80_FR_64578 80 FR 64373 - Airworthiness Directives; Engine Alliance Turbofan Engines

80 FR 64373 - Airworthiness Directives; Engine Alliance Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 205 (October 23, 2015)

Page Range64373-64375
FR Document2015-26755

We propose to adopt a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270 turbofan engines. This proposed AD was prompted by reports of the installation of non-conforming honeycomb seals in the high-pressure compressor (HPC) adjacent to the HPC rotor stage 2 to 5 spool and stage 7 to 9 spool. This proposed AD would require removal and replacement of the affected HPC rotor stage 2 to 5 and stage 7 to 9 spools. We are proposing this AD to prevent failure of the HPC rotor stage 2 to 5 and stage 7 to 9 spools, which could lead to uncontained engine failure and damage to the airplane.

Federal Register, Volume 80 Issue 205 (Friday, October 23, 2015) 
[Federal Register Volume 80, Number 205 (Friday, October 23, 2015)]
[Proposed Rules]
[Pages 64373-64375]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-26755]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3713; Directorate Identifier 2015-NE-23-AD]
RIN 2120-AA64


Airworthiness Directives; Engine Alliance Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Engine Alliance (EA) GP7270 turbofan engines. This proposed AD 
was prompted by reports of the installation of non-conforming honeycomb 
seals in the high-pressure compressor (HPC) adjacent to the HPC rotor 
stage 2 to 5 spool and stage 7 to 9 spool. This proposed AD would 
require removal and replacement of the affected HPC rotor stage 2 to 5 
and stage 7 to 9 spools. We are proposing this AD to prevent failure of 
the HPC rotor stage 2 to 5 and stage 7 to 9 spools, which could lead to 
uncontained engine failure and damage to the airplane.

DATES: We must receive comments on this proposed AD by December 22, 
2015.

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 http://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 proposed AD, contact 
Engine Alliance, 400 Main St., East Hartford, CT 06108, M/S 169-10, 
phone: 800-565-0140; email: [email protected];

[[Page 64374]]

Web site: www.engineallianceportal.com. You may view this service 
information at the 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.

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-
3713; 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 proposed 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: Martin Adler, Aerospace Engineer, 
Engine & Propeller Directorate, FAA, 12 New England Executive Park, 
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-2015-3713; 
Directorate Identifier 2015-NE-23-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We learned from the manufacturer that non-conforming honeycomb 
seals were installed in the affected HPCs adjacent to the HPC rotor 
stage 2 to 5 spools and stage 7 to 9 spools. The honeycomb seals in the 
HPC were machined to an incorrect radial height which resulted in 
reduced clearances between the honeycomb and the rotating spools. This 
error could lead to cracks on the spools prior to reaching their full 
life. This condition, if not corrected, could result in failure of the 
HPC rotor stage 2 to 5 and stage 7 to 9 spools, which could lead to 
uncontained engine failure, and damage to the airplane.

Relevant Service Information Under 1 CFR Part 51

    Engine Alliance has issued EA Service Bulletin (SB) No. EAGP7-72-
327, dated July 21, 2015; and SB No. EAGP7-72-328, dated July 21, 2015. 
The SBs describe procedures for removal and replacement of HPC rotor 
stage 2 to 5 spools and HPC rotor stage 7 to 9 spools, respectively. 
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 of this document.

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 HPC rotor stage 2 to 5 and stage 7 to 9 spools.

Costs of Compliance

    We estimate that this proposed AD affects zero engines installed on 
airplanes of U.S. registry. The average labor rate is $85 per hour. 
Based on these figures, we estimate the cost of this proposed AD on 
U.S. operators to be $0.

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

    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 to the extent 
that it justifies making a regulatory distinction, 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):

Engine Alliance: Docket No. FAA-2015-3713; Directorate Identifier 
2015-NE-23-AD.

(a) Comments Due Date

    We must receive comments by December 22, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Engine Alliance (EA) GP7270 turbofan engines 
with one or both of the following installed:

[[Page 64375]]

    (1) A high-pressure compressor (HPC) rotor stage 2 to 5 spool, 
part number (P/N) 382-104-807-0, with a serial number (S/N) listed 
in EA Service Bulletin (SB) No. EAGP7-72-327, dated July 21, 2015; 
or
    (2) an HPC rotor stage 7 to 9 spool, P/N 2031M90G04, 2031M90G05, 
or 2031M90G07, with an S/N listed in EA SB No. EAGP7-72-328, dated 
July 21, 2015.

(d) Unsafe Condition

    This AD was prompted by reports of the installation of non-
conforming honeycomb seals in the HPC adjacent to the HPC rotor 
stage 2 to 5 spool and stage 7 to 9 spool. We are issuing this AD to 
prevent failure of the HPC rotor stage 2 to 5 spools and stage 7 to 
9 spools, 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. Within 30 days after the effective date of this 
AD or before accumulating 2,100 engine cycles since the last 
disassembly of the compressor module of the engine, whichever occurs 
later:
    (1) For engines with an HPC rotor stage 2 to 5 spool, P/N 382-
104-807-0, installed with a S/N listed in EA SB No. EAGP7-72-327, 
dated July 21, 2015, do the following:
    (i) Remove the HPC rotor stage 2 to 5 spool from service and 
replace with a part eligible for installation.
    (ii) Remove and replace the honeycomb seals on the HPC stage 5 
vanes.
    (2) For engines with an HPC rotor stage 7 to 9 spool, P/N 
2031M90G04, 2031M90G05, or 2031M90G07 installed with an S/N listed 
in EA SB No. EAGP7-72-328, dated July 21, 2015, do the following:
    (i) Remove the HPC rotor stage 7 to 9 spool from service and 
replace with a part eligible for installation.
    (ii) Remove and replace the honeycomb seals on the HPC stage 6, 
stage 7, and stage 8 vanes.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, 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].

(g) Related Information

    (1) For more information about this AD, contact Martin Adler, 
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7157; 
fax: 781-238-7199; email: [email protected].
    (2) EA SBs No. EAGP7-72-327, dated July 21, 2015; and No. EAGP7-
72-328, dated July 21, 2015 can be obtained from EA using the 
contact information in paragraph (g)(3) of this proposed AD.
    (3) For service information identified in this AD, contact 
Engine Alliance, 400 Main St., East Hartford, CT 06108, M/S 169-10, 
phone: 800-565-0140; email: [email protected]; Web site: 
www.engineallianceportal.com.
    (4) You may view this service information at the 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.

    Issued in Burlington, Massachusetts, on October 16, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-26755 Filed 10-22-15; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64373 4. Will not have a significant (f) Compliance Issued in Renton, Washington, on October economic impact, positive or negative, Comply with this AD within the 15, 2015. on a substantial number of small entities compliance times specified, unless already Jeffrey E. Duven, under the criteria of the Regulatory done. Manager, Transport Airplane Directorate, Flexibility Act. Aircraft Certification Service. (g) One-Time Inspection and Repair [FR Doc. 2015–26691 Filed 10–22–15; 8:45 am] List of Subjects in 14 CFR Part 39 Within 12 months after the effective date BILLING CODE 4910–13–P of this AD: Do the actions required by Air transportation, Aircraft, Aviation paragraphs (g)(1), (g)(2), and (g)(3) of this AD, safety, Incorporation by reference, in accordance with the Accomplishment Safety. Instructions of UTC Aerospace Systems DEPARTMENT OF TRANSPORTATION Service Bulletin 300723–28–03 (V–1577), The Proposed Amendment Federal Aviation Administration Revision 01, dated July 20, 2015. Accordingly, under the authority (1) Perform a one-time general visual inspection for damage of the outer tank 14 CFR Part 39 delegated to me by the Administrator, sensor harness, and if any damage is found [Docket No. FAA–2015–3713; Directorate the FAA proposes to amend 14 CFR part on the expando sleeving, before further flight, Identifier 2015–NE–23–AD] 39 as follows: do a detailed inspection of the underlying wires for exposed conductor wires. If any RIN 2120–AA64 PART 39—AIRWORTHINESS exposed conductor wire is found, before DIRECTIVES further flight, replace the outer wing harness Airworthiness Directives; Engine assembly. Alliance Turbofan Engines ■ 1. The authority citation for part 39 (2) Install new brackets and re-route the AGENCY: Federal Aviation continues to read as follows: surge tank overflow sensor harness. Administration (FAA), DOT. Authority: 49 U.S.C. 106(g), 40113, 44701. (3) Modify the harness protection. ACTION: Notice of proposed rulemaking (h) Credit for Previous Actions (NPRM). § 39.13 [Amended] This paragraph provides credit for actions ■ 2. The FAA amends § 39.13 by adding required by paragraph (g) of this AD, if those SUMMARY: We propose to adopt a new the following new airworthiness actions were performed before the effective airworthiness directive (AD) for certain directive (AD): date of this AD using UTC Aerospace Engine Alliance (EA) GP7270 turbofan Systems Service Bulletin 300723–28–03 (V– engines. This proposed AD was Airbus: Docket No. FAA–2015–4204; Directorate Identifier 2015–NM–001–AD. 1577), dated October 10, 2014. This service prompted by reports of the installation information is not incorporated by reference of non-conforming honeycomb seals in (a) Comments Due Date in this AD. the high-pressure compressor (HPC) We must receive comments by December 7, (i) Alternative Methods of Compliance adjacent to the HPC rotor stage 2 to 5 2015. (AMOCs) spool and stage 7 to 9 spool. This (b) Affected ADs (1) The Manager, Boston Aircraft proposed AD would require removal Certification Office (ACO) ANE–150, FAA, and replacement of the affected HPC None. has the authority to approve AMOCs for this rotor stage 2 to 5 and stage 7 to 9 spools. (c) Applicability AD, if requested using the procedures found We are proposing this AD to prevent This AD applies to the Airbus airplanes in 14 CFR 39.19. In accordance with 14 CFR failure of the HPC rotor stage 2 to 5 and specified in paragraphs (c)(1), (c)(2), (c)(3), 39.19, send your request to your principal stage 7 to 9 spools, which could lead to and (c)(4) of this AD; certificated in any inspector or local Flight Standards District uncontained engine failure and damage category; modified by Simmonds Precision Office, as appropriate. If sending information to the airplane. Products, Inc., supplemental type certificate directly to the manager of the ACO, send it DATES: We must receive comments on (STC) ST00092BO (http://rgl.faa.gov/ to the attention of the person identified in paragraph (j)(1) of this AD. this proposed AD by December 22, Regulatory_and_Guidance_Library/rgstc.nsf/ (2) Before using any approved AMOC, 2015. 0/D41C5AE8E46B4901862v574900069E004 ?OpenDocument&Highlight=st00092bo). notify your appropriate principal inspector, ADDRESSES: You may send comments, (1) Model A300 B4–601, B4–603, B4–620, or lacking a principal inspector, the manager using the procedures found in 14 CFR and B4–622 airplanes. of the local flight standards district office/ 11.43 and 11.45, by any of the following (2) Model A300 B4–605R and B4–622R certificate holding district office. methods: airplanes. (j) Related Information • Federal eRulemaking Portal: Go to (3) Model A300 F4–605R and F4–622R http://www.regulations.gov. Follow the airplanes. (1) For more information about this AD, contact Marc Ronell, Aerospace Engineer, instructions for submitting comments. (4) Model A300 C4–605R Variant F airplanes. Boston ACO, FAA, 12 New England • Fax: 202–493–2251. Executive Park, Burlington, MA 01803; • Mail: U.S. Department of (d) Subject phone: 781–238–7776; fax: 781–238–7170; Transportation, Docket Operations, M– Air Transport Association (ATA) of email: marc.ronell@faa.gov. 30, West Building Ground Floor, Room America Code 28, Fuel. (2) For service information identified in W12–140, 1200 New Jersey Avenue SE., this AD, contact Simmonds Precision Washington, DC 20590. (e) Reason Products, Inc., A UTC Aerospace Company, • Hand Delivery: Deliver to Mail mstockstill on DSK4VPTVN1PROD with PROPOSALS This AD was prompted by a report of 100 Panton Road, Vergennes, Vermont 05491; address above between 9 a.m. and 5 chafing found on the overflow sensor harness phone 802–877–2911; fax 802–877–4444; p.m., Monday through Friday, except of the surge tank, and subsequent contact Internet http://www.utcaerospace between the electrical wiring and fuel tank systems.com. You may view this referenced Federal holidays. structure. We are issuing this AD to prevent service information at the FAA, Transport For service information identified in chafing of the harness and subsequent Airplane Directorate, 1601 Lind Avenue SW., this proposed AD, contact Engine contact between the electrical wiring and fuel Renton, WA. For information on the Alliance, 400 Main St., East Hartford, tank structure, which could result in availability of this material at the FAA, call CT 06108, M/S 169–10, phone: 800– electrical arcing and a fuel tank explosion. 425–227–1221. 565–0140; email: help24@pw.utc.com; VerDate Sep<11>2014 17:40 Oct 22, 2015 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\23OCP1.SGM 23OCP1

64374 Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules Web site: rotating spools. This error could lead to because it addresses an unsafe condition www.engineallianceportal.com. You cracks on the spools prior to reaching that is likely to exist or develop on may view this service information at the their full life. This condition, if not products identified in this rulemaking FAA, Engine & Propeller Directorate, 12 corrected, could result in failure of the action. New England Executive Park, HPC rotor stage 2 to 5 and stage 7 to 9 Regulatory Findings Burlington, MA. For information on the spools, which could lead to availability of this material at the FAA, uncontained engine failure, and damage We determined that this proposed AD call 781–238–7125. to the airplane. would not have federalism implications under Executive Order 13132. This Examining the AD Docket Relevant Service Information Under 1 proposed AD would not have a You may examine the AD docket on CFR Part 51 substantial direct effect on the States, on the Internet at http:// Engine Alliance has issued EA the relationship between the national www.regulations.gov by searching for Service Bulletin (SB) No. EAGP7–72– Government and the States, or on the and locating Docket No. FAA–2015– 327, dated July 21, 2015; and SB No. distribution of power and 3713; or in person at the Docket EAGP7–72–328, dated July 21, 2015. responsibilities among the various Management Facility between 9 a.m. The SBs describe procedures for levels of government. and 5 p.m., Monday through Friday, removal and replacement of HPC rotor For the reasons discussed above, I except Federal holidays. The AD docket stage 2 to 5 spools and HPC rotor stage certify this proposed regulation: contains this proposed AD, the 7 to 9 spools, respectively. This service (1) Is not a ‘‘significant regulatory regulatory evaluation, any comments information is reasonably available action’’ under Executive Order 12866, received, and other information. The because the interested parties have (2) Is not a ‘‘significant rule’’ under street address for the Docket Office access to it through their normal course the DOT Regulatory Policies and (phone: 800–647–5527) is in the of business or by the means identified Procedures (44 FR 11034, February 26, ADDRESSES section. Comments will be in the ADDRESSES section of this 1979), available in the AD docket shortly after document. (3) Will not affect intrastate aviation receipt. in Alaska to the extent that it justifies FOR FURTHER INFORMATION CONTACT: FAA’s Determination making a regulatory distinction, and Martin Adler, Aerospace Engineer, We are proposing this AD because we (4) Will not have a significant Engine & Propeller Directorate, FAA, 12 evaluated all the relevant information economic impact, positive or negative, New England Executive Park, and determined the unsafe condition on a substantial number of small entities Burlington, MA 01803; phone: 781– described previously is likely to exist or under the criteria of the Regulatory 238–7157; fax: 781–238–7199; email: develop in other products of the same Flexibility Act. martin.adler@faa.gov. type design. SUPPLEMENTARY INFORMATION: List of Subjects in 14 CFR Part 39 Proposed AD Requirements Comments Invited Air transportation, Aircraft, Aviation This proposed AD would require safety, Incorporation by reference, We invite you to send any written removal and replacement of the affected Safety. relevant data, views, or arguments about HPC rotor stage 2 to 5 and stage 7 to 9 this proposal. Send your comments to spools. The Proposed Amendment an address listed under the ADDRESSES Accordingly, under the authority Costs of Compliance section. Include ‘‘Docket No. FAA– delegated to me by the Administrator, 2015–3713; Directorate Identifier 2015– We estimate that this proposed AD the FAA proposes to amend 14 CFR part NE–23–AD’’ at the beginning of your affects zero engines installed on 39 as follows: comments. We specifically invite airplanes of U.S. registry. The average comments on the overall regulatory, labor rate is $85 per hour. Based on PART 39—AIRWORTHINESS economic, environmental, and energy these figures, we estimate the cost of DIRECTIVES aspects of this proposed AD. We will this proposed AD on U.S. operators to consider all comments received by the be $0. ■ 1. The authority citation for part 39 closing date and may amend this Authority for This Rulemaking continues to read as follows: proposed AD because of those Authority: 49 U.S.C. 106(g), 40113, 44701. comments. Title 49 of the United States Code We will post all comments we specifies the FAA’s authority to issue § 39.13 [Amended] receive, without change, to http:// rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding www.regulations.gov, including any section 106, describes the authority of the following new airworthiness personal information you provide. We the FAA Administrator. Subtitle VII: directive (AD): will also post a report summarizing each Aviation Programs, describes in more detail the scope of the Agency’s Engine Alliance: Docket No. FAA–2015– substantive verbal contact we receive 3713; Directorate Identifier 2015–NE– about this proposed AD. authority. 23–AD. We are issuing this rulemaking under Discussion the authority described in Subtitle VII, (a) Comments Due Date We learned from the manufacturer Part A, Subpart III, Section 44701: mstockstill on DSK4VPTVN1PROD with PROPOSALS We must receive comments by December that non-conforming honeycomb seals ‘‘General requirements.’’ Under that 22, 2015. were installed in the affected HPCs section, Congress charges the FAA with (b) Affected ADs adjacent to the HPC rotor stage 2 to 5 promoting safe flight of civil aircraft in spools and stage 7 to 9 spools. The air commerce by prescribing regulations None. honeycomb seals in the HPC were for practices, methods, and procedures (c) Applicability machined to an incorrect radial height the Administrator finds necessary for This AD applies to Engine Alliance (EA) which resulted in reduced clearances safety in air commerce. This regulation GP7270 turbofan engines with one or both of between the honeycomb and the is within the scope of that authority the following installed: VerDate Sep<11>2014 17:40 Oct 22, 2015 Jkt 238001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\23OCP1.SGM 23OCP1

Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64375 (1) A high-pressure compressor (HPC) rotor 12 New England Executive Park, Burlington, Washington, DC, between 9 a.m. and 5 stage 2 to 5 spool, part number (P/N) 382– MA. For information on the availability of p.m., Monday through Friday, except 104–807–0, with a serial number (S/N) listed this material at the FAA, call 781–238–7125. Federal holidays. in EA Service Bulletin (SB) No. EAGP7–72– For Airbus service information Issued in Burlington, Massachusetts, on 327, dated July 21, 2015; or October 16, 2015. identified in this proposed AD, contact (2) an HPC rotor stage 7 to 9 spool, P/N 2031M90G04, 2031M90G05, or 2031M90G07, Colleen M. D’Alessandro, Airbus, Airworthiness Office—EIAS, 1 with an S/N listed in EA SB No. EAGP7–72– Directorate Manager, Engine & Propeller Rond Point Maurice Bellonte, 31707 328, dated July 21, 2015. Directorate, Aircraft Certification Service. Blagnac Cedex, France; telephone +33 5 [FR Doc. 2015–26755 Filed 10–22–15; 8:45 am] 61 93 36 96; fax +33 5 61 93 44 51; email (d) Unsafe Condition BILLING CODE 4910–13–P account.airworth-eas@airbus.com; This AD was prompted by reports of the Internet http://www.airbus.com. For Air installation of non-conforming honeycomb Cruisers service information identified seals in the HPC adjacent to the HPC rotor DEPARTMENT OF TRANSPORTATION in this proposed AD, contact Air stage 2 to 5 spool and stage 7 to 9 spool. We are issuing this AD to prevent failure of the Cruisers Company, Cage Code 70167, HPC rotor stage 2 to 5 spools and stage 7 to Federal Aviation Administration 1747 State Route 34, Wall Township, NJ 9 spools, which could lead to uncontained 07727–3935; telephone 732–681–3527; engine failure and damage to the airplane. 14 CFR Part 39 fax 732–681–9163; Internet http://www. zodiacaerospace.com/en/our-activities/ (e) Compliance [Docket No. FAA–2015–4202; Directorate Identifier 2014–NM–016–AD] aerosafety/zodiac-evacuation-systems. Comply with this AD within the You may view this referenced service compliance times specified, unless already RIN 2120–AA64 information at the FAA, Transport done. Within 30 days after the effective date of this AD or before accumulating 2,100 Airplane Directorate, 1601 Lind Avenue Airworthiness Directives; Airbus SW., Renton, WA. For information on engine cycles since the last disassembly of the compressor module of the engine, Airplanes the availability of this material at the whichever occurs later: AGENCY: Federal Aviation FAA, call 425–227–1221. (1) For engines with an HPC rotor stage 2 Administration (FAA), DOT. to 5 spool, P/N 382–104–807–0, installed Examining the AD Docket with a S/N listed in EA SB No. EAGP7–72– ACTION: Notice of proposed rulemaking You may examine the AD docket on 327, dated July 21, 2015, do the following: (NPRM). the Internet at http:// (i) Remove the HPC rotor stage 2 to 5 spool www.regulations.gov by searching for from service and replace with a part eligible SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012–18– and locating Docket No. FAA–2015– for installation. (ii) Remove and replace the honeycomb 12, for certain Airbus Model A318, 4202; or in person at the Docket seals on the HPC stage 5 vanes. A319, and A320 series airplanes. AD Management Facility between 9 a.m. (2) For engines with an HPC rotor stage 7 and 5 p.m., Monday through Friday, 2012–18–12 currently requires to 9 spool, P/N 2031M90G04, 2031M90G05, except Federal holidays. The AD docket modifying the off-wing escape slide or 2031M90G07 installed with an S/N listed contains this proposed AD, the in EA SB No. EAGP7–72–328, dated July 21, (OWS) enclosures on the left-hand (LH) regulatory evaluation, any comments 2015, do the following: side and right-hand (RH) side of the received, and other information. The (i) Remove the HPC rotor stage 7 to 9 spool fuselage. Since we issued AD 2012–18– street address for the Docket Operations from service and replace with a part eligible 12, we have received reports that office (telephone 800–647–5527) is in for installation. additional OWS part numbers have been (ii) Remove and replace the honeycomb the ADDRESSES section. Comments will affected. This proposed AD would seals on the HPC stage 6, stage 7, and stage be available in the AD docket shortly retain the requirements of AD 2012–18– 8 vanes. after receipt. 12 and expand the applicability to all FOR FURTHER INFORMATION CONTACT: (f) Alternative Methods of Compliance Airbus Model A318, A319, and A320 (AMOCs) series airplanes. We are proposing this Sanjay Ralhan, Aerospace Engineer, AD to prevent off-wing exits on the LH International Branch, ANM–116, The Manager, Engine Certification Office, and RH sides of the fuselage from Transport Airplane Directorate, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make 1601 Lind Avenue SW., Renton, WA becoming inoperative, which, during an your request. You may email your request to: 98057–3356; telephone 425–227–1405; emergency, could impair the safe ANE-AD-AMOC@faa.gov. fax 425–227–1149. evacuation of occupants, possibly resulting in personal injuries. SUPPLEMENTARY INFORMATION: (g) Related Information (1) For more information about this AD, DATES: We must receive comments on Comments Invited contact Martin Adler, Aerospace Engineer, this proposed AD by December 7, 2015. We invite you to send any written Engine & Propeller Directorate, FAA, 12 New ADDRESSES: You may send comments by relevant data, views, or arguments about England Executive Park, Burlington, MA any of the following methods: this proposed AD. Send your comments 01803; phone: 781–238–7157; fax: 781–238– 7199; email: martin.adler@faa.gov. • Federal eRulemaking Portal: Go to to an address listed under the (2) EA SBs No. EAGP7–72–327, dated July http://www.regulations.gov. Follow the ADDRESSES section. Include ‘‘Docket No. 21, 2015; and No. EAGP7–72–328, dated July instructions for submitting comments. FAA–2015–4202; Directorate Identifier 21, 2015 can be obtained from EA using the • Fax: 202–493–2251. 2014–NM–016–AD’’ at the beginning of contact information in paragraph (g)(3) of this • Mail: U.S. Department of your comments. We specifically invite mstockstill on DSK4VPTVN1PROD with PROPOSALS proposed AD. Transportation, Docket Operations, M– comments on the overall regulatory, (3) For service information identified in 30, West Building Ground Floor, Room economic, environmental, and energy this AD, contact Engine Alliance, 400 Main W12–140, 1200 New Jersey Avenue SE., St., East Hartford, CT 06108, M/S 169–10, aspects of this proposed AD. We will phone: 800–565–0140; email: help24@ Washington, DC 20590. consider all comments received by the pw.utc.com; Web site: • Hand Delivery: U.S. Department of closing date and may amend this www.engineallianceportal.com. Transportation, Docket Operations, M– proposed AD based on those comments. (4) You may view this service information 30, West Building Ground Floor, Room We will post all comments we at the FAA, Engine & Propeller Directorate, W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// VerDate Sep<11>2014 17:40 Oct 22, 2015 Jkt 238001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\23OCP1.SGM 23OCP1


Document Created: 2015-12-14 15:32:50
Document Modified: 2015-12-14 15:32:50
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by December 22, 2015.
ContactMartin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected]
FR Citation80 FR 64373 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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