Federal Register / Vol. 81, No. 142 / Monday, July 25, 2016 / Rules and Regulations 48321 

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

44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for Bombardier Model DHC–8– 

100/–200/–300 series airplanes 

modified by Avmax Aviation Services 

Inc. 

In lieu of the requirements of 14 CFR 

25.1353(c)(1) through (c)(4) at 

Amendment 25–51, all rechargeable 

lithium batteries and battery systems on 

Model DHC–8–100/–200/–300 

airplanes, as modified by Avmax 

Aviation Services Inc., must be designed 

and installed as follows: 

1. Safe cell temperatures and 

pressures must be maintained during 

any foreseeable charging or discharging 

condition and during any failure of the 

charging or battery monitoring system 

not shown to be extremely remote. The 

rechargeable lithium battery installation 

must preclude explosion in the event of 

those failures. 

2. Design of the rechargeable lithium 

batteries must preclude the occurrence 

of self-sustaining, uncontrolled 

increases in temperature or pressure. 

3. No explosive or toxic gases emitted 

by any rechargeable lithium battery in 

normal operation, or as the result of any 

failure of the battery charging system, 

monitoring system, or battery 

installation which is not shown to be 

extremely remote, may accumulate in 

hazardous quantities within the 

airplane. 

4. Installations of rechargeable 

lithium batteries must meet the 

requirements of § 25.863(a) through (d). 

5. No corrosive fluids or gases that 

may escape from any rechargeable 

lithium battery may damage 

surrounding structure or any adjacent 

systems, equipment, or electrical wiring 

of the airplane in such a way as to cause 

a major or more-severe failure 

condition, in accordance with 

§ 25.1309(b) and applicable regulatory 

guidance. 

6. Each rechargeable lithium battery 

installation must have provisions to 

prevent any hazardous effect on 

structure or essential systems caused by 

the maximum amount of heat the 

battery can generate during a short 

circuit of the battery or of its individual 

cells. 

7. Lithium battery installations must 

have a system to control the charging 

rate of the battery automatically, 

designed to prevent battery overheating 

or overcharging, and, 

a. A battery-temperature sensing and 

over-temperature warning system with a 

means for automatically disconnecting 

the battery from its charging source in 

the event of an over-temperature 

condition, or, 

b. A battery-failure sensing and 

warning system with a means for 

automatically disconnecting the battery 

from its charging source in the event of 

battery failure. 

8. Any rechargeable lithium battery 

installation, the function of which is 

required for safe operation of the 

airplane, must incorporate a monitoring 

and warning feature that will provide an 

indication to the appropriate flight 

crewmembers whenever the state-ofcharge of the batteries has fallen below 

levels considered acceptable for 

dispatch of the airplane. 

9. The instructions for continued 

airworthiness required by § 25.1529 

must contain maintenance requirements 

to assure that the battery is sufficiently 

charged at appropriate intervals 

specified by the battery manufacturer 

and the equipment manufacturer that 

contain the rechargeable lithium battery 

or rechargeable lithium battery system. 

This is required to ensure that 

rechargeable lithium batteries and 

rechargeable lithium battery systems 

will not degrade below specified 

ampere-hour levels sufficient to power 

the airplane systems for intended 

applications. The instructions for 

continued airworthiness must also 

contain procedures for the maintenance 

of batteries in spares storage to prevent 

the replacement of batteries with 

batteries that have experienced 

degraded charge retention ability or 

other damage due to prolonged storage 

at a low state of charge. Replacement 

batteries must be of the same 

manufacturer and part number as 

approved by the FAA. Precautions 

should be included, in the instructions 

for continued airworthiness 

maintenance instructions, to prevent 

mishandling of the rechargeable lithium 

battery and rechargeable lithium battery 

systems, which could result in shortcircuit, or other unintentional impact 

damage caused by dropping batteries or 

other destructive means that could 

result in personal injury or property 

damage. 

Note 1: The term ‘‘sufficiently charged’’ 

means that the battery will retain enough of 

a charge, expressed in ampere-hours, to 

ensure that the battery cells will not be 

damaged. A battery cell may be damaged by 

lowering the charge below a point where the 

battery experiences a reduction in the ability 

to charge and retain a full charge. This 

reduction would be greater than the 

reduction that may result from normal 

operational degradation. 

Note 2: These special conditions are not 

intended to replace § 25.1353(c) in the 

certification basis of Bombardier Model 

DHC–8–100/–200/–300 series airplanes. 

These special conditions apply only to 

rechargeable lithium batteries and lithium 

battery systems and their installations on 

Bombardier Model DHC–8–100/–200/–300 

series airplanes, as modified by Avmax. The 

requirements of § 25.1353(c) remain in effect 

for batteries and battery installations on 

Bombardier Model DHC–8–100/–200/–300 

series airplanes that do not use lithium 

batteries. 

Issued in Renton, Washington, on July 15, 

2016. 

Michael Kaszycki, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–17428 Filed 7–22–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1289; Directorate 

Identifier 2012–NE–43–AD; Amendment 39– 

18591; AD 2016–14–10] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. Turbofan Engines 

Modified by Supplemental Type 

Certificate SE00034EN 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2013–02– 

02 for certain CFM International, S.A. 

CFM56–3, CFM56–3B, and CFM56–3C 

turbofan engines. AD 2013–02–02 

required removal from service of certain 

high-pressure turbine (HPT) disks 

manufactured by Global Material 

Solutions of Pratt & Whitney, at reduced 

maximum life limits. This AD corrects 

the serial numbers (S/Ns) listed in AD 

2013–02–02. This AD was prompted by 

reports that certain HPT disk S/Ns in 

AD 2013–02–02 and in certain Pratt & 

Whitney service information are 

incorrect. We are issuing this AD to 

prevent uncontained release of multiple 

turbine blades, damage to the engine, 

and damage to the airplane. 

DATES: This AD is effective August 9, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 


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48322 Federal Register / Vol. 81, No. 142 / Monday, July 25, 2016 / Rules and Regulations 

of a certain publication listed in this AD 

as of August 9, 2016. 

We must receive any comments on 

this AD by September 8, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Pratt & Whitney, 400 

Main St., East Hartford, CT 06108; 

phone: 860–565–7700; fax: 860–565– 

1605. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2012– 

1289. 

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–2012– 

1289; 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 AD, the mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

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: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7765; fax: 781–238–7199; 

email: kenneth.steeves@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 14, 2013, we issued AD 

2013–02–02, Amendment 39–17323 (78 

FR 5712, January 28, 2013), (‘‘AD 2013– 

02–02’’) for all CFM56–3, CFM56–3B, 

and CFM56–3C turbofan engines 

modified by Supplemental Type 

Certificate SE00034EN, with certain 

HPT disks, installed. AD 2013–02–02 

required removal from service of certain 

high-pressure turbine (HPT) disks 

manufactured by Global Material 

Solutions of Pratt & Whitney, at reduced 

maximum life limits. AD 2013–02–02 

resulted from a report of a forging 

process error during manufacture of 

these HPT disks. We issued AD 2013– 

02–02 to prevent uncontained release of 

multiple turbine blades, damage to the 

engine, and damage to the airplane. 

Actions Since AD 2013–02–02 Was 

Issued 

Since we issued AD 2013–02–02, we 

received reports that certain HPT disk 

S/Ns GLKBAA9307, GLKBAA9335, 

GLKBAA9404, GLKBAA9407, and 

GLKBAA9409, in AD 2013–02–02 and 

in certain Pratt & Whitney service 

information are incorrect. The correct S/ 

Ns are: GKLBAA9307, GKLBAA9335, 

GKLBAA9404, GKLBAA9407, and 

GKLBAA9409. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Pratt & Whitney Corp. 

Special Instruction No. 6F–12, Revision 

A, dated May 17, 2016. The Special 

Instruction describes procedures for 

reducing the maximum life limit for 

affected HPT disks. 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 issuing 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. 

AD Requirements 

This AD requires removal from 

service of affected HPT disks at certain 

recalculated reduced maximum life 

limits. 

FAA’s Justification and Determination 

of the Effective Date 

No domestic operators use this 

product. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–1289; Directorate Identifier 2012– 

NE–43–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 0 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 61 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $0 per engine. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $0. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 


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Federal Register / Vol. 81, No. 142 / Monday, July 25, 2016 / Rules and Regulations 48323 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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 

removing airworthiness directive (AD) 

2013–02–02, Amendment 39–17323 (78 

FR 5712, January 28, 2013), (‘‘AD 2013– 

02–02’’), and adding the following new 

AD: 

2016–14–10 CFM International, S.A. 

Turbofan Engines Modified by 

Supplemental Type Certificate 

SE00034EN: Amendment 39–18591; 

Docket No. FAA–2012–1289; Directorate 

Identifier 2012–NE–43–AD. 

(a) Effective Date 

This AD is effective August 9, 2016. 

(b) Affected ADs 

This AD supersedes AD 2013–02–02. 

(c) Applicability 

This AD applies to CFM International, S.A. 

CFM56–3, CFM56–3B, and CFM56–3C 

turbofan engines, modified by Supplemental 

Type Certificate SE00034EN, with a highpressure turbine (HPT) disk, part number (P/ 

N) 880026, serial number (S/N) 

GKLBAA9307, GKLBAA9335, GKLBAA9404, 

GKLBAA9407, or GKLBAA9409, installed. 

(d) Unsafe Condition 

This AD was prompted by reports that 

certain HPT disk serial numbers in AD 2013– 

02–02 and in certain Pratt & Whitney service 

information are incorrect. We are issuing this 

AD to prevent uncontained release of 

multiple turbine blades, damage to the 

engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For CFM56–3, CFM56–3B, and CFM56– 

3C turbofan engines operating to 20,100 lbs 

maximum takeoff (MTO) thrust, remove the 

HPT disk from service on or before 

accumulating 8,000 cycles-since-new (CSN). 

(2) For CFM56–3B and CFM56–3C turbofan 

engines operating to 22,100 lbs MTO thrust, 

remove the HPT disk from service on or 

before accumulating 8,000 CSN. 

(3) For CFM56–3C turbofan engines 

operating to 23,500 lbs MTO thrust, remove 

the HPT disk from service on or before 

accumulating 4,000 CSN. 

(4) For HPT disks that have been used in 

multiple models or thrust installations, use 

the formula in the ADDED DATA section of 

Pratt & Whitney Special Instruction 6F–12, 

Revision A, dated May 17, 2016 to calculate 

the remaining life on the disk. 

(f) 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. 

(g) Related Information 

For more information about this AD, 

contact Kenneth Steeves, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7765; fax: 781–238–7199; email: 

kenneth.steeves@faa.gov. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Pratt & Whitney Corp. Special 

Instruction No. 6F–12, Revision A, dated 

May 17, 2016. 

(ii) Reserved. 

(3) For Pratt & Whitney service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, CT 

06108; phone: 860–565–7700; fax: 860–565– 

1605. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

July 11, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–17442 Filed 7–22–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 93 

[Docket No.: FAA–2010–0302; Amdt. No. 

93–99] 

RIN 2120–AK84 

Extension of the Requirement for 

Helicopters to Use the New York North 

Shore Helicopter Route 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rulemaking amends the 

expiration date of the final rule 

requiring pilots operating civil 

helicopters under Visual Flight Rules to 

use the New York North Shore 

Helicopter Route when operating along 

that area of Long Island, New York. The 

current rule expires on August 6, 2016. 

The FAA finds it necessary to extend 

the rule for an additional four years to 

preserve the current operating 

environment while the FAA conducts 

ongoing helicopter research that will be 

considered to determine appropriate 

future actions. 

DATES: This final rule is effective August 

7, 2016, through August 6, 2020. 

ADDRESSES: For information on where to 

obtain copies of rulemaking documents 

and other information related to this 

final rule, see ‘‘How To Obtain 

Additional Information’’ in the 

SUPPLEMENTARY INFORMATION section of 

this document. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Kenneth Ready, Airspace 

and Rules Team, AJV–113, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone (202) 

267–3396; email kenneth.ready@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules on 

aviation safety is found in Title 49 of the 


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