, with a compliance date of April 25, 2018. Because of the overlap in compliance times, the action required by AD 2013-05- 03 may not be fully completed by the time the requirements of this AD become effective. To ensure that the actuator change, in accordance with Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, is done prior to the wiring change in accordance with Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, we have required Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, as a concurrent requirement in this AD. Without this concurrent requirement, it is possible that this AD could approve certain configurations that are not compliant and safe. The concurrent requirement eliminates this possibility. The requirements of Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, and related credit for previous actions, will remain as stated. We have not changed this AD in this regard. Request To Use Boeing Information Notice for Completing the Requirements in the AD ANA requested that we include Boeing Service Bulletin Information Notice 777-28-0061, IN 03, dated November 16, 2015, to this AD to allow the operators to complete the proposed requirements of the NPRM. We partially agree with the commenter's request. We cannot include Boeing Service Bulletin Information Notice 777-28-0061, IN 03, dated November 16, 2015, as an [[Page 79386]] appropriate source of service information in this AD because it is not an FAA-approved document. However, we acknowledge that for certain airplanes, Figure 22, Sheet 9, of Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, includes an editorial error, which shows incorrect wire routing. Boeing Service Bulletin Information Notice 777-28-0061, IN 03, dated November 16, 2015, allows for a modification of Group 2 airplanes that meets the requirements of the AD without an additional burden to operators. We have included a corrected figure in paragraph (h) of this AD to address this issue. In addition, Figure 11, Sheet 1, of Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, is incorrect in that it shows the cap and stow of an existing wire, W4255- 1002-20, which is terminated at splice SP41201. The correct wire number to be capped and stowed is W6251-1002-20, which is terminated at splice SP41201. We have clarified this information in paragraph (h)(2) of this AD. Request To Clarify the Terminating Action JAL and UAL requested that we clarify the terminating action specified in the proposed rule. JAL asked that Boeing Service Bulletin 777-28A0034 be used as a terminating action for the requirements of the proposed rule. UAL stated that since AD 2013-05-03 already addressed MOV actuator P/N MA20A2027 and P/N MA30A1001, it contradicts airworthiness limitations (AWL) 28-AWL-MOV, which was mandated in AD 2015-19-01, Amendment 39-18264 (80 FR 55521, dated September 16, 2015) (``AD 2015-19-01''). We agree that clarification is necessary. We agree that certain configurations in Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, in conjunction with previous airplane configurations, alleviate the need to do the AWL task implemented by AD 2013-05-03 because the configurations are outside the applicability of that AWL. However, we disagree with using Boeing Service Bulletin 777- 28A0034, Revision 3, dated September 25, 2015, as a terminating action because the requirement of AD 2015-19-01 is to implement the airworthiness limitations items (ALI) into an operator's maintenance program, and this must be done regardless of the configuration of the airplane. Further, certain MOV actuator part numbers can be installed that will place an airplane in the applicability of AWL 28-AWL-MOV, thus requiring periodic inspections to ensure safe operation. Each operator has the option to select a configuration best for its circumstances and can evaluate its configurations and determine if AWL 28-AWL-MOV is applicable to their fleet configuration. We have not changed this AD in this regard. Request To Review the Design and Certification Process Geoffrey Barrance requested that we review the design and certification process that allowed for the unsafe condition to exist, as well as a review of designs in other airplanes with similar unsafe conditions. Mr. Barrance commented that the unsafe condition indicated a failure has occurred in the design and certification process for the airplane type. Mr. Barrance also commented that a review of the airplane design is required to prevent the implementation of common mode fault exposures for redundant systems. We acknowledge the commenter's concerns. We continuously evaluate our certification system and procedures and improve them when problems are found. If the FAA is made aware of potential design deficiencies occurring on a certificated product, we conduct an investigation, evaluate the manufacturer's root-cause analysis, and make a determination whether or not an unsafe condition exists. We then take appropriate action to mitigate the unsafe condition and to identify and incorporate certification system process improvements for future designs. Furthermore, the manufacturer performs a cross model evaluation to determine if the condition exists on other models. We agree with the manufacturer's actions in this regard. We have not changed this AD regarding this issue. 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 and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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 Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015. The service information describes procedures for modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. We have also reviewed Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015. The service information describes procedures for an inspection of the MOV actuators of the left and right engine fuel spar valves for (P/N) MA20A1001-1, replacement of MOV actuators, measurement of the electrical resistance of the bond from the adapter plate to the airplane structure, and applicable corrective actions. 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 133 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Installation and modification... 119 work-hours x Up to $3,780 Up to $13,895 Up to $1,848,035 $85 per hour = depending on depending on depending on $10,115. airplane airplane airplane configuration. configuration. configuration. Inspection of MOV actuators 1 work-hour x $85 $0................ $85............... $11,305. [concurrent requirements]. per hour = $85. ---------------------------------------------------------------------------------------------------------------- [[Page 79387]] We estimate the following costs to do any necessary replacements and bonding resistance measurements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Replacement of MOV actuators for the Up to 105 work-hours x Up to $10,954.......... Up to $19,879. left and right engine fuel spar $85 per hour = $8,925. valves. Bonding resistance measurements...... 1 work-hour x $85 per $0..................... $85. hour = $85. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data on the costs of the corrective actions for the bonding resistance measurement in this 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 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 adding the following new airworthiness directive (AD): 2016-21-05 The Boeing Company: Amendment 39-18686; Docket No. FAA- 2015-7527; Directorate Identifier 2015-NM-094-AD. (a) Effective Date This AD is effective December 19, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777-200, -200LR, - 300, and -300ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015. (d) Subject Air Transport Association (ATA) of America Code 2822, Fuel Boost Pump. (e) Unsafe Condition This AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification Within 60 months after the effective date of this AD, modify the wiring and install new relay brackets in new locations to allow installation of new relays for the left and right engine fuel spar valves, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, except as required by paragraph (h) of this AD. (h) Exceptions to the Service Information (1) Where Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, specifies to use Figure 22, Sheet 9, for the wiring installation of the right engine fuel spar valve, this AD requires using figure 1 to paragraph (h) of this AD. (2) Boeing Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, specifies to use Figure 11, Sheet 1, for the wiring change at E2-6--Shelf to Disconnect Panel and Splice Area. The figure shows the capping and stowing of an existing wire, W4255-1002-20, which is terminated at splice SP41201. The wire number is incorrect. The correct wire number to cap and stow is W6251-1002-20, which is terminated at splice SP41201. BILLING CODE 4910-13-P [[Page 79388]] [GRAPHIC] [TIFF OMITTED] TR14NO16.003 BILLING CODE 4910-13-C (i) Concurrent Requirements (1) Prior to or concurrently with accomplishing the requirements of paragraph (g) of this AD: Do an inspection of the motor operated valve (MOV) actuators of the left and right engine fuel spar valves for part number (P/N) MA20A1001-1, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review. (2) If any MOV actuator having P/N MA20A1001-1 is found during the inspection required by paragraph (i)(1) of this AD, prior to or concurrently with accomplishing the requirements of paragraph (g) of this AD, replace the MOV actuator with either a new or serviceable MOV actuator having P/N MA30A1001, MA30A1017, MA20A2027, or an MOV actuator that meets the criteria specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD; and, as applicable, measure the electrical resistance of the bond from the adapter plate to the airplane structure and, before further flight, do all applicable corrective actions. All actions specified in this paragraph for the left and right engine fuel spar valves must be done in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777- 28A0034, Revision 3, dated September 25, 2015. (i) The replacement MOV actuator must be a Boeing part that is approved after the issuance of Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015, by the Manager, Seattle Aircraft [[Page 79389]] Certification Office (ACO), FAA; or the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to approve the part. (ii) The replacement MOV actuator must be fully interchangeable with the part specified in Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015. (j) Credit for Previous Actions (1) This paragraph provides credit for the requirements of paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777-28-0061, dated October 25, 2010; or Boeing Special Attention Service Bulletin 777-28-0061, Revision 1, dated January 26, 2012; as applicable. These documents are not incorporated by reference in this AD. (2) This paragraph provides credit for the requirements of paragraph (i) of this AD, if those actions were performed before April 25, 2013 (the effective date of AD 2013-05-03, Amendment 39- 17375 (78 FR 17290, March 21, 2013), ``AD 2013-05-03''), using Boeing Alert Service Bulletin 777-28A0034, dated August 2, 2007; or Boeing Alert Service Bulletin 777-28A0034, Revision 1, dated May 20, 2010; except that the replacement of MOV actuators of the left and right engine fuel spar valves must also include cap sealing the bonding jumper, as described in Boeing Service Bulletin 777-28A0034, Revision 2, dated September 20, 2010; and provided that the replacement is an MOV actuator identified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD. Boeing Alert Service Bulletin 777-28A0034, dated August 2, 2007, and Boeing Alert Service Bulletin 777-28A0034, Revision 1, dated May 20, 2010, are not incorporated by reference in this AD. Boeing Service Bulletin 777-28A0034, Revision 2, dated September 20, 2010, is incorporated by reference in AD 2013-05-03. (i) An MOV actuator that has P/N MA30A1001, MA30A1017, or MA20A2027. (ii) An MOV actuator that has a part number other than P/N MA20A1001-1 and meets the criteria specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (3) This paragraph provides credit for the requirements of paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 777-28A0034, Revision 2, dated September 20, 2010, which was incorporated by reference in AD 2013-05-03. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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: [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 ODA that has been authorized by the Manager, Seattle 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. (l) Related Information (1) For more information about this AD, contact Brendan Shanley, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6492; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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 Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015. (ii) Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 2015. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 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 October 7, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-25491 Filed 11-10-16; 8:45 am] BILLING CODE 4910-13-P
![79384 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations
(n) New Requirement of This AD: flight standards district office/certificate DEPARTMENT OF TRANSPORTATION
Terminating Action holding district office.
For airplanes on which any incorrectly (2) Contacting the Manufacturer: For any Federal Aviation Administration
oriented fastener, and no fractured or missing requirement in this AD to obtain corrective
fastener, was detected during any inspection actions from a manufacturer, the action must 14 CFR Part 39
required by paragraph (g), (h)(2), (i), and (j)(1) be accomplished using a method approved
of this AD: Within 24 months after the by the Manager, New York ACO, ANE–170, [Docket No. FAA–2015–7527; Directorate
effective date of this AD, replace all forward FAA; or TCCA; or Bombardier, Inc.’s TCCA Identifier 2015–NM–094–AD; Amendment
and aft fasteners, regardless of condition or DAO. If approved by the DAO, the approval 39–18686; AD 2016–21–05]
orientation, at WS 76.50 and WS 127.25, on must include the DAO-authorized signature.
RIN 2120–AA64
affected wings, in accordance with the (q) Related Information
Accomplishment Instructions of the Airworthiness Directives; The Boeing
applicable service information specified in (1) Refer to Mandatory Continuing
paragraphs (k)(1) and (k)(2) of this AD, except Airworthiness Information (MCAI) Canadian Company Airplanes
as provided by paragraph (m) of this AD. Emergency AD CF–2013–39R2, dated
AGENCY: Federal Aviation
Doing the replacements specified in this December 12, 2014, for related information.
This MCAI may be found in the AD docket Administration (FAA), DOT.
paragraph terminates the requirements of this
AD. Doing the replacements specified in this on the Internet at http://www.regulations.gov ACTION: Final rule.
paragraph terminates the requirements of by searching for and locating Docket No.
paragraphs (g) and (j) of AD 2014–03–17, FAA–2016–5593. SUMMARY: We are adopting a new
only for the airplane on which the (2) Service information identified in this airworthiness directive (AD) for certain
replacement was done. AD that is not incorporated by reference is The Boeing Company Model 777–200,
(o) Credit for Previous Actions
available at the addresses specified in –200LR, –300, and –300ER series
paragraphs (r)(4) and (r)(5) of this AD. airplanes. This AD was prompted by a
This paragraph restates the provisions of report indicating that the manufacturer
paragraph (n) of AD 2015–02–23, with new (r) Material Incorporated by Reference
credit for paragraph (n) of this AD. This
discovered locations where the control
(1) The Director of the Federal Register
paragraph provides credit for actions approved the incorporation by reference components and wiring of the left and
required by paragraphs (g), (h), (i), and (n) of (IBR) of the service information listed in this right engine fuel spar valves do not have
this AD, if those actions were performed paragraph under 5 U.S.C. 552(a) and 1 CFR adequate physical separation to meet
before the effective date of this AD using the part 51. the redundant system separation
applicable service information identified in (2) You must use this service information requirements. This AD requires
paragraphs (o)(1) through (o)(4) of this AD. as applicable to do the actions required by modifying the wiring, and installing a
(1) Bombardier Alert Service Bulletin this AD, unless this AD specifies otherwise. new relay bracket and new location for
A600–0763, including Appendixes 1 and 2, (3) The following service information was
dated September 26, 2013, which was
the relay on the left and right engine
approved for IBR on February 18, 2015 (80 fuel spar valves. This AD also requires
previously incorporated by reference on FR 5670, February 3, 2015).
March 6, 2014 (79 FR 9389, February 19, an inspection to identify the part
(i) Bombardier Alert Service Bulletin
2014). A600–0763, Revision 02, dated December 9, number of the motor operated valve
(2) Bombardier Alert Service Bulletin 2014, including Appendixes 1 and 2, dated (MOV) actuators for the left and right
A600–0763, Revision 01, dated February 26, September 26, 2013. engine fuel spar valves; replacement of
2014, including Appendixes 1 and 2, dated (ii) Bombardier Alert Service Bulletin specified MOV actuators with new MOV
September 26, 2013, which is not A601–0627, Revision 02, dated December 9, actuators; certain bonding resistance
incorporated by reference in this AD. 2014, including Appendixes 1 and 2, dated measurements; and applicable
(3) Bombardier Alert Service Bulletin September 26, 2013.
A601–0627, including Appendixes 1 and 2,
corrective actions. We are issuing this
(4) For service information identified in AD to prevent loss of control of both the
dated September 26, 2013, which was this AD, contact Bombardier, Inc., 400 Côte-
previously incorporated by reference on left and right engine fuel spar valves
Vertu Road West, Dorval, Québec H4S 1Y9,
March 6, 2014 (79 FR 9389, February 19, during a single event, such as local wire
Canada; Widebody Customer Response
2014). Center North America toll-free telephone: 1– bundle damage or a wire bundle fire,
(4) Bombardier Alert Service Bulletin 866–538–1247 or direct-dial telephone: 1– which could cause both engines to shut
A601–0627, Revision 01, dated February 26, 514–855–2999; fax 514–855–7401; email: down or result in the inability to control
2014, including Appendixes 1 and 2, dated ac.yul@aero.bombardier.com; Internet: an engine fire.
September 26, 2013, which is not http://www.bombardier.com.
incorporated by reference in this AD. DATES: This AD is effective December
(5) You may view this service information 19, 2016.
(p) Other FAA AD Provisions at the FAA, Transport Airplane Directorate, The Director of the Federal Register
1601 Lind Avenue SW., Renton, WA. For
The following provisions also apply to this approved the incorporation by reference
AD: information on the availability of this
material at the FAA, call 425–227–1221.
of certain publications listed in this AD
(1) Alternative Methods of Compliance as of December 19, 2016.
(AMOCs): The Manager, New York ACO, (6) You may view this service information
that is incorporated by reference at the ADDRESSES: For service information
ANE–170, FAA, has the authority to approve
AMOCs for this AD, if requested using the National Archives and Records identified in this final rule, contact
procedures found in 14 CFR 39.19. In Administration (NARA). For information on Boeing Commercial Airplanes,
accordance with 14 CFR 39.19, send your the availability of this material at NARA, call Attention: Data & Services Management,
request to your principal inspector or local 202–741–6030, or go to: http:// P.O. Box 3707, MC 2H–65, Seattle, WA
Flight Standards District Office, as www.archives.gov/federal-register/cfr/ibr-
98124–2207; telephone 206–544–5000,
appropriate. If sending information directly locations.html.
extension 1; fax 206–766–5680; Internet
to the ACO, send it to ATTN: Program Issued in Renton, Washington, on October https://www.myboeingfleet.com. You
Lhorne on DSK30JT082PROD with RULES
Manager, Continuing Operational Safety, 7, 2016. may view this referenced service
FAA, New York ACO, 1600 Stewart Avenue, Michael Kaszycki,
Suite 410, Westbury, NY 11590; telephone: information at the FAA, Transport
Acting Manager, Transport Airplane Airplane Directorate, 1601 Lind Avenue
516–228–7300; fax: 516–794–5531. Before
Directorate, Aircraft Certification Service. SW., Renton, WA. For information on
using any approved AMOC, notify your
appropriate principal inspector, or lacking a [FR Doc. 2016–25009 Filed 11–10–16; 8:45 am] the availability of this material at the
principal inspector, the manager of the local BILLING CODE 4910–13–P FAA, call 425–227–1221. It is also
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![79386 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations
appropriate source of service AWL. However, we disagree with using actions in this regard. We have not
information in this AD because it is not Boeing Service Bulletin 777–28A0034, changed this AD regarding this issue.
an FAA-approved document. However, Revision 3, dated September 25, 2015,
Conclusion
we acknowledge that for certain as a terminating action because the
airplanes, Figure 22, Sheet 9, of Boeing requirement of AD 2015–19–01 is to We reviewed the relevant data,
Special Attention Service Bulletin 777– implement the airworthiness limitations considered the comments received, and
28–0061, Revision 2, dated May 4, 2015, items (ALI) into an operator’s determined that air safety and the
includes an editorial error, which shows maintenance program, and this must be public interest require adopting this AD
incorrect wire routing. Boeing Service done regardless of the configuration of with the changes described previously
Bulletin Information Notice 777–28– the airplane. Further, certain MOV and minor editorial changes. We have
0061, IN 03, dated November 16, 2015, actuator part numbers can be installed determined that these minor changes:
allows for a modification of Group 2 that will place an airplane in the • Are consistent with the intent that
airplanes that meets the requirements of applicability of AWL 28–AWL–MOV, was proposed in the NPRM for
the AD without an additional burden to thus requiring periodic inspections to correcting the unsafe condition; and
operators. We have included a corrected ensure safe operation. Each operator has
figure in paragraph (h) of this AD to the option to select a configuration best • Do not add any additional burden
address this issue. for its circumstances and can evaluate upon the public than was already
In addition, Figure 11, Sheet 1, of its configurations and determine if AWL proposed in the NPRM.
Boeing Special Attention Service 28–AWL–MOV is applicable to their We also determined that these
Bulletin 777–28–0061, Revision 2, dated fleet configuration. We have not changes will not increase the economic
May 4, 2015, is incorrect in that it changed this AD in this regard. burden on any operator or increase the
shows the cap and stow of an existing scope of this AD.
wire, W4255–1002–20, which is Request To Review the Design and
Certification Process Related Service Information Under 1
terminated at splice SP41201. The CFR Part 51
correct wire number to be capped and Geoffrey Barrance requested that we
stowed is W6251–1002–20, which is review the design and certification We reviewed Boeing Special
terminated at splice SP41201. We have process that allowed for the unsafe Attention Service Bulletin 777–28–
clarified this information in paragraph condition to exist, as well as a review 0061, Revision 2, dated May 4, 2015.
(h)(2) of this AD. of designs in other airplanes with The service information describes
similar unsafe conditions. Mr. Barrance procedures for modifying the wiring,
Request To Clarify the Terminating commented that the unsafe condition and installing a new relay bracket and
Action indicated a failure has occurred in the new location for the relay on the left
JAL and UAL requested that we design and certification process for the and right engine fuel spar valves.
clarify the terminating action specified airplane type. Mr. Barrance also We have also reviewed Boeing Service
in the proposed rule. JAL asked that commented that a review of the airplane Bulletin 777–28A0034, Revision 3,
Boeing Service Bulletin 777–28A0034 design is required to prevent the dated September 25, 2015. The service
be used as a terminating action for the implementation of common mode fault information describes procedures for an
requirements of the proposed rule. UAL exposures for redundant systems. inspection of the MOV actuators of the
stated that since AD 2013–05–03 We acknowledge the commenter’s left and right engine fuel spar valves for
already addressed MOV actuator P/N concerns. We continuously evaluate our (P/N) MA20A1001–1, replacement of
MA20A2027 and P/N MA30A1001, it certification system and procedures and
MOV actuators, measurement of the
contradicts airworthiness limitations improve them when problems are
electrical resistance of the bond from
(AWL) 28–AWL–MOV, which was found. If the FAA is made aware of
the adapter plate to the airplane
mandated in AD 2015–19–01, potential design deficiencies occurring
structure, and applicable corrective
Amendment 39–18264 (80 FR 55521, on a certificated product, we conduct an
actions.
dated September 16, 2015) (‘‘AD 2015– investigation, evaluate the
19–01’’). manufacturer’s root-cause analysis, and This service information is reasonably
We agree that clarification is make a determination whether or not an available because the interested parties
necessary. We agree that certain unsafe condition exists. We then take have access to it through their normal
configurations in Boeing Service appropriate action to mitigate the unsafe course of business or by the means
Bulletin 777–28A0034, Revision 3, condition and to identify and identified in the ADDRESSES section.
dated September 25, 2015, in incorporate certification system process Costs of Compliance
conjunction with previous airplane improvements for future designs.
configurations, alleviate the need to do Furthermore, the manufacturer performs We estimate that this AD affects 133
the AWL task implemented by AD a cross model evaluation to determine if airplanes of U.S. registry.
2013–05–03 because the configurations the condition exists on other models. We estimate the following costs to
are outside the applicability of that We agree with the manufacturer’s comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Installation and modifica- 119 work-hours × $85 per Up to $3,780 depending Up to $13,895 depending Up to $1,848,035 depend-
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tion. hour = $10,115. on airplane configuration. on airplane configuration. ing on airplane configu-
ration.
Inspection of MOV actu- 1 work-hour × $85 per $0 ...................................... $85 .................................... $11,305.
ators [concurrent re- hour = $85.
quirements].
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![Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations 79387
We estimate the following costs to do would be required based on the results determining the number of aircraft that
any necessary replacements and of the inspection. We have no way of might need these replacements:
bonding resistance measurements that
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Replacement of MOV actuators for Up to 105 work-hours × $85 per Up to $10,954 ............................... Up to $19,879.
the left and right engine fuel hour = $8,925.
spar valves.
Bonding resistance measurements 1 work-hour × $85 per hour = $85 $0 .................................................. $85.
We have received no definitive data (4) Will not have a significant (e) Unsafe Condition
on the costs of the corrective actions for economic impact, positive or negative, This AD was prompted by a report
the bonding resistance measurement in on a substantial number of small entities indicating that the manufacturer discovered
this AD. under the criteria of the Regulatory locations where the control components and
Flexibility Act. wiring of the left and right engine fuel spar
Authority for This Rulemaking
valves do not have adequate physical
Title 49 of the United States Code List of Subjects in 14 CFR Part 39 separation to meet the redundant system
specifies the FAA’s authority to issue Air transportation, Aircraft, Aviation separation requirements. We are issuing this
rules on aviation safety. Subtitle I, safety, Incorporation by reference, AD to prevent loss of control of both the left
section 106, describes the authority of Safety. and right engine fuel spar valves during a
the FAA Administrator. Subtitle VII: single event, such as local wire bundle
Aviation Programs, describes in more Adoption of the Amendment damage or a wire bundle fire, which could
detail the scope of the Agency’s cause both engines to shut down or result in
Accordingly, under the authority the inability to control an engine fire.
authority. delegated to me by the Administrator,
We are issuing this rulemaking under the FAA amends 14 CFR part 39 as (f) Compliance
the authority described in Subtitle VII, follows: Comply with this AD within the
Part A, Subpart III, Section 44701: compliance times specified, unless already
‘‘General requirements.’’ Under that PART 39—AIRWORTHINESS done.
section, Congress charges the FAA with DIRECTIVES
promoting safe flight of civil aircraft in (g) Modification
air commerce by prescribing regulations ■ 1. The authority citation for part 39 Within 60 months after the effective date
for practices, methods, and procedures continues to read as follows: of this AD, modify the wiring and install new
the Administrator finds necessary for Authority: 49 U.S.C. 106(g), 40113, 44701.
relay brackets in new locations to allow
safety in air commerce. This regulation installation of new relays for the left and
is within the scope of that authority § 39.13 [Amended] right engine fuel spar valves, in accordance
because it addresses an unsafe condition with the Accomplishment Instructions of
that is likely to exist or develop on ■ 2. The FAA amends § 39.13 by adding Boeing Special Attention Service Bulletin
products identified in this rulemaking the following new airworthiness 777–28–0061, Revision 2, dated May 4, 2015,
action. directive (AD): except as required by paragraph (h) of this
2016–21–05 The Boeing Company: AD.
Regulatory Findings Amendment 39–18686; Docket No. (h) Exceptions to the Service Information
This AD will not have federalism FAA–2015–7527; Directorate Identifier
(1) Where Boeing Special Attention Service
implications under Executive Order 2015–NM–094–AD.
Bulletin 777–28–0061, Revision 2, dated May
13132. This AD will not have a (a) Effective Date 4, 2015, specifies to use Figure 22, Sheet 9,
substantial direct effect on the States, on This AD is effective December 19, 2016. for the wiring installation of the right engine
the relationship between the national fuel spar valve, this AD requires using figure
government and the States, or on the (b) Affected ADs 1 to paragraph (h) of this AD.
distribution of power and None. (2) Boeing Special Attention Service
responsibilities among the various Bulletin 777–28–0061, Revision 2, dated May
(c) Applicability
levels of government. 4, 2015, specifies to use Figure 11, Sheet 1,
For the reasons discussed above, I This AD applies to The Boeing Company for the wiring change at E2–6—Shelf to
certify that this AD: Model 777–200, –200LR, –300, and –300ER Disconnect Panel and Splice Area. The figure
(1) Is not a ‘‘significant regulatory series airplanes, certificated in any category, shows the capping and stowing of an existing
as identified in Boeing Special Attention wire, W4255–1002–20, which is terminated
action’’ under Executive Order 12866, Service Bulletin 777–28–0061, Revision 2,
(2) Is not a ‘‘significant rule’’ under at splice SP41201. The wire number is
dated May 4, 2015. incorrect. The correct wire number to cap
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), (d) Subject and stow is W6251–1002–20, which is
(3) Will not affect intrastate aviation terminated at splice SP41201.
Air Transport Association (ATA) of
in Alaska, and America Code 2822, Fuel Boost Pump. BILLING CODE 4910–13–P
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![Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations 79389
Certification Office (ACO), FAA; or the or lacking a principal inspector, the manager DEPARTMENT OF JUSTICE
Boeing Commercial Airplanes Organization of the local flight standards district office/
Designation Authorization (ODA) that has certificate holding district office. Drug Enforcement Administration
been authorized by the Manager, Seattle (3) An AMOC that provides an acceptable
ACO, to approve the part. level of safety may be used for any repair, 21 CFR Part 1308
(ii) The replacement MOV actuator must be modification, or alteration required by this
fully interchangeable with the part specified AD if it is approved by the Boeing [Docket No. DEA–440]
in Boeing Service Bulletin 777–28A0034, Commercial Airplanes ODA that has been
Revision 3, dated September 25, 2015. authorized by the Manager, Seattle ACO, to Schedules of Controlled Substances:
(j) Credit for Previous Actions make those findings. To be approved, the Temporary Placement of U–47700 Into
repair method, modification deviation, or Schedule I
(1) This paragraph provides credit for the
requirements of paragraph (g) of this AD, if alteration deviation must meet the
AGENCY: Drug Enforcement
those actions were performed before the certification basis of the airplane and the
Administration, Department of Justice.
effective date of this AD using Boeing Special approval must specifically refer to this AD.
Attention Service Bulletin 777–28–0061, ACTION: Final order.
(l) Related Information
dated October 25, 2010; or Boeing Special
Attention Service Bulletin 777–28–0061, (1) For more information about this AD, SUMMARY: The Administrator of the Drug
Revision 1, dated January 26, 2012; as contact Brendan Shanley, Aerospace Enforcement Administration is issuing
applicable. These documents are not Engineer, Systems and Equipment Branch, this final order to temporarily schedule
incorporated by reference in this AD. ANM–130S, FAA, Seattle Aircraft the synthetic opioid, 3,4-dichloro-N-[2-
(2) This paragraph provides credit for the Certification Office, 1601 Lind Avenue SW., (dimethylamino)cyclohexyl]-N-
requirements of paragraph (i) of this AD, if Renton, WA 98057–3356; telephone: 425– methylbenzamide (also known as
those actions were performed before April 917–6492; fax: 425–917–6590; email: U–47700), and its isomers, esters,
25, 2013 (the effective date of AD 2013–05– brendan.shanley@faa.gov. ethers, salts and salts of isomers, esters
03, Amendment 39–17375 (78 FR 17290, (2) Service information identified in this and ethers, into schedule I pursuant to
March 21, 2013), ‘‘AD 2013–05–03’’), using AD that is not incorporated by reference is
Boeing Alert Service Bulletin 777–28A0034,
the temporary scheduling provisions of
available at the addresses specified in the Controlled Substances Act. This
dated August 2, 2007; or Boeing Alert Service paragraphs (m)(3) and (m)(4) of this AD.
Bulletin 777–28A0034, Revision 1, dated action is based on a finding by the
May 20, 2010; except that the replacement of (m) Material Incorporated by Reference Administrator that the placement of
MOV actuators of the left and right engine (1) The Director of the Federal Register U–47700 into schedule I of the
fuel spar valves must also include cap sealing Controlled Substances Act is necessary
approved the incorporation by reference
the bonding jumper, as described in Boeing to avoid an imminent hazard to the
(IBR) of the service information listed in this
Service Bulletin 777–28A0034, Revision 2, public safety. As a result of this order,
dated September 20, 2010; and provided that paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51. the regulatory controls and
the replacement is an MOV actuator
identified in paragraph (j)(2)(i) or (j)(2)(ii) of (2) You must use this service information administrative, civil, and criminal
this AD. Boeing Alert Service Bulletin 777– as applicable to do the actions required by sanctions applicable to schedule I
28A0034, dated August 2, 2007, and Boeing this AD, unless the AD specifies otherwise. controlled substances will be imposed
Alert Service Bulletin 777–28A0034, (i) Boeing Special Attention Service on persons who handle (manufacture,
Revision 1, dated May 20, 2010, are not Bulletin 777–28–0061, Revision 2, dated May distribute, reverse distribute, import,
incorporated by reference in this AD. Boeing 4, 2015. export, engage in research, conduct
Service Bulletin 777–28A0034, Revision 2, (ii) Boeing Service Bulletin 777–28A0034, instructional activities or chemical
dated September 20, 2010, is incorporated by Revision 3, dated September 25, 2015. analysis, or possess), or propose to
reference in AD 2013–05–03. (3) For Boeing service information handle,
(i) An MOV actuator that has P/N identified in this AD, contact Boeing
MA30A1001, MA30A1017, or MA20A2027.
U–47700.
Commercial Airplanes, Attention: Data &
(ii) An MOV actuator that has a part DATES: This final order is effective on
Services Management, P.O. Box 3707, MC
number other than P/N MA20A1001–1 and 2H–65, Seattle, WA 98124–2207; telephone November 14, 2016.
meets the criteria specified in paragraphs 206–544–5000, extension 1; fax 206–766– FOR FURTHER INFORMATION CONTACT:
(i)(2)(i) and (i)(2)(ii) of this AD. Michael J. Lewis, Diversion Control
5680; Internet https://
(3) This paragraph provides credit for the
requirements of paragraph (i) of this AD, if
www.myboeingfleet.com. Division, Drug Enforcement
those actions were performed before the (4) You may view this service information Administration; Mailing Address: 8701
effective date of this AD using Boeing Service at FAA, Transport Airplane Directorate, 1601 Morrissette Drive, Springfield, Virginia
Bulletin 777–28A0034, Revision 2, dated Lind Avenue SW., Renton, WA. For 22152; Telephone: (202) 598–6812.
September 20, 2010, which was incorporated information on the availability of this
SUPPLEMENTARY INFORMATION:
by reference in AD 2013–05–03. material at the FAA, call 425–227–1221.
(5) You may view this service information Legal Authority
(k) Alternative Methods of Compliance that is incorporated by reference at the
(AMOCs) The Drug Enforcement
National Archives and Records
(1) The Manager, Seattle ACO, FAA, has Administration (NARA). For information on
Administration (DEA) implements and
the authority to approve AMOCs for this AD, the availability of this material at NARA, call enforces titles II and III of the
if requested using the procedures found in 14 202–741–6030, or go to: http:// Comprehensive Drug Abuse Prevention
CFR 39.19. In accordance with 14 CFR 39.19, www.archives.gov/federal-register/cfr/ibr- and Control Act of 1970, as amended. 21
send your request to your principal inspector locations.html. U.S.C. 801–971. Titles II and III are
or local Flight Standards District Office, as referred to as the ‘‘Controlled
appropriate. If sending information directly Issued in Renton, Washington, on October
Substances Act’’ and the ‘‘Controlled
Lhorne on DSK30JT082PROD with RULES
to the manager of the ACO, send it to the 7, 2016.
Substances Import and Export Act,’’
attention of the person identified in Michael Kaszycki,
paragraph (l)(1) of this AD. Information may
respectively, and are collectively
Acting Manager, Transport Airplane referred to as the ‘‘Controlled
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Directorate, Aircraft Certification Service. Substances Act’’ or the ‘‘CSA’’ for the
Requests@faa.gov.
(2) Before using any approved AMOC, [FR Doc. 2016–25491 Filed 11–10–16; 8:45 am] purpose of this action. The DEA
notify your appropriate principal inspector, BILLING CODE 4910–13–P publishes the implementing regulations
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Document Created: 2018-10-24 10:48:07
Document Modified: 2018-10-24 10:48:07
| 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 December 19, 2016. | |
| Contact | Brendan Shanley, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6492; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 79384 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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