Airworthiness Directives; CFE Company Turbofan Engines, 52-54 [2016-30951]

Download as PDF 52 Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Proposed Rules 5889, 5903, 5907, 5916, 5924, 5958, 5984, 5994, 6000, 6004, 6054, 6080, 6107, 6166, 6176, 6234, 6266, 6293, 6335, 6344, 6365, 6430, and 6444. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Reason This AD was prompted by in-service experience and further analysis, which showed that the galley 5 without kick-load retainers was unable to withstand the expected loading during several flight phases or in case of emergency landing. We are issuing this AD to prevent galley/trolley detachment and collapse into an adjacent cabin aisle or cabin zone, possibly spreading loose galley equipment items or compartment doors, or leaking fluids. These hazards could block an evacuation route and result in injury to crew or passengers. (f) Compliance Comply with this AD within the compliance times specified, unless already done. sradovich on DSK3GMQ082PROD with PROPOSALS (g) Install Kick-Load Retainers Within 12 months after the effective date of this AD, install kick-load retainers on the galley 5 trolley compartments as specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. (1) For Airbus Model A319 airplanes, manufacturer’s serial numbers 5678, 5698, 5704, 5745, 5753, 5761, 5781, 5786, 5788, 5789, 5798, 5810, 5827, and 5842, do the installation in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–25–1B29, dated June 19, 2014. (2) For Airbus Model A320 airplanes, manufacturer’s serial numbers 5458, 5517, 5624, 5672, and 5804, do the installation in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 25–1B30, dated June 19, 2014. (3) For airplanes not identified in paragraph (g)(1) or (g)(2) of this AD, use a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116- VerDate Sep<11>2014 22:13 Dec 30, 2016 Jkt 241001 AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0040, dated March 2, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–9519. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. Issued in Renton, Washington, on December 15, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–30806 Filed 12–30–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; CFE Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain CFE Company (CFE) turbofan engines. This proposed AD was prompted by a quality escape for high-pressure compressor (HPC) impellers made from forgings with nonconforming material grain size. This proposed AD would require removal of the HPC impeller. We are proposing this AD to correct the unsafe condition on these products. SUMMARY: Frm 00005 Fmt 4702 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9380; 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 Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238– 7199; email: martin.adler@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited [Docket No. FAA–2016–9380; Directorate Identifier 2016–NE–21–AD] PO 00000 We must receive comments on this proposed AD by February 17, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: Sfmt 4702 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– 2016–9380; Directorate Identifier 2016– NE–21–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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. E:\FR\FM\03JAP1.SGM 03JAP1 53 Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Proposed Rules Discussion We propose to adopt an AD for certain CFE CFE738–1–1B model turbofan engines with HPC impeller, part number (P/N) 6079T77P07 or P/N 6079T77P09 installed. This proposed AD was prompted by a quality escape for HPC impellers made from forgings with nonconforming material grain size. This condition, if not corrected, could result in failure of the HPC impeller, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed CFE Service Bulletin (SB) CFE738–72–8080, Revision 0, dated August 18, 2016. The SB describes procedures for replacing specific serial numbered HPC impellers, P/N 6079T77P07 or P/N 6079T77P09. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require removal of affected HPC impellers from service and replacement with a part eligible for installation. Costs of Compliance We estimate that this proposed AD affects 176 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Pro-rated HPC impeller ................................................................................... 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. 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 sradovich on DSK3GMQ082PROD with PROPOSALS Authority: 49 U.S.C. 106(g), 40113, 44701. 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 22:13 Dec 30, 2016 Jkt 241001 § 39.13 Cost per product $42,240 $42,240 Cost on U.S. operators $7,434,240 high-pressure compressor (HPC) impeller, part number (P/N) 6079T77P07 or P/N 6079T77P09, with a serial number listed in CFE Service Bulletin (SB) CFE738–72–8080, Revision 0, dated August 18, 2016, installed. (d) Subject Joint Aircraft System Component (JASC) of America Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by a quality escape for HPC impellers made from forgings with nonconforming material grain size. We are issuing this AD to prevent uncontained failure of the HPC impeller, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Action 1. The authority citation for part 39 continues to read as follows: ■ Regulatory Findings VerDate Sep<11>2014 $0.00 Parts cost Remove all affected HPC impellers from service at the next piece-part exposure and replace with a part eligible for installation. (h) Definition [Amended] ■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): For the purposes of this AD, ‘‘piece-part exposure’’ is defined as separation of the impeller from the compressor rotor assembly. CFE Company: Docket No. FAA–2016–9380; Directorate Identifier 2016–NE–21–AD. (i) Alternative Methods of Compliance (AMOCs) (a) Comments Due Date We must receive comments by February 17, 2017. (1) 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. (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. (b) Affected ADs None. (c) Applicability This AD applies to CFE Company (CFE) CFE738–1–1B model turbofan engines with a PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\03JAP1.SGM 03JAP1 54 Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Proposed Rules (j) Related Information (1) For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238–7199; email: martin.adler@faa.gov. (2) For service information identified in this proposed AD, contact CFE Company, 111 S. 34th Street, Phoenix, Arizona 85034–2802; phone: 800–601–3099; Internet: https:// www.myaerospace.com. (3) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on December 15, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–30951 Filed 12–30–16; 8:45 am] BILLING CODE 4910–13–P Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9520; Directorate Identifier 2016–NM–163–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This proposed AD was prompted by reports of cracks on the underwing longerons. This proposed AD would require repetitive inspections of the left and right side underwing longerons for any crack, and related investigative and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 17, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. sradovich on DSK3GMQ082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 22:13 Dec 30, 2016 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone: 562–797–1717; Internet: https:// www.myboeingfleet.com. You may view this referenced service information at the 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. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9520. Jkt 241001 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9520; 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: Eric Lin, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6412; fax: 425– 917–6590; email: eric.lin@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–9520; Directorate Identifier 2016– NM–163–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 https:// www.regulations.gov, including any PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report indicating that cracks have been found which led to an underwing longeron becoming severed. The first underwing longeron crack was discovered in service. An operator had reports of a fuel smell in the forward cargo area. During a subsequent investigation, a crack was found in the center wing tank that was attributed to the longeron crack. All models except some Model 777–200 airplanes without a center wing tank are affected by the potential for a fuel leak into the forward cargo area. Subsequently, three more operators have reported cracks on the left underwing longeron. The cracks have been reported in Model 777–300ER and 777–200 airplanes. The cracks have been reported as early as 3,784 flight cycles and 31,240 flight hours. As the cracks grow in the longeron, further cracking has been reported and three operators noted the lower front spar chord had cracked. This condition, if not corrected, could result in fuel leakage into the forward cargo area and consequent increased risk of a fire or, in a more severe case, could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 777–53A0081, dated September 8, 2016 (‘‘ASB 777–53A0081, Revision 0’’). The service information describes procedures for repetitive detailed inspections, ultrasonic inspections, and high frequency eddy current (HFEC) inspections of the left and right side longerons, and related investigative and corrective actions if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under E:\FR\FM\03JAP1.SGM 03JAP1

Agencies

[Federal Register Volume 82, Number 1 (Tuesday, January 3, 2017)]
[Proposed Rules]
[Pages 52-54]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30951]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9380; Directorate Identifier 2016-NE-21-AD]
RIN 2120-AA64


Airworthiness Directives; CFE Company Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain CFE Company (CFE) turbofan engines. This proposed AD was 
prompted by a quality escape for high-pressure compressor (HPC) 
impellers made from forgings with nonconforming material grain size. 
This proposed AD would require removal of the HPC impeller. We are 
proposing this AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by February 17, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9380; 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 Certification Office, FAA, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7157; fax: 781-238-7199; email: 
martin.adler@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-9380; 
Directorate Identifier 2016-NE-21-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 https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

[[Page 53]]

Discussion

    We propose to adopt an AD for certain CFE CFE738-1-1B model 
turbofan engines with HPC impeller, part number (P/N) 6079T77P07 or P/N 
6079T77P09 installed. This proposed AD was prompted by a quality escape 
for HPC impellers made from forgings with nonconforming material grain 
size. This condition, if not corrected, could result in failure of the 
HPC impeller, damage to the engine, and damage to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed CFE Service Bulletin (SB) CFE738-72-8080, Revision 0, 
dated August 18, 2016. The SB describes procedures for replacing 
specific serial numbered HPC impellers, P/N 6079T77P07 or P/N 
6079T77P09. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require removal of affected HPC impellers 
from service and replacement with a part eligible for installation.

Costs of Compliance

    We estimate that this proposed AD affects 176 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                     Action                         Labor cost      Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Pro-rated HPC impeller..........................           $0.00         $42,240         $42,240      $7,434,240
----------------------------------------------------------------------------------------------------------------

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):

CFE Company: Docket No. FAA-2016-9380; Directorate Identifier 2016-
NE-21-AD.

(a) Comments Due Date

    We must receive comments by February 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFE Company (CFE) CFE738-1-1B model turbofan 
engines with a high-pressure compressor (HPC) impeller, part number 
(P/N) 6079T77P07 or P/N 6079T77P09, with a serial number listed in 
CFE Service Bulletin (SB) CFE738-72-8080, Revision 0, dated August 
18, 2016, installed.

(d) Subject

    Joint Aircraft System Component (JASC) of America Code 7230, 
Turbine Engine Compressor Section.

(e) Unsafe Condition

    This AD was prompted by a quality escape for HPC impellers made 
from forgings with nonconforming material grain size. We are issuing 
this AD to prevent uncontained failure of the HPC impeller, damage 
to the engine, and damage to the airplane.

(f) Compliance

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

(g) Required Action

    Remove all affected HPC impellers from service at the next 
piece-part exposure and replace with a part eligible for 
installation.

(h) Definition

    For the purposes of this AD, ``piece-part exposure'' is defined 
as separation of the impeller from the compressor rotor assembly.

(i) Alternative Methods of Compliance (AMOCs)

    (1) 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.
    (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.

[[Page 54]]

(j) Related Information

    (1) For more information about this AD, contact Martin Adler, 
Aerospace Engineer, Engine Certification Office, FAA, 1200 District 
Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-
7199; email: martin.adler@faa.gov.
    (2) For service information identified in this proposed AD, 
contact CFE Company, 111 S. 34th Street, Phoenix, Arizona 85034-
2802; phone: 800-601-3099; Internet: https://www.myaerospace.com.
    (3) You may view this service information at FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on December 15, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30951 Filed 12-30-16; 8:45 am]
BILLING CODE 4910-13-P
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