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 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 


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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. 


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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 Coˆte-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: 


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