Airworthiness Directives; The Boeing Company Airplanes, 23581-23586 [2016-09000]

Download as PDF Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 14 CFR part 25, and current systemsafety assessment policy and techniques, do not address potential security vulnerabilities by unauthorized access to airplane data busses and servers. Therefore, these special conditions are issued to ensure that the security, integrity, and availability of airplane systems are not compromised by certain wired or wireless electronic connections between airplane data busses and networks. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Applicability As discussed above, these special conditions are applicable to the Model GVII–G500 airplane. Should Gulfstream apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only a certain novel or unusual design feature on one model series of airplane. It is not a rule of general applicability. The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. asabaliauskas on DSK3SPTVN1PROD with RULES Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for electronic system- 16:23 Apr 21, 2016 Jkt 238001 Issued in Renton, Washington, on April 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–09335 Filed 4–21–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5592; Directorate Identifier 2016–NM–040–AD; Amendment 39–18488; AD 2016–08–12] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787–8 and 787– 9 airplanes powered by General Electric (GE) GEnx–1B engines. This AD requires revising the airplane flight manual (AFM) to provide the flight crew a revised fan ice removal procedure and a new associated mandatory flight crew briefing to reduce the likelihood of engine damage due to fan ice shedding. This AD also removes certain dispatch relief. For airplanes with certain engines, this AD also requires reworking or replacing at least one engine. This AD SUMMARY: List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: VerDate Sep<11>2014 security protection from unauthorized external access on the Gulfstream Aerospace Corporation Model GVII– G500 airplane. 1. The applicant must ensure that the airplane electronic systems are protected from access by unauthorized sources external to the airplane, including those possibly caused by maintenance activity. 2. The applicant must ensure that electronic system-security threats are identified and assessed, and that effective electronic system-security protection strategies are implemented to protect the airplane from all adverse impacts on safety, functionality, and continued airworthiness. 3. The applicant must establish appropriate procedures to allow the operator to ensure that continued airworthiness of the airplane is maintained, including all post-typecertification modifications that may have an impact on the approved electronic system-security safeguards. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 23581 was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent susceptibility to heavy fan blade rubs, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines. DATES: This AD is effective May 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 18, 2016 (81 FR 14704, March 18, 2016). We must receive comments on this AD by June 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 https://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: 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 final rule, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5592. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5592; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and E:\FR\FM\22APR1.SGM 22APR1 23582 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 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: Sue 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: Suzanne.Lucier@ faa.gov. SUPPLEMENTARY INFORMATION: asabaliauskas on DSK3SPTVN1PROD with RULES Discussion On March 14, 2016, we issued AD 2016–06–08, Amendment 39–18439 (81 FR 14704, March 18, 2016) (‘‘AD 2016– 06–08’’), for Boeing Model 787–8 and 787–9 airplanes powered by GE GEnx engines. AD 2016–06–08 was prompted by a report of a significant fan rub event involving a GEnx–1B Performance Improvement Program (PIP) 2 engine, apparently caused by partial fan ice shedding and a resulting fan imbalance that in turn caused substantial damage to the engine and an in-flight nonrestartable power loss. GEnx–1B PIP1 engines have model designators GEnx– 1B( )/P1. GEnx–1B PIP2 engines have model designators GEnx–1B( )/P2. We continue to investigate this issue with Boeing and GE; however, the engine damage appears to be a result of susceptibility to heavy fan blade rubs common to the GEnx–1B PIP2 engine. The other engine on the event airplane was an older design GEnx–1B PIP1 configuration that incurred expected wear and minor damage during the icing event and continued to operate normally. The event occurred in icing conditions at an altitude of 20,000 feet. The urgency of this issue stems from the safety concern over continued safe flight and landing for airplanes that are powered by two GEnx–1B PIP2 engines operating in a similar environment to the event airplane. In this case both GEnx–1B PIP2 engines may be similarly damaged and unable to be restarted in flight. The potential for common cause failure of both engines in flight is an urgent safety issue. AD 2016–06–08 requires revising the airplane flight manual (AFM) to provide the flight crew a new fan ice removal procedure to reduce the likelihood of engine damage due to fan ice shedding. AD 2016–06–08 also requires, for certain airplanes, reworking the fan stator module assembly on GEnx–1B PIP2 engines. Susceptibility to heavy fan blade rubs, if not corrected, could result in engine damage and a possible in-flight non- VerDate Sep<11>2014 16:23 Apr 21, 2016 Jkt 238001 restartable power loss of one or both engines. We are issuing this AD to correct the unsafe condition on these products. The preamble to AD 2016–06–08 explains that we regard the requirements ‘‘interim action’’ and were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this AD follows from that determination. Related Service Information Under 1 CFR Part 51 We reviewed GE GEnx–1B Service Bulletins 72–0309 R00, dated March 11, 2016; and 72–0314 R00, dated April 1, 2016. The service information describes procedures for reworking the fan stator module assembly on GEnx–1B PIP2 engines. 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 issuing 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. AD Requirements This AD requires revising the AFM to provide the flight crew a revised fan ice removal procedure and a new associated mandatory flight crew briefing to reduce the likelihood of engine damage due to fan ice shedding. This AD also removes certain dispatch relief. For an airplane with two GEnx–1B PIP2 engines having specified model and part numbers, this AD also requires reworking or replacing at least one engine. Interim Action We consider this AD interim action. This action addresses rework of a single engine on any airplane that has two GEnx–1B PIP2 engines having certain model and part numbers. We may consider issuing further rulemaking to require rework of the remainder of the GEnx–1B PIP2 engines in this fleet. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because susceptibility to heavy fan blade rubs could result in engine damage and a possible in-flight non- PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 restartable power loss of one or both engines. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Explanation of Compliance Times The FAA has evaluated the safety risk associated with this condition and has determined that in the interest of safety it is necessary to mandate three actions: • Revise the Boeing Model 787 AFM to provide the flight crew a revised fan ice removal procedure and a new daily flight crew briefing on the existing engine ice shed procedure. The compliance time is 7 days. • Removes certain dispatch relief, effective within 7 days. • Rework or replacement of at least one engine, for airplanes with two GEnx–1B PIP2 engines. The compliance time is about 150 calendar days after issuance of this AD. Boeing and the engine manufacturer, GE, have developed a maintenance plan to support this compliance schedule. The FAA has determined that allowing for notice and public comment through a notice of proposed rulemaking (NPRM) prior to mandating these actions is neither practicable nor in the public interest. Recognizing the urgency of this safety issue, this AD represents a compressed schedule to rework a large number of airplanes located around the world. Both specialized tooling and trained personnel are required on-site to perform the rework at various maintenance facilities around the world. To complete the work, 29 airlines will need to reallocate 176 airplanes from revenue service to maintenance in order to conduct the (on-wing) rework. The FAA has determined that 150 days is the minimum time to rework one engine per airplane on the entire fleet. Issuing an NPRM would require time to allow for public comment, and time for the FAA to consider and respond to those comments. As a result, the time allowed for the operators to perform the engine rework would be significantly reduced from 150 days, owing to the time that elapsed during the notice and comment period. As a result, the considerable reduction in allowable compliance time would require operators to perform the rework significantly out of sequence with the maintenance schedule plan. In some cases, airplanes could be grounded. Thus, the reduced compliance time could substantially disrupt certain operators. The FAA E:\FR\FM\22APR1.SGM 22APR1 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations considers that this is neither practicable nor in the public interest. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2016–5592 and Directorate Identifier 2016–NM–040–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// 23583 www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 43 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost AFM revisions ...... Rework ................. 1 work-hour × $85 per hour = $85 ............................................................ 40 work-hours × $85 per hour = $3,400 ................................................... asabaliauskas on DSK3SPTVN1PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Sep<11>2014 16:23 Apr 21, 2016 Jkt 238001 (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–08–12 The Boeing Company: Amendment 39–18488; Docket No. FAA–2016–5592; Directorate Identifier 2016–NM–040–AD. (a) Effective Date This AD is effective May 9, 2016. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 $0 0 Cost on U.S. operators $85 3,400 $3,655 146,200 (b) Affected ADs This AD affects AD 2016–06–08, Amendment 39–18439 (81 FR 14704, March 18, 2016) (‘‘AD 2016–06–08’’). (c) Applicability This AD applies to The Boeing Company Model 787–8 and 787–9 airplanes, certificated in any category, powered by General Electric (GE) GEnx–1B engines. (d) Subject Air Transport Association (ATA) of America Code 72, engines. (e) Unsafe Condition This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent susceptibility to heavy fan blade rubs, which could result in engine damage and a possible in-flight nonrestartable power loss of one or both engines. (f) Compliance ■ § 39.13 Cost per product Parts cost Comply with this AD within the compliance times specified, unless already done. (g) Airplane Flight Manual (AFM) Revision: Certificate Limitations Within 7 days after the effective date of this AD, revise the Certificate Limitations chapter of the applicable Boeing 787 AFM to include the statement provided in figure 1 to paragraph (g) of this AD. This may be done by inserting a copy of this AD into the AFM. Once accomplished, the AFM revision required by this paragraph terminates the requirements of paragraph (g) of AD 2016– 06–08, and the AFM revision required by paragraph (g) of AD 2016–06–08 must be removed from the AFM. E:\FR\FM\22APR1.SGM 22APR1 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations (h) AFM Revision: Operating Procedures asabaliauskas on DSK3SPTVN1PROD with RULES Within 7 days after the effective date of this AD, revise the Operating Procedures chapter of the Boeing 787 AFM to include the VerDate Sep<11>2014 16:23 Apr 21, 2016 Jkt 238001 statement provided in figure 2 to paragraph (h) of this AD. This may be done by inserting a copy of this AD into the AFM. Once accomplished, the AFM revision required by this AD terminates the requirements of PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 paragraph (h) of AD 2016–06–08, and the AFM revision required by paragraph (h) of AD 2016–06–08 must be removed from the AFM. BILLING CODE 4910–13–P E:\FR\FM\22APR1.SGM 22APR1 ER22AP16.036</GPH> 23584 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 23585 Figure 2 to Paragraph (h) of this AD Cold Weather Operations Fan Ice Removal Procedure (required by AD 2016-08-12) This procedure is required when in icing conditions above 12,500 feet MSL by the Engine Operational Limits Cold Weather Operations Fan Ice Removal limitation contained in the Certificate Limitations chapter of this manual. The language below shall not be modified. When an EAI EICAS indication is shown with N1 settings below 85%, or when fan icing is suspected due to high engine vibration, the fan blades must be cleared of any ice. Do the following procedure every 5 minutes on both engines, one engine at a time: Increase to a minimum of 85% N1 momentarily, then resume normal operation. Fan Ice Removal Procedure briefing (required by AD 2016-0812) The following briefing is important to ensure the flightcrew understands the importance of complying with the revised Fan Ice Removal procedure. This is also necessary to remind the crew that they will need to monitor, and react to an indication not normally used for any crew action but now requires timely, mandatory crew actions. The briefing must include the following items: • Whenever airborne above 12,500 feet MSL and either or both Engine Anti Ice (EAI) EICAS indication show and N1 is below 85%: 1. Immediately start a timer. 2. At 5-minute intervals accelerate each engine to at least 85% N1 momentarily, one engine at a time. 3. Continue this procedure as long as the EAI indication remains shown. • Perform the "Fan Ice Removal" procedure any time fan ice is suspected due to high engine vibrations. BILLING CODE 4910–13–C (i) Removal of Certain Dispatch Relief As of 7 days after the effective date of this AD: Notwithstanding the provisions of the operator’s minimum equipment list (MEL), VerDate Sep<11>2014 16:23 Apr 21, 2016 Jkt 238001 dispatch of an airplane is prohibited unless the equipment specified in paragraph (i)(1) and (i)(2) is operational. (1) At least one Engine Anti-Ice (EAI) Indication. (2) At least one Ice Detector. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 (j) Engine Rework or Replacement For an airplane powered by two engines having any model number GEnx–1B64/P2, –1B67/P2, –1B70/P2, –1B70C/P2, –1B70/75/ P2, or –1B74/75/P2, and any GEnx engine E:\FR\FM\22APR1.SGM 22APR1 ER22AP16.037</GPH> asabaliauskas on DSK3SPTVN1PROD with RULES 4. IfEAI indicator(s) blank before the 5-minute interval, perform a fan ice clearance procedure per step 2 above, then resume normal operation. 23586 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations assembly part number 2447M10G01 or 2447M10G02: Before October 1, 2016, do the actions specified by paragraph (j)(1) or (j)(2) of this AD. (1) Rework at least one engine in accordance with paragraph 3.B. or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016; or paragraph 3.B. or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0314 R00, dated April 1, 2016. Although GE GEnx Service Bulletins GEnx–1B 72–0314 R00, dated April 1, 2016; and GEnx–1B 72–0309 R00, dated March 11, 2016; specify submitting certain tip clearance measurements to GE, no report is required by this AD. (2) Remove at least one engine and replace with an engine that is eligible for installation that is not identified in the introductory text to paragraph (j) of this AD. (k) 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 (l) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, 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. asabaliauskas on DSK3SPTVN1PROD with RULES (l) Related Information For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425– 917–6590; email: Suzanne.Lucier@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on May 9, 2016. (i) GE GEnx–1B Service Bulletin 72–0314 R00, dated April 1, 2016. (ii) Reserved. VerDate Sep<11>2014 16:23 Apr 21, 2016 Jkt 238001 (4) The following service information was approved for IBR on March 18, 2016 (81 FR 14704, March 18, 2016). (i) GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016. (ii) Reserved. (5) For service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com. (6) You may view this 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on April 7, 2016. Ann C. Mollica, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. Issued in Renton, Washington, on April 12, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–09000 Filed 4–21–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2965; Directorate Identifier 2014–NM–227–AD; Amendment 39–18487; AD 2016–08–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–17– 13, which applied to certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. For certain airplanes, AD 2012–17–13 required using redefined flight cycle counts; determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made of 7079 aluminum, if necessary. For all SUMMARY: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 airplanes, AD 2012–17–13 required inspecting certain structurally significant items, and repairing discrepancies if necessary. This new AD adds a requirement to replace all chord segments made of 7079 aluminum with new, improved chord segments made of 7075 aluminum. This AD was prompted by a determination that all chord segments made of 7079 aluminum must be replaced with new, improved chord segments made of 7075 aluminum. We are issuing this AD to detect and correct stress corrosion and potential early fatigue cracking in the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer. DATES: This AD is effective May 27, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 27, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of October 16, 2012 (77 FR 55681, September 11, 2012). ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800– 0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2965. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2965; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. E:\FR\FM\22APR1.SGM 22APR1

Agencies

[Federal Register Volume 81, Number 78 (Friday, April 22, 2016)]
[Rules and Regulations]
[Pages 23581-23586]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09000]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5592; Directorate Identifier 2016-NM-040-AD; 
Amendment 39-18488; AD 2016-08-12]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for The 
Boeing Company Model 787-8 and 787-9 airplanes powered by General 
Electric (GE) GEnx-1B engines. This AD requires revising the airplane 
flight manual (AFM) to provide the flight crew a revised fan ice 
removal procedure and a new associated mandatory flight crew briefing 
to reduce the likelihood of engine damage due to fan ice shedding. This 
AD also removes certain dispatch relief. For airplanes with certain 
engines, this AD also requires reworking or replacing at least one 
engine. This AD was prompted by a recent engine fan blade rub event 
that caused an in-flight non-restartable power loss. We are issuing 
this AD to prevent susceptibility to heavy fan blade rubs, which could 
result in engine damage and a possible in-flight non-restartable power 
loss of one or both engines.

DATES: This AD is effective May 9, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 9, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
18, 2016 (81 FR 14704, March 18, 2016).
    We must receive comments on this AD by June 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 https://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: 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 final rule, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
aviation.fleetsupport@ge.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 https://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-5592.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5592; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and

[[Page 23582]]

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: Sue 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: Suzanne.Lucier@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On March 14, 2016, we issued AD 2016-06-08, Amendment 39-18439 (81 
FR 14704, March 18, 2016) (``AD 2016-06-08''), for Boeing Model 787-8 
and 787-9 airplanes powered by GE GEnx engines. AD 2016-06-08 was 
prompted by a report of a significant fan rub event involving a GEnx-1B 
Performance Improvement Program (PIP) 2 engine, apparently caused by 
partial fan ice shedding and a resulting fan imbalance that in turn 
caused substantial damage to the engine and an in-flight non-
restartable power loss. GEnx-1B PIP1 engines have model designators 
GEnx-1B( )/P1. GEnx-1B PIP2 engines have model designators GEnx-1B( )/
P2.
    We continue to investigate this issue with Boeing and GE; however, 
the engine damage appears to be a result of susceptibility to heavy fan 
blade rubs common to the GEnx-1B PIP2 engine. The other engine on the 
event airplane was an older design GEnx-1B PIP1 configuration that 
incurred expected wear and minor damage during the icing event and 
continued to operate normally. The event occurred in icing conditions 
at an altitude of 20,000 feet.
    The urgency of this issue stems from the safety concern over 
continued safe flight and landing for airplanes that are powered by two 
GEnx-1B PIP2 engines operating in a similar environment to the event 
airplane. In this case both GEnx-1B PIP2 engines may be similarly 
damaged and unable to be restarted in flight. The potential for common 
cause failure of both engines in flight is an urgent safety issue.
    AD 2016-06-08 requires revising the airplane flight manual (AFM) to 
provide the flight crew a new fan ice removal procedure to reduce the 
likelihood of engine damage due to fan ice shedding. AD 2016-06-08 also 
requires, for certain airplanes, reworking the fan stator module 
assembly on GEnx-1B PIP2 engines.
    Susceptibility to heavy fan blade rubs, if not corrected, could 
result in engine damage and a possible in-flight non-restartable power 
loss of one or both engines. We are issuing this AD to correct the 
unsafe condition on these products.
    The preamble to AD 2016-06-08 explains that we regard the 
requirements ``interim action'' and were considering further 
rulemaking. We now have determined that further rulemaking is indeed 
necessary, and this AD follows from that determination.

Related Service Information Under 1 CFR Part 51

    We reviewed GE GEnx-1B Service Bulletins 72-0309 R00, dated March 
11, 2016; and 72-0314 R00, dated April 1, 2016. The service information 
describes procedures for reworking the fan stator module assembly on 
GEnx-1B PIP2 engines. 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 issuing 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.

AD Requirements

    This AD requires revising the AFM to provide the flight crew a 
revised fan ice removal procedure and a new associated mandatory flight 
crew briefing to reduce the likelihood of engine damage due to fan ice 
shedding. This AD also removes certain dispatch relief. For an airplane 
with two GEnx-1B PIP2 engines having specified model and part numbers, 
this AD also requires reworking or replacing at least one engine.

Interim Action

    We consider this AD interim action. This action addresses rework of 
a single engine on any airplane that has two GEnx-1B PIP2 engines 
having certain model and part numbers. We may consider issuing further 
rulemaking to require rework of the remainder of the GEnx-1B PIP2 
engines in this fleet.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
susceptibility to heavy fan blade rubs could result in engine damage 
and a possible in-flight non-restartable power loss of one or both 
engines. Therefore, we find that notice and opportunity for prior 
public comment are impracticable and that good cause exists for making 
this amendment effective in less than 30 days.

Explanation of Compliance Times

    The FAA has evaluated the safety risk associated with this 
condition and has determined that in the interest of safety it is 
necessary to mandate three actions:
     Revise the Boeing Model 787 AFM to provide the flight crew 
a revised fan ice removal procedure and a new daily flight crew 
briefing on the existing engine ice shed procedure. The compliance time 
is 7 days.
     Removes certain dispatch relief, effective within 7 days.
     Rework or replacement of at least one engine, for 
airplanes with two GEnx-1B PIP2 engines. The compliance time is about 
150 calendar days after issuance of this AD. Boeing and the engine 
manufacturer, GE, have developed a maintenance plan to support this 
compliance schedule.
    The FAA has determined that allowing for notice and public comment 
through a notice of proposed rulemaking (NPRM) prior to mandating these 
actions is neither practicable nor in the public interest.
    Recognizing the urgency of this safety issue, this AD represents a 
compressed schedule to rework a large number of airplanes located 
around the world. Both specialized tooling and trained personnel are 
required on-site to perform the rework at various maintenance 
facilities around the world. To complete the work, 29 airlines will 
need to reallocate 176 airplanes from revenue service to maintenance in 
order to conduct the (on-wing) rework. The FAA has determined that 150 
days is the minimum time to rework one engine per airplane on the 
entire fleet.
    Issuing an NPRM would require time to allow for public comment, and 
time for the FAA to consider and respond to those comments. As a 
result, the time allowed for the operators to perform the engine rework 
would be significantly reduced from 150 days, owing to the time that 
elapsed during the notice and comment period.
    As a result, the considerable reduction in allowable compliance 
time would require operators to perform the rework significantly out of 
sequence with the maintenance schedule plan. In some cases, airplanes 
could be grounded. Thus, the reduced compliance time could 
substantially disrupt certain operators. The FAA

[[Page 23583]]

considers that this is neither practicable nor in the public interest.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2016-5592 and 
Directorate Identifier 2016-NM-040-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 43 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                         Labor cost              Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AFM revisions...................  1 work-hour x $85 per hour =                $0             $85          $3,655
                                   $85.
Rework..........................  40 work-hours x $85 per hour =               0           3,400         146,200
                                   $3,400.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-08-12 The Boeing Company: Amendment 39-18488; Docket No. FAA-
2016-5592; Directorate Identifier 2016-NM-040-AD.

(a) Effective Date

    This AD is effective May 9, 2016.

(b) Affected ADs

    This AD affects AD 2016-06-08, Amendment 39-18439 (81 FR 14704, 
March 18, 2016) (``AD 2016-06-08'').

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 and 787-9 
airplanes, certificated in any category, powered by General Electric 
(GE) GEnx-1B engines.

(d) Subject

    Air Transport Association (ATA) of America Code 72, engines.

(e) Unsafe Condition

    This AD was prompted by a recent engine fan blade rub event that 
caused an in-flight non-restartable power loss. We are issuing this 
AD to prevent susceptibility to heavy fan blade rubs, which could 
result in engine damage and a possible in-flight non-restartable 
power loss of one or both engines.

(f) Compliance

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

(g) Airplane Flight Manual (AFM) Revision: Certificate Limitations

    Within 7 days after the effective date of this AD, revise the 
Certificate Limitations chapter of the applicable Boeing 787 AFM to 
include the statement provided in figure 1 to paragraph (g) of this 
AD. This may be done by inserting a copy of this AD into the AFM. 
Once accomplished, the AFM revision required by this paragraph 
terminates the requirements of paragraph (g) of AD 2016-06-08, and 
the AFM revision required by paragraph (g) of AD 2016-06-08 must be 
removed from the AFM.

[[Page 23584]]

[GRAPHIC] [TIFF OMITTED] TR22AP16.036

(h) AFM Revision: Operating Procedures

    Within 7 days after the effective date of this AD, revise the 
Operating Procedures chapter of the Boeing 787 AFM to include the 
statement provided in figure 2 to paragraph (h) of this AD. This may 
be done by inserting a copy of this AD into the AFM. Once 
accomplished, the AFM revision required by this AD terminates the 
requirements of paragraph (h) of AD 2016-06-08, and the AFM revision 
required by paragraph (h) of AD 2016-06-08 must be removed from the 
AFM.
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[[Page 23585]]

[GRAPHIC] [TIFF OMITTED] TR22AP16.037

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(i) Removal of Certain Dispatch Relief

    As of 7 days after the effective date of this AD: 
Notwithstanding the provisions of the operator's minimum equipment 
list (MEL), dispatch of an airplane is prohibited unless the 
equipment specified in paragraph (i)(1) and (i)(2) is operational.
    (1) At least one Engine Anti-Ice (EAI) Indication.
    (2) At least one Ice Detector.

(j) Engine Rework or Replacement

    For an airplane powered by two engines having any model number 
GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, or -1B74/
75/P2, and any GEnx engine

[[Page 23586]]

assembly part number 2447M10G01 or 2447M10G02: Before October 1, 
2016, do the actions specified by paragraph (j)(1) or (j)(2) of this 
AD.
    (1) Rework at least one engine in accordance with paragraph 3.B. 
or 3.C. of the Accomplishment Instructions of GE GEnx-1B Service 
Bulletin 72-0309 R00, dated March 11, 2016; or paragraph 3.B. or 
3.C. of the Accomplishment Instructions of GE GEnx-1B Service 
Bulletin 72-0314 R00, dated April 1, 2016. Although GE GEnx Service 
Bulletins GEnx-1B 72-0314 R00, dated April 1, 2016; and GEnx-1B 72-
0309 R00, dated March 11, 2016; specify submitting certain tip 
clearance measurements to GE, no report is required by this AD.
    (2) Remove at least one engine and replace with an engine that 
is eligible for installation that is not identified in the 
introductory text to paragraph (j) of this AD.

(k) 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 (l) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, 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.

(l) Related Information

    For more information about this AD, contact Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6438; 
fax: 425-917-6590; email: Suzanne.Lucier@faa.gov.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 9, 2016.
    (i) GE GEnx-1B Service Bulletin 72-0314 R00, dated April 1, 
2016.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
March 18, 2016 (81 FR 14704, March 18, 2016).
    (i) GE GEnx-1B Service Bulletin 72-0309 R00, dated March 11, 
2016.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
aviation.fleetsupport@ge.com.
    (6) You may view this 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on April 7, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
    Issued in Renton, Washington, on April 12, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-09000 Filed 4-21-16; 8:45 am]
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