81_FR_1590 81 FR 1582 - Airworthiness Directives; General Electric Company Turbofan Engines

81 FR 1582 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 8 (January 13, 2016)

Page Range1582-1584
FR Document2015-33097

We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This proposed AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This proposed AD would require eddy current inspections (ECIs) or ultrasonic inspections (USIs) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are proposing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.

Federal Register, Volume 81 Issue 8 (Wednesday, January 13, 2016) 
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Proposed Rules]
[Pages 1582-1584]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-33097]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company 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 all 
General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, 
and GE90-94B turbofan engines. This proposed AD was prompted by an 
uncontained failure of the high-pressure compressor (HPC) stage 8-10 
spool, leading to an airplane fire. This proposed AD would require eddy 
current inspections (ECIs) or ultrasonic inspections (USIs) of the HPC 
stage 8-10 spool and removing from service those parts that fail 
inspection. We are proposing this AD to prevent failure of the HPC 
stage 8-10 spool, uncontained rotor release, damage to the engine, and 
damage to the airplane.

DATES: We must receive comments on this proposed AD by March 14, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to 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 
General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; email: 
[email protected]. 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-
7491; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket

[[Page 1583]]

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: John Frost, Aerospace Engineer, Engine 
Certification Office, FAA, 12 New England Executive Park, Burlington, 
MA 01803; phone: 781-238-7756; 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 NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-7491; 
Directorate Identifier 2015-NE-39-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 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 NPRM.

Discussion

    We received a report of an HPC stage 8-10 spool uncontained failure 
resulting in an airplane fire. Ongoing investigations have determined 
that a crack initiated in the stage 8 aft web upper face of the HPC 8-
10 spool and propagated until spool rupture. The root cause of the 
crack initiation is not yet known. This condition, if not corrected, 
could result in failure of the HPC stage 8-10 spool, uncontained rotor 
release, damage to the engine, and damage to the airplane. We are 
issuing this AD to correct the unsafe condition on these products.

Related Service Information

    We reviewed the following chapters of GE GE90 Engine Manual, 
GEK100700, Revision 66, dated September 1, 2015:
     Chapter 72-31-08, Special Procedure 003, piece-part level 
ECI,
     Chapter 72-00-31, Special Procedure 006, rotor assembly 
and module level ECI and,
     Chapter 72-00-31, Special Procedure 007, rotor assembly 
level USI.

FAA's Determination

    We are proposing this NPRM 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 NPRM would require accomplishing an ECI or USI of the stage 8 
aft web upper face of the HPC stage 8-10 spool and removing from 
service those parts that fail inspection.

Interim Action

    We consider this proposed AD interim action. GE is determining the 
root cause for the unsafe condition identified in this proposed AD. 
Once a root cause is identified, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this proposed AD affects 54 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 7 
hours per engine to comply with this AD. The average labor rate is $85 
per hour. We estimate one part will fail inspection at a cost of 
$780,000. Based on these figures, we estimate the total cost of the AD 
to U.S. operators to be $812,130.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    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):

General Electric Company: Docket No. FAA-2015-7491; Directorate 
Identifier 2015-NE-39-AD.

(a) Comments Due Date

    We must receive comments by March 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) GE90-76B, GE90-
77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with a high-
pressure compressor (HPC) 8-10 stage spool, part numbers (P/Ns) 
1694M80G04, 1844M90G01, or 1844M90G02, installed.

(d) Unsafe Condition

    This AD was prompted by an uncontained failure of the HPC stage 
8-10 spool. We are issuing this AD to prevent failure of the HPC 
stage 8-10 spool, uncontained rotor release, damage to the engine, 
and damage to the airplane.

(e) Compliance

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

[[Page 1584]]

    (1) Perform an eddy current inspection (ECI) or ultrasonic 
inspection (USI) of the stage 8 aft web upper face of the HPC stage 
8-10 spool, before exceeding 10,500 cycles since new or within 500 
cycles in service, after the effective date of this AD, whichever 
occurs later.
    (2) At each shop visit, perform an ECI or USI of the stage 8 aft 
web upper face of the HPC stage 8-10 spool.
    (3) Remove from service any HPC stage 8-10 spool that fails the 
inspection required by paragraphs (e)(1) and (e)(2) of this AD and 
replace the spool with a spool eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, an HPC stage 8-10 spool, P/
Ns 1694M80G04, 1844M90G01, and 1844M90G02, is not eligible for 
installation into any engine, unless the spool has passed an ECI or 
USI required by paragraphs (e)(1) and (e)(2) of this AD.

(g) Definition

    For the purpose of this AD, an engine shop visit is the 
induction of an engine into the shop for maintenance during which 
the compressor discharge pressure seal face is exposed.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: [email protected].

(i) Related Information

    (1) For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, 12 New England 
Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-
238-7199; email: [email protected].
    (2) GE GE90 Engine Manual, GEK100700, Revision 66, dated 
September 1, 2015, Chapter 72-31-08, Special Procedure 003, Chapter 
72-00-31, Special Procedure 006, and Chapter 72-00-31, Special 
Procedure 007, rotor assembly level USI can be obtained from General 
Electric Company, using the contact information in paragraph (i)(3) 
of this AD.
    (3) For service information identified in this proposed AD, 
contact General Electric Company, GE-Aviation, Room 285, 1 Neumann 
Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; 
email: [email protected].
    (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 December 22, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-33097 Filed 1-12-16; 8:45 am]
BILLING CODE 4910-13-P

1582 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules TABLE 1 TO PARAGRAPH (g) OF THIS AD—NORMAL PROCEDURES AND LIMITATIONS Affected airplane/configuration Applicable AFM change Model Mystère Falcon 900 airplanes ....................................................... Change Proposal 118 (TC118), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ dated December 18, 2014, to the Dassault Mystère Fal- con 900 Airplane Flight Manual, DTM20103. Model Mystère Falcon 900 airplanes with Dassault Aviation production Change Proposal 48 (TC048), ‘‘AFM: Yaw Damper Off In Line Up Pro- modification M1975, or production modification M2695 embodied, or cedure,’’ dated December 16, 2014, to the Dassault Mystère Falcon modified in service by Dassault Aviation Service Bulletin F900–250 900, F900C Version, Airplane Flight Manual (FM900C), TC048. (‘‘Falcon 900 C’’ version). Model Falcon 900EX airplanes ................................................................ Change Proposal 12 (CP012), ‘‘AFM: Yaw Damper Off In Line Up Pro- cedure,’’ Dassault Falcon 900EX Airplane Flight Manual DTM561. Model Falcon 900EX airplanes with Dassault Aviation production modi- Change Proposal 31 (CP031), ‘‘AFM: Yaw Damper Off In Line Up Pro- fication M3083 embodied (Falcon 900EX ‘‘EASy’’ version). cedure,’’ Dassault Falcon 900EX EASy, Airplane Flight Manual DGT84972). Model Falcon 2000EX airplanes .............................................................. Change Proposal 17 (CP017), ‘‘AFM: Yaw Damper Off in Line Up Pro- cedure,’’ dated January 23, 2015, to the Dassault Falcon 2000EX Airplane Flight Manual, DGT84278. Model Falcon 2000EX airplanes with Dassault Aviation production Change Proposal 46 (CP046), ‘‘AFM: Yaw Damper Off In Line Up Pro- modification M1691 embodied (Falcon 2000EX ‘‘EASy’’ version). cedure,’’ dated December 15, 2014, to the Dassault Falcon 2000EX EASy Version, Airplane Flight Manual, DGT88898. (h) Other FAA AD Provisions 2000, South Hackensack, NJ 07606; those parts that fail inspection. We are The following provisions also apply to this telephone 201–440–6700; Internet http:// proposing this AD to prevent failure of AD: www.dassaultfalcon.com. You may view this the HPC stage 8–10 spool, uncontained (1) Alternative Methods of Compliance service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., rotor release, damage to the engine, and (AMOCs): The Manager, International damage to the airplane. Branch, ANM–116, Transport Airplane Renton, WA. For information on the availability of this material at the FAA, call DATES: We must receive comments on Directorate, FAA, has the authority to approve AMOCs for this AD, if requested 425–227–1221. this proposed AD by March 14, 2016. using the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on ADDRESSES: You may send comments, In accordance with 14 CFR 39.19, send your December 23, 2015. using the procedures found in 14 CFR request to your principal inspector or local John Piccola, 11.43 and 11.45, by any of the following Flight Standards District Office, as Acting Manager, Transport Airplane methods: appropriate. If sending information directly Directorate, Aircraft Certification Service. • Federal eRulemaking Portal: Go to to the International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, [FR Doc. 2015–33178 Filed 1–12–16; 8:45 am] http://www.regulations.gov. Follow the International Branch, ANM–116, Transport BILLING CODE 4910–13–P instructions for submitting comments. Airplane Directorate, FAA, 1601 Lind • Fax: 202–493–2251. Avenue SW., Renton, Washington 98057– • Mail: U.S. Department of 3356; telephone 425–227–1137; fax 425–227– DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M– 1149. Information may be emailed to: 9- 30, West Building Ground Floor, Room ANM-116-AMOC-REQUESTS@faa.gov. Federal Aviation Administration W12–140, 1200 New Jersey Avenue SE., Before using any approved AMOC, notify Washington, DC 20590. your appropriate principal inspector, or 14 CFR Part 39 • Hand Delivery: Deliver to Mail lacking a principal inspector, the manager of [Docket No. FAA–2015–7491; Directorate address above between 9 a.m. and 5 the local flight standards district office/ certificate holding district office. The AMOC Identifier 2015–NE–39–AD] p.m., Monday through Friday, except approval letter must specifically reference Federal holidays. RIN 2120–AA64 For service information identified in this AD. (2) Contacting the Manufacturer: For any this proposed AD, contact General Airworthiness Directives; General Electric Company, GE-Aviation, Room requirement in this AD to obtain corrective actions from a manufacturer, the action must Electric Company Turbofan Engines 285, 1 Neumann Way, Cincinnati, OH be accomplished using a method approved AGENCY: Federal Aviation 45215, phone: 513–552–3272; fax: 513– by the Manager, International Branch, ANM– Administration (FAA), DOT. 552–3329; email: geae.aoc@ge.com. You 116, Transport Airplane Directorate, FAA; or may view this service information at the the European Aviation Safety Agency ACTION: Notice of proposed rulemaking (EASA); or Dassault Aviation’s EASA Design (NPRM). FAA, Engine & Propeller Directorate, 12 Organization Approval (DOA). If approved by New England Executive Park, the DOA, the approval must include the SUMMARY: We propose to adopt a new Burlington, MA. For information on the DOA-authorized signature. airworthiness directive (AD) for all availability of this material at the FAA, General Electric Company (GE) GE90– call 781–238–7125. (i) Related Information 76B, GE90–77B, GE90–85B, GE90–90B, asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (1) Refer to Mandatory Continuing and GE90–94B turbofan engines. This Examining the AD Docket Airworthiness Information (MCAI) EASA proposed AD was prompted by an You may examine the AD docket on Airworthiness Directive 2015–0005, dated uncontained failure of the high-pressure the Internet at http:// January 14, 2015, for related information. compressor (HPC) stage 8–10 spool, www.regulations.gov by searching for This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov leading to an airplane fire. This and locating Docket No. FAA–2015– by searching for and locating Docket No. proposed AD would require eddy 7491; or in person at the Docket FAA–2015–8426. current inspections (ECIs) or ultrasonic Management Facility between 9 a.m. (2) For service information identified in inspections (USIs) of the HPC stage 8– and 5 p.m., Monday through Friday, this AD, contact Dassault Falcon Jet, P.O. Box 10 spool and removing from service except Federal holidays. The AD docket VerDate Sep<11>2014 16:20 Jan 12, 2016 Jkt 238001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\13JAP1.SGM 13JAP1

Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 1583 contains this proposed AD, the FAA’s Determination responsibilities among the various regulatory evaluation, any comments We are proposing this NPRM because levels of government. received, and other information. The we evaluated all the relevant For the reasons discussed above, I street address for the Docket Office information and determined the unsafe certify this proposed regulation: (phone: 800–647–5527) is in the condition described previously is likely (1) Is not a ‘‘significant regulatory ADDRESSES section. Comments will be to exist or develop in other products of action’’ under Executive Order 12866, available in the AD docket shortly after the same type design. (2) Is not a ‘‘significant rule’’ under receipt. the DOT Regulatory Policies and Proposed AD Requirements Procedures (44 FR 11034, February 26, FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine This NPRM would require 1979), Certification Office, FAA, 12 New accomplishing an ECI or USI of the stage (3) Will not affect intrastate aviation England Executive Park, Burlington, MA 8 aft web upper face of the HPC stage in Alaska, and 01803; phone: 781–238–7756; fax: 781– 8–10 spool and removing from service (4) Will not have a significant 238–7199; email: john.frost@faa.gov. those parts that fail inspection. economic impact, positive or negative, on a substantial number of small entities SUPPLEMENTARY INFORMATION: Interim Action under the criteria of the Regulatory Comments Invited We consider this proposed AD Flexibility Act. interim action. GE is determining the We invite you to send any written root cause for the unsafe condition List of Subjects in 14 CFR Part 39 relevant data, views, or arguments about identified in this proposed AD. Once a Air transportation, Aircraft, Aviation this NPRM. Send your comments to an root cause is identified, we might safety, Incorporation by reference, address listed under the ADDRESSES consider additional rulemaking. Safety. section. Include ‘‘Docket No. FAA– 2015–7491; Directorate Identifier 2015– Costs of Compliance The Proposed Amendment NE–39–AD’’ at the beginning of your We estimate that this proposed AD Accordingly, under the authority comments. We specifically invite affects 54 engines installed on airplanes delegated to me by the Administrator, comments on the overall regulatory, of U.S. registry. We also estimate that it the FAA proposes to amend 14 CFR part economic, environmental, and energy will take about 7 hours per engine to 39 as follows: aspects of this NPRM. We will consider comply with this AD. The average labor all comments received by the closing rate is $85 per hour. We estimate one PART 39—AIRWORTHINESS date and may amend this NPRM part will fail inspection at a cost of DIRECTIVES because of those comments. $780,000. Based on these figures, we We will post all comments we estimate the total cost of the AD to U.S. ■ 1. The authority citation for part 39 receive, without change, to http:// operators to be $812,130. continues to read as follows: www.regulations.gov, including any Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking personal information you provide. We Title 49 of the United States Code § 39.13 [Amended] will also post a report summarizing each substantive verbal contact we receive specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding about this NPRM. rules on aviation safety. Subtitle I, the following new airworthiness section 106, describes the authority of directive (AD): Discussion the FAA Administrator. Subtitle VII: General Electric Company: Docket No. FAA– We received a report of an HPC stage Aviation Programs, describes in more 2015–7491; Directorate Identifier 2015– 8–10 spool uncontained failure resulting detail the scope of the Agency’s NE–39–AD. in an airplane fire. Ongoing authority. We are issuing this rulemaking under (a) Comments Due Date investigations have determined that a We must receive comments by March 14, crack initiated in the stage 8 aft web the authority described in Subtitle VII, Part A, Subpart III, Section 44701: 2016. upper face of the HPC 8–10 spool and propagated until spool rupture. The root ‘‘General requirements.’’ Under that (b) Affected ADs cause of the crack initiation is not yet section, Congress charges the FAA with None. known. This condition, if not corrected, promoting safe flight of civil aircraft in air commerce by prescribing regulations (c) Applicability could result in failure of the HPC stage for practices, methods, and procedures This AD applies to General Electric 8–10 spool, uncontained rotor release, Company (GE) GE90–76B, GE90–77B, GE90– damage to the engine, and damage to the the Administrator finds necessary for safety in air commerce. This regulation 85B, GE90–90B, and GE90–94B turbofan airplane. We are issuing this AD to engines with a high-pressure compressor correct the unsafe condition on these is within the scope of that authority (HPC) 8–10 stage spool, part numbers (P/Ns) products. because it addresses an unsafe condition 1694M80G04, 1844M90G01, or 1844M90G02, that is likely to exist or develop on installed. Related Service Information products identified in this rulemaking action. (d) Unsafe Condition We reviewed the following chapters This AD was prompted by an uncontained asabaliauskas on DSK5VPTVN1PROD with PROPOSALS of GE GE90 Engine Manual, GEK100700, Regulatory Findings failure of the HPC stage 8–10 spool. We are Revision 66, dated September 1, 2015: We determined that this proposed AD issuing this AD to prevent failure of the HPC • Chapter 72–31–08, Special would not have federalism implications stage 8–10 spool, uncontained rotor release, Procedure 003, piece-part level ECI, under Executive Order 13132. This damage to the engine, and damage to the • Chapter 72–00–31, Special proposed AD would not have a airplane. Procedure 006, rotor assembly and substantial direct effect on the States, on (e) Compliance module level ECI and, the relationship between the national Comply with this AD within the • Chapter 72–00–31, Special Government and the States, or on the compliance times specified, unless already Procedure 007, rotor assembly level USI. distribution of power and done. VerDate Sep<11>2014 16:20 Jan 12, 2016 Jkt 238001 PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 E:\FR\FM\13JAP1.SGM 13JAP1

1584 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules (1) Perform an eddy current inspection DEPARTMENT OF TRANSPORTATION at the FAA, Transport Airplane (ECI) or ultrasonic inspection (USI) of the Directorate, 1601 Lind Avenue SW., stage 8 aft web upper face of the HPC stage Federal Aviation Administration Renton, WA. For information on the 8–10 spool, before exceeding 10,500 cycles availability of this material at the FAA, since new or within 500 cycles in service, 14 CFR Part 39 call 425–227–1221. after the effective date of this AD, whichever occurs later. [Docket No. FAA–2015–8435; Directorate Examining the AD Docket (2) At each shop visit, perform an ECI or Identifier 2015–NM–049–AD] USI of the stage 8 aft web upper face of the You may examine the AD docket on RIN 2120–AA64 the Internet at http:// HPC stage 8–10 spool. (3) Remove from service any HPC stage 8– www.regulations.gov by searching for Airworthiness Directives; Bombardier, and locating Docket No. FAA–2015– 10 spool that fails the inspection required by Inc. Airplanes 8435; or in person at the Docket paragraphs (e)(1) and (e)(2) of this AD and replace the spool with a spool eligible for AGENCY: Federal Aviation Management Facility between 9 a.m. installation. Administration (FAA), DOT. and 5 p.m., Monday through Friday, (f) Installation Prohibition ACTION: Notice of proposed rulemaking except Federal holidays. The AD docket (NPRM). contains this proposed AD, the After the effective date of this AD, an HPC stage 8–10 spool, P/Ns 1694M80G04, regulatory evaluation, any comments 1844M90G01, and 1844M90G02, is not SUMMARY: We propose to adopt a new received, and other information. The eligible for installation into any engine, airworthiness directive (AD) for certain street address for the Docket Operations unless the spool has passed an ECI or USI Bombardier, Inc. Model BD–700–1A10 office (telephone 800–647–5527) is in required by paragraphs (e)(1) and (e)(2) of and BD–700–1A11 airplanes. This the ADDRESSES section. Comments will this AD. proposed AD was prompted by reports be available in the AD docket shortly (g) Definition of operator inability to open the main after receipt. passenger door following severe hot FOR FURTHER INFORMATION CONTACT: For the purpose of this AD, an engine shop visit is the induction of an engine into the soak conditions. This proposed AD Cesar A. Gomez, Aerospace Engineer, shop for maintenance during which the would require the incorporation of a Airframe and Mechanical Systems compressor discharge pressure seal face is new configuration to the passenger door Branch, ANE–171, FAA, New York exposed. external handle detent to enhance the Aircraft Certification Office (ACO), 1600 performance across the full range of the Stewart Avenue, Suite 410, Westbury, (h) Alternative Methods of Compliance airplane operating temperatures. We are NY 11590; telephone 516–228–7318; fax (AMOCs) proposing this AD to prevent thermal 516–794–5531. The Manager, Engine Certification Office, expansion and permanent deformation FAA, may approve AMOCs for this AD. Use SUPPLEMENTARY INFORMATION: at severe hot soak conditions, creating the procedures found in 14 CFR 39.19 to high friction between the spring pot Comments Invited make your request. You may email your request to: ANE-AD-AMOC@faa.gov. housing and the slider that could result We invite you to send any written in inability to open the main passenger relevant data, views, or arguments about (i) Related Information door and impede evacuation in the this proposed AD. Send your comments (1) For more information about this AD, event of an emergency. to an address listed under the contact John Frost, Aerospace Engineer, DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. Engine Certification Office, FAA, 12 New this proposed AD by February 29, 2016. FAA–2015–8435; Directorate Identifier England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238– ADDRESSES: You may send comments, 2015–NM–049–AD’’ at the beginning of 7199; email: john.frost@faa.gov. using the procedures found in 14 CFR your comments. We specifically invite (2) GE GE90 Engine Manual, GEK100700, 11.43 and 11.45, by any of the following comments on the overall regulatory, Revision 66, dated September 1, 2015, methods: economic, environmental, and energy Chapter 72–31–08, Special Procedure 003, • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will Chapter 72–00–31, Special Procedure 006, http://www.regulations.gov. Follow the consider all comments received by the and Chapter 72–00–31, Special Procedure instructions for submitting comments. closing date and may amend this 007, rotor assembly level USI can be obtained • Fax: 202–493–2251. proposed AD based on those comments. from General Electric Company, using the • Mail: U.S. Department of We will post all comments we contact information in paragraph (i)(3) of this AD. Transportation, Docket Operations, M– receive, without change, to http:// (3) For service information identified in 30, West Building Ground Floor, Room www.regulations.gov, including any this proposed AD, contact General Electric W12–140, 1200 New Jersey Avenue SE., personal information you provide. We Company, GE-Aviation, Room 285, 1 Washington, DC 20590. will also post a report summarizing each Neumann Way, Cincinnati, OH 45215, • Hand Delivery: U.S. Department of substantive verbal contact we receive phone: 513–552–3272; fax: 513–552–3329; Transportation, Docket Operations, M– about this proposed AD. email: geae.aoc@ge.com. 30, West Building Ground Floor, Room (4) You may view this service information W12–140, 1200 New Jersey Avenue SE., Discussion at the FAA, Engine & Propeller Directorate, Washington, DC, between 9 a.m. and 5 Transport Canada Civil Aviation 12 New England Executive Park, Burlington, (TCCA), which is the aviation authority p.m., Monday through Friday, except asabaliauskas on DSK5VPTVN1PROD with PROPOSALS MA. For information on the availability of this material at the FAA, call 781–238–7125. Federal holidays. for Canada, has issued Canadian For service information identified in Airworthiness Directive CF–2015–03, Issued in Burlington, Massachusetts, on this proposed AD, contact Bombardier, dated March 13, 2015 (referred to after December 22, 2015. Inc., 400 Côte-Vertu Road West, Dorval, this as the Mandatory Continuing Colleen M. D’Alessandro, Québec H4S 1Y9, Canada; telephone Airworthiness Information, or ‘‘the Directorate Manager, Engine & Propeller 514–855–5000; fax 514–855–7401; email MCAI’’), to correct an unsafe condition Directorate, Aircraft Certification Service. thd.crj@aero.bombardier.com; Internet for certain Bombardier Inc. Model BD– [FR Doc. 2015–33097 Filed 1–12–16; 8:45 am] http://www.bombardier.com. You may 700–1A10 and BD–700–1A11 airplanes. BILLING CODE 4910–13–P view this referenced service information The MCAI states: VerDate Sep<11>2014 16:20 Jan 12, 2016 Jkt 238001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\13JAP1.SGM 13JAP1


Document Created: 2016-01-13 01:01:19
Document Modified: 2016-01-13 01:01:19
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 March 14, 2016.
ContactJohn Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected]
FR Citation81 FR 1582 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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