Airworthiness Directives; International Aero Engines AG Turbofan Engines, 22740-22743 [2019-10231]

Download as PDF 22740 Federal Register / Vol. 84, No. 97 / Monday, May 20, 2019 / Proposed Rules (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211–535E4–37, RB211–535E4–B–37, RB211–535E4–C–37, and RB–211–535E4–B– 75 model turbofan engines except those with fan blades that have all incorporated RollsRoyce Service Bulletin (SB) RB.211–72– C946, Revision 4, dated June 22, 2010 (or any earlier revision). (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by small cracks found in the low-pressure compressor (LPC) fan blade roots on the conclave root flank during an engine overhaul. We are issuing this AD to detect cracks in the LPC fan blade roots. The unsafe condition, if not addressed, could result in uncontained LPC fan blade release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For engine models being used in the flight profiles indicated in Table 1 to paragraph (g)(1) of this AD, perform initial and repetitive ultrasonic inspections of the affected fan blades in accordance with the Accomplishment Instructions, paragraphs 3.A., 3.B., and 3.C., of Rolls-Royce Alert NonModification Service Bulletin (NMSB) RB211–72–AC879, Revision 9, dated April 23, 2018, as follows: (i) Perform an initial ultrasonic root or surface wave inspection of each LPC fan blade before exceeding the inspection threshold as indicated in Table 1 to paragraph (g)(1) of this AD, or within 30 days after the effective date of this AD, whichever occurs later. (ii) Thereafter, perform a repetitive ultrasonic root or surface wave inspection of each LPC fan blade at intervals not to exceed engine flight cycles (EFCs) since the previous inspection using the applicable EFCs specified in Table 1 to paragraph (g)(1) of this AD. TABLE 1 TO PARAGRAPH (g)(1)—FLIGHT PROFILE INSPECTION INTERVALS Model Flight profile 535 E4–37 ............................. 535E4–C–37 .......................... 535E4–B–37 .......................... 535E4–B–75 .......................... 535E4–37 ............................... 535E4–B–37 .......................... B and G ......... F ..................... E and C ......... All ................... A .................... D .................... (2) For engine models that, after the effective date of this AD, change flight profiles, inspect the affected fan blades before exceeding the initial threshold of the new flight profile or reinspection interval, as applicable, or within 200 EFCs after changing flight profiles, whichever occurs later, without exceeding the previous flight profile initial inspection threshold or reinspection interval. (3) If, during any inspection required by paragraph (g)(1) or (2) of this AD, any crack is found in the affected fan blades that exceeds the criteria in the Accomplishment Instructions, paragraphs 3.A., 3.B., or 3.C., of Rolls-Royce Alert NMSB RB211–72–AC879, Revision 9, dated April 23, 2018, before the next flight, replace the LPC fan blade with a LPC fan blade eligible for installation. khammond on DSKBBV9HB2PROD with PROPOSALS (h) Optional Terminating Action Modification of any RR RB211–535E4–37, RB211–535E4–B–37, RB211–535E4–C–37, and RB–211–535E4–B–75 model turbofan engine in accordance with Rolls-Royce SB RB.211–72–C946, Revision 4, dated June 22, 2010, constitutes terminating action to this AD. (i) Credit for Previous Actions Any initial ultrasonic inspection accomplished before the effective date of this AD that uses Rolls-Royce NMSB No. RB.211– 72–C879, Revision 8, dated November 18, 2015, or earlier versions, meets the requirement of the initial inspection, as applicable. Any repetitive ultrasonic inspection accomplished before the effective date of this AD that uses RR NMSB No. RB.211–72–C879, Revision 8, dated November 18, 2015, or earlier versions, meets the requirement of that single repetitive inspection, as applicable. Further repetitive VerDate Sep<11>2014 16:03 May 17, 2019 Jkt 247001 Initial inspection threshold, EFCs since new 15,000 15,000 20,000 20,000 20,000 20,000 EFCs EFCs EFCs EFCs EFCs EFCs .......................... .......................... .......................... .......................... .......................... .......................... Reinspection interval; root probe method 850 EFCs ............................... 850 EFCs ............................... 1,200 EFCs ............................ 1,200 EFCs ............................ 1,400 EFCs ............................ 1,500 EFCs ............................ inspections, as mandated by paragraph (g) of this AD, are still required. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, 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 ECO Branch, send it to the attention of the person identified in paragraph (k)(1) of this AD. You may email your request to: ANE-AD-AMOC@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 (1) For more information about this AD, contact Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7735; fax: 781–238–7199; email: matthew.c.smith@faa.gov. (2) Refer to European Union Aviation Safety Agency (EASA) AD 2018–0202R1, dated September 25, 2018, for more information. You may examine the EASA AD in the AD docket on the internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2018–1034. (3) For RR service information identified in this AD, contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011– 44–1332–242424; fax: 011–44–1332–249936. You may view this referenced service information at the FAA, Engine & Propeller Standards Branch, 1200 District Avenue, PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Reinspection interval; surface wave probe method 700 EFCs. 700 EFCs. 1,000 EFCs. 1,000 EFCs. 1,150 EFCs. 1,200 EFCs. Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. Issued in Burlington, Massachusetts, on May 13, 2019. Robert J. Ganley, Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2019–10233 Filed 5–17–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0274; Product Identifier 2019–NE–07–AD] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2525–D5 and V2528–D5 model turbofan engines. This proposed AD was prompted by reports of cracked turbine exhaust cases (TECs). This proposed AD would require initial and repetitive inspections of the affected TEC and, SUMMARY: E:\FR\FM\20MYP1.SGM 20MYP1 22741 Federal Register / Vol. 84, No. 97 / Monday, May 20, 2019 / Proposed Rules depending on the results of the inspections, its replacement with a part eligible for installation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 5, 2019. 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact International Aero Engines AG, 400 Main Street, East Hartford, CT, 06118; phone: 800–565– 0140; email: help24@pw.utc.com; internet: https://fleetcare.pw.utc.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. 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–2019– 0274; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7157; fax: 781–238–7199; email: Martin.Adler@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2019–0274; Product Identifier 2019– NE–07–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM. investigation, IAE concluded that the cracks were due to corrosion pitting at a high-stress location. This condition, if not addressed, could result in failure of the TEC, engine separation, and loss of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed IAE Non-Modification Service Bulletin (NMSB) V2500–ENG– 72–0694, Revision No. 2, dated July 2, 2018. The NMSB describes procedures for detecting any cracks that develop along the rear mount stiffener rail on the TEC. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require initial and repetitive inspections of the affected TEC and, depending on the results of the inspections, its replacement with a part eligible for installation. Discussion Costs of Compliance We learned of cracks along the rear mount stiffener rails on three IAE V2525–D5 and V2528–D5 model turbofan engine TECs that were found during routine inspections. After an We estimate that this proposed AD affects 173 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspect turbine exhaust case .......................... 3 work-hours × $85 per hour = $255 ............. We estimate the following costs to do any necessary replacements that would Cost per product Parts cost be required based on the results of the proposed inspection. We have no way of $0 $255 Cost on U.S. operators $44,115 determining the number of aircraft that might need this replacement: khammond on DSKBBV9HB2PROD with PROPOSALS ON-CONDITION COSTS Action Labor cost Replace turbine exhaust case ...................................... 2 work-hours × $85 per hour = $170 ........................... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Sep<11>2014 16:03 May 17, 2019 Jkt 247001 section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Parts cost $725,000 Cost per product $725,170 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\20MYP1.SGM 20MYP1 22742 Federal Register / Vol. 84, No. 97 / Monday, May 20, 2019 / Proposed Rules 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. khammond on DSKBBV9HB2PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: VerDate Sep<11>2014 16:03 May 17, 2019 Jkt 247001 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): ■ International Aero Engines AG: Docket No. FAA–2019–0274; Product Identifier 2019–NE–07–AD. (a) Comments Due Date We must receive comments by July 5, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all International Aero Engines AG (IAE) V2525–D5 and V2528–D5 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine section. (e) Unsafe Condition This AD was prompted by reports of a cracked turbine exhaust case (TEC). We are issuing this AD to prevent failure of the TEC. The unsafe condition, if not addressed, could result in engine separation and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) At the next engine shop visit, but not later than 4,000 flight cycles (FCs) after the effective date of this AD, perform an eddy current inspection (ECI) and high sensitivity fluorescent penetrant inspection (FPI) of the TEC front and rear mount stiffener rails for cracking indications as follows: (i) Perform an ECI using the Accomplishment Instructions, Part I—For Engines Installed on Aircraft, paragraphs 2 through 19 inclusive, or Part II—For Engines Not Installed on Aircraft, paragraphs 2 through 18 inclusive, of IAE NonModification Service Bulletin (NMSB) V2500–ENG–72–0694, Revision No. 2, dated July 2, 2018 (‘‘IAE NMSB V2500–ENG–72– 0694’’). (ii) If a rejectable indication was found during the ECI, perform a local high sensitivity FPI to confirm a crack. (iii) If a rejectable indication was found during the ECI, but no crack(s) were confirmed using the local high sensitivity FPI, then clean, blend and repeat the ECI in the local area of the part. Use the Accomplishment Instructions, Part I—For Engines Installed on Aircraft, paragraph 20.A.(3), or Part II—For Engines Not Installed on Aircraft, paragraph 19.A.(3), of IAE NMSB V2500–ENG–72–0694 to perform the cleaning and blending. Use the PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Accomplishment Instructions, Part I—For Engines Installed on Aircraft, paragraphs 2 through 19 inclusive, or Part II—For Engines Not Installed on Aircraft, paragraphs 2 through 18 inclusive, of IAE NMSB V2500– ENG–72–0694 to perform the repeat ECI. (iv) If a rejectable indication was again found during the repeat ECI, then repeat the local high sensitivity FPI inspection in the local area of the part. If the local high sensitivity FPI does not confirm a crack, follow the instructions in the Accomplishment Instructions, Part I—For Engines Installed on Aircraft, paragraph 20.A.(5)(a), or Part II—For Engines Not Installed on Aircraft, paragraph 19.A.(5)(a), of IAE NMSB V2500–ENG–72–0694. (2) If no cracks were found, within 2,000 FCs since the last inspection, and thereafter, repeat the inspections of paragraphs (g)(1)(i) through (iv) of this AD. (3) If a crack was confirmed during the FPI and visual inspection required by paragraphs (g)(1)(ii) or (iv), before further flight, remove the part from service and replace with a part eligible for installation. (h) Credit for Previous Actions You may take credit for the inspections required by paragraph (g)(1) of this AD if you performed these inspections before the effective date of this AD, using IAE NMSB V2500–ENG–72–0694, Revision No. 1, dated February 7, 2018; or IAE NMSB V2500–ENG– 72–0694, Original Issue, dated January 5, 2018. (i) No Reporting Requirement No reporting requirement contained within the NMSB referenced in paragraph (g) of this AD is required by this AD. (j) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine case flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (k) Special Flight Permit A special flight permit is not permitted if the crack indication extends past the mount stiffener rail or if there is evidence of an FPI indication on the outer diameter of the case. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, 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 certification office, send it to the attention of the person identified in paragraph (m)(1) of this AD. You may email your request to: ANE-ADAMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager E:\FR\FM\20MYP1.SGM 20MYP1 Federal Register / Vol. 84, No. 97 / Monday, May 20, 2019 / Proposed Rules of the local flight standards district office/ certificate holding district office. 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to (m) Related Information https://www.regulations.gov. Follow the (1) For more information about this AD, instructions for submitting comments. contact Martin Adler, Aerospace Engineer, • Fax: 202–493–2251. ECO Branch, FAA, 1200 District Avenue, • Mail: U.S. Department of Burlington, MA 01803; phone: 781–238– Transportation, Docket Operations, M– 7157; fax: 781–238–7199; email: 30, West Building Ground Floor, Room Martin.Adler@faa.gov. W12–140, 1200 New Jersey Avenue SE, (2) For service information identified in this AD, contact International Aero Engines Washington, DC 20590. AG, 400 Main Street, East Hartford, CT • Hand Delivery: Deliver to Mail 06118; phone: 800–565–0140; email: help24@ address above between 9 a.m. and 5 pw.utc.com; internet: https:// p.m., Monday through Friday, except fleetcare.pw.utc.com. You may view this Federal holidays. referenced service information at the FAA, For service information identified in Engine and Propeller Standards Branch, 1200 this NPRM, contact International Aero District Avenue, Burlington, MA, 01803. For Engines AG, 400 Main Street, East information on the availability of this Hartford, CT 06118; phone: 800–565– material at the FAA, call 781–238–7759. 0140; email: help24@pw.utc.com; Issued in Burlington, Massachusetts, on internet: https://fleetcare.pw.utc.com. May 13, 2019. You may view this service information Robert J. Ganley, at the FAA, Engine and Propeller Manager, Engine and Propeller Standards Standards Branch, 1200 District Branch, Aircraft Certification Service. Avenue, Burlington, MA 01803. For [FR Doc. 2019–10231 Filed 5–17–19; 8:45 am] information on the availability of this BILLING CODE 4910–13–P material at the FAA, call 781–238–7759. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0268; Product Identifier 2019–NE–08–AD] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2500 model turbofan engines. This proposed AD was prompted by an inspection that determined that material anomalies exist in certain low-pressure turbine (LPT) stage 6 disks. This proposed AD would require removal from service of the affected LPT stage 6 disks and their replacement with a part eligible for installation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 5, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR khammond on DSKBBV9HB2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:03 May 17, 2019 Jkt 247001 You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0268; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Scott Hopper, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7154; fax: 781–238–7199; email: scott.hopper@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2019–0268; Product Identifier 2019– NE–08–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 22743 date and may amend this NPRM 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 NPRM. Discussion We received reports based on an inspection of material anomalies in certain LPT stage 6 disks. A manufacturer produced 18 V2500 LPT stage 6 disks from ATI, a supplier of material ingots, in late 2017. Six of those disks were rejected prior to shipment by MTU Aero Engines, a disk supplier, for melt defects at final inspection. The other twelve disks that initially passed inspection are now considered suspect. Four disk were recovered and quarantined prior to entering into service. This AD addresses the eight remaining affected disks. The material anomaly may reduce the life of the LPT stage 6 disks; therefore, all affected disks must be removed from service within the times specified in this AD. This condition, if not addressed, could result in failure of the LPT, uncontained release of the LPT stage 6 disk, damage to the engine, and damage to the airplane. Related Service Information We reviewed IAE Alert Service Bulletin (ASB) V2500–ENG–72–A0697, Revision No. 1, dated November 27, 2018. The ASB describes procedures for removal of the affected LPT stage 6 disks. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require removal and replacement of the affected LPT stage 6 disks. Costs of Compliance We estimate that this proposed AD affects 1 engine installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\20MYP1.SGM 20MYP1

Agencies

[Federal Register Volume 84, Number 97 (Monday, May 20, 2019)]
[Proposed Rules]
[Pages 22740-22743]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-10231]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0274; Product Identifier 2019-NE-07-AD]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
International Aero Engines AG (IAE) V2525-D5 and V2528-D5 model 
turbofan engines. This proposed AD was prompted by reports of cracked 
turbine exhaust cases (TECs). This proposed AD would require initial 
and repetitive inspections of the affected TEC and,

[[Page 22741]]

depending on the results of the inspections, its replacement with a 
part eligible for installation. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 5, 2019.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact 
International Aero Engines AG, 400 Main Street, East Hartford, CT, 
06118; phone: 800-565-0140; email: [email protected]; internet: https://fleetcare.pw.utc.com. You may view this service information at the FAA, 
Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7759.

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-2019-
0274; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7157; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0274; 
Product Identifier 2019-NE-07-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    We learned of cracks along the rear mount stiffener rails on three 
IAE V2525-D5 and V2528-D5 model turbofan engine TECs that were found 
during routine inspections. After an investigation, IAE concluded that 
the cracks were due to corrosion pitting at a high-stress location. 
This condition, if not addressed, could result in failure of the TEC, 
engine separation, and loss of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed IAE Non-Modification Service Bulletin (NMSB) V2500-ENG-
72-0694, Revision No. 2, dated July 2, 2018. The NMSB describes 
procedures for detecting any cracks that develop along the rear mount 
stiffener rail on the TEC. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require initial and repetitive inspections 
of the affected TEC and, depending on the results of the inspections, 
its replacement with a part eligible for installation.

Costs of Compliance

    We estimate that this proposed AD affects 173 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect turbine exhaust case..........  3 work-hours x $85 per                $0            $255         $44,115
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace turbine exhaust case..................  2 work-hours x $85 per hour =           $725,000        $725,170
                                                 $170.
----------------------------------------------------------------------------------------------------------------

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,

[[Page 22742]]

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

International Aero Engines AG: Docket No. FAA-2019-0274; Product 
Identifier 2019-NE-07-AD.

(a) Comments Due Date

    We must receive comments by July 5, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all International Aero Engines AG (IAE) 
V2525-D5 and V2528-D5 model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
section.

(e) Unsafe Condition

    This AD was prompted by reports of a cracked turbine exhaust 
case (TEC). We are issuing this AD to prevent failure of the TEC. 
The unsafe condition, if not addressed, could result in engine 
separation and loss of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) At the next engine shop visit, but not later than 4,000 
flight cycles (FCs) after the effective date of this AD, perform an 
eddy current inspection (ECI) and high sensitivity fluorescent 
penetrant inspection (FPI) of the TEC front and rear mount stiffener 
rails for cracking indications as follows:
    (i) Perform an ECI using the Accomplishment Instructions, Part 
I--For Engines Installed on Aircraft, paragraphs 2 through 19 
inclusive, or Part II--For Engines Not Installed on Aircraft, 
paragraphs 2 through 18 inclusive, of IAE Non-Modification Service 
Bulletin (NMSB) V2500-ENG-72-0694, Revision No. 2, dated July 2, 
2018 (``IAE NMSB V2500-ENG-72-0694'').
    (ii) If a rejectable indication was found during the ECI, 
perform a local high sensitivity FPI to confirm a crack.
    (iii) If a rejectable indication was found during the ECI, but 
no crack(s) were confirmed using the local high sensitivity FPI, 
then clean, blend and repeat the ECI in the local area of the part. 
Use the Accomplishment Instructions, Part I--For Engines Installed 
on Aircraft, paragraph 20.A.(3), or Part II--For Engines Not 
Installed on Aircraft, paragraph 19.A.(3), of IAE NMSB V2500-ENG-72-
0694 to perform the cleaning and blending. Use the Accomplishment 
Instructions, Part I--For Engines Installed on Aircraft, paragraphs 
2 through 19 inclusive, or Part II--For Engines Not Installed on 
Aircraft, paragraphs 2 through 18 inclusive, of IAE NMSB V2500-ENG-
72-0694 to perform the repeat ECI.
    (iv) If a rejectable indication was again found during the 
repeat ECI, then repeat the local high sensitivity FPI inspection in 
the local area of the part. If the local high sensitivity FPI does 
not confirm a crack, follow the instructions in the Accomplishment 
Instructions, Part I--For Engines Installed on Aircraft, paragraph 
20.A.(5)(a), or Part II--For Engines Not Installed on Aircraft, 
paragraph 19.A.(5)(a), of IAE NMSB V2500-ENG-72-0694.
    (2) If no cracks were found, within 2,000 FCs since the last 
inspection, and thereafter, repeat the inspections of paragraphs 
(g)(1)(i) through (iv) of this AD.
    (3) If a crack was confirmed during the FPI and visual 
inspection required by paragraphs (g)(1)(ii) or (iv), before further 
flight, remove the part from service and replace with a part 
eligible for installation.

(h) Credit for Previous Actions

    You may take credit for the inspections required by paragraph 
(g)(1) of this AD if you performed these inspections before the 
effective date of this AD, using IAE NMSB V2500-ENG-72-0694, 
Revision No. 1, dated February 7, 2018; or IAE NMSB V2500-ENG-72-
0694, Original Issue, dated January 5, 2018.

(i) No Reporting Requirement

    No reporting requirement contained within the NMSB referenced in 
paragraph (g) of this AD is required by this AD.

(j) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine case flanges, except that 
the separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(k) Special Flight Permit

    A special flight permit is not permitted if the crack indication 
extends past the mount stiffener rail or if there is evidence of an 
FPI indication on the outer diameter of the case.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, 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 
certification office, send it to the attention of the person 
identified in paragraph (m)(1) of this AD. You may email your 
request to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager

[[Page 22743]]

of the local flight standards district office/certificate holding 
district office.

(m) Related Information

    (1) For more information about this AD, contact Martin Adler, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: 
[email protected].
    (2) For service information identified in this AD, contact 
International Aero Engines AG, 400 Main Street, East Hartford, CT 
06118; phone: 800-565-0140; email: [email protected]; internet: 
https://fleetcare.pw.utc.com. You may view this referenced service 
information at the FAA, Engine and Propeller Standards Branch, 1200 
District Avenue, Burlington, MA, 01803. For information on the 
availability of this material at the FAA, call 781-238-7759.

    Issued in Burlington, Massachusetts, on May 13, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-10231 Filed 5-17-19; 8:45 am]
BILLING CODE 4910-13-P

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