Airworthiness Directives; the Boeing Company Airplanes, 63903-63907 [2013-25134]

Download as PDF Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules Novel or Unusual Design Features List of Subjects in 14 CFR Part 25 The Model EMB–550 airplane will incorporate the following novel or unusual design features: The design of the electronic flight control system incorporates normal load factor limiting on a full-time basis that will prevent the flight crew from inadvertently or intentionally exceeding the positive or negative airplane limit load factor. This feature is considered novel and because the current regulations do not provide standards for maneuverability and controllability evaluations for such systems. Therefore, a special condition is needed to ensure adequate maneuverability and controllability when using this design feature. Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Discussion Title 14 Code of Federal Regulations (14 CFR) part 25 sections do not specify requirements or policy for demonstrating maneuver control that impose any handling qualities requirements beyond the design limit structural loads. Nevertheless, some pilots have become accustomed to the availability of this excess maneuver capacity in case of extreme emergency such as upset recoveries or collision avoidance. As with previous fly-by-wire airplanes, the FAA has no regulatory or safety reason to prohibit a design for an electronic flight control system with load factor limiting. It is possible that pilots accustomed to this feature feel more freedom in commanding full-stick displacement maneuvers because of the following: • Knowledge that the limit system will protect the structure, • Low stick force/displacement gradients, • Smooth transition from pilot elevator control to limit control. The special conditions will ensure adequate maneuverability and controllability when using this design feature. tkelley on DSK3SPTVN1PROD with PROPOSALS Applicability As discussed above, these special conditions are applicable to the Model EMB–550 airplane. Should Embraer S.A. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model of airplanes. It is not a rule of general applicability. VerDate Mar<15>2010 17:00 Oct 24, 2013 Jkt 232001 Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Embraer S.A. Model EMB–550 airplanes. 1. Flight Envelope Protection: Normal Load Factor (g) Limiting. To meet the intent of adequate maneuverability and controllability required by § 25.143(a), and in addition to the requirements of § 25.143(a) and in the absence of other limiting factors, the following special conditions are proposed based on § 25.333(b): (a) The positive limiting load factor must not be less than: (1) 2.5g for the normal state of the electronic flight control system with the high lift devices retracted. (2) 2.0g for the normal state of the electronic flight control system with the high lift devices extended. (b) The negative limiting load factor must be equal to or more negative than: (1) Minus 1.0g for the normal state of the electronic flight control system with the high lift devices retracted. (2) 0.0g for the normal state of the electronic flight control system with high lift devices extended. (c) Maximum reachable positive load factor wings level may be limited by the characteristics of the electronic flight control system or flight envelope protections (other than load factor protection) provided that: (1) The required values are readily achievable in turns, and (2) That wings level pitch up is satisfactory. (d) Maximum achievable negative load factor may be limited by the characteristics of the electronic flight control system or flight envelope protections (other than load factor protection) provided that: (1) Pitch down responsiveness is satisfactory, and (2) From level flight, 0g is readily achievable or alternatively, a satisfactory trajectory change is readily achievable at operational speeds. For the FAA to consider a trajectory change as satisfactory, the applicant should propose and justify a pitch rate that provides sufficient maneuvering capability in the most critical scenarios. (e) Compliance demonstration with the above requirements may be PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 63903 performed without ice accretion on the airframe. (f) These proposed special conditions do not impose an upper bound for the normal load factor limit, nor does it require that the limiter exist. If the limit is set at a value beyond the structural design limit maneuvering load factor n of §§ 25.333(b), 25.337(b), 25.337 (c), there should be a very obvious positive tactile feel built into the controller so that it serves as a deterrent to inadvertently exceeding the structural limit. Issued in Renton, Washington, on September 6, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–25204 Filed 10–24–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0867; Directorate Identifier 2013–NM–115–AD] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD was prompted by reports of severe corrosion on bonding jumpers installed on the flight control surfaces. This proposed AD would require repetitive bonding jumper inspections for corrosion, sealant disbond, and insufficient sealant coverage, and corrective actions if necessary. This proposed AD also specifies an optional action of doing an inspection for corrosion damage of the bonding brackets, and corrective actions if necessary, which would terminate the repetitive inspections. For certain airplanes, this proposed AD would also require installing certain bonding jumpers and related ground clips and fasteners to the elevators, horizontal stabilizers, rudder, and vertical fin, removing certain bonding jumpers and installing new bonding jumpers, and replacing single-tabbed brackets with two-tabbed brackets. We are proposing this AD to detect and correct corrosion SUMMARY: E:\FR\FM\25OCP1.SGM 25OCP1 63904 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules on bonding jumpers installed on the flight control surfaces, which, in the event of a lighting strike, could damage the actuator control electronics (ACEs) and result in the loss of the ability to command individual flight control surfaces or cause uncommanded motion of individual flight control surfaces. We must receive comments on this proposed AD by December 9, 2013. DATES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 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 review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. tkelley on DSK3SPTVN1PROD with PROPOSALS FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6482; fax: 425–917– 6590; email: Georgios.Roussos@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Mar<15>2010 17:00 Oct 24, 2013 Jkt 232001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0867; Directorate Identifier 2013– NM–115–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 We have received a report of severe corrosion on 15 bonding jumpers on the ailerons, horizontal stabilizers, and vertical fins of six airplanes that were approximately eight years old. We also received a similar report on an airplane that was approximately seven years old. The corrosion is caused by sealant voids, which allow moisture under the sealant and then trap it inside. The bonding jumpers are part of the lightning protection ground path for the flight control surfaces that prevent excessive lightning energy from traveling to the primary flight control actuators and then to one of the four ACEs. Corrosion damage on the bonding jumper connections creates high resistance bonding paths that could, in the event of a lightning strike, potentially expose multiple flight control system ACEs to high voltage transients. The excessive voltage could cause damage to the ACEs and result in the loss of the ability to command individual flight control surfaces or cause uncommanded motion of individual flight control surfaces. A new category 2 fay seal method has been developed to improve the integrity of the bonding jumper connections. This new method creates a continuous layer of sealant inside and outside of all mating surfaces to keep moisture away from the bonding surfaces and prevent corrosion. Relevant Service Information We reviewed the following service bulletins: • Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 • Boeing Service Bulletin 777– 55A0010, Revision 1, dated April 17, 2001 • Boeing Service Bulletin 777– 55A0014, Revision 1, dated April 1, 2010 For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2013–0867. Other Relevant Rulemaking This proposed AD is related to AD 2012–08–13, Amendment 39–17030 (77 FR 24357, April 24, 2012). AD 2012–08– 13 requires replacing certain singletabbed bonding brackets in the airplane empennage with two-tabbed bonding brackets. AD 2012–08–13 also requires, for certain airplanes, installing new bonding jumpers, and measuring the resistance of the modified installation to verify resistance is within specified limits. AD 2012–08–13 refers to Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001; and Boeing Service Bulletin 777–55A0014, Revision 1, dated April 1, 2010; as the appropriate sources of service information for accomplishing the required actions. This proposed AD would require inspecting the installation of the bonding jumpers associated with AD 2012–08–13, Amendment 39–17030 (77 FR 24357, April 24, 2012). 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 require accomplishing the actions specified in the service information identified previously, except as discussed under ‘‘Differences Between the Proposed Rule and the Service Information.’’ The phrase ‘‘corrective actions’’ might be used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Difference Between the Proposed Rule and the Service Bulletin Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing E:\FR\FM\25OCP1.SGM 25OCP1 63905 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 131 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Inspection of bonding jumpers ............... Cost on U.S. operators Up to $5,695 per inspection cycle. Up to $51,358 ........ Up to $746,045 per inspection cycle. Up to $6,727,898. 2,668 $8,278 .................... $1,084,418. 1,235 Up to 67 work–hours × $85 per hour = Up to $5,695 per inspection cycle. Up to 158 work–hours × $85 per hour = Up to $13,430. 66 work–hours × $85 per hour = $5,610 Cost per product 37,928 Labor cost $3,020 .................... $395,620. 21 work-hours × $85 per hour = $1,785 Replacement of bonding brackets ......... Concurrent cost Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001. Concurrent cost Boeing Service Bulletin 777–55A0014, Revision 1, dated April 1, 2010. We estimate the following costs to do any necessary replacements that would Parts cost $0 be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement of bonding brackets ............. Up to 158 work–hours × $85 per hour = Up to $13,430 ............. We have received no definitive data that would enable us to provide cost estimates for certain on-condition repairs specified in this proposed AD. tkelley on DSK3SPTVN1PROD with PROPOSALS 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 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 VerDate Mar<15>2010 17:00 Oct 24, 2013 Jkt 232001 Parts cost 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 this 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 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 $37,928 Cost per product Up to $51,358. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2013–0867; Directorate Identifier 2013– NM–115–AD. (a) Comments Due Date We must receive comments by December 9, 2013. (b) Affected ADs This AD affects AD 2012–08–13, Amendment 39–17030 (77 FR 24357, April 24, 2012). (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 Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by reports of severe corrosion on bonding jumpers installed on the flight control surfaces. We are issuing this AD to detect and correct corrosion on bonding jumpers installed on the flight control surfaces, which, in the event of a lighting strike, could damage the actuator control electronics (ACEs) and result in the E:\FR\FM\25OCP1.SGM 25OCP1 63906 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules loss of the ability to command individual flight control surfaces or cause uncommanded motion of individual flight control surfaces. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Bonding Jumper or Bracket Inspection At the applicable compliance time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013, except as specified in paragraphs (j)(1) and (j)(2) of this AD: Do a general visual inspection or a detailed inspection using a borescope, as applicable, for corrosion, sealant disbond, and insufficient sealant coverage of bonding jumpers; and do all applicable corrective actions; in accordance with Option 1, and Option 2, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013, except as required by paragraph (j)(3) of this AD. Do a detailed inspection using a borescope if the horizontal stabilizer tips have not been removed. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 48 months. Doing the actions specified in paragraph (h)(1) of this AD on a bonding jumper terminates the repetitive inspections required by this paragraph. Doing the actions specified in paragraph (h)(2) of this AD terminates repetitive inspections required by this paragraph for that bonding jumper. tkelley on DSK3SPTVN1PROD with PROPOSALS (h) Optional Terminating Action and Termination of Certain Repetitive Inspections (1) Doing a general visual inspection or a detailed inspection for corrosion damage of the bonding jumper brackets, and all applicable corrective actions; in accordance with Option 2 of the Accomplishment Instructions of Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013; terminates the repetitive inspections required by paragraph (g) of this AD. Do all applicable corrective actions before further flight. (2) The repetitive inspections required by paragraph (g) of this AD are not required on the bonding jumpers that were removed, inspected, and replaced with new bonding jumpers and new fasteners using the new category 2 fay sealed direct standard ground stud installation method, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013. (i) Prior and Concurrent Requirements (1) For Group 1 airplanes, as identified in Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013: Prior to or concurrently with accomplishing the actions required by paragraph (g) of this AD, install new bonding jumpers, and do resistance measurements of the modified installation to verify resistance is within the limits specified in the Accomplishment Instructions of Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001. Do the actions in accordance with the VerDate Mar<15>2010 17:00 Oct 24, 2013 Jkt 232001 Accomplishment Instructions of Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001. Note 1 to paragraph (i)(1) of this AD: AD 2012–08–13, Amendment 39–17030 (77 FR 24357, April 24, 2012), refers to Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001, as the appropriate source of service information for accomplishing the actions specified in paragraph (h) of AD 2012–08–13. (2) For Group 1 and Group 2 airplanes, as identified in Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013: Prior to or concurrently with accomplishing the actions required by paragraph (g) of this AD, replace certain single-tabbed bonding brackets in the airplane empennage with twotabbed bonding brackets, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–55A0014, Revision 1, dated April 1, 2010. Note 2 to paragraph (i)(2) of this AD: AD 2012–08–13, Amendment 39–17030 (77 FR 24357, April 24, 2012), refers to Boeing Service Bulletin 777–55A0014, Revision 1, dated April 1, 2010, as the appropriate source of service information for accomplishing the actions specified in paragraph (g) of AD 2012–08–13. (j) Exceptions to Service Information (1) Where Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013, specifies a compliance time after the ‘‘Original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) The ‘‘Condition’’ column in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013, refers to a condition as of the ‘‘Original Issue date of this service bulletin.’’ This AD applies to the corresponding condition as of the effective date of this AD. (3) If any corrosion damage is found during any inspection required by this AD, and Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013, specifies to contact Boeing for appropriate action: Before further flight, repair the corrosion damage using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) Credit for Previous Actions (1) For Groups 1, 2, and 6 through 9, as identified in Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009: This paragraph provides credit for actions required by paragraph (g) of this AD and the actions specified in paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD. (2) For Groups 3 through 5, as identified in Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009: This paragraph provides credit for actions required by paragraph (g) of this AD, except for the actions required for bonding jumpers 21 and 22, if those actions were performed before the effective date of this AD using PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD. If a check of the airplane’s maintenance records positively determines that bonding jumpers 21 and 22 were inspected before the effective date of this AD in accordance with Option 1 of Work Package 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, this paragraph provides credit for the actions required by paragraph (g) of this AD for the inspected bonding jumpers. (3) For Groups 3 through 5, as identified in Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009: This paragraph provides credit for actions specified in paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD; provided that a check of the airplane’s maintenance records positively determines that bonding jumpers 21 and 22 were replaced in accordance with Option 2 of Work Package 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, or were replaced using the new Category 2 fay sealed direct ground stud installation method. (4) This paragraph provides credit for actions required by paragraph (i)(1) of this AD if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–55A0010, dated October 26, 2000, which is not incorporated by reference in this AD. (5) This paragraph provides credit for actions required by paragraph (i)(2) of this AD if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–55A0014, dated May 8, 2008, which is not incorporated by reference in this AD. (l) 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 (m) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. E:\FR\FM\25OCP1.SGM 25OCP1 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules (m) Related Information (1) For more information about this AD, Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6482; fax: 425– 917–6590; email: Georgios.Roussos@faa.gov. (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 review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on October 15, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–25134 Filed 10–24–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Costruzioni Aeronautiche Tecnam Airworthiness Office, Via Maiorise–81043 Capua (CE) Italy; telephone: +39 0823 620134; fax: +39 0823 622899; email: m.oliva@tecnam.com or g.paduano@ tecnam.com; Internet: www.tecnam.com/it-IT/documenti/ service-bulletins.aspx. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket 14 CFR Part 39 [Docket No. FAA–2013–0888; Directorate Identifier 2013–CE–024–AD] RIN 2120–AA64 Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks of the nose landing gear (NLG) lower link. We are issuing this proposed AD to require actions to address the unsafe condition on these products. tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: We must receive comments on this proposed AD by December 9, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go tohttp://www.regulations.gov. Follow DATES: VerDate Mar<15>2010 17:00 Oct 24, 2013 Jkt 232001 You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0888; Directorate Identifier 2013–CE–024–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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 63907 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:// 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 European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2013– 0134, dated July 2, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During an inspection of a P2006T, a nose landing gear (NLG) lower link was found with two cracks. The affected NLG lower link is part of NLG lower link assembly P/N 26– 8–1417–000. This condition, if not detected and corrected, could lead to NLG failure, possibly resulting in damage to the aeroplane and injury to the occupants. To address this potential unsafe condition, Costruzioni Aeronautiche Tecnam (hereafter referred to as Tecnam) issued Service Bulletin (SB) SB–128–CS, providing inspection instructions. Tecnam also developed an improved NLG lower link assembly with P/N 26–8–8000–000, which can be installed in service by accomplishment of Tecnam SB–104–CS. For the reasons described above, this AD requires, for aeroplanes equipped with NLG lower link assembly P/N 26–8–1417–000, a one-time inspection of the NLG lower link and, depending on findings, accomplishment of the applicable corrective action. This AD also requires installation of the improved NLG lower link assembly P/N 26–8–8000– 000. You may obtain further information by examining the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA– 2013–0888. Relevant Service Information Costruzioni Aeronautiche Tecnam srl issued Service Bulletin No. SB 104–CS, Edition 2, Revision 1, dated March 28, 2013 (now superseded); Service Bulletin No. SB 128–CS, Revision 0, dated May 15, 2013; Job Card 442, Revision 1, dated February 11, 2013; Job Card 468, dated October 12, 2012; and Job Card 528, Revision 1, dated April 2, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\25OCP1.SGM 25OCP1

Agencies

[Federal Register Volume 78, Number 207 (Friday, October 25, 2013)]
[Proposed Rules]
[Pages 63903-63907]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25134]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0867; Directorate Identifier 2013-NM-115-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777-200, -200LR, -300, and -300ER 
series airplanes. This proposed AD was prompted by reports of severe 
corrosion on bonding jumpers installed on the flight control surfaces. 
This proposed AD would require repetitive bonding jumper inspections 
for corrosion, sealant disbond, and insufficient sealant coverage, and 
corrective actions if necessary. This proposed AD also specifies an 
optional action of doing an inspection for corrosion damage of the 
bonding brackets, and corrective actions if necessary, which would 
terminate the repetitive inspections. For certain airplanes, this 
proposed AD would also require installing certain bonding jumpers and 
related ground clips and fasteners to the elevators, horizontal 
stabilizers, rudder, and vertical fin, removing certain bonding jumpers 
and installing new bonding jumpers, and replacing single-tabbed 
brackets with two-tabbed brackets. We are proposing this AD to detect 
and correct corrosion

[[Page 63904]]

on bonding jumpers installed on the flight control surfaces, which, in 
the event of a lighting strike, could damage the actuator control 
electronics (ACEs) and result in the loss of the ability to command 
individual flight control surfaces or cause uncommanded motion of 
individual flight control surfaces.

DATES: We must receive comments on this proposed AD by December 9, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification 
Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; 
phone: 425-917-6482; fax: 425-917-6590; email: 
Georgios.Roussos@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0867; 
Directorate Identifier 2013-NM-115-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

    We have received a report of severe corrosion on 15 bonding jumpers 
on the ailerons, horizontal stabilizers, and vertical fins of six 
airplanes that were approximately eight years old. We also received a 
similar report on an airplane that was approximately seven years old. 
The corrosion is caused by sealant voids, which allow moisture under 
the sealant and then trap it inside.
    The bonding jumpers are part of the lightning protection ground 
path for the flight control surfaces that prevent excessive lightning 
energy from traveling to the primary flight control actuators and then 
to one of the four ACEs. Corrosion damage on the bonding jumper 
connections creates high resistance bonding paths that could, in the 
event of a lightning strike, potentially expose multiple flight control 
system ACEs to high voltage transients. The excessive voltage could 
cause damage to the ACEs and result in the loss of the ability to 
command individual flight control surfaces or cause uncommanded motion 
of individual flight control surfaces.
    A new category 2 fay seal method has been developed to improve the 
integrity of the bonding jumper connections. This new method creates a 
continuous layer of sealant inside and outside of all mating surfaces 
to keep moisture away from the bonding surfaces and prevent corrosion.

Relevant Service Information

    We reviewed the following service bulletins:

 Boeing Service Bulletin 777-27A0078, Revision 1, dated April 
1, 2013
 Boeing Service Bulletin 777-55A0010, Revision 1, dated April 
17, 2001
 Boeing Service Bulletin 777-55A0014, Revision 1, dated April 
1, 2010

For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0867.

Other Relevant Rulemaking

    This proposed AD is related to AD 2012-08-13, Amendment 39-17030 
(77 FR 24357, April 24, 2012). AD 2012-08-13 requires replacing certain 
single-tabbed bonding brackets in the airplane empennage with two-
tabbed bonding brackets. AD 2012-08-13 also requires, for certain 
airplanes, installing new bonding jumpers, and measuring the resistance 
of the modified installation to verify resistance is within specified 
limits. AD 2012-08-13 refers to Boeing Service Bulletin 777-55A0010, 
Revision 1, dated April 17, 2001; and Boeing Service Bulletin 777-
55A0014, Revision 1, dated April 1, 2010; as the appropriate sources of 
service information for accomplishing the required actions.
    This proposed AD would require inspecting the installation of the 
bonding jumpers associated with AD 2012-08-13, Amendment 39-17030 (77 
FR 24357, April 24, 2012).

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 require accomplishing the actions specified 
in the service information identified previously, except as discussed 
under ``Differences Between the Proposed Rule and the Service 
Information.''
    The phrase ``corrective actions'' might be used in this proposed 
AD. ``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Difference Between the Proposed Rule and the Service Bulletin

    Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1, 
2013, specifies to contact the manufacturer for instructions on how to 
repair certain conditions, but this proposed AD would require repairing

[[Page 63905]]

those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 131 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of bonding jumpers..  Up to 67 work-hours x                $0  Up to $5,695 per    Up to $746,045 per
                                  $85 per hour = Up to                     inspection cycle.   inspection cycle.
                                  $5,695 per inspection
                                  cycle.
Replacement of bonding brackets  Up to 158 work-hours x           37,928  Up to $51,358.....  Up to $6,727,898.
                                  $85 per hour = Up to
                                  $13,430.
Concurrent cost Boeing Service   66 work-hours x $85 per           2,668  $8,278............  $1,084,418.
 Bulletin 777-55A0010, Revision   hour = $5,610.
 1, dated April 17, 2001.
Concurrent cost Boeing Service   21 work-hours x $85 per           1,235  $3,020............  $395,620.
 Bulletin 777-55A0014, Revision   hour = $1,785.
 1, dated April 1, 2010.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 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 bonding brackets.......  Up to 158 work-hours x            $37,928  Up to $51,358.
                                         $85 per hour = Up to
                                         $13,430.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for certain on-condition repairs 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 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 this 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0867; Directorate Identifier 
2013-NM-115-AD.

(a) Comments Due Date

    We must receive comments by December 9, 2013.

(b) Affected ADs

    This AD affects AD 2012-08-13, Amendment 39-17030 (77 FR 24357, 
April 24, 2012).

(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 Service Bulletin 777-27A0078, Revision 1, dated 
April 1, 2013.

 (d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    This AD was prompted by reports of severe corrosion on bonding 
jumpers installed on the flight control surfaces. We are issuing 
this AD to detect and correct corrosion on bonding jumpers installed 
on the flight control surfaces, which, in the event of a lighting 
strike, could damage the actuator control electronics (ACEs) and 
result in the

[[Page 63906]]

loss of the ability to command individual flight control surfaces or 
cause uncommanded motion of individual flight control surfaces.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Bonding Jumper or Bracket Inspection

    At the applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 777-27A0078, Revision 1, 
dated April 1, 2013, except as specified in paragraphs (j)(1) and 
(j)(2) of this AD: Do a general visual inspection or a detailed 
inspection using a borescope, as applicable, for corrosion, sealant 
disbond, and insufficient sealant coverage of bonding jumpers; and 
do all applicable corrective actions; in accordance with Option 1, 
and Option 2, as applicable, of the Accomplishment Instructions of 
Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1, 
2013, except as required by paragraph (j)(3) of this AD. Do a 
detailed inspection using a borescope if the horizontal stabilizer 
tips have not been removed. Do all applicable corrective actions 
before further flight. Repeat the inspection thereafter at intervals 
not to exceed 48 months. Doing the actions specified in paragraph 
(h)(1) of this AD on a bonding jumper terminates the repetitive 
inspections required by this paragraph. Doing the actions specified 
in paragraph (h)(2) of this AD terminates repetitive inspections 
required by this paragraph for that bonding jumper.

(h) Optional Terminating Action and Termination of Certain Repetitive 
Inspections

    (1) Doing a general visual inspection or a detailed inspection 
for corrosion damage of the bonding jumper brackets, and all 
applicable corrective actions; in accordance with Option 2 of the 
Accomplishment Instructions of Boeing Service Bulletin 777-27A0078, 
Revision 1, dated April 1, 2013; terminates the repetitive 
inspections required by paragraph (g) of this AD. Do all applicable 
corrective actions before further flight.
    (2) The repetitive inspections required by paragraph (g) of this 
AD are not required on the bonding jumpers that were removed, 
inspected, and replaced with new bonding jumpers and new fasteners 
using the new category 2 fay sealed direct standard ground stud 
installation method, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-27A0078, Revision 1, 
dated April 1, 2013.

(i) Prior and Concurrent Requirements

    (1) For Group 1 airplanes, as identified in Boeing Service 
Bulletin 777-27A0078, Revision 1, dated April 1, 2013: Prior to or 
concurrently with accomplishing the actions required by paragraph 
(g) of this AD, install new bonding jumpers, and do resistance 
measurements of the modified installation to verify resistance is 
within the limits specified in the Accomplishment Instructions of 
Boeing Service Bulletin 777-55A0010, Revision 1, dated April 17, 
2001. Do the actions in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-55A0010, Revision 1, 
dated April 17, 2001.

    Note 1 to paragraph (i)(1) of this AD:  AD 2012-08-13, Amendment 
39-17030 (77 FR 24357, April 24, 2012), refers to Boeing Service 
Bulletin 777-55A0010, Revision 1, dated April 17, 2001, as the 
appropriate source of service information for accomplishing the 
actions specified in paragraph (h) of AD 2012-08-13.

    (2) For Group 1 and Group 2 airplanes, as identified in Boeing 
Service Bulletin 777-27A0078, Revision 1, dated April 1, 2013: Prior 
to or concurrently with accomplishing the actions required by 
paragraph (g) of this AD, replace certain single-tabbed bonding 
brackets in the airplane empennage with two-tabbed bonding brackets, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-55A0014, Revision 1, dated April 1, 2010.

    Note 2 to paragraph (i)(2) of this AD: AD 2012-08-13, Amendment 
39-17030 (77 FR 24357, April 24, 2012), refers to Boeing Service 
Bulletin 777-55A0014, Revision 1, dated April 1, 2010, as the 
appropriate source of service information for accomplishing the 
actions specified in paragraph (g) of AD 2012-08-13.

(j) Exceptions to Service Information

    (1) Where Boeing Service Bulletin 777-27A0078, Revision 1, dated 
April 1, 2013, specifies a compliance time after the ``Original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) The ``Condition'' column in paragraph 1.E., ``Compliance,'' 
of Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1, 
2013, refers to a condition as of the ``Original Issue date of this 
service bulletin.'' This AD applies to the corresponding condition 
as of the effective date of this AD.
    (3) If any corrosion damage is found during any inspection 
required by this AD, and Boeing Service Bulletin 777-27A0078, 
Revision 1, dated April 1, 2013, specifies to contact Boeing for 
appropriate action: Before further flight, repair the corrosion 
damage using a method approved in accordance with the procedures 
specified in paragraph (l) of this AD.

(k) Credit for Previous Actions

    (1) For Groups 1, 2, and 6 through 9, as identified in Boeing 
Alert Service Bulletin 777-27A0078, dated September 10, 2009: This 
paragraph provides credit for actions required by paragraph (g) of 
this AD and the actions specified in paragraph (h) of this AD, if 
those actions were performed before the effective date of this AD 
using Boeing Alert Service Bulletin 777-27A0078, dated September 10, 
2009, which is not incorporated by reference in this AD.
    (2) For Groups 3 through 5, as identified in Boeing Alert 
Service Bulletin 777-27A0078, dated September 10, 2009: This 
paragraph provides credit for actions required by paragraph (g) of 
this AD, except for the actions required for bonding jumpers 21 and 
22, if those actions were performed before the effective date of 
this AD using Boeing Alert Service Bulletin 777-27A0078, dated 
September 10, 2009, which is not incorporated by reference in this 
AD. If a check of the airplane's maintenance records positively 
determines that bonding jumpers 21 and 22 were inspected before the 
effective date of this AD in accordance with Option 1 of Work 
Package 3 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-27A0078, dated September 10, 2009, this paragraph 
provides credit for the actions required by paragraph (g) of this AD 
for the inspected bonding jumpers.
    (3) For Groups 3 through 5, as identified in Boeing Alert 
Service Bulletin 777-27A0078, dated September 10, 2009: This 
paragraph provides credit for actions specified in paragraph (h) of 
this AD, if those actions were performed before the effective date 
of this AD using Boeing Alert Service Bulletin 777-27A0078, dated 
September 10, 2009, which is not incorporated by reference in this 
AD; provided that a check of the airplane's maintenance records 
positively determines that bonding jumpers 21 and 22 were replaced 
in accordance with Option 2 of Work Package 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-27A0078, dated 
September 10, 2009, or were replaced using the new Category 2 fay 
sealed direct ground stud installation method.
    (4) This paragraph provides credit for actions required by 
paragraph (i)(1) of this AD if those actions were performed before 
the effective date of this AD using Boeing Alert Service Bulletin 
777-55A0010, dated October 26, 2000, which is not incorporated by 
reference in this AD.
    (5) This paragraph provides credit for actions required by 
paragraph (i)(2) of this AD if those actions were performed before 
the effective date of this AD using Boeing Alert Service Bulletin 
777-55A0014, dated May 8, 2008, which is not incorporated by 
reference in this AD.

(l) 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 (m) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes ODA that has been authorized by the 
Manager, Seattle ACO, to make those findings. For a repair method to 
be approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

[[Page 63907]]

(m) Related Information

    (1) For more information about this AD, Georgios Roussos, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, Seattle 
Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: 425-917-6482; fax: 425-917-6590; 
email: Georgios.Roussos@faa.gov.
    (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 review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on October 15, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25134 Filed 10-24-13; 8:45 am]
BILLING CODE 4910-13-P