81 FR 47084 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 139 (July 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 139 (July 20, 2016)
| Page Range | 47084-47087 | |
| FR Document | 2016-16906 |
[Federal Register Volume 81, Number 139 (Wednesday, July 20, 2016)] [Proposed Rules] [Pages 47084-47087] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16906] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8179; Directorate Identifier 2015-NM-201-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-26- 03, which applies to certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2011-26-03 currently requires installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. AD 2011-26-03 resulted from fuel system reviews conducted by the manufacturer. Since we issued AD 2011-26-03, we have received a report indicating that additional airplanes are affected by the identified unsafe condition. This proposed AD would add airplanes to the applicability. This AD would also add, for certain airplanes, detailed inspections of certain wire bundle clamps, certain Teflon sleeves, and certain fasteners; corrective actions if necessary; and installation of Teflon sleeves under certain wire bundle clamps. We are proposing this AD to prevent electrical arcing on the fuel tank boundary structure or inside the fuel tanks, which could result in a fire or explosion. DATES: We must receive comments on this proposed AD by September 6, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 8179. 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-2016- 8179; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6438; fax: 425-917-6590; email: [email protected]. [[Page 47085]] SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8179; Directorate Identifier 2015-NM-201-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ``Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (``SFAR 88''), Amendment 21-78. Subsequently, SFAR 88 was amended by: Amendment 21-82 (67 FR 57490, September 10, 2002; corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR 72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to change ``21-82'' to ``21-83''). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, combination of failures, and unacceptable (failure) experience. For all three failure criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. On December 5, 2011, we issued AD 2011-26-03, Amendment 39-16893 (76 FR 78138, December 16, 2011) (``AD 2011-26-03''), for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2011-26-03 requires installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. AD 2011-26-03 resulted from fuel system reviews conducted by the manufacturer. We issued AD 2011-26-03 to prevent electrical arcing on the fuel tank boundary structure or inside the fuel tanks, which could result in a fire or explosion. Actions Since AD 2011-26-03 Was Issued Since we issued AD 2011-26-03, we have received a report indicating that additional airplanes are affected by the identified unsafe condition. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. The service information describes procedures for installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks; as well as detailed inspections of certain wire bundle clamps, certain Teflon sleeves, and certain fasteners; corrective actions if necessary; and installation of Teflon sleeves under certain wire bundle clamps. 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all of the requirements of AD 2011- 26-03. This proposed AD would also revise the applicability by adding Boeing Model 777-200LR and 777F series airplanes. This proposed AD would also require accomplishing the actions specified in the service information described previously, except as described in ``Differences Between this Proposed AD and the Service Information''. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-8179. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing has issued Alternative Method of Compliance (AMOC) Notice 777-57A0050 AMOC 02, dated February 15, 2016, to provide the correct group applicability for ``WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation,'' Figure 3, and Figure 100 of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. We have included these changes in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. Costs of Compliance We estimate that this proposed AD affects 182 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 47086]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Install Teflon sleeving and Up to 358 work- $2,241 Up to $32,671........ Up to $5,946,122. cap sealing (retained hours x $85 per actions from AD 2011-26-03). hour = $30,430. Detailed inspections and Up to 53 work- \1\ 0 Up to $4,505......... Up to $819,910. installation of Teflon hours x $85 per sleeves (new proposed hour = $4,505. actions). ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide parts cost estimates for the installation of Teflon sleeves (new proposed action) specified in this proposed AD. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-26-03, Amendment 39-16893 (76 FR 78138, December 16, 2011), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-8179; Directorate Identifier 2015-NM-201-AD. (a) Comments Due Date The FAA must receive comments on this AD action by September 6, 2016. (b) Affected ADs This AD replaces AD 2011-26-03, Amendment 39-16893 (76 FR 78138, December 16, 2011) (``AD 2011-26-03''). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, as identified in the applicable service information specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) For The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F airplanes: Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. (2) For The Boeing Company Model 777-200 and -300 airplanes: Boeing Alert Service Bulletin 777-57A0051, dated May 15, 2006. (3) For The Boeing Company Model 777-200, -300, and -300ER airplanes: Boeing Alert Service Bulletin 777-57A0057, Revision 1, dated August 2, 2007. (4) For The Boeing Company Model 777-200, -200LR, -300, and - 300ER airplanes: Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing on the fuel tank boundary structure or inside the main and center fuel tanks, which could result in a fire or explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Corrective Actions (Installing Teflon Sleeving, Cap Sealing, One-Time Inspection), With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2011-26-03, with revised service information. Within 60 months after January 20, 2011 (the effective date of AD 2010-24-12, Amendment 39- 16531 (75 FR 78588, December 16, 2010) (``AD 2010-24-12'')), do the applicable actions specified in paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this AD, except as required by paragraph (k)(2) of this AD. (1) For airplanes identified in Boeing Service Bulletin 777- 57A0050, Revision 2, dated May 14, 2009: Install Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap seal certain penetrating fasteners of the fuel tanks, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 2009; or Revision 4, dated September 28, 2015. As of the effective date of this AD, only use Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, for accomplishing the actions required by this paragraph. (2) For airplanes identified in Boeing Alert Service Bulletin 777-57A0051, dated May 15, 2006: Cap seal certain penetrating fasteners of the fuel tanks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-57A0051, dated May 15, 2006. (3) For airplanes identified in Boeing Alert Service Bulletin 777-57A0057, Revision 1, dated August 2, 2007: Do a general visual inspection to determine if certain fasteners are cap sealed, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777- 57A0057, Revision 1, dated August 2, 2007. Do all applicable corrective actions before further flight. [[Page 47087]] (4) For Model 777-200, -300, and -300ER airplanes identified in Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008: Cap seal the fasteners in the center fuel tanks that were not sealed during production, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008. (h) Retained Cap Sealing the Fasteners, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011-26-03, with no changes. For Model 777-200LR airplanes identified in Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008: Within 60 months after January 3, 2012 (the effective date of AD 2011-26-03), cap seal the fasteners in the center fuel tanks that were not sealed during production, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008. (i) New Detailed Inspection and Corrective Actions For Group 1, Configurations 2 through 4 airplanes; Groups 2 through 4, Configurations 3 through 5 airplanes; Groups 5 through 43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: Within 60 months after the effective date of this AD, do the applicable actions specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, except as required by paragraph (k)(2) of this AD. (1) For Group 1, Configurations 2 through 4 airplanes; Groups 2 through 4, Configurations 3 through 5 airplanes; Groups 5 through 43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for installation of Teflon sleeves on certain wire bundle clamps, as applicable; a detailed inspection to determine the type of wire bundle clamp; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (2) For Group 1, Configurations 2 through 4 airplanes; and Groups 2 through 4, Configurations 3 through 5 airplanes; as identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for correct installation of certain Teflon sleeves, as applicable; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (3) For Group 1, Configurations 2 through 4 airplanes; and Groups 2 through 4, Configurations 3 through 5 airplanes; as identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for cap sealing of certain fasteners, as applicable; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (j) New Installation of Teflon Sleeves For Group 1, Configurations 2 through 5 airplanes; Groups 2 through 4, Configurations 3 through 6 airplanes; and Groups 5 through 43, Configuration 2 airplanes; as identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: Within 60 months after the effective date of this AD, install Teflon sleeves under certain wire bundle clamps, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, except as required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (k) Exception to the Service Information (1) Where ``WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation'' of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, specifies ``Groups 5 through 43, Configuration 2,'' for this AD, ``WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation'' of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies to Groups 5 through 43. (2) Where Figure 3 of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, specifies ``Groups 1 through 7, and 9 through 43,'' for this AD, Figure 3 of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies to Groups 1 through 43. (3) Where Figure 100 of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, specifies ``Groups 5 through 43, Configuration 2,'' for this AD, Figure 100 of Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies to Groups 5 through 43. (l) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraph (g)(1) of this AD, if those actions were performed before January 20, 2011 (the effective date of AD 2010-24-12), using Boeing Alert Service Bulletin 777-57A0050, dated January 26, 2006; or Revision 1, dated August 2, 2007; provided that the applicable additional work specified in Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 2009, is done within the compliance time specified in paragraph (g) of this AD. The additional work must be done in accordance with Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 2009. (2) This paragraph provides credit for the actions specified in paragraph (g)(3) of this AD, if those actions were performed before January 20, 2011 (the effective date of AD 2010-24-12), using Boeing Alert Service Bulletin 777-57A0057, dated August 7, 2006. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 (n)(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, 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. (4) AMOCs approved previously for AD 2011-26-03 are approved as AMOCs for the corresponding provisions of this AD. (n) Related Information (1) For more information about this AD, contact Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6438; fax: 425-917-6590; email: [email protected]. (2) For 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. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on July 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-16906 Filed 7-19-16; 8:45 am] BILLING CODE 4910-13-P
![47084 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules
variable CCT or CRI), the manufacturer may must indicate in the test report which mode 3.6. To measure initial lumen output, input
select any of these modes for testing; was selected for testing and include detail power, input voltage, and input current use
however, all measurements must be taken at such that another laboratory could operate the test procedures in the table in this
the same selected mode. The manufacturer the lamp in the same mode. section.
TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES
Lamp type Referenced test procedure
General service incandescent lamps ....................................................... Appendix R to Subpart B of 10 CFR part 430.
Compact fluorescent lamps ...................................................................... Appendix W to Subpart B of 10 CFR part 430.
Integrated LED lamps ............................................................................... Appendix BB to Subpart B of 10 CFR part 430.
Other incandescent lamps that are not reflector lamps ........................... IES LM–45–15, sections 4–6, and section 7.1.
Other incandescent lamps that are reflector lamps ................................. IES LM–20–13, sections 4–6, and section 8.
Other fluorescent lamps ........................................................................... IES LM–9–09–DD, sections 4–6, and section 7.5.
OLED lamps ............................................................................................. IES LM–79–08–DD, sections 1.3 (except 1.3[f]), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.
Non-integrated LED lamps ....................................................................... IES LM–79–08–DD, sections 1.3 (except 1.3[f]), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.
* (incorporated by reference, see § 430.3)
3.7. Determine initial lamp efficacy by Notice of proposed rulemaking
ACTION: • Hand Delivery: Deliver to Mail
dividing the measured initial lumen output (NPRM). address above between 9 a.m. and 5
(lumens) by the measured initial input power p.m., Monday through Friday, except
(watts). SUMMARY: We propose to supersede Federal holidays.
3.8. Determine power factor by dividing Airworthiness Directive (AD) 2011–26– For service information identified in
the measured initial input power (watts) by 03, which applies to certain The Boeing
the product of the measured input voltage this NPRM, contact Boeing Commercial
Company Model 777–200, –200LR, Airplanes, Attention: Data & Services
(volts) and measured input current (amps).
–300, and –300ER series airplanes. AD Management, P.O. Box 3707, MC 2H–65,
4. Standby Mode Test Procedure
4.1. Measure standby mode power only for 2011–26–03 currently requires installing Seattle, WA 98124–2207; telephone:
lamps that are capable of standby mode Teflon sleeving under the clamps of 206–544–5000, extension 1; fax: 206–
operation. certain wire bundles routed along the 766–5680; Internet: https://
4.2. Connect the lamp to the manufacturer- fuel tank boundary structure, and cap www.myboeingfleet.com. You may view
specified wireless control network (if sealing certain penetrating fasteners of this referenced service information at
applicable) and configure the lamp in the main and center fuel tanks. AD the FAA, Transport Airplane
standby mode by sending a signal to the lamp 2011–26–03 resulted from fuel system
instructing it to have zero light output. Lamp Directorate, 1601 Lind Avenue SW.,
reviews conducted by the manufacturer. Renton, WA. For information on the
must remain connected to the network
Since we issued AD 2011–26–03, we availability of this material at the FAA,
throughout testing.
4.3. Operate the lamp at the rated voltage have received a report indicating that call 425–227–1221. It is also available
throughout testing. For lamps with multiple additional airplanes are affected by the on the Internet at http://
rated voltages including 120 volts, operate identified unsafe condition. This www.regulations.gov by searching for
the lamp at 120 volts. If a lamp is not rated proposed AD would add airplanes to the and locating Docket No. FAA–2016–
for 120 volts, operate the lamp at the highest applicability. This AD would also add, 8179.
rated input voltage. for certain airplanes, detailed
4.4. Stabilize the lamp prior to inspections of certain wire bundle Examining the AD Docket
measurement as specified in section 5 of IEC clamps, certain Teflon sleeves, and You may examine the AD docket on
62301–DD (incorporated by reference; see
certain fasteners; corrective actions if the Internet at http://
§ 430.3).
4.5. Measure the standby mode power in necessary; and installation of Teflon www.regulations.gov by searching for
watts as specified in section 5 of IEC 62301– sleeves under certain wire bundle and locating Docket No. FAA–2016–
DD (incorporated by reference; see § 430.3). clamps. We are proposing this AD to 8179; or in person at the Docket
[FR Doc. 2016–17135 Filed 7–19–16; 8:45 am]
prevent electrical arcing on the fuel tank Management Facility between 9 a.m.
boundary structure or inside the fuel and 5 p.m., Monday through Friday,
BILLING CODE 6450–01–P
tanks, which could result in a fire or except Federal holidays. The AD docket
explosion. contains this proposed AD, the
DATES: We must receive comments on regulatory evaluation, any comments
DEPARTMENT OF TRANSPORTATION received, and other information. The
this proposed AD by September 6, 2016.
ADDRESSES: You may send comments, street address for the Docket Office
Federal Aviation Administration
using the procedures found in 14 CFR (phone: 800–647–5527) is in the
11.43 and 11.45, by any of the following ADDRESSES section. Comments will be
14 CFR Part 39
methods: available in the AD docket shortly after
[Docket No. FAA–2016–8179; Directorate • Federal eRulemaking Portal: Go to receipt.
mstockstill on DSK3G9T082PROD with PROPOSALS
Identifier 2015–NM–201–AD] http://www.regulations.gov. Follow the FOR FURTHER INFORMATION CONTACT:
instructions for submitting comments. Suzanne Lucier, Aerospace Engineer,
RIN 2120–AA64
• Fax: 202–493–2251. Propulsion Branch, ANM 140S, FAA,
Airworthiness Directives; The Boeing • Mail: U.S. Department of Seattle Aircraft Certification Office
Company Airplanes Transportation, Docket Operations, M– (ACO), 1601 Lind Avenue SW., Renton,
30, West Building Ground Floor, Room WA 98057–3356; phone: 425–917–6438;
AGENCY:Federal Aviation W12–140, 1200 New Jersey Avenue SE., fax: 425–917–6590; email:
Administration (FAA), DOT. Washington, DC 20590. suzanne.lucier@faa.gov.
VerDate Sep<11>2014 17:58 Jul 19, 2016 Jkt 238001 PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 E:\FR\FM\20JYP1.SGM 20JYP1](https://thefederalregister.org/doc/81_FR_47223/page/1.svg)
![47086 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Install Teflon sleeving and cap sealing Up to 358 work-hours × $85 per hour = $2,241 Up to $32,671 .. Up to $5,946,122.
(retained actions from AD 2011–26–03). $30,430.
Detailed inspections and installation of Up to 53 work-hours × $85 per hour = 10 Up to $4,505 ..... Up to $819,910.
Teflon sleeves (new proposed actions). $4,505.
1 We have received no definitive data that would enable us to provide parts cost estimates for the installation of Teflon sleeves (new proposed
action) specified in this proposed AD.
We have received no definitive data List of Subjects in 14 CFR Part 39 (d) Subject
that would enable us to provide cost Air Transport Association (ATA) of
Air transportation, Aircraft, Aviation
estimates for the on-condition actions America Code 57, Wings.
safety, Incorporation by reference,
specified in this proposed AD. (e) Unsafe Condition
Safety.
Authority for This Rulemaking This AD was prompted by fuel system
The Proposed Amendment reviews conducted by the manufacturer. We
Title 49 of the United States Code are issuing this AD to prevent electrical
specifies the FAA’s authority to issue Accordingly, under the authority
delegated to me by the Administrator, arcing on the fuel tank boundary structure or
rules on aviation safety. Subtitle I, inside the main and center fuel tanks, which
Section 106, describes the authority of the FAA proposes to amend 14 CFR part could result in a fire or explosion.
the FAA Administrator. Subtitle VII, 39 as follows:
(f) Compliance
Aviation Programs, describes in more PART 39—AIRWORTHINESS Comply with this AD within the
detail the scope of the Agency’s DIRECTIVES compliance times specified, unless already
authority. done.
We are issuing this rulemaking under ■ 1. The authority citation for part 39
the authority described in Subtitle VII, (g) Retained Corrective Actions (Installing
continues to read as follows: Teflon Sleeving, Cap Sealing, One-Time
Part A, Subpart III, Section 44701,
Authority: 49 U.S.C. 106(g), 40113, 44701. Inspection), With Revised Service
‘‘General requirements.’’ Under that Information
section, Congress charges the FAA with § 39.13 [Amended]
This paragraph restates the requirements of
promoting safe flight of civil aircraft in ■ 2. The FAA amends § 39.13 by paragraph (g) of AD 2011–26–03, with
air commerce by prescribing regulations removing Airworthiness Directive (AD) revised service information. Within 60
for practices, methods, and procedures 2011–26–03, Amendment 39–16893 (76 months after January 20, 2011 (the effective
the Administrator finds necessary for FR 78138, December 16, 2011), and date of AD 2010–24–12, Amendment 39–
safety in air commerce. This regulation adding the following new AD: 16531 (75 FR 78588, December 16, 2010)
is within the scope of that authority (‘‘AD 2010–24–12’’)), do the applicable
because it addresses an unsafe condition The Boeing Company: Docket No. FAA– actions specified in paragraph (g)(1), (g)(2),
that is likely to exist or develop on 2016–8179; Directorate Identifier 2015– (g)(3), or (g)(4) of this AD, except as required
NM–201–AD. by paragraph (k)(2) of this AD.
products identified in this rulemaking (1) For airplanes identified in Boeing
action. (a) Comments Due Date Service Bulletin 777–57A0050, Revision 2,
Regulatory Findings The FAA must receive comments on this dated May 14, 2009: Install Teflon sleeving
AD action by September 6, 2016. under the clamps of certain wire bundles
We have determined that this routed along the fuel tank boundary
(b) Affected ADs
proposed AD would not have federalism structure, and cap seal certain penetrating
implications under Executive Order This AD replaces AD 2011–26–03, fasteners of the fuel tanks, in accordance
13132. This proposed AD would not Amendment 39–16893 (76 FR 78138, with the Accomplishment Instructions of
December 16, 2011) (‘‘AD 2011–26–03’’). Boeing Service Bulletin 777–57A0050,
have a substantial direct effect on the
(c) Applicability Revision 2, dated May 14, 2009; or Revision
States, on the relationship between the 4, dated September 28, 2015. As of the
national Government and the States, or This AD applies to The Boeing Company effective date of this AD, only use Boeing
on the distribution of power and airplanes, certificated in any category, as Service Bulletin 777–57A0050, Revision 4,
responsibilities among the various identified in the applicable service dated September 28, 2015, for accomplishing
levels of government. information specified in paragraphs (c)(1), the actions required by this paragraph.
For the reasons discussed above, I (c)(2), (c)(3), and (c)(4) of this AD. (2) For airplanes identified in Boeing Alert
(1) For The Boeing Company Model 777– Service Bulletin 777–57A0051, dated May
certify that the proposed regulation:
200, –200LR, –300, –300ER, and 777F 15, 2006: Cap seal certain penetrating
(1) Is not a ‘‘significant regulatory airplanes: Boeing Service Bulletin 777– fasteners of the fuel tanks, in accordance
action’’ under Executive Order 12866, 57A0050, Revision 4, dated September 28, with the Accomplishment Instructions of
(2) Is not a ‘‘significant rule’’ under 2015. Boeing Alert Service Bulletin 777–57A0051,
the DOT Regulatory Policies and (2) For The Boeing Company Model 777– dated May 15, 2006.
Procedures (44 FR 11034, February 26, 200 and –300 airplanes: Boeing Alert Service (3) For airplanes identified in Boeing Alert
mstockstill on DSK3G9T082PROD with PROPOSALS
1979), Bulletin 777–57A0051, dated May 15, 2006. Service Bulletin 777–57A0057, Revision 1,
(3) Will not affect intrastate aviation (3) For The Boeing Company Model 777– dated August 2, 2007: Do a general visual
in Alaska, and 200, –300, and –300ER airplanes: Boeing inspection to determine if certain fasteners
Alert Service Bulletin 777–57A0057, are cap sealed, and do all applicable
(4) Will not have a significant Revision 1, dated August 2, 2007. corrective actions, in accordance with the
economic impact, positive or negative, (4) For The Boeing Company Model 777– Accomplishment Instructions of Boeing Alert
on a substantial number of small entities 200, –200LR, –300, and –300ER airplanes: Service Bulletin 777–57A0057, Revision 1,
under the criteria of the Regulatory Boeing Alert Service Bulletin 777–57A0059, dated August 2, 2007. Do all applicable
Flexibility Act. dated October 30, 2008. corrective actions before further flight.
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![Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules 47087
(4) For Model 777–200, –300, and –300ER Boeing Service Bulletin 777–57A0050, CFR 39.19. In accordance with 14 CFR 39.19,
airplanes identified in Boeing Alert Service Revision 4, dated September 28, 2015. Do all send your request to your principal inspector
Bulletin 777–57A0059, dated October 30, applicable corrective actions before further or local Flight Standards District Office, as
2008: Cap seal the fasteners in the center fuel flight. appropriate. If sending information directly
tanks that were not sealed during production, to the manager of the ACO, send it to the
(j) New Installation of Teflon Sleeves attention of the person identified in
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin For Group 1, Configurations 2 through 5 paragraph (n)(1) of this AD. Information may
777–57A0059, dated October 30, 2008. airplanes; Groups 2 through 4, Configurations be emailed to: 9-ANM-Seattle-ACO-AMOC-
3 through 6 airplanes; and Groups 5 through Requests@faa.gov.
(h) Retained Cap Sealing the Fasteners, With 43, Configuration 2 airplanes; as identified in (2) Before using any approved AMOC,
No Changes Boeing Service Bulletin 777–57A0050, notify your appropriate principal inspector,
This paragraph restates the requirements of Revision 4, dated September 28, 2015: or lacking a principal inspector, the manager
paragraph (i) of AD 2011–26–03, with no Within 60 months after the effective date of of the local flight standards district office/
changes. For Model 777–200LR airplanes this AD, install Teflon sleeves under certain certificate holding district office.
identified in Boeing Alert Service Bulletin wire bundle clamps, as applicable, in (3) An AMOC that provides an acceptable
777–57A0059, dated October 30, 2008: accordance with the Accomplishment level of safety may be used for any repair,
Within 60 months after January 3, 2012 (the Instructions of Boeing Service Bulletin 777– modification, or alteration required by this
effective date of AD 2011–26–03), cap seal 57A0050, Revision 4, dated September 28, AD if it is approved by the Boeing
the fasteners in the center fuel tanks that 2015, except as required by paragraphs (k)(1), Commercial Airplanes Organization
were not sealed during production, in (k)(2), and (k)(3) of this AD. Designation Authorization (ODA) that has
accordance with the Accomplishment been authorized by the Manager, Seattle
(k) Exception to the Service Information
Instructions of Boeing Alert Service Bulletin ACO, to make those findings. To be
777–57A0059, dated October 30, 2008. (1) Where ‘‘WORK PACKAGE 21: More approved, the repair method, modification
Work: Rear Spar Wire Bundle Teflon sleeve deviation, or alteration deviation must meet
(i) New Detailed Inspection and Corrective Installation’’ of Boeing Service Bulletin 777– the certification basis of the airplane, and the
Actions 57A0050, Revision 4, dated September 28, approval must specifically refer to this AD.
For Group 1, Configurations 2 through 4 2015, specifies ‘‘Groups 5 through 43, (4) AMOCs approved previously for AD
airplanes; Groups 2 through 4, Configurations Configuration 2,’’ for this AD, ‘‘WORK 2011–26–03 are approved as AMOCs for the
3 through 5 airplanes; Groups 5 through 43, PACKAGE 21: More Work: Rear Spar Wire corresponding provisions of this AD.
Configuration 1 airplanes; and Groups 44 and Bundle Teflon sleeve Installation’’ of Boeing
Service Bulletin 777–57A0050, Revision 4, (n) Related Information
45 airplanes; as identified in Boeing Service
Bulletin 777–57A0050, Revision 4, dated dated September 28, 2015, applies to Groups (1) For more information about this AD,
September 28, 2015: Within 60 months after 5 through 43. contact Suzanne Lucier, Aerospace Engineer,
the effective date of this AD, do the (2) Where Figure 3 of Boeing Service Propulsion Branch, ANM 140S, FAA, Seattle
applicable actions specified in paragraphs Bulletin 777–57A0050, Revision 4, dated Aircraft Certification Office (ACO), 1601 Lind
(i)(1), (i)(2), and (i)(3) of this AD, except as September 28, 2015, specifies ‘‘Groups 1 Avenue SW., Renton, WA 98057–3356;
required by paragraph (k)(2) of this AD. through 7, and 9 through 43,’’ for this AD, phone: 425–917–6438; fax: 425–917–6590;
(1) For Group 1, Configurations 2 through Figure 3 of Boeing Service Bulletin 777– email: suzanne.lucier@faa.gov.
4 airplanes; Groups 2 through 4, 57A0050, Revision 4, dated September 28, (2) For service information identified in
Configurations 3 through 5 airplanes; Groups 2015, applies to Groups 1 through 43. this AD, contact Boeing Commercial
5 through 43, Configuration 1 airplanes; and (3) Where Figure 100 of Boeing Service Airplanes, Attention: Data & Services
Bulletin 777–57A0050, Revision 4, dated Management, P.O. Box 3707, MC 2H–65,
Groups 44 and 45 airplanes; as identified in
September 28, 2015, specifies ‘‘Groups 5 Seattle, WA 98124–2207; telephone: 206–
Boeing Service Bulletin 777–57A0050,
through 43, Configuration 2,’’ for this AD, 544–5000, extension 1; fax: 206–766–5680;
Revision 4, dated September 28, 2015: Do a
Figure 100 of Boeing Service Bulletin 777– Internet: https://www.myboeingfleet.com.
detailed inspection for installation of Teflon
57A0050, Revision 4, dated September 28, You may view this referenced service
sleeves on certain wire bundle clamps, as
2015, applies to Groups 5 through 43. information at the FAA, Transport Airplane
applicable; a detailed inspection to
Directorate, 1601 Lind Avenue SW., Renton,
determine the type of wire bundle clamp; (l) Credit for Previous Actions
WA. For information on the availability of
and do all applicable corrective actions; in (1) This paragraph provides credit for the this material at the FAA, call 425–227–1221.
accordance with the Accomplishment actions specified in paragraph (g)(1) of this
Instructions of Boeing Service Bulletin 777– AD, if those actions were performed before Issued in Renton, Washington, on July 8,
57A0050, Revision 4, dated September 28, January 20, 2011 (the effective date of AD 2016.
2015. Do all applicable corrective actions 2010–24–12), using Boeing Alert Service Michael Kaszycki,
before further flight. Bulletin 777–57A0050, dated January 26, Acting Manager, Transport Airplane
(2) For Group 1, Configurations 2 through 2006; or Revision 1, dated August 2, 2007; Directorate, Aircraft Certification Service.
4 airplanes; and Groups 2 through 4, provided that the applicable additional work [FR Doc. 2016–16906 Filed 7–19–16; 8:45 am]
Configurations 3 through 5 airplanes; as specified in Boeing Service Bulletin 777–
identified in Boeing Service Bulletin 777– BILLING CODE 4910–13–P
57A0050, Revision 2, dated May 14, 2009, is
57A0050, Revision 4, dated September 28, done within the compliance time specified in
2015: Do a detailed inspection for correct paragraph (g) of this AD. The additional work
installation of certain Teflon sleeves, as must be done in accordance with Boeing DEPARTMENT OF VETERANS
applicable; and do all applicable corrective Service Bulletin 777–57A0050, Revision 2, AFFAIRS
actions; in accordance with the dated May 14, 2009.
Accomplishment Instructions of Boeing (2) This paragraph provides credit for the 38 CFR Part 14
Service Bulletin 777–57A0050, Revision 4, actions specified in paragraph (g)(3) of this
dated September 28, 2015. Do all applicable AD, if those actions were performed before RIN 2900–AP51
corrective actions before further flight. January 20, 2011 (the effective date of AD
mstockstill on DSK3G9T082PROD with PROPOSALS
(3) For Group 1, Configurations 2 through 2010–24–12), using Boeing Alert Service Recognition of Tribal Organizations for
4 airplanes; and Groups 2 through 4, Bulletin 777–57A0057, dated August 7, 2006. Representation of VA Claimants
Configurations 3 through 5 airplanes; as
identified in Boeing Service Bulletin 777– (m) Alternative Methods of Compliance AGENCY: Department of Veterans Affairs.
57A0050, Revision 4, dated September 28, (AMOCs) ACTION: Proposed rule.
2015: Do a detailed inspection for cap sealing (1) The Manager, Seattle Aircraft
of certain fasteners, as applicable; and do all Certification Office (ACO), FAA, has the SUMMARY: The Department of Veterans
applicable corrective actions; in accordance authority to approve AMOCs for this AD, if Affairs (VA) is proposing to amend its
with the Accomplishment Instructions of requested using the procedures found in 14 regulations concerning recognition of
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Document Created: 2018-02-08 07:56:55
Document Modified: 2018-02-08 07:56:55
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 6, 2016. | |
| Contact | Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6438; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 47084 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft and Aviation Safety |
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