Airworthiness Directives; Pratt & Whitney Division Turbofan Engines, 77384-77385 [2014-30283]

Download as PDF 77384 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. This parts installation prohibition ends the parts installation prohibition specified in paragraph (o) of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), for the airplanes identified in paragraph (c) of this AD. (m) Exceptions to Service Information Specifications Where Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, specifies a post-repair detailed inspection in accordance with Table 9, this AD requires a detailed inspection in accordance with paragraph 3.B., Part 2, of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (n) 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 (o) 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 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. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. mstockstill on DSK4VPTVN1PROD with RULES (o) Related Information For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov. (p) 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) Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 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. (4) You may view this service information at 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/ibrlocations.html. www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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. [FR Doc. 2014–30132 Filed 12–23–14; 8:45 am] JoAnn Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7105; fax: 781–238– 7199; email: jo-ann.theriault@faa.gov. BILLING CODE 4910–13–P SUPPLEMENTARY INFORMATION: Issued in Renton, Washington, on November 19, 2014. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0072; Directorate Identifier 2013–NE–04–AD; Amendment 39– 18017; AD 2014–23–01] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Division Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engine models with certain second-stage high-pressure turbine (HPT) air seals installed. The time required to perform the initial eddy current inspection (ECI) in the Compliance section is incorrect. This document corrects that error. In all other respects, the original document remains the same. DATES: This final rule is effective on December 26, 2014. The effective date of AD 2014–23–01, Amendment 39–18017 (79 FR 69369, November 21, 2014) remains December 26, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 17, 2013 (78 FR 49111, August 13, 2013). ADDRESSES: You may examine the AD docket on the Internet at https:// SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: AD 2014– 23–01, Amendment 39–18017 (79 FR 69369, November 21, 2014), requires initial and repetitive inspections for cracks in second-stage HPT air seals, the removal of the mating hardware if the second-stage HPT air seal is found with a through-crack, and a mandatory terminating action for all PW PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engine models with certain second-stage HPT air seals installed. As published, the time required to perform the initial ECI in the Compliance section is incorrect. AD 2014–23–01, paragraph (e)(2)(i), requires an initial ECI for cracks within 1,000 cycles-in-service after September 17, 2013, or before further flight, whichever occurs later. That compliance time is more restrictive than intended and will likely ground airplanes. The intent was to require an initial ECI for cracks before reaching 2,200 cycles since new, or within 1,000 cycles-in-service after September 17, 2013, or before further flight, whichever occurs later. No other part of the preamble or regulatory information has been changed. The effective date of AD 2014–23–01 remains December 26, 2014. Correction of Regulatory Text § 39.13 [Corrected] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–15–09, Amendment 39–17525 (78 FR 49111, August 13, 2013), and adding the following new AD: ■ 2014–23–01 Pratt & Whitney Division: Amendment 39–18017; Docket No. FAA–2013–0072; Directorate Identifier 2013–NE–04–AD. E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations (a) Effective Date This AD is effective December 26, 2014. (b) Affected ADs This AD supersedes AD 2013–15–09, Amendment 39–17525 (78 FR 49111, August 13, 2013). (c) Applicability This AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090– 3 turbofan engine models with second-stage high-pressure turbine (HPT) air seal, part number (P/N) 54L041, 50L960, or 50L976, installed. (d) Unsafe Condition This AD was prompted by additional reports of cracking in the second-stage HPT air seal. We are issuing this AD to prevent failure of the second-stage HPT air seal, which could lead to uncontained engine failure and damage to the airplane. mstockstill on DSK4VPTVN1PROD with RULES (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) At the next piece-part exposure after the effective date of this AD, do the following: (i) Remove from service second-stage HPT air seals, P/Ns 50L960, 50L976, and 54L041. (ii) Perform a fluorescent-penetrant inspection (FPI) of the second-stage HPT air seal, P/N 54L041, for a through-crack in the front forward fillet radius. (iii) If a through-crack in the front forward fillet radius is found, remove the first-stage HPT hub, second-stage HPT hub, and secondstage HPT blade retaining plate from service. Do not reinstall the first-stage HPT hub, second-stage HPT hub, or second-stage HPT blade retaining plate into any engine. (2) For engines with second-stage HPT air seals, P/N 54L041, installed, perform initial and repetitive inspections for cracks on-wing until the part is removed from the engine as follows: (i) Perform an initial eddy current inspection (ECI) for cracks before reaching 2,200 cycles since new, within 1,000 cyclesin-service after September 17, 2013, or before further flight, whichever occurs later. (ii) Thereafter, repeat the ECI every 1,200 cycles since last inspection, or fewer, depending on the results of the inspection. (iii) Use section 4.0 of the appendix of PW Alert Service Bulletin (ASB) No. PW4G–112– A72–330, Revision 2, dated July 11, 2013, to perform the inspection and use paragraph 8 of the Accomplishment Instructions of PW ASB No. PW4G–112–A72–330, Revision 2, dated July 11, 2013, to disposition the results of the inspection. (f) Installation Prohibition (1) After the effective date of this AD, do not install any second-stage HPT air seal, P/ N 54L041, P/N 50L960, or P/N 50L976, into any engine. (2) After the effective date of this AD, do not install any spare first-stage HPT hub, second-stage HPT hub, or second-stage HPT blade retaining plate that was previously mated in service to a second-stage HPT air VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 seal, P/N 54L041, that was found to have a through-crack in the front forward fillet radius, into any engine. (g) Definitions For the purpose of this AD: (1) Piece-part exposure is when the secondstage HPT air seal is removed from the engine and fully disassembled. (2) A through-crack is a crack that has propagated through the thickness of the part and can be seen on both the inner diameter and outer diameter of the front forward fillet radius. (h) Credit for Previous Actions 77385 MA. For information on the availability of this material at the FAA, call 781–238–7125. (6) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on December 22, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine and Propeller Directorate, Aircraft Certification Service. (1) If you performed an ECI of the secondstage HPT air seal before the effective date of this AD, using PW ASB No. PW4G–112– A72–330, Revision 1, dated February 14, 2013, or an earlier version, you have met the requirements of paragraph (e)(2)(i) of this AD. (2) If you performed an in-shop FPI of the second-stage HPT air seal before the effective date of this AD, you have met the requirements of paragraph (e)(2)(i) of this AD. [FR Doc. 2014–30283 Filed 12–23–14; 8:45 am] (i) Alternative Methods of Compliance (AMOCs) 21 CFR Part 172 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: ANE-AD-AMOC@faa.gov. (j) Related Information (1) For more information about this AD, contact Jo-Ann Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7105; fax: 781–238– 7199; email: jo-ann.theriault@faa.gov. (2) PW Service Bulletin (SB) No. PW4G– 112–72–332, Revision 3, dated June 25, 2014, which is not incorporated by reference in this AD, can be obtained from PW, using the contact information in paragraph (k)(3) of this AD. This SB provides guidance on how to replace the second-stage HPT air seal with an air seal that is more resistant to low cycle fatigue cracks. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on September 17, 2013 (78 FR 49111, August 13, 2013). (i) Pratt & Whitney (PW) Alert Service Bulletin No. PW4G–112–A72–330, Revision 2, dated July 11, 2013. (ii) Reserved. (4) For PW service information identified in this AD, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06108; phone: 860–565–8770; fax: 860–565–4503. (5) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration [Docket No. FDA–2009–F–0303] Food Additives Permitted for Direct Addition to Food for Human Consumption; Advantame AGENCY: Food and Drug Administration, HHS. Final rule; response to objections. ACTION: The Food and Drug Administration (FDA or we) is responding to objections we received on the final rule that amended the food additive regulations to provide for the safe use of advantame as a non-nutritive sweetener and flavor enhancer in foods generally, except in meat and poultry. After reviewing the objections to the final rule, we have concluded that they do not provide a basis for modifying or revoking the regulation. We are also confirming the effective date of May 21, 2014, for the final rule. DATES: The effective date of the final rule published on May 21, 2014 (79 FR 29078), is confirmed: May 21, 2014. FOR FURTHER INFORMATION CONTACT: Felicia M. Ellison, Center for Food Safety and Applied Nutrition (HFS– 265), Food and Drug Administration, 5100 Paint Branch Pkwy., College Park, MD 20740–3835, 240–402–1264. SUPPLEMENTARY INFORMATION: SUMMARY: I. Background In the Federal Register of July 21, 2009 (74 FR 35871), we announced that a food additive petition (FAP 9A4778), had been filed by Ajinomoto Co., Inc., c/o Ajinomoto Corporate Services LLC, 1120 Connecticut Ave. NW., suite 1010, Washington, DC 20036. The petition E:\FR\FM\24DER1.SGM 24DER1

Agencies

[Federal Register Volume 79, Number 247 (Wednesday, December 24, 2014)]
[Rules and Regulations]
[Pages 77384-77385]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30283]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0072; Directorate Identifier 2013-NE-04-AD; 
Amendment 39-18017; AD 2014-23-01]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Division Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

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

SUMMARY: The FAA is correcting an airworthiness directive (AD) that 
published in the Federal Register. That AD applies to all Pratt & 
Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, 
PW4090, and PW4090-3 turbofan engine models with certain second-stage 
high-pressure turbine (HPT) air seals installed. The time required to 
perform the initial eddy current inspection (ECI) in the Compliance 
section is incorrect. This document corrects that error. In all other 
respects, the original document remains the same.

DATES: This final rule is effective on December 26, 2014. The effective 
date of AD 2014-23-01, Amendment 39-18017 (79 FR 69369, November 21, 
2014) remains December 26, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
17, 2013 (78 FR 49111, August 13, 2013).

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this 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: Jo-Ann Theriault, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7105; 
fax: 781-238-7199; email: jo-ann.theriault@faa.gov.

SUPPLEMENTARY INFORMATION: AD 2014-23-01, Amendment 39-18017 (79 FR 
69369, November 21, 2014), requires initial and repetitive inspections 
for cracks in second-stage HPT air seals, the removal of the mating 
hardware if the second-stage HPT air seal is found with a through-
crack, and a mandatory terminating action for all PW PW4074, PW4074D, 
PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine models 
with certain second-stage HPT air seals installed.
    As published, the time required to perform the initial ECI in the 
Compliance section is incorrect. AD 2014-23-01, paragraph (e)(2)(i), 
requires an initial ECI for cracks within 1,000 cycles-in-service after 
September 17, 2013, or before further flight, whichever occurs later. 
That compliance time is more restrictive than intended and will likely 
ground airplanes. The intent was to require an initial ECI for cracks 
before reaching 2,200 cycles since new, or within 1,000 cycles-in-
service after September 17, 2013, or before further flight, whichever 
occurs later.
    No other part of the preamble or regulatory information has been 
changed.
    The effective date of AD 2014-23-01 remains December 26, 2014.

Correction of Regulatory Text


Sec.  39.13  [Corrected]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-15-09, Amendment 39-17525 (78 FR 49111, August 13, 2013), and 
adding the following new AD:

2014-23-01 Pratt & Whitney Division: Amendment 39-18017; Docket No. 
FAA-2013-0072; Directorate Identifier 2013-NE-04-AD.

[[Page 77385]]

(a) Effective Date

    This AD is effective December 26, 2014.

(b) Affected ADs

    This AD supersedes AD 2013-15-09, Amendment 39-17525 (78 FR 
49111, August 13, 2013).

(c) Applicability

    This AD applies to all Pratt & Whitney Division (PW) PW4074, 
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan 
engine models with second-stage high-pressure turbine (HPT) air 
seal, part number (P/N) 54L041, 50L960, or 50L976, installed.

(d) Unsafe Condition

    This AD was prompted by additional reports of cracking in the 
second-stage HPT air seal. We are issuing this AD to prevent failure 
of the second-stage HPT air seal, which could lead to uncontained 
engine failure and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next piece-part exposure after the effective date of 
this AD, do the following:
    (i) Remove from service second-stage HPT air seals, P/Ns 50L960, 
50L976, and 54L041.
    (ii) Perform a fluorescent-penetrant inspection (FPI) of the 
second-stage HPT air seal, P/N 54L041, for a through-crack in the 
front forward fillet radius.
    (iii) If a through-crack in the front forward fillet radius is 
found, remove the first-stage HPT hub, second-stage HPT hub, and 
second-stage HPT blade retaining plate from service. Do not 
reinstall the first-stage HPT hub, second-stage HPT hub, or second-
stage HPT blade retaining plate into any engine.
    (2) For engines with second-stage HPT air seals, P/N 54L041, 
installed, perform initial and repetitive inspections for cracks on-
wing until the part is removed from the engine as follows:
    (i) Perform an initial eddy current inspection (ECI) for cracks 
before reaching 2,200 cycles since new, within 1,000 cycles-in-
service after September 17, 2013, or before further flight, 
whichever occurs later.
    (ii) Thereafter, repeat the ECI every 1,200 cycles since last 
inspection, or fewer, depending on the results of the inspection.
    (iii) Use section 4.0 of the appendix of PW Alert Service 
Bulletin (ASB) No. PW4G-112-A72-330, Revision 2, dated July 11, 
2013, to perform the inspection and use paragraph 8 of the 
Accomplishment Instructions of PW ASB No. PW4G-112-A72-330, Revision 
2, dated July 11, 2013, to disposition the results of the 
inspection.

(f) Installation Prohibition

    (1) After the effective date of this AD, do not install any 
second-stage HPT air seal, P/N 54L041, P/N 50L960, or P/N 50L976, 
into any engine.
    (2) After the effective date of this AD, do not install any 
spare first-stage HPT hub, second-stage HPT hub, or second-stage HPT 
blade retaining plate that was previously mated in service to a 
second-stage HPT air seal, P/N 54L041, that was found to have a 
through-crack in the front forward fillet radius, into any engine.

(g) Definitions

    For the purpose of this AD:
    (1) Piece-part exposure is when the second-stage HPT air seal is 
removed from the engine and fully disassembled.
    (2) A through-crack is a crack that has propagated through the 
thickness of the part and can be seen on both the inner diameter and 
outer diameter of the front forward fillet radius.

(h) Credit for Previous Actions

    (1) If you performed an ECI of the second-stage HPT air seal 
before the effective date of this AD, using PW ASB No. PW4G-112-A72-
330, Revision 1, dated February 14, 2013, or an earlier version, you 
have met the requirements of paragraph (e)(2)(i) of this AD.
    (2) If you performed an in-shop FPI of the second-stage HPT air 
seal before the effective date of this AD, you have met the 
requirements of paragraph (e)(2)(i) of this AD.

(i) 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: ANE-AD-AMOC@faa.gov.

(j) Related Information

    (1) For more information about this AD, contact Jo-Ann 
Theriault, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7105; fax: 781-238-7199; email: 
jo-ann.theriault@faa.gov.
    (2) PW Service Bulletin (SB) No. PW4G-112-72-332, Revision 3, 
dated June 25, 2014, which is not incorporated by reference in this 
AD, can be obtained from PW, using the contact information in 
paragraph (k)(3) of this AD. This SB provides guidance on how to 
replace the second-stage HPT air seal with an air seal that is more 
resistant to low cycle fatigue cracks.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 17, 2013 (78 FR 49111, August 13, 2013).
    (i) Pratt & Whitney (PW) Alert Service Bulletin No. PW4G-112-
A72-330, Revision 2, dated July 11, 2013.
    (ii) Reserved.
    (4) For PW service information identified in this AD, contact 
Pratt & Whitney Division, 400 Main St., East Hartford, CT 06108; 
phone: 860-565-8770; fax: 860-565-4503.
    (5) You may view this service information at FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.
    (6) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Burlington, Massachusetts, on December 22, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine and Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2014-30283 Filed 12-23-14; 8:45 am]
BILLING CODE 4910-13-P

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