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(i) Visually inspect the exposed areas of the lower grip pad and upper and lower grip plates of each M/R blade for a crack and any corrosion.

(ii) On the upper and lower exposed surfaces of each M/R blade from blade stations 24.5 to 35 for the chord width, visually inspect each layered doubler and blade skin for a crack and any corrosion. Pay particular attention for any cracking in a doubler or skin near or at the same blade station as the blade retention bolt hole (blade station 28).

(iii) Visually inspect the exposed areas of each bond line at the edges of the lower grip pad, upper and lower grip plates, and each layered doubler (bond lines) on the upper and lower surfaces of each M/R blade for the entire length and chord width for an edge void, any corrosion, loose or damaged adhesive squeeze-out, and an edge delamination. Pay particular attention to any crack in the paint finish that follows the outline of a grip pad, grip plate, or doubler, and to any loose or damaged adhesive squeeze-out, as these may be the indication of an edge void.

(2) If there is a crack, any corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination during any inspection in paragraph (f)(1) of this AD, before further flight, do the following:

(i) If there is a crack in a grip pad or any grip plate or doubler, replace the M/R blade with an airworthy M/R blade.

(ii) If there is a crack in the M/R blade skin that is within maximum repair damage limits, repair the M/R blade. If the crack exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/ R blade.

(iii) If there is any corrosion within maximum repair damage limits, repair the M/ R blade. If the corrosion exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade.

(iv) If there is an edge void in the grip pad or in a grip plate or doubler, determine the length and depth using a feeler gauge. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade.

(v) If there is an edge void in a grip plate or doubler near the outboard tip, tap inspect the affected area to determine the size and shape of the void. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade.

(vi) If there is any loose or damaged adhesive squeeze-out along any of the bond lines, trim or scrape away the adhesive without damaging the adjacent surfaces or parent material of the M/R blade. Determine if there is an edge void or any corrosion by lightly sanding the trimmed area smooth using 280 or finer grit paper. If there is no edge void or corrosion, refinish the sanded

area.

(vii) If there is an edge delamination along any of the bond lines or a crack in the paint finish, determine if there is an edge void or a crack in the grip pad, grip plate, doubler, or skin by removing paint from the affected area by lightly sanding in a span-wise direction using 180–220 grit paper. If there are no edge voids and no cracks, refinish the sanded area.

(viii) If any parent material is removed during any sanding or trimming in paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, repair the M/R blade if the damage is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade.
(g) Special Flight Permit

Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Fort Worth Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5140; email 7- AVS-ASW-170@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.

(i) Additional Information

Bell Helicopter Alert Service Bulletin (ASB) No. UH–1H–13–09, dated January 14, 2013, and ASB No. 204–75–1 and ASB No. 205–75–5, both Revision C and both dated April 25, 1979, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280– 3391; fax (817) 280–6466; or at http:// www.bellcustomer.com/files/. You may review the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N– 321, Fort Worth, TX 76177.
(j) Subject

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

Issued in Fort Worth, Texas, on April 15,

2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016–10523 Filed 5–4–16; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3941; Directorate Identifier 2015–SW–052–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Helicopters Deutschland GmbH**  **Helicopters**

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117A–3, MBB–BK 117A–4, MBB–BK 117B–1, MBB–BK 117B–2, and MBB–BK 117C– 1 helicopters. This proposed AD would require removing adhesive seals from the exterior and interior door jettisoning system on the left and right sliding doors. This proposed AD is prompted by reports that the adhesive seal prevented the doors from jettisoning properly. The proposed actions are intended to remove the adhesive seal to allow the doors to jettison properly so occupants can exit the helicopter during
an emergency.
**DATES :**  We must receive comments on this proposed AD by July 5, 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–2015– 3941; 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 European Aviation Safety Agency (EASA) AD, the economic evaluation,


### 27058 Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules

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 Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. 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 :**  Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@ 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

EASA, which is the aviation authority for the Member States of the European Union, has issued EASA AD No. 2015– 0163, dated August 6, 2015, to correct an unsafe condition for Airbus Helicopters Model MBB–BK 117A–3, MBB–BK 117A–4, MBB–BK 117B–1, MBB–BK 117B–2, and MBB–BK 117C– 1 helicopters. EASA advises that difficulties were reported regarding the jettisoning of doors. The malfunction was caused by the adhesive seal, which hampered the free movement of the inner handle. According to EASA, a subsequent investigation showed that the adhesive seal has mechanical and physical properties that do not meet relevant certification requirements. EASA states that this condition, if not detected and corrected, could lead to a malfunction of the door’s jettisoning mechanism, reducing or preventing the evacuation of the helicopter during an emergency, possibly resulting in injury to occupants. To address this condition, the EASA AD requires inspecting the exterior and interior door jettisoning system on the left and right sliding doors for adhesive seal part number (P/N) 117–800201.01 and removing any adhesive seals that are installed.

FAA’s Determination

These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design.

Related Service Information Under 1 CFR Part 51

We reviewed Airbus Helicopters Alert Service Bulletin MBB–BK117–20A–114, Revision 1, dated July 30, 2015 (ASB) for Model MBB–BK 117A–3, MBB–BK 117A–4, MBB–BK 117B–1, MBB–BK 117B–2, and MBB–BK 117C–1 helicopters. The ASB reports that the proper functioning of the sliding door jettison system is hampered by an adhesive seal. The seal was not manufactured correctly, and therefore did not perform as the test seal did during door jettisoning tests. The ASB calls for removing any adhesive seals on the exterior and interior door jettison system and discarding any adhesive seals that have not yet been installed.

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. Proposed AD Requirements

This proposed AD would require, within 25 hours time-in-service, removing the adhesive seal from the interior and exterior of each door. This proposed AD would also prohibit installing adhesive seal P/N 117– 800201.01 on any helicopter sliding door. Differences Between This Proposed AD and the EASA AD

The EASA AD requires removing adhesive seal, P/N 117–800201.01, within 30 days. The proposed AD would require removing the adhesive seal within 25 hours TIS. Costs of Compliance

We estimate that this proposed AD would affect 69 helicopters of U.S. Registry and that labor costs would average $85 per work-hour. Based on these estimates, we expect that removing the adhesive seals would require a half work-hour for a labor cost of about $43 per helicopter. No parts would be needed, so the cost for the U.S. fleet would total $2,967. 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);


### 27059 Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules

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):
Airbus Helicopters Deutschland GmbH: Docket No. FAA–2015–3941; Directorate Identifier 2015–SW–052–AD.
(a) Applicability

This AD applies to Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117A–3, MBB–BK 117A–4, MBB–BK 117B–1, MBB–BK 117B–2, and MBB–BK 117C–1 helicopters with an adhesive seal part number (P/N) 117– 800201.01 installed on an exterior or interior sliding door, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition the presence of sealant on a sliding door (door). This condition could result in the door failing to jettison, preventing helicopter occupants from exiting the helicopter during
an emergency. (c) Comments Due Date

We must receive comments by July 5, 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

(1) Within 25 hours time-in-service, remove adhesive seal P/N 117–800201.01 from the interior and exterior of each door. The areas where the seal is installed are shown in Figure 1 and Figure 2 of Airbus Helicopters Alert Service Bulletin MBB– BK117–20A–114, Revision 1, dated July 30,
2015.

(2) After the effective date of this AD, do not install adhesive seal P/N 117–800201.01 on any helicopter sliding door.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9- ASW-FTW-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) Additional Information

The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015–0163, dated August 6, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 5220, Emergency Exits.

Issued in Fort Worth, Texas, on April 19,
2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016–10285 Filed 5–4–16; 8:45 am]

**BILLING CODE 4910–13–P**

**SOCIAL SECURITY ADMINISTRATION**

**20 CFR Part 421**

**[Docket No. SSA–2016–0011]**

**RIN 0960–AH95**

**Implementation of the NICS Improvement Amendments Act of 2007** 

**AGENCY :**  Social Security Administration.

**ACTION :**  Notice of proposed rulemaking.

**SUMMARY :**  We propose to implement provisions of the NICS Improvement Amendments Act of 2007 (NIAA) that require Federal agencies to provide relevant records to the Attorney General for inclusion in the National Instant Criminal Background Check System (NICS). Under the proposed rule, we would identify, on a prospective basis, individuals who receive Disability Insurance benefits under title II of the Social Security Act (Act) or Supplemental Security Income (SSI) payments under title XVI of the Act and also meet certain other criteria, including an award of benefits based on a finding that the individual’s mental impairment meets or medically equals the requirements of section 12.00 of the Listing of Impairments (Listings) and receipt of benefits through a representative payee. We propose to provide pertinent information about these individuals to the Attorney General on not less than a quarterly basis. As required by the NIAA, at the commencement of the adjudication process we would also notify individuals, both orally and in writing, of their possible Federal prohibition on possessing or receiving firearms, the consequences of such inclusion, the criminal penalties for violating the Gun Control Act, and the availability of relief from the prohibitions imposed by Federal law. Finally, we also propose to establish a program that permits individuals to request relief from the Federal firearms prohibitions based on our adjudication. The proposed rule would allow us to fulfill responsibilities that we have under the NIAA.

**DATES :**  To ensure that your comments are considered, we must receive them no later than July 5, 2016.

**ADDRESSES :**  You may submit comments by any one of three methods—Internet, fax, or mail. Do not submit the same comment multiple times or by more than one method. Regardless of which method you choose, please state that your comments refer to Docket No. SSA–2016–0011 so that we may associate your comments with the correct regulation.

Caution: You should be careful to include in your comments only information that you wish to make publicly available. We strongly urge you not to include in your comments any personal information, such as Social Security numbers or medical information.

1. Internet: We strongly recommend that you submit your comments via the Internet. Please visit the Federal eRulemaking portal at http:// www.regulations.gov. Use the ‘‘Search’’ function to find docket number SSA– 2016–0011. The system will issue a tracking number to confirm your submission. You will not be able to view your comment immediately because we must post each comment manually. It may take up to a week or more for your comment to be viewable.

2. Fax: Fax comments to (410) 966–
2830.

3. Mail: Mail your comments to NICS Comments, Social Security Administration, 3100 West High Rise Building, 6401 Security Boulevard, Baltimore, Maryland 21235–6401.