Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 61091 

Issued in Renton, Washington, on 

September 30, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–25495 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0913; Directorate 

Identifier 2012–NE–23–AD; Amendment 39– 

18261; AD 2015–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

(Type Certificate Previously Held by 

AlliedSignal Inc., Garrett Engine 

Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. TPE331–5, 

–5A, –5AB, –5B, –10, –10R, –10U, 

–10UF, –10UG, –10UGR, and –10UR 

model turboprop engines. This AD was 

prompted by engine propeller shaft 

coupling failures, leading to unexpected 

propeller pitch changes causing 

increased aerodynamic and asymmetric 

drag on the airplanes using these 

engines. This AD requires removing 

certain part number (P/N) engine 

propeller shaft couplings from service. 

This AD also requires inserting a copy 

of certain airplane operating procedures 

into applicable flight manuals. We are 

issuing this AD to prevent loss of 

airplane control, leading to an accident. 

DATES: This AD is effective November 

13, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Honeywell 

International Inc., 111 S. 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Internet: http://

portal.honeywell.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. It is also available on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2012–0913. 

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– 

0913; 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 regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Honeywell 

International Inc. TPE331–5, –5A, 

–5AB, –5B, –10, –10R, –10U, –10UF, 

–10UG, –10UGR, and –10UR model 

turboprop engines. The NPRM 

published in the Federal Register on 

May 12, 2014 (79 FR 26906). The NPRM 

was prompted by numerous reports of 

engine propeller shaft coupling failures, 

leading to engine overspeed and 

unexpected propeller pitch changes. 

This condition causes high aerodynamic 

and asymmetric drag that has resulted 

in uncommanded airplane yaw and roll. 

The NPRM proposed to require 

removing certain P/N engine propeller 

shaft couplings from service within 

certain compliance times to address the 

flight safety risk. The NPRM also 

proposed to insert a copy of certain 

airplane operating procedures into the 

applicable flight manuals. These 

procedures describe an emergency 

procedure for pilot reaction to an engine 

overspeed event after an engine 

propeller shaft coupling failure. We are 

issuing this AD to prevent loss of 

airplane control, leading to an accident. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 26906, 

May 12, 2014) and the FAA’s response 

to the comment. 

Request To Change Compliance Time 

Basis 

Honeywell International questioned 

whether compliance time should be 

stated in flight hours as opposed to 

flight cycles as used in the NPRM (79 

FR 26906, May 12, 2014). Major 

periodic inspections are based on hours 

and not cycles. 

We disagree. The FAA practice of 

stating compliance time is based on the 

component’s mode of failure. In this 

case the failure mode was fatigue; 

therefore, a compliance time in flight 

cycles is appropriate. We did not change 

this AD. 

Clarified Requirement 

Since we issued the NPRM (79 FR 

26906, May 12, 2014), we discovered 

that paragraph (e)(4) of the Compliance 

section required clarification. We 

clarified that paragraph in this AD by 

deleting the requirement to insert a copy 

of Honeywell International Inc. 

Operating Information Letter (OIL) and 

requiring that Figure 1 to Paragraph 

(e)—Airplane Operating Procedures be 

inserted. Reference to the OIL was 

added as related information. The 

replacement procedure provides 

simplified, more concise text, for 

increased clarity. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with clarification. 

Costs of Compliance 

We estimate that this AD will affect 

485 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about one hour per engine to 

perform the actions required by this AD, 

if done at the next scheduled turbine 

hot section inspection (HSI), and 40 

hours per engine if done during an 

unscheduled access of the engine 

propeller shaft coupling. We also 

estimate that 400 engines will have the 

replacement actions done at a scheduled 

time of next turbine HSI, and 85 engines 

will have the replacement actions done 

at an unscheduled access of the engine 

propeller shaft coupling. The average 

labor rate is $85 per hour. Required 

parts will cost about $12,000 per engine. 

Based on these figures, we estimate the 

total cost of this AD to U.S. operators to 

be $6,143,000. 


rmajette on DSK7SPTVN1PROD with RULES
61092 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 

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 

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 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): 

2015–18–03 Honeywell International Inc. 

(Type Certificate previously held by 

AlliedSignal Inc., Garrett Engine 

Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona): 

Docket No. FAA–2012–0913; Directorate 

Identifier 2012–NE–23–AD. 

(a) Effective Date 

This AD is effective November 13, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell 

International Inc. TPE331–5, –5A, –5AB, 

–5B, –10, –10R, –10U, –10UF, –10UG, 

–10UGR, and –10UR model turboprop 

engines, with an engine propeller shaft 

coupling, part number (P/N) 3107065–1, 

865888–3, 865888–6, or 865888–8, installed. 

(d) Unsafe Condition 

This AD was prompted by engine propeller 

shaft coupling failures, leading to unexpected 

propeller pitch changes causing increased 

aerodynamic and asymmetric drag on the 

airplanes using these engines. We are issuing 

this AD to prevent loss of airplane control, 

leading to an accident. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Engines Installed in Mitsubishi MU–2B 

Series (MU–2 Series) Airplanes: 

(i) Remove from service the affected engine 

propeller shaft coupling at the earliest of the 

following: 

(A) Next piece-part exposure; or 

(B) Next turbine (hot) section inspection 

(HSI); or 

(C) Before accumulating an additional 

1,200 cycles after the effective date of this 

AD. 

(2) Engines Installed in Construcciones 

Aeronauticas, S.A. (CASA) C–212 Series, and 

Twin Commander 690 and 695 Series 

(Jetprop Commander) Airplanes: 

(i) Remove from service the affected engine 

propeller shaft coupling at the earliest of the 

following: 

(A) Next piece-part exposure; or 

(B) Next turbine HSI; or 

(C) Before accumulating an additional 

2,400 cycles after the effective date of this 

AD. 

(3) Engines Installed in British Aerospace 

Jetstream 3101 Series, Dornier Luftfahrt 

Dornier 228 Series, and M7 (formerly 

Fairchild, Swearingen) SA226 and SA227 

Series Airplanes, and all other airplanes not 

listed in this AD using affected engines: 

(i) Remove from service the affected engine 

propeller shaft coupling at the earliest of the 

following: 

(A) Next piece-part exposure; or 

(B) Next turbine HSI; or 

(C) Before accumulating an additional 

3,600 cycles after the effective date of this 

AD. 

(4) Within 60 days after the effective date 

of this AD, for all airplanes that use the 

affected engines, insert a copy of Figure 1 to 

paragraph (e) of this AD, into the Emergency 

Procedures Section of the Airplane Flight 

Manual (AFM), Pilot Operating Handbook 

(POH), and the Manufacturer’s Operating 

Manual (MOM). 


rmajette on DSK7SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 61093 

(f) Definition 

For the purpose of this AD, next piece-part 

exposure is when the nose cone assembly is 

removed from the engine. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any engine propeller shaft coupling, 

P/N 3107065–1, 865888–3, 865888–6, or 

865888–8, into any engine. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(2) Allied-Signal Aerospace Company 

Service Bulletin No. TPE331–72–0873, 

Revision 1, dated May 20, 1993 and 

Honeywell International Inc. Operating 

Information Letter OI331–26, dated March 2, 

2010, which are not incorporated by 

reference in this AD, can be obtained from 

Honeywell International, using the contact 

information in paragraph (i)(3) of this AD. 

(3) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; phone: 800–601–3099; Internet: http:// 

portal.honeywell.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. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on: 

October 2, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25606 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0108; Directorate 

Identifier 2011–NM–049–AD; Amendment 

39–18215; AD 2015–15–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–13– 

01 for certain The Boeing Company 

Model 767 airplanes. AD 2003–13–01 

required an inspection to detect cracks 

and fractures of the outboard hinge 

fitting assemblies on the trailing edge of 

the inboard main flap, and follow-on 

and corrective actions if necessary. For 

certain airplanes, AD 2003–13–01 

required an inspection to determine if a 

tool runout option has been performed 

in the area. This new AD reduces 

certain compliance times, adds 

airplanes to the applicability, and 

provides optional terminating action for 

certain inspections. This AD was 

prompted by reports of hinge assembly 

fractures found before certain required 

compliance times in AD 2003–13–01. 

We are issuing this AD to prevent the 

inboard aft flap from separating from the 

wing and potentially striking the 

airplane, which could result in damage 

to the surrounding structure and 

potential personal injury. 

DATES: This AD is effective November 

13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 29, 2003 (68 FR 

37402, June 24, 2003). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; 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–2012– 

0108. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.govby searching for 

and locating Docket No. FAA–2012– 

0108; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


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