| Page Range | 41208-41211 | |
| FR Document | 2016-14474 |
[Federal Register Volume 81, Number 122 (Friday, June 24, 2016)] [Rules and Regulations] [Pages 41208-41211] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-14474] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD; Amendment 39-18569; AD 2016-13-05] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This AD requires eddy current inspection (ECI) or ultrasonic inspection (USI) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. DATES: This AD is effective July 29, 2016. ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 7491; 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 Document 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: John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all GE GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. The NPRM published in the Federal Register on January 13, 2016 (81 FR 1582). The NPRM was prompted by an uncontained failure of the HPC stage 8-10 spool, leading to an airplane fire. The NPRM proposed to require ECIs or USIs of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (81 FR 1582, January 13, 2016) and the FAA's response to each comment. Support for the NPRM (81 FR 1582, January 13, 2016) The Air Line Pilots Association expressed support for the NPRM (81 FR 1582, January 13, 2016). Request To Change Applicability British Airways, United Airlines, and The Boeing Company commented that HPC stage 8-10 spool, part numbers (P/Ns) 1844M90G01 and 1844M90G02 are not required in the Applicability paragraph of this AD. They noted that the associated AD 2015-27-01, (81 FR 1291, January 12, 2016) and the precipitating event involved only HPC stage 8-10 spool, P/N 1694M80G04. We disagree. HPC stage 8-10 spool P/Ns 1844M90G01 and 1844M90G02 are susceptible to the same failure mode as HPC stage 8-10 spool, P/N 1694M80G04. However, we [[Page 41209]] acknowledge that the one-time inspection is not needed for the majority of HPC stage 8-10 spool P/Ns 1844M90G01 and 1844M90G02. Therefore, we revised paragraph (e)(1) of this AD to apply to only specific serial numbers (S/Ns) of P/Ns 1844M90G01 and 1844M90G02 for the one-time inspection. Request To Change Compliance Time British Airways requested that we clarify if a repetitive on-wing inspection is required. They reasoned that the service information lists the on-wing inspection as one time only. We disagree. Paragraph (e)(1) of this AD mandates that specific parts be inspected prior to a cycle limit. This initial inspection may be performed on wing using USI or at shop visit using ECI. Repetitive inspections prior to shop visit are not mandated, however we acknowledge that GE has commented that they should be performed. We did not change this AD. Request To Change Terminating Action GE requested that we remove the repetitive shop visit inspection from the Compliance section of this AD and instead mandate that the airworthiness limitations section (ALS) of the engine manual include the repetitive inspections. They also requested that the Summary section and Related Information section of this AD be revised to reflect this change. They reasoned that this will allow a terminating action for this AD. We disagree. At this time we do not feel that a change to the ALS is appropriate as root cause has not been determined. We did not change this AD. Request To Change Installation Prohibition GE requested that we clarify that the installation prohibition does not apply to new parts. They stated that new parts do not need to be inspected prior to installation. The inspections are only applicable to parts that have been used in service. We agree. We revised paragraph (f) of this AD to specify that inspections are only required for parts that have been used in service. Request To Change Service Information GE and British Airways requested that we revise the Related Service Information paragraph of this AD to remove the reference to Engine Manual, Chapter 72-00-31, Special Procedure 007 and add a reference to GE GE90 SB 72-1146. They reasoned that the Special Procedure is considered an additional inspection technique and the other inspection procedures listed provide full detection capability of defects in the area of concern. We disagree. The service information is not incorporated by reference in this AD and was previously included for information purposes only. However, to preclude any confusion on this point, we removed all service information from the Related Information section of this AD. Request To Change Applicability GE requested that we reduce the applicability for the initial inspection. GE has determined that an older manufacturing process may be a contributor to part failure and that all parts manufactured using this process should be inspected prior to shop visit. We agree. We revised the applicability of the initial inspection to include all HPC stage 8-10 spool, P/N 1694M80G04, and specific S/Ns of HPC stage 8-10 spool, P/Ns 1844M90G01 and 1844M90G02, that were manufactured using the older process. Request To Change Compliance Time GE has requested that the initial USI compliance time be reduced and to add repetitive inspections every 500 cycles until shop visit ECI for the parts manufactured using the older manufacturing process noted above. GE has determined that the smallest detectable flaw using USI with the compressor blades installed is larger than what was used in the prior analysis. We partially agree. We agree that the USI inspection is not as capable as what was used in the prior analysis. We also agree that a reduced threshold for initial inspection is appropriate. So, we reduced the initial inspection threshold in paragraph (e)(1) of this AD from 10,500 cycles to 9,000 cycles and removed USI as an option for the inspections in paragraph (e)(2) of this AD. We disagree with including the 500 cycle repetitive inspections; however, repetitive inspections would be a consideration for additional rulemaking. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (81 FR 1582, January 13, 2016) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (81 FR 1582, January 13, 2016). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Interim Action GE is determining the root cause for the unsafe condition identified in this AD. Once a root cause is identified, we will consider additional rulemaking. Costs of Compliance We estimate that this AD affects 54 engines installed on airplanes of U.S. registry. We also estimate that it will take about 7 hours per engine to comply with this AD. The average labor rate is $85 per hour. We estimate one part will fail inspection at a cost of $780,000. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $812,130. 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 [[Page 41210]] (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): 2016-13-05 General Electric Company: Amendment 39-18569; Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD. (a) Effective Date This AD is effective July 29, 2016. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) GE90-76B, GE90- 77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with a high- pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or 1844M90G02, installed. (d) Unsafe Condition This AD was prompted by an uncontained failure of the HPC stage 8-10 spool. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For HPC stage 8-10 spool, P/N 1694M80G04, all serial numbers (S/Ns), or HPC stage 8-10 spool, P/N 1844M90G01 or 1844M90G02, with a S/N listed in Figure 1 to paragraph (e) of this AD; perform an eddy current inspection (ECI) or ultrasonic inspection (USI) of the stage 8 aft web upper face, after reaching 8,000 cycles since new (CSN), but, before exceeding 9,000 CSN, or within 500 cycles in service after the effective date of this AD, whichever occurs later. Figure 1 to Paragraph (e)--HPC Stage 8-10 Spool S/Ns -------------------------------------------------------------------------------------------------------------------------------------------------------- -------------------------------------------------------------------------------------------------------------------------------------------------------- Part Nos. Serial Nos. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1844M90G01..................... GWN005MF GWNBK753 GWNBS077 GWNBS497 GWNBS724 -------------------------------------------------------------------------------------------------------------------------------------------------------- GWN005MG GWNBK754 GWNBS078 GWNBS499 GWNBS794 GWN0087M GWNBK841 GWNBS079 GWNBS500 GWNBS810 GWN0087N GWNBK842 GWNBS080 GWNBS501 GWNBS811 GWN00DGK GWNBK843 GWNBS081 GWNBS502 GWNBS812 GWN00DGL GWNBK844 GWNBS157 GWNBS609 GWNBS813 GWNBJ992 GWNBK952 GWNBS158 GWNBS610 GWNBS814 GWNBK667 GWNBK953 GWNBS159 GWNBS611 GWNBS910 GWNBK674 GWNBK954 GWNBS160 GWNBS612 GWNBS911 GWNBK675 GWNBK955 GWNBS266 GWNBS613 GWNBS912 GWNBK743 GWNBK956 GWNBS267 GWNBS614 GWNBS914 GWNBK744 GWNBK957 GWNBS268 GWNBS721 GWNBS915 GWNBK751 GWNBK958 GWNBS269 GWNBS722 GWNBS982 GWNBK752 GWNBK959 GWNBS270 GWNBS723 GWNBS983 -------------------------------------------------------------------------------------------------------------------------------------------------------- 1844M90G02..................... GWN00C2T GWN01C5N GWN02N8D GWN03RTM GWN04E21 GWN00C2V GWN01GE2 GWN02T3R GWN03RTP GWN04GHT GWN00G2N GWN01GE3 GWN02WGM GWN040RL GWN04GHW GWN00G2P GWN01GE4 GWN0311K GWN040RM GWN04GJ0 GWN00PFP GWN01GE6 GWN035PP GWN040RN GWN04JW6 GWN00PFR GWN01WH1 GWN038TD GWN040RP GWN04JW7 GWN00T2N GWN02688 GWN039TG GWN04202 GWN04JW8 GWN00YHV GWN02689 GWN03G2R GWN0435W GWN04L7K GWN0125G GWN0268A GWN03G2W GWN04360 GWN04L7L GWN0125H GWN02DP2 GWN03G30 GWN04361 GWN04MT7 GWN0166K GWN02DP3 GWN03JPC GWN04362 GWN04MT8 GWN01C5K GWN02F9F GWN03JPD GWN04ATG GWNBS984 GWN01C5L GWN02F9G GWN03N8P GWN04ATH ...................... GWN01C5M GWN02L9T GWN03N8R GWN04E20 ...................... -------------------------------------------------------------------------------------------------------------------------------------------------------- (2) For all HPC stage 8-10 spools, P/N 1694M80G04, 1844M90G01, or 1844M90G02, perform an ECI of the stage 8 aft web upper face of the HPC stage 8-10 spool at each shop visit. (3) Remove from service any HPC stage 8-10 spool that fails the inspection required by paragraphs (e)(1) or (e)(2) of this AD, and replace with a spool eligible for installation. (f) Installation Prohibition After the effective date of this AD, do not re-install into any engine, any HPC stage 8-10 spool, P/Ns 1694M80G04, 1844M90G01, or 1844M90G02, unless the spool has passed an ECI of the stage 8 aft web upper face as specified in paragraph (e)(1) or (e)(2) of this AD. (g) Definition For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance during which the compressor discharge pressure seal face is exposed. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (i) Related Information For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; [[Page 41211]] phone: 781-238-7756; fax: 781-238-7199; email: [email protected]. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on June 15, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-14474 Filed 6-23-16; 8:45 am] BILLING CODE 4910-13-P
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective July 29, 2016. | |
| Contact | John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 81 FR 41208 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |