Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules 27057 

(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, 


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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); 


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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. 


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