### 53030 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules

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.

We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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):
MD Helicopters Inc.: Docket No. FAA–2015– 3659; Directorate Identifier 2014–SW– 050–AD. (a) Applicability

This AD applies to Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with an Aerometals main rotor blade attach pin (pin) part number (P/N) 369X1004–5 installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a pin remaining in service beyond its fatigue life. This condition could result in failure of a pin, loss of a main rotor blade, and subsequent loss of control of the helicopter.
(c) Comments Due Date

We must receive comments by November 2, 2015. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions

(1) Within 100 hours time-in-service (TIS) or during the next annual inspection, whichever occurs first:

(i) Review the maintenance records and determine the hours TIS of each pin P/N 369X1004–5 and whether there is a pin life limit listed in the Airworthiness Limitations Section of the applicable maintenance manual or Instructions for Continued Airworthiness (ICA). If the hours TIS on a pin is unknown, remove the pin from service.

(ii) For Model 369A, 369HE, 369HM, and 369HS helicopters, if there is no pin life limit, establish a new life limit of 5,760 hours TIS for each pin P/N 369X1004–5 by making pen-and-ink changes or by inserting a copy of this AD into the Airworthiness Limitations Section of the maintenance manual or the ICA. Remove from service any pin that has 5,760 or more hours TIS.

(iii) For Model 369D, 369E, 369FF, 500N, and 600N helicopters, if there is no pin life limit, establish a new life limit of 7,600 hours TIS for each pin P/ N 369X1004–5 by making pen-and-ink changes or by inserting a copy of this AD into the Airworthiness Limitations Section of the maintenance manual or the ICA. Remove from service any pin that has 7,600 or more hours TIS.

(iv) For all model helicopters, add the following statement to the Airworthiness Limitations Section of the maintenance manual or the ICA by making pen-and-ink changes or by inserting a copy of this AD: If interchanged between different model helicopters, the life limit of pin P/N 369X1004–5 must be restricted to the lowest life limit indicated for the helicopter models and serial numbers affected.

(2) Do not install a pin P/N 369X1004–5 on any helicopter before the requirements of this AD have been accomplished.
(f) Alternative Methods of Compliance (AMOC)

(1) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Galib Abumeri, Aviation Safety Engineer, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627–5324 or email at 9-ANM-LAACO-AMOCREQUESTS@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information

Aerometals Service Bulletin Aero– SB–1103, dated July 2, 2014, and Aerometals Aero–ICA–101 Supplemental Instructions for Continued Airworthiness, Revision NC, dated May 22, 2014, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Aerometals, 3920 Sandstone Dr., El Dorado Hills, CA 95762, telephone (916) 939–6888, fax (916) 939–6555, www.aerometals.aero. You may review a copy of information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (h) Subject

Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor Blades.

Issued in Fort Worth, Texas, on August 21,
2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015–21680 Filed 9–1–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3658; Directorate Identifier 2014–SW–039–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; MD Helicopters Inc. (MDHI) Helicopters** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain MDHI Model 369A (Army OH–6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. This proposed AD would require inspecting the auxiliary fuel pump (fuel pump) wire routing in the left-hand fuel cell and corrective action, if necessary. This proposed AD would also require installing a warning decal on the left-hand fuel cell access cover. This proposed AD is prompted by accidents resulting from incorrectly positioned fuel pump wiring within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity


### 53031 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules

indication in the cockpit. The proposed actions are intended to detect and correct routing of the fuel pump wiring to prevent interference with the fuel quantity sensor float, an erroneous fuel quantity indication in the cockpit, and subsequent fuel exhaustion and emergency landing.

**DATES :**  We must receive comments on this proposed AD by November 2, 2015.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.

• Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001.

• Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic 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 service information identified in this proposed AD, contact MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, AZ 85215– 9734; telephone 1–800–388–3378; fax 480–346–6813; or at http:// www.mdhelicopters.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, Texas 76177.

**FOR FURTHER INFORMATION CONTACT :**  Danny Nguyen, Aerospace Engineer, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627– 5247; email danny.nguyen@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time.

We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive.

Discussion

We propose to adopt a new AD for certain MDHI Model 369A (Army OH– 6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. This proposed AD would require inspecting the routing of the fuel pump wiring to determine whether the fuel pump wire is properly wrapped around the fuel inlet hose and correcting the routing of the wiring if it is not. This proposed AD would also require installing a decal regarding correct installation of the fuel pump wiring. This proposed AD is prompted by two accidents and one incident that occurred on Model 369D helicopters resulting from an incorrectly positioned fuel pump wire within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity reading in the cockpit. Because the fuel pump is installed on all the affected model helicopters, we are including them in the applicability. According to MDHI, because maintenance personnel caused the incorrect wire routing by failing to follow procedures for installing the fuel pump, it is also necessary to install a decal on the left-hand fuel cell access cover to refer maintenance personnel to the appropriate manual procedures. The proposed actions are intended to detect and correct routing of the fuel pump wiring to prevent interference with the fuel quantity sensor float, an erroneous fuel quantity indication in the cockpit, and subsequent fuel exhaustion and emergency landing.

FAA’s Determination

We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs.

Related Service Information Under 1 CFR Part 51

MDHI issued one Service Bulletin on April 30, 2014, with five different numbers: SB369H–255, SB369E–111, SB500N–049, SB369D–213, and SB369F–098. The service bulletin specifies a one-time inspection of therouting of the fuel pump wire in the lefthand fuel cell and corrective action, if necessary. The service bulletin also specifies installing a warning decal on the left-hand fuel cell access cover that refers personnel to the procedures for routing the fuel pump wire that is contained in the appropriate maintenance manual. The service bulletin states that recent field incidents have occurred where maintenance personnel have not followed the procedures for installation of the fuel pump. Also, the service bulletin states that an incorrectly installed fuel pump wire can interfere with the fuel quantity sensor float, which can result in erroneous fuel quantity indications. To prevent this situation, the service information states that the fuel pump wire must be wrapped around the fuel inlet hose as shown in the applicable maintenance manual. 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 of this NPRM. Proposed AD Requirements

This proposed AD would require, within 100 hours time-in-service:

• Removing the fuel quantity sensor and, using a mirror and light, inspecting to determine whether the fuel pump wire is wrapped around the left-hand fuel cell fuel inlet hose assembly a minimum of one revolution.

Æ If the fuel pump wire is correctly wrapped around the left-hand fuel cell fuel inlet hose, installing the fuel quantity sensor and performing a fuel quantity sensor functional test for proper fuel float arm function.

Æ If the fuel pump wire is not correctly wrapped around the left-hand fuel cell fuel inlet hose, reinstalling the fuel quantity sensor, routing the fuel pump wire around the left-hand fuel cell fuel inlet hose, and performing a


### 53032 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules

fuel quantity sensor functional test for proper fuel float arm function.

• Installing a warning decal referencing the fuel pump installation procedures. Costs of Compliance

We estimate that this proposed AD would affect 833 helicopters of U.S. Registry.

We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per hour. Inspecting the fuel pump wire routing and installing a decal would take 3 hours, and parts would cost $20 for a total cost of $275 per helicopter and $229,075 for the U.S. fleet. If required, rerouting the wiring would require 1 work-hour for a total cost of $85 per helicopter. 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, 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 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.

We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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):
MD Helicopters Inc.: Docket No. FAA–2015– 3658; Directorate Identifier 2014–SW– 039–AD. (a) Applicability

This AD applies to the following helicopters, certificated in any category: (1) Model 369A (Army OH–6A), 369H, 369HE, 369HM, 369HS, and 369D;

(2) Model 369E with a serial number (S/N) 0001E through 0620E;

(3) Model 369F and 369FF with a S/N 0001FF through 0212FF, 0600FF, 0601FF, 0602FF, and 0700FF through 0711FF) and with an auxiliary fuel pump part number (P/N) 369A8143–3 installed; and

(4) Model 500N (S/N LN001 through LN0111).

(b) Unsafe Condition

This AD defines the unsafe condition as incorrect routing of the auxiliary fuel pump (fuel pump) wiring. This condition could result in an erroneous fuel quantity indication in the cockpit and subsequent fuel exhaustion and emergency landing.

(c) Comments Due Date

We must receive comments by November 2, 2015. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Within 100 hours time-in-service: (1) Remove the fuel quantity sensor by following the Accomplishment Instructions, paragraph 2.B., of MD Helicopters Service Bulletin SB369H–255/SB369E111/SB500N– 049/SB369D–213/SB369F–098, dated April 30, 2014 (SB). Using a mirror and light, inspect the routing of the fuel pump wire in the area depicted in Figure 2 of the SB and determine whether the fuel pump wire is wrapped around the left-hand fuel cell fuel inlet hose assembly a minimum of one revolution.

(i) If the fuel pump wire is wrapped around the left-hand fuel cell fuel inlet hose a minimum of one revolution, install the fuel quantity sensor and perform a fuel quantity sensor functional test for proper fuel float arm function.

(ii) If the fuel pump wire is not wrapped around the left-hand fuel cell fuel inlet hose a minimum of one revolution, install the fuel quantity sensor, route the fuel pump wire around the left-hand fuel cell fuel inlet hose by following paragraphs 2.E.(1) through 2.E.(8) of the SB, and perform a fuel quantity sensor functional test for proper fuel float arm function.

(2) Install start pump warning decal, P/N MHS5861–66 or equivalent, on the left-hand fuel cell cover by following paragraph 2.G. of the SB.
(f) Alternative Methods of Compliance (AMOC)

(1) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Danny Nguyen, Aerospace Engineer Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627–5247; email 9- ANM-LAACO-AMOC-REQUESTS@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(g) Subject

Joint Aircraft Service Component (JASC) Code: 2840 Fuel Quantity Indicating System.

Issued in Fort Worth, Texas, on August 21,

2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015–21686 Filed 9–1–15; 8:45 am]

**BILLING CODE 4910–13–P**