This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

17412 

Vol. 81, No. 60 

Tuesday, March 29, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23706; Directorate 

Identifier 2006–NE–03–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2015–12– 

04, which applies to all Honeywell 

International Inc. (Honeywell) TPE331– 

1, –2, –2UA, –3U, –3UW, –5, –5A, 

–5AB, –5B, –6, –6A, –10, –10AV, 

–10GP, –10GT, –10P, –10R, –10T, –10U, 

–10UA, –10UF, –10UG, –10UGR, 

–10UR, –11U, –12JR, –12UA, –12UAR, 

and –12UHR turboprop engines with 

certain Woodward fuel control unit 

(FCU) assemblies, installed. AD 2015– 

12–04 currently requires initial and 

repetitive dimensional inspections of 

the affected fuel control drives and 

insertion of certain airplane operating 

procedures into the applicable flight 

manuals. This proposed AD would 

correct compliance requirements and 

relax the inspection interval. We are 

proposing this AD to prevent failure of 

the fuel control drive, damage to the 

engine, and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 31, 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 Honeywell 

International Inc., 111 S. 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Internet: https://

myaerospace.honeywell.com/wps/

portal. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, 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–2006– 

23706. 

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–2006– 

23706; 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: 

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: 

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– 

2006–23706; Directorate Identifier 

2006–NE–03–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 

On June 5, 2015, we issued AD 2015– 

12–04, Amendment 39–18177, (80 FR 

34534, June 17, 2015) (‘‘AD 2015–12– 

04’’), for all Honeywell International 

Inc. TPE331–1, –2, –2UA, –3U, –3UW, 

–5, –5A, –5AB, –5B, –6, –6A, –10, 

–10AV, –10GP, –10GT, –10P, –10R, 

–10T, –10U, –10UA, –10UF, –10UG, 

–10UGR, –10UR, –11U, –12JR, –12UA, 

–12UAR, and –12UHR turboprop 

engines with certain Woodward FCU 

assemblies, installed. AD 2015–12–04 

requires initial and repetitive 

dimensional inspections of the affected 

fuel control drives and insertion of 

certain airplane operating procedures 

into the applicable flight manuals. AD 

2015–12–04 resulted from reports of 

loss of the fuel control drive, leading to 

engine overspeed, overtorque, 

overtemperature, uncontained rotor 

failure, and asymmetric thrust in multiengine airplanes. We issued AD 2015– 

12–04 to prevent failure of the fuel 

control drive, damage to the engine, and 

damage to the airplane. 

Actions Since AD 2015–12–04 Was 

Issued 

We received a request to change 

compliance time from 50 hours to 100 

hours for fuel control part numbers 

affected by paragraph (e)(2) of this AD. 

We concluded that because the number 

of fuel control drives in-service that had 

not completed an initial inspection was 

small, changing the compliance time to 

100 hours would not add additional risk 

of fuel control drive failure and, 

therefore, is appropriate. 

We also received reports that some 

airplanes do not use the condition lever 

to shut down the engine, and so could 

not comply with the AD. We concluded 

that references to a condition lever were 

inappropriate. This proposed AD 

eliminates references to a condition 

lever. 

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Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17413 

Related Service Information 

We reviewed Honeywell Operating 

Information Letter (OIL) OI331–12R6, 

dated May 26, 2009, for multi-engine 

airplanes; and OIL OI331–18R4, dated 

May 26, 2009, for single-engine 

airplanes and Honeywell TPE331 

maintenance manuals. The service 

information describes procedures for 

conducting fuel control drive 

inspections and engine shutdown. 

FAA’s Determination 

We are proposing this NPRM because 

we information evaluated all the 

relevant 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 increase the 

inspection time limits for the FCU 

assembly from 50 to 100 hours-inservice in Compliance paragraph (e)(2) 

of this AD. This NPRM would also 

delete reference to the condition lever. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2,250 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 8 

hours per engine to comply with this 

proposed AD. The average labor rate is 

$85 per hour. We estimate that 10% of 

affected engines will require FCU 

assembly stub shaft replacement and 

fuel pump or fuel control repair. We 

also estimate that repairs will cost about 

$10,000 per engine. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $525,587 per 

year. 

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 have 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 that the 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 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. 

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 

removing airworthiness directive (AD) 

2015–12–04, Amendment 39–18177 (80 

FR 34534, June 17, 2015) (‘‘AD 2015– 

12–04’’), and adding the following new 

AD: 

Honeywell International Inc.: Docket No. 

FAA–2006–23706; Directorate Identifier 

2006–NE–03–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 31, 2016. 

(b) Affected ADs 

This AD replaces AD 2015–12–04. 

(c) Applicability 

This AD applies to all Honeywell 

International Inc. (Honeywell) TPE331–1, –2, 

–2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, 

–6A, –10, –10AV, –10GP, –10GT, –10P, –10R, 

–10T, –10U, –10UA, –10UF, –10UG, 

–10UGR, –10UR, –11U, –12JR, –12UA, 

–12UAR, and –12UHR turboprop engines 

with Woodward fuel control unit (FCU) 

assemblies with Honeywell part numbers (P/ 

Ns) as listed in Table 1 to paragraph (c) of 

this AD, installed. 

TABLE 1 TO PARAGRAPH (c)—AFFECTED FCU ASSEMBLY P/NS

Group # Engine FCU Assembly P/Ns 

1 ................... TPE331–1, –2, and –2UA ......................... P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, 

–34, and –35. 

2 ................... TPE331–1, –2, and –2UA ......................... P/N 869199–9, –10, –11, –12, –14, –16, –17, and –18. 

3 ................... TPE331–3U, –3UW, –5, –5A, –5AB, –5B, 

–6, –6A, –l0AV, –10GP, –10GT, –10P, 

and –10T.

P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, –29; and 

P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. 

4 ................... TPE331–3U, –3UW, –5, –5B, –6, –6A, 

and –10T.

P/N 893561–4, –5, –12, –13; and 

P/N 897770–5, –8, and –13. 

5 ................... TPE331–10, –l0R, –10U, –10UA, –10UF, 

–10UG, –10UGR, –10UR, –11U, 

–12JR, –12UA, –12UAR, and –12UHR.

P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19, 

–21, –24, –25, –26, –27; and 

P/N 897780–1, –2, –3, –4, –5, –6, –7, –8, –9, –10, –11, –14, –15, –16, –17, –18, 

–19, –20, –21, –22, –23, –24, –25, –26, –27, –30, –32, –34, –36, –37, –38; and 

P/N 893561–17, –18, and –19. 

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17414 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 

(d) Unsafe Condition 

This AD was prompted by reports of loss 

of the fuel control drive, leading to engine 

overspeed and engine failure. We are issuing 

this AD to prevent failure of the fuel control 

drive, damage to the engine, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspection of Engines With FCU 

Assembly P/Ns in Groups 2 or 4 

For FCU assembly P/Ns in Groups 2 or 4 

listed in Table 1 to paragraph (c) of this AD: 

(i) At the next scheduled inspection of the 

fuel control drive, or within 500 hours-inservice (HIS) after the effective date of this 

AD, whichever occurs first, inspect the fuel 

control drive for wear. 

(ii) Thereafter, re-inspect the fuel control 

drive within every 1,000 HIS since-lastinspection (SLI). 

(2) Inspection of Engines With FCU 

Assembly P/Ns in Groups 1, 3, or 5 

For FCU assembly P/Ns in Groups 1, 3, or 

5 listed in Table 1 to paragraph (c) of this AD: 

(i) If on the effective date of this AD the 

FCU assembly has 900 or more HIS SLI, 

inspect the fuel control drive for wear within 

100 HIS after the effective date of this AD. 

(ii) If on the effective date of this AD the 

FCU assembly has fewer than 900 HIS SLI, 

inspect the fuel control drive for wear within 

1,000 HIS. 

(iii) Thereafter, re-inspect the fuel control 

drive for wear within every 1,000 HIS SLI. 

(3) Airplane Operating Procedures 

Within 60 days after the effective date of 

this AD, insert the information in Figure 1 to 

paragraph (e) of this AD, into the Emergency 

Procedures Section of the applicable 

Airplane Flight Manual (AFM), Pilot 

Operating Handbook (POH), or the 

Manufacturer’s Operating Manual (MOM). 

(f) Optional Terminating Action 

Replacing the affected FCU assembly with 

an FAA-approved FCU assembly not listed in 

this AD by P/N is terminating action for the 

initial and repetitive inspections required by 

this AD, and for inserting the information in 

Figure 1 to paragraph (e) of this AD into the 

AFM, POH, and MOM. 

(g) Definitions 

For the purposes of this AD: 


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Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17415 

(1) The ‘‘fuel control drive’’ is a series of 

mating splines located between the fuel 

pump and fuel control governor. 

(2) The fuel control drive consists of four 

drive splines: The fuel pump internal spline, 

the fuel control external ‘‘quill shaft’’ spline, 

and the stub shaft internal and external 

splines. 

(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) Information pertaining to operating 

recommendations for affected engines after a 

fuel control drive failure is contained in 

Honeywell Operating Information Letter 

(OIL) OI331–12R6, dated May 26, 2009, for 

multi-engine airplanes; and OIL OI331–18R4, 

dated May 26, 2009, for single-engine 

airplanes. Information on fuel control drive 

inspection can be found in Section 72–00–00 

of the applicable TPE331 maintenance 

manuals. These Honeywell OILs and the 

TPE331 maintenance manuals can be 

obtained from Honeywell using the contact 

information in paragraph (i)(3) of this 

proposed 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: 

https://myaerospace.honeywell.com/wps/

portal. 

(4) You may view this service information 

at the 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 

March 15, 2016. 

Ann C. Mollica, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–06936 Filed 3–28–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5034; Directorate 

Identifier 2015–NM–172–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and 900ER series 

airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the S–14L and S–14R lap 

splices are subject to widespread fatigue 

damage (WFD). This proposed AD 

would require repetitive low frequency 

eddy current inspections for cracking in 

the lower fastener row of the S–14L and 

S–14R lap splices and repair if 

necessary. We are proposing this AD to 

detect and correct widespread cracking 

in the S–14L and S–14R lap splices that 

could rapidly link up and result in 

possible rapid decompression and 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 13, 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 NPRM, 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 http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

5034. 

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–2016– 

5034; 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: 

Jason Deutschman, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6595; 

fax: 425–917–6590; email: 

Jason.deutschman@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– 

2016–5034; Directorate Identifier 2015– 

NM–172–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 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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitemstockstill on DSK4VPTVN1PROD with PROPOSALS