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 rotorfailure, 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.


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

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 FCUassembly 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)—A FFECTED 

### FCU ASSEMBLY 

### P/N S

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.


### 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 thefuel 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 controldrive 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:


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

(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 adjacentframes or stringers. Multiple-siteVerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1mstockstill on DSK4VPTVN1PROD with PROPOSALS