### 3344 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules

grain and other grains regarding kind, class, quality and condition. The mixed grain standards, established by USDA on July 2, 1934, were last revised in 1987 and appear in the USGSA regulations at 7 CFR 810.801 through 810.805. The standards facilitate mixed grain marketing and define U.S. mixed grain quality in the domestic and global marketplace. The standards define commonly used industry terms; contain basic principles governing the application of standards, such as the type of sample used for a particular quality analysis; the basis of determination; and specify grades and grade requirements. Official procedures for determining grading factors are provided in GIPSA’s Grain Inspection Handbook, Book II, Chapter 6, ‘‘Mixed grain’’ which also includes standardized procedures for additional quality attributes not used to determine grade, such as dockage and moisture content. Together, the grading standards and testing procedures allow buyers and sellers to communicate quality requirements, compare mixed grain quality using equivalent forms of measurement and assist in price discovery.

GIPSA’s grading and inspection services are provided through a network of federal, state, and private laboratories that conduct tests to determine the quality and condition of mixed grain. These tests are conducted in accordance with applicable standards using approved methodologies and can be applied at any point in the marketing chain. Furthermore, the tests yield rapid, reliable and consistent results. In addition, GIPSA-issued certificates describing the quality and condition of graded mixed grain are accepted as prima facie evidence in all Federal courts. U.S. mixed grain standards and the affiliated grading and testing services offered by GIPSA verify that a seller’s mixed grain meets specified requirements, and ensure that customers receive the quality of mixed grain they purchased.

In order for U.S. standards and grading procedures for mixed grain to remain relevant, GIPSA is issuing this request for information to invite interested parties to submit comments, ideas, and suggestions on all aspects of the U.S. mixed grain standards and inspection procedures.

Authority: 7 U.S.C. 71–87K.
Larry Mitchell, Administrator, Grain Inspection, Packers and Stockyards Administration.

[FR Doc. 2016–01046 Filed 1–20–16; 8:45 am]

**BILLING CODE 3410–KD–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–0183; Directorate Identifier 2015–SW–016–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Kaman Aerospace Corporation** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K–1200 helicopters. This proposed AD would require revising the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—LOAD’’ sections of the rotorcraft flight manual (RFM). This proposed AD is prompted by a report of certain flight maneuvers that may lead to main rotor (M/R) blade to opposing hub contact. The proposed actions are intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter.

**DATES :**  We must receive comments on this proposed AD by March 21, 2016.

**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 by searching for and locating Docket No. FAA–2016– 0183; 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 rule, contact Kaman Aerospace Corporation, Old Windsor Rd., P.O. Box 2, Bloomfield, Connecticut 06002–0002; telephone (860) 242–4461; fax (860) 243–7047; or
at http://www.kamanaero.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, TX 76177.

**FOR FURTHER INFORMATION CONTACT :**  Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7190; email kirk.gustafson@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 Kaman Model K–1200 helicopters. This proposed AD would require revising the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—LOAD’’ sections of the RFM by inserting a warning and limitations about rearward to forward flight, establishing maximum rearward and sideward flight speeds, and prohibiting weather-vanning takeoffs and departures to turn the helicopter. This proposed AD is prompted by a


### 3345 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules

report of a Model K1200 helicopter turning suddenly and causing blade contact with the hub. The report suggests that a rapid aircraft yaw rate and subsequent yaw arresting maneuver may cause low clearance of the M/R blades with the opposing M/R hub. This condition could cause an M/R blade to strike the opposing rotor’s flight controls. The proposed actions are intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter.

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 the same type design.

Related Service Information

We reviewed Kaman K–1200 RFM, Revision 5, dated April 14, 2015. This revision of the limitations section of the RFM inserts, for both load operations and no load operations, a warning and limitations about departing from rearward to forward flight, a maximum rearward flight speed of 25 knots, a maximum sideward flight speed of 17knots, and a prohibition on weathervanning takeoffs and departures as a method to turn aircraft. Proposed AD Requirements

This proposed AD would require, within 10 hours time-in-service, revising the Limitations section of the RFM by inserting a copy of this AD or by making pen-and-ink changes. This proposed AD, under ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—LOAD,’’ would insert a warning and limitations about departing from rearward to forward flight to avoid high rates of turn and minimize yaw and cyclic control inputs, establish a maximum rearward flight speed of 25 knots, establish a maximum sideward flight speed of 17 knots, and prohibit weather-vanning takeoffs and departures as a method to turn the helicopter. Costs of Compliance

We estimate that this proposed AD would affect 16 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work-hour, we expect revising the RFM would require 0.5 work-hour, for cost of about $43 per helicopter, or $688 for the U.S. fleet. 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):
Kaman Aerospace Corporation (Kaman): Docket No. FAA–2016–0183; Directorate Identifier 2015–SW–016–AD.
(a) Applicability

This AD applies to Model K–1200 helicopters, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a main rotor (M/R) blade striking the opposing rotor’s flight controls. This condition could result in damage to the M/R flight controls and subsequent loss of control of the helicopter.

(c) Comments Due Date

We must receive comments by March 21,

2016. (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 10 hours time-in-service, revise Section 2 Limitations of the Kaman K–1200 Rotorcraft Flight Manual (RFM) by inserting a copy of this AD into the RFM or by making pen-and-ink changes, as follows:

(1) In the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—WITH LOAD,’’ sections, add the information in Figure 1 to paragraph (e)(1) of this AD.

**WARNING**
When departing from rearward to forward flight, avoid high rates of turn and minimize yaw and cyclic control inputs to prevent exceeding 17

knot sideward flight limit.

Figure 1 to paragraph (e)(1).

(2) In the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—WITH LOAD’’ sections, add the following: Maximum rearward flight speed: 25 knots. Maximum sideward flight speed: 17 knots. Weather—


### 3346 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules

vanning takeoffs/departures as a method to turn aircraft: Prohibited.
(f) Credit for Actions Previously Completed

Incorporating the changes contained in Kaman K–1200 RFM, Revision 5, dated April 14, 2015, before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (e) of this AD.
(g) Alternative Methods of Compliance (AMOC)

(1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7190; email kirk.gustafson@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.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control.

Issued in Fort Worth, Texas, on January 12,

2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016–00947 Filed 1–20–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–0459; Directorate Identifier 2015–NM–081–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

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

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 2015–10– 03, for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. AD 2015–10–03 currently requires a detailed inspection for visible chrome of each affected main landing gear (MLG) sidestay upper cardan pin, associated nuts, and retainer assembly; pin replacement if needed; measurement of cardan pin clearance dimensions (gap check); corrective actions if necessary; and a report of all findings. Since we issued AD 2015–10–03, further investigation concluded that the reported MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. This proposed AD would require a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and if necessary, replacement of the cardan pin and nut threads. This proposed AD would also revise the applicability to include additional airplane models. We are proposing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.

**DATES :**  We must receive comments on this proposed AD by March 7, 2016.

**ADDRESSES :**  You may send comments 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet http://www.airbus.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.
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– 0459; 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 Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2016–0459; Directorate Identifier 2015–NM–081–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 based on 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

On April 30, 2015, we issued AD 2015–10–03, Amendment 39–18158 (80 FR 30608, May 29, 2015). AD 2015–10– 03 requires actions intended to address an unsafe condition on certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes.

Since we issued AD 2015–10–03, Amendment 39–18158 (80 FR 30608, May 29, 2015), further investigation concluded that the reported MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. Therefore, this issue affects any MLG that had an upper cardan pin replacement or reinstallation, regardless of MLG overhaul. Any corrosion on the upper cardan pin and nut threads would not have been detected during the currently required detailed inspection.

The European Aviation Safety Agency (EASA), which is the Technical Agent