Airworthiness Directives; The Boeing Company Airplanes, 14704-14707 [2016-06117]

Download as PDF 14704 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations (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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–06–06 Quest Aircraft Design, LLC: Amendment 39–18437; Docket No. FAA–2015–5318; Directorate Identifier 2015–CE–035–AD. (a) Effective Date This AD is effective April 22, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Quest Aircraft Design, LLC Model KODIAK 100 airplanes, all serial numbers 100–0001 through 100–0149, that are certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 2730; Elevator Control System. asabaliauskas on DSK3SPTVN1PROD with RULES (e) Unsafe Condition This AD was prompted by a report of limited control yoke movement due to cushion edging jammed in the elevator control anti-rotation guide slot. We are issuing this AD to prevent failure of the elevator control system, which could result in loss of control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspect Cushion Edging Before further flight April 22, 2016 (after the effective date of this AD) and repetitively thereafter at intervals not to exceed 50 hours time-in-service until the terminating action specified in paragraph (i) of this AD is done, inspect the cushion edging, part number (P/ N) M22529/2–3R–25, located on each side of VerDate Sep<11>2014 18:10 Mar 17, 2016 Jkt 238001 the elevator control anti-rotation guide slot, P/N 100–619–0008, for the pilot and co-pilot control yoke assemblies, following section 5.1 Cushion Edging Inspection of Quest Aircraft Company Field Service Instruction, Elevator Control System—Cushion Edging Inspection, Report No. FSI–105, Revision 00, not dated, as specified in Quest Aircraft KODIAK Mandatory Service Bulletin SB14– 07, dated August 26, 2014; and Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015. (h) Replace Cushion Edging If damage or wear is found during any inspection required in paragraph (g) of this AD, before further flight, replace the cushion edging following section 5.3 of Quest Aircraft Company Field Service Instruction, Elevator Control System—Cushion Edging Inspection, Report No. FSI–105, Revision 00, not dated, as specified in Quest Aircraft KODIAK Mandatory Service Bulletin SB14–07, dated August 26, 2014; and Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015. (i) Install Wear Pads (Terminating Action for the Repetitive Inspections) Within 1 year after April 22, 2016 (the effective date of this AD), remove the cushion edging, P/N M22529/2–3R–25, installed on the elevator control anti-rotation guide, and install wear pads, P/N 100–619–0037, on the elevator bearing assembly link arm following section 5. Instructions, including all subsections, of Quest Aircraft Field Service Instruction, Yoke Anti-Rotation Guide Wear Pad Upgrade, Report No. FSI–108, Revision 00, not dated, as specified in Quest Aircraft KODIAK 100 Recommended Service Bulletin SB15–01, dated March 26, 2015. Installing all four wear pads on the pilot and co-pilot arms of the elevator bearing assemblies terminates the repetitive inspections required in paragraph (g) of this AD. (j) 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 (k) 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. (k) Related Information For more information about this AD, contact David Herron, Aerospace Engineer, Seattle ACO, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; phone: (425) 917–6469; fax: (425) 917–6591; email: david.herron@faa.gov. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015. (ii) Quest Aircraft KODIAK Mandatory Service Bulletin SB14–07, dated August 26, 2014. (iii) Quest Aircraft Company Field Service Instruction, Elevator Control System— Cushion Edging Inspection, Report No. FSI– 105, Revision 00, not dated. (iv) Quest Aircraft KODIAK 100 Recommended Service Bulletin SB15–01, dated March 26, 2015. (v) Quest Aircraft Field Service Instruction, Yoke Anti-Rotation Guide Wear Pad Upgrade, Report No. FSI–108, Revision 00, not dated. (3) For Quest Aircraft Design, LLC service information identified in this AD, contact Quest Aircraft Design, LLC, 1200 Turbine Drive, Sandpoint, Idaho 83864; telephone: (208) 263–1111; toll free: (866) 263–1112; email: CustomerService@QuestAircraft.com; Internet: www.questaircraft.com. (4) You may view this service information at 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. In addition, you can access this service information on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015–5318. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on March 10, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–05898 Filed 3–17–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–4227; Directorate Identifier 2016–NM–025–AD; Amendment 39–18439; AD 2016–06–08] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations Final rule; request for comments. ACTION: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787–8 and 787– 9 airplanes powered by GE GEnx engines. This AD requires revising the airplane flight manual to provide the flight crew a new fan ice removal procedure to reduce the likelihood of engine damage due to fan ice shedding. This AD also requires, for certain airplanes, reworking the fan stator module assembly on GE GEnx–1B Performance Improvement Program (PIP) 2 engines. 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 reduced fan tip clearance, 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 March 18, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 18, 2016. We must receive comments on this AD by May 2, 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: geae.aoc@ 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– 4227. asabaliauskas on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 18:10 Mar 17, 2016 Jkt 238001 14705 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– 4227; 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 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: and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Discussion We received a report of a significant GE GEnx–1B PIP2 engine fan rub event, 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. We continue to investigate this issue with Boeing and GE; however, the engine damage appears to be a result of reduced fan tip clearances common to the GEnx–1B PIP2 engine. The other engine on the event airplane was a 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. Reduced fan tip clearance, 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. 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 reduced fan tip clearance 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. Related Service Information Under 1 CFR Part 51 We reviewed GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016, which 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 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 AD Requirements This AD requires accomplishing the actions specified in the GE service information described previously. This AD also 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. Interim Action We consider this AD interim action. The engine manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking. FAA’s Justification and Determination of the Effective Date 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–2016–4227 and Directorate Identifier 2016–NM–025–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. E:\FR\FM\18MRR1.SGM 18MRR1 14706 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations Costs of Compliance the following costs to comply with this AD: We estimate that this AD affects 34 airplanes of U.S. registry. We estimate ESTIMATED COSTS Action Labor cost AFM revision .............. Rework ....................... 1 work-hour × $85 per hour = $85 ........... 40 work-hours × $85 per hour = $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. asabaliauskas on DSK3SPTVN1PROD with RULES 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. VerDate Sep<11>2014 18:10 Mar 17, 2016 Jkt 238001 Cost per product Parts cost $0 0 $85 3,400 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–06–08 The Boeing Company: Amendment 39–18439; Docket No. FAA–2016–4227; Directorate Identifier 2016–NM–025–AD. (a) Effective Date This AD is effective March 18, 2016. (b) Affected ADs None. (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 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 reduced fan tip clearance, 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) Revision of Airplane Flight Manual (AFM): 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. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Cost on U.S. operators $2,890. 3,400 (1 affected airplane). FIGURE 1 TO PARAGRAPH (g) OF THIS AD Engine Operational Limits Cold Weather Operations Fan Ice Removal In order to avoid possible fan damage and engine failure, when in icing conditions above 12,500 feet MSL, the flight crew must comply with the Cold Weather Operations Additional Fan Ice Removal procedure contained in the Operating Procedures chapter of this manual. (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. FIGURE 2 TO PARAGRAPH (h) OF THIS AD Cold Weather Operations Additional Fan Ice Removal Procedure 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. During flight in icing conditions (EAI EICAS indication showing) 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. (i) Rework For airplanes with two engines with engine serial numbers listed in paragraph 1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016: On or before March 25, 2016, rework the fan stator module assembly of one of the engines, in accordance with paragraphs 3.A.(1)(b), 3.B., or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016. (j) Parts Installation Limitation As of March 25, 2016, no person may operate an airplane that has two engines with engine serial numbers listed in paragraph E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016, unless at least one engine has been reworked in accordance with paragraph 3.A.(1)(b), 3.B., or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016. (k) Reporting Provisions Although GE GEnx Service Bulletin GEnx– 1B 72–0309 R00, dated March 11, 2016, specifies reporting certain tip clearance measurements to GE, this AD does not require any report. (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 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 (m) 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. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016. (ii) Reserved. (3) 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: geae.aoc@ge.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For VerDate Sep<11>2014 18:10 Mar 17, 2016 Jkt 238001 information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 14, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–06117 Filed 3–17–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–AD; Amendment 39–18438; AD 2016–06–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2006–22– 15 for all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747– 300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. AD 2006–22–15 required repetitive inspections for cracking of certain panel webs and stiffeners of the nose wheel well (NWW), and corrective actions if necessary; and replacement of certain panels with new panels, which terminates the repetitive inspections. This new AD reduces a compliance time and adds certain inspections and an applicable repair. This AD was prompted by multiple reports of fatigue cracking in the NWW top panel and side panel webs and stiffeners. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage. SUMMARY: This AD is effective April 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 22, 2016. DATES: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 14707 For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0774. ADDRESSES: 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–2014– 0774; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: Bill.Ashforth@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006) (‘‘AD 2006–22–15’’). AD 2006–22–15 applied to all The Boeing Company Model 747– 100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. The SNPRM published in the Federal Register on September 18, 2015 (80 FR 56407) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on November 17, 2014 (79 FR 68388) (‘‘the NPRM’’). The NPRM proposed to continue to require repetitive inspections for cracking of E:\FR\FM\18MRR1.SGM 18MRR1

Agencies

[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14704-14707]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4227; Directorate Identifier 2016-NM-025-AD; 
Amendment 39-18439; AD 2016-06-08]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 14705]]


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 GE GEnx 
engines. This AD requires revising the airplane flight manual to 
provide the flight crew a new fan ice removal procedure to reduce the 
likelihood of engine damage due to fan ice shedding. This AD also 
requires, for certain airplanes, reworking the fan stator module 
assembly on GE GEnx-1B Performance Improvement Program (PIP) 2 engines. 
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 reduced fan tip clearance, 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 March 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 18, 
2016.
    We must receive comments on this AD by May 2, 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: geae.aoc@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-2016-4227.

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-
4227; 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 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

    We received a report of a significant GE GEnx-1B PIP2 engine fan 
rub event, 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. We continue to 
investigate this issue with Boeing and GE; however, the engine damage 
appears to be a result of reduced fan tip clearances common to the 
GEnx-1B PIP2 engine. The other engine on the event airplane was a 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. Reduced fan 
tip clearance, 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.

Related Service Information Under 1 CFR Part 51

    We reviewed GE GEnx-1B Service Bulletin 72-0309 R00, dated March 
11, 2016, which 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 accomplishing the actions specified in the GE 
service information described previously. This AD also 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.

Interim Action

    We consider this AD interim action. The engine manufacturer is 
currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we may consider additional rulemaking.

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 
reduced fan tip clearance 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.

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-2016-4227 and 
Directorate Identifier 2016-NM-025-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.

[[Page 14706]]

Costs of Compliance

    We estimate that this AD affects 34 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 revision.....................  1 work-hour x $85 per               $0             $85  $2,890.
                                    hour = $85.
Rework...........................  40 work-hours x $85                  0           3,400  3,400 (1 affected
                                    per hour = $3,400.                                      airplane).
----------------------------------------------------------------------------------------------------------------

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):

2016-06-08 The Boeing Company: Amendment 39-18439; Docket No. FAA-
2016-4227; Directorate Identifier 2016-NM-025-AD.

(a) Effective Date

    This AD is effective March 18, 2016.

(b) Affected ADs

    None.

(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 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 reduced fan tip clearance, 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) Revision of Airplane Flight Manual (AFM): 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.

                  Figure 1 to Paragraph (g) of This AD
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
Engine Operational Limits
 
Cold Weather Operations Fan Ice Removal
 
In order to avoid possible fan damage and engine failure, when in icing
 conditions above 12,500 feet MSL, the flight crew must comply with the
 Cold Weather Operations Additional Fan Ice Removal procedure contained
 in the Operating Procedures chapter of this manual.
------------------------------------------------------------------------

(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.

                  Figure 2 to Paragraph (h) of This AD
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
Cold Weather Operations
Additional Fan Ice Removal Procedure
 
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.
 
During flight in icing conditions (EAI EICAS indication showing) 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.
------------------------------------------------------------------------

(i) Rework

    For airplanes with two engines with engine serial numbers listed 
in paragraph 1.A., ``Effectivity,'' of GE GEnx-1B Service Bulletin 
72-0309 R00, dated March 11, 2016: On or before March 25, 2016, 
rework the fan stator module assembly of one of the engines, in 
accordance with paragraphs 3.A.(1)(b), 3.B., or 3.C. of the 
Accomplishment Instructions of GE GEnx-1B Service Bulletin 72-0309 
R00, dated March 11, 2016.

(j) Parts Installation Limitation

    As of March 25, 2016, no person may operate an airplane that has 
two engines with engine serial numbers listed in paragraph

[[Page 14707]]

1.A., ``Effectivity,'' of GE GEnx-1B Service Bulletin 72-0309 R00, 
dated March 11, 2016, unless at least one engine has been reworked 
in accordance with paragraph 3.A.(1)(b), 3.B., or 3.C. of the 
Accomplishment Instructions of GE GEnx-1B Service Bulletin 72-0309 
R00, dated March 11, 2016.

(k) Reporting Provisions

    Although GE GEnx Service Bulletin GEnx-1B 72-0309 R00, dated 
March 11, 2016, specifies reporting certain tip clearance 
measurements to GE, this AD does not require any report.

(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 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.

(m) 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.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) GE GEnx-1B Service Bulletin 72-0309 R00, dated March 11, 
2016.
    (ii) Reserved.
    (3) 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: geae.aoc@ge.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on March 14, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-06117 Filed 3-17-16; 8:45 am]
 BILLING CODE 4910-13-P
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