### 1582 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

TABLE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### THIS 

### AD—N ORMAL 

### P ROCEDURES AND 

### L IMITATIONS

Affected airplane/configuration Applicable AFM change

Model Myste ` re Falcon 900 airplanes ....................................................... Change Proposal 118 (TC118), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ dated December 18, 2014, to the Dassault Myste ` re Falcon 900 Airplane Flight Manual, DTM20103. Model Myste ` re Falcon 900 airplanes with Dassault Aviation production modification M1975, or production modification M2695 embodied, or modified in service by Dassault Aviation Service Bulletin F900–250 (‘‘Falcon 900 C’’ version). Change Proposal 48 (TC048), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ dated December 16, 2014, to the Dassault Myste ` re Falcon 900, F900C Version, Airplane Flight Manual (FM900C), TC048.

Model Falcon 900EX airplanes ................................................................ Change Proposal 12 (CP012), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ Dassault Falcon 900EX Airplane Flight Manual DTM561.Model Falcon 900EX airplanes with Dassault Aviation production modification M3083 embodied (Falcon 900EX ‘‘EASy’’ version). Change Proposal 31 (CP031), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ Dassault Falcon 900EX EASy, Airplane Flight Manual DGT84972).Model Falcon 2000EX airplanes .............................................................. Change Proposal 17 (CP017), ‘‘AFM: Yaw Damper Off in Line Up Procedure,’’ dated January 23, 2015, to the Dassault Falcon 2000EX Airplane Flight Manual, DGT84278. Model Falcon 2000EX airplanes with Dassault Aviation production

modification M1691 embodied (Falcon 2000EX ‘‘EASy’’ version). Change Proposal 46 (CP046), ‘‘AFM: Yaw Damper Off In Line Up Procedure,’’ dated December 15, 2014, to the Dassault Falcon 2000EX EASy Version, Airplane Flight Manual, DGT88898.

(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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone 425–227–1137; fax 425–227– 1149. Information may be emailed to: 9- ANM-116-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 Dassault Aviation’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 2015–0005, dated January 14, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–8426.

(2) For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// www.dassaultfalcon.com. You may view this 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.

Issued in Renton, Washington, on December 23, 2015. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–33178 Filed 1–12–16; 8:45 am]

**BILLING CODE 4910–13–P**

**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).

**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: geae.aoc@ge.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– 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


### 1583 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

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: john.frost@faa.gov.

**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** 

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

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

**§ 39.13 [Amended]**

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


### 1584 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

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

(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: john.frost@faa.gov.

(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: geae.aoc@ge.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 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 DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–8435; Directorate Identifier 2015–NM–049–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–700–1A10 and BD–700–1A11 airplanes. This proposed AD was prompted by reports of operator inability to open the main passenger door following severe hot soak conditions. This proposed AD would require the incorporation of a new configuration to the passenger door external handle detent to enhance the performance across the full range of the airplane operating temperatures. We are proposing this AD to prevent thermal expansion and permanent deformation at severe hot soak conditions, creating high friction between the spring pot housing and the slider that could result in inability to open the main passenger door and impede evacuation in the event of an emergency.

**DATES :**  We must receive comments on this proposed AD by February 29, 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Bombardier, Inc., 400 Co ˆ te-Vertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.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. 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– 8435; 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 Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax
516–794–5531.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2015–8435; Directorate Identifier 2015–NM–049–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 based on 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

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2015–03, dated March 13, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier Inc. Model BD– 700–1A10 and BD–700–1A11 airplanes. The MCAI states: