58256 Federal Register / Vol. 78, No. 184 / Monday, September 23, 2013 / Proposed Rules 

burden by requiring investigations to be 

continually reinvestigated. In addition, 

permitting access and amendment to such 

information could disclose security-sensitive 

information that could be detrimental to 

homeland security. 

(3) From subsection (e)(1) (Relevancy and 

Necessity of Information) because in the 

course of investigations into potential 

violations of federal law, the accuracy of 

information obtained or introduced 

occasionally may be unclear, or the 

information may not be strictly relevant or 

necessary to a specific investigation. In the 

interests of effective law enforcement, it is 

appropriate to retain all information that may 

aid in establishing patterns of unlawful 

activity. 

(4) From subsection (e)(2) (Collection of 

Information from Individuals) because 

requiring that information be collected from 

the subject of an investigation would alert the 

subject to the nature or existence of the 

investigation, thereby interfering with that 

investigation and related law enforcement 

activities. 

(5) From subsection (e)(3) (Notice to 

Subjects) because providing such detailed 

information could impede law enforcement 

by compromising the existence of a 

confidential investigation or reveal the 

identity of witnesses or confidential 

informants. 

(6) From subsections (e)(4)(G), (e)(4)(H), 

and (e)(4)(I) (Agency Requirements) and (f) 

(Agency Rules), because portions of this 

system are exempt from the individual access 

provisions of subsection (d) for the reasons 

noted above, and therefore DHS is not 

required to establish requirements, rules, or 

procedures with respect to such access. 

Providing notice to individuals with respect 

to existence of records pertaining to them in 

the system of records or otherwise setting up 

procedures pursuant to which individuals 

may access and view records pertaining to 

themselves in the system would undermine 

investigative efforts and reveal the identities 

of witnesses, potential witnesses, and 

confidential informants. 

(7) From subsection (e)(5) (Collection of 

Information) because with the collection of 

information for law enforcement purposes, it 

is impossible to determine in advance what 

information is accurate, relevant, timely, and 

complete. Compliance with subsection (e)(5) 

would preclude DHS agents from using their 

investigative training and exercise of good 

judgment to both conduct and report on 

investigations. 

(8) From subsection (e)(8) (Notice on 

Individuals) because compliance would 

interfere with DHS’s ability to obtain, serve, 

and issue subpoenas, warrants, and other law 

enforcement mechanisms that may be filed 

under seal and could result in disclosure of 

investigative techniques, procedures, and 

evidence. 

(9) From subsection (g)(1) (Civil Remedies) 

to the extent that the system is exempt from 

other specific subsections of the Privacy Act. 

Dated: August 6, 2013. 

Jonathan R. Cantor, 

Acting Chief Privacy Officer, Department of 

Homeland Security. 

[FR Doc. 2013–22691 Filed 9–20–13; 8:45 am] 

BILLING CODE 4411–14–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0822; Directorate 

Identifier 2013–SW–004–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

AS350B3 helicopters with a certain 

modification (MOD) installed. The 

existing AD currently requires installing 

two placards and revising the Rotorcraft 

Flight Manual (RFM). The AD also 

requires certain checks and inspecting 

and replacing, if necessary, all four 

laminated half-bearings (bearings). 

Since we issued that AD, we have 

determined that the unsafe condition 

applies to additional model helicopters, 

and that a recently developed 

Eurocopter modification should be a 

required terminating action for the 

repetitive checks required by the AD. 

This proposed AD would retain the 

existing AD requirements, require 

certain modifications which would be 

terminating action for the airspeed 

limitations, and would add certain 

helicopter models to the bearing 

inspection with a different inspection 

interval. The proposed actions are 

intended to prevent vibration due to a 

failed bearing, failure of the tail rotor, 

and subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by November 22, 

2013. 

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 

foreign authority’s 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 American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.eurocopter.com/techpub. You may 

review service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@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 


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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 

On April 24, 2013, we issued AD 

2012–25–04, Amendment 39–17285 (78 

FR 24041) for Eurocopter Model 

AS350B3 helicopters with MOD 07 5601 

installed. AD 2012–25–04 requires, 

before further flight, installing two 

placards on the instrument panel and 

revising the RFM to reduce the Velocity 

Never Exceed (VNE) indicated airspeed 

(IAS) limitation. It also requires, before 

further flight and thereafter after each 

flight, visually checking all visible faces 

of the pressure side of the bearings for 

separation, a crack, or an extrusion, and 

replacing the four bearings if there is an 

extrusion or if there is a separation or 

a crack greater than 5 millimeters (.196 

inches). AD 2012–25–04 also requires 

checking the suction side of the bearings 

for extrusions and replacing all four 

bearings if an extrusion is present. 

Lastly, AD 2012–25–04 requires 

performing a one-time disassembly and 

inspection of the bearings for a 

separation, a crack, or an extrusion, and 

replacing the four bearings if there is a 

separation, crack, or extrusion. AD 

2012–25–04 superseded Emergency AD 

(EAD) No. 2012–21–51, dated October 

17, 2012 (EAD 2012–21–51), which had 

the same requirements but which only 

applied to helicopters with certain partnumbered half-bearings and tail rotor 

blades. 

AD 2012–25–04 and EAD 2012–21–51 

were prompted by Emergency AD No. 

2012–0207–E, dated October 5, 2012 

(EAD 2012–0207–E), and Emergency AD 

No. 2012–0217–E, dated October 19, 

2012 (EAD 2012–0217–E), issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA advised of premature 

failures of the bearings, three cases of 

vibrations originating from the tail rotor 

due to premature failure of the bearings 

installed with certain tail rotor blades, 

and an accident. EAD 2012–0217–E 

supersedes EAD 2012–0207–E to correct 

an inconsistency where the new 

airspeed limitation defined in the 

placards and the RFM were stated in 

both true airspeed (TAS) and indicated 

airspeed (IAS). EAD 2012–0217–E 

retains some of the requirements of EAD 

2012–0207–E, removes the airspeed 

limitations defined in TAS, and requires 

inserting a temporary engine health 

check procedure into the RFM. The 

actions required by AD 2012–25–04 and 

EAD 2012–21–51 are intended to 

prevent vibration due to a failed 

bearing, failure of the T/R, and 

subsequent loss of control of the 

helicopter. 

Actions Since Existing AD Was Issued 

After we issued EAD No. 2012–21–51, 

dated October 17, 2012, EASA issued 

EAD No. 2012–0257–E, dated December 

5, 2012 (EAD 2012–0257–E), for Model 

AS350B, AS350BA, AS350BB, 

AS350B1, AS350B2, AS350B3 without 

Modification (MOD) 07 5601, AS350D, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters. 

EAD 2012–0257–E describes the 

previous issues with the bearings on the 

AS350B3 helicopters, and states that the 

criticality of the bearing failures should 

apply to all AS355 and AS350 

helicopters, although service experience 

has not demonstrated premature 

deterioration of the bearings on these 

model helicopters. EAD 2012–0257–E 

requires repetitive post-flight checks of 

the bearings, similar to the checks 

required by EAD 2012–0217–E. 

EASA then superseded EAD 2012– 

0217–E with EASA AD No. 2013–0029, 

dated February 8, 2013 (AD 2013–0029), 

to correct an unsafe condition for 

Eurocopter Model AS 350 B3 

helicopters modified by MOD 07 5601, 

except for helicopters modified by MOD 

07 5606 in production. EASA advises 

that Eurocopter has designed MOD 07 

5606, which restores the tail rotor 

dynamic load level to that on 

helicopters before installation of MOD 

07 5601 and eliminates the modified 

loading conditions of bearings which 

caused the intensified deterioration and 

reported failures. For these reasons, 

EASA AD 2013–0029 requires 

incorporation of MOD 07 5606 as a 

terminating action. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, 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 helicopters of the same 

type design. 

Related Service Information 

We reviewed Eurocopter Service 

Bulletin (SB) No. AS350–01.00.66, 

Revision 1, dated February 15, 2013 (SB 

AS350–01.00.66), which describes 

procedures for removing the additional 

chin weights installed on the tail rotor, 

installing a load compensator, and 

modifying the electrical system 

installation, to reduce the dynamic 

loads on the tail rotor. Eurocopter refers 

to the procedures in this SB as MOD 07 

5606. SB AS350–01.00.66 only applies 

to helicopters with MOD 07 5601 

installed. 

We reviewed one Eurocopter 

Emergency Alert Service Bulletin 

(EASB) with two numbers: No. 01.00.65 

for the Model AS350B3 helicopters and 

No. 01.00.24 for the non-FAA type 

certificated Model AS550C3 helicopters 

(EASB 01.00.65). EASB 01.00.65 is 

Revision 3, dated February 4, 2013. 

EASB 01.00.65 specifies installing a 

placard on the instrument panel and 

revising the RFM to limit airspeed to 

100 knots IAS, revising the RFM to 

include a procedure in case of in-flight 

vibrations originating in the tail rotor 

and an ‘‘engine health check,’’ checking 

the bearings after each flight, and 

performing a one-time inspection of the 

bearings. EASB 01.00.65 does not apply 

to helicopters with MOD 07 5606 

installed. 

We also reviewed one Eurocopter 

EASB with four numbers: No 05.00.71 

for Model AS350B, BA, BB, D, B1, B2, 

B3, and the non-FAA type certificated 

L1 helicopters; No. 05.00.63 for Model 

AS355E, F, F1, F2, N, and NP 

helicopters; No. 05.00.46 for the nonFAA type certificated Model AS550A2, 

C2, C3, and U2 helicopters; and No. 

05.00.42 for the non-FAA type 

certificated Model AS555AF, AN, SN, 

UF, and UN helicopters (EASB 

05.00.71). EASB 05.00.71 is Revision 2, 

dated December 19, 2012. EASB 

05.00.71 specifies procedures for 

checking the bearings for deterioration 

or damage after the last flight of each 

day. EASB 05.00.71 does not apply to 

helicopters with MOD 07 5601 installed. 

We also reviewed Eurocopter SB No. 

AS350–64.00.11, Revision 0, dated 

December 19, 2012 (SB AS350– 

64.00.11), which describes procedures 

for modifying the tail rotor chin weight 

support to prevent interference with the 

bearings. Eurocopter refers to the 

procedures in this SB as MOD 07 6604. 

SB AS350–64.00.11 only applies to 

helicopters with MOD 07 5601 installed. 

Proposed AD Requirements 

This proposed AD would retain the 

requirements of AD 2012–25–04, 

Amendment 39–17285 (78 FR 24041, 

April 24, 2013). Additionally, this 

proposed AD would require, for 

AS350B3 helicopters with MOD 07 5601 

installed: 


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• Modifying the chin weight support 

and replacing any bearings with more 

than 5 hours time-in-service (TIS) by 

following the procedures specified in 

SB AS350–64.00.11; 

• Following certain procedures 

specified in SB AS350–01.00.66 for 

removing the additional chin weights 

and installing blanks, modifying the 

rotating pitch-change spider assembly, 

installing a load compensator, and 

modifying the electrical installation. 

• After modifying the helicopter, 

removing the RFM limitations and 

placards required to be installed by AD 

2012–25–04, Amendment 39–17285 (78 

FR 24041, April 24, 2013). Modifying 

the helicopter would be terminating 

action for the repetitive checks and 

inspections. 

For Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, AS355NP 

helicopters, and Model AS350B3 

helicopters that do not have MOD 07 

5601 installed, the proposed AD would 

also require: 

• After the last flight of each day, 

without exceeding 10 hours TIS 

between two checks, checking the 

bearings for separation or a crack. These 

checks may be performed by the owner/ 

operator (pilot) holding at least a private 

pilot certificate as it only requires a 

visual check of the bearings. This 

authorization is an exception to our 

standard maintenance regulations and 

must be entered into the aircraft records 

showing compliance with the proposed 

AD; and 

• If there is separation or a crack over 

a specific size, replacing the bearings 

before further flight. 

Differences Between the Proposed AD 

and the EASA ADs 

The EASA AD requires removing the 

placard and RFM changes with the TAS 

limitation and replacing it with an IAS 

limitation. Since the FAA EAD did not 

include the TAS limitation, this 

proposed AD would not require 

removing it. This proposed AD would 

not require inserting the temporary 

engine health check procedure in the 

RFM. 

Costs of Compliance 

We estimate that the pilot checks of 

the bearings in the proposed AD would 

affect 938 helicopters of U.S. Registry, 

and that 50 helicopters would be 

affected by the remaining requirements. 

The cost for the pilot checks is minimal. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. At an average labor rate 

of $85 per hour, installing a placard and 

revising the RFM will require about .5 

work-hour, for a cost per helicopter of 

$43 and a total cost to U.S. operators of 

$2,150. Disassembling and inspecting 

the bearings will require about 6 workhours, for a cost per helicopter of $510 

and a total cost to U.S. operators of 

$25,500. Modifying the chin weight 

support will require about 8 workhours, for a cost per helicopter of $680, 

and a total cost to U.S. operators of 

$34,000. Removing the additional chin 

weights installed on the tail rotor, 

modifying the rotating pitch-change 

spider assembly, installing a load 

compensator, and modifying the 

electrical system installation will 

require about 200 work-hours, and 

required parts will cost $18,343, for a 

cost per helicopter of $35,343, and a 

total cost to U.S. operators of 

$1,767,150. 

If necessary, replacing the bearings 

installed on the aircraft will require 

about 6 work-hours, at an average labor 

rate of $85, and required parts will cost 

$2,415, for a cost per helicopter of 

$2,925. 

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 

removing airworthiness directive (AD) 

2012–25–04, Amendment 39–17285 (78 

FR 24041, April 24, 2013), and adding 

the following new (AD): 

Eurocopter France: Docket No. FAA–2013– 

0822; Directorate Identifier 2013–SW– 

004–AD. 

(a) Applicability 

This AD applies to Model AS350B, 

AS350BA, AS350B1, AS350B2, AS350B3 

(except AS350B3 helicopters with 

modification (MOD) 07 5606 installed), 

AS350C, AS350D, AS350D1, AS355E, 

AS355F, AS355F1, AS355F2, AS355N, and 

AS355NP helicopters, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

severe vibrations due to failure of laminated 

half-bearings (bearings). This condition could 

result in failure of the tail rotor and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD No. 2012–25–04, 

Amendment 39–17285 (78 FR 24041, April 

24, 2013). 

(d) Comments Due Date 

We must receive comments by November 

22, 2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 


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specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For Model AS350B3 helicopters with 

MOD 07 5601 installed: 

Note 1 to paragraph (f): MOD 075601 is an 

integral part of a specific Model AS350B3 

configuration, commercially identified as 

‘‘AS350B3e’’ and is not fitted on Model 

AS350B3 helicopters of other configurations. 

(i) Before further flight: 

(A) Install a velocity never exceed (VNE) 

placard that reads as follows on the 

instrument panel in full view of the pilot and 

co-pilot with 6-millimeter red letters on a 

white background: 

VNE LIMITED TO 100 KTS IAS. 

(B) Replace the IAS limit versus the flight 

altitude placard located inside the cabin on 

the center post with the placard as depicted 

in Table 1 to paragraph (f) of this AD: 

VNE POWER ON

Hp 

(ft) 

IAS 

(kts) 

0 100 

2000 97 

4000 94 

6000 91 

8000 88 

10000 85 

12000 82 

14000 79 

16000 76 

18000 73 

20000 70 

VNE POWER ON—Continued 

Hp 

(ft) 

IAS 

(kts) 

22000 67 

Valid for VNE POWER OFF 

Table 1 to paragraph (f). 

(ii) Before further flight, revise the 

Rotorcraft Flight Manual (RFM) by inserting 

a copy of this AD into the RFM or by making 

pen and ink changes as follows: 

(A) Revise paragraph 2.3 of the RFM by 

inserting the following: 

VNE limited to 100 kts IAS. 

(B) Revise paragraph 2.6 of the RFM by 

inserting Table 2 to Paragraph (f) of this AD. 

VNE POWER ON 

Hp 

(ft) 

IAS 

(kts) 

0 100 

2000 97 

4000 94 

6000 91 

8000 88 

10000 85 

12000 82 

14000 79 

16000 76 

18000 73 

20000 70 

22000 67 

Valid for VNE POWER OFF 

Table 2 to Paragraph (f). 

(C) Add the following as paragraph 3.3.3 to 

the RFM: 

3.3.3 IN–FLIGHT VIBRATIONS FELT IN 

THE PEDALS 

Symptom: 

IN-FLIGHT VIBRATIONS FELT IN THE 

PEDALS 

1. CHECK PEDAL EFFECTIVENESS 

2. SMOOTHLY REDUCE THE SPEED TO 

VY 

3. AVOID SIDESLIP AS MUCH AS 

POSSIBLE 

LAND AS SOON AS POSSIBLE 

(iii) Before further flight, and thereafter 

after each flight, without exceeding 3 hours 

time-in-service (TIS) between two checks, 

visually check each bearing as follows: 

(A) Position both tail rotor blades 

horizontally. 

(B) Apply load (F) by hand, perpendicular 

to the pressure face of one tail rotor blade (a), 

as shown in Figure 1 to paragraph (f) of this 

AD, taking care not to reach the extreme 

position against the tail rotor hub. The load 

will deflect the tail rotor blade towards the 

tail boom. 

(C) While maintaining the load, check all 

the visible faces of the bearings (front and 

side faces) in area B of DETAIL A of Figure 

1 to paragraph (f) of this AD for separation 

between the elastomer and metal parts, a 

crack in the elastomer, or an extrusion (see 

example in Figure 2 to paragraph (f) of this 

AD). A flashlight may be used to enhance the 

check. 

BILLING CODE 4910–13–P 


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(D) Repeat paragraphs (f)(1)(iii)(A) through 

(f)(1)(iii)(C) on the other tail rotor blade. 

(E) Apply load (G) by hand perpendicular 

to the suction face of one tail rotor blade as 

shown in Figure 3 to paragraph (f) of this AD. 

The load will deflect the tail rotor blade away 

from the tail boom. 


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(F) While maintaining the load, check 

visible faces of Area C as shown in Figure 3 

to paragraph (f) of this AD for any extrusion. 

A flashlight may be used to enhance the 

check. 

(G) Repeat paragraphs (f)(1)(iii)(E) and 

(f)(1)(iii)(F) on the other tail rotor blade. 

(iv) The actions required by paragraphs 

(f)(1)(iii)(A) through (f)(1)(iii)(G) of this AD 

may be performed by the owner/operator 

(pilot) holding at least a private pilot 

certificate, and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 

§§ 43.9(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). 

The record must be maintained as required 

by 14 CFR §§ 91.417, 121.380, or 135.439. 

(v) If there is an extrusion on any bearing, 

before further flight, replace the four bearings 

with airworthy bearings. 

(vi) If there is a separation or a crack on 

the pressure side bearing, measure the 

separation or the crack. If the separation or 

crack is greater than 5 millimeters (.196 

inches) as indicated by dimension ‘‘L’’ in 

Figure 4 to paragraph (f) of this AD, before 

further flight, replace the four bearings with 

airworthy bearings. 


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BILLING CODE 4910–13–C 

(vii) No later than after the last flight of the 

day, perform a one-time inspection by 

removing the bearings and inspecting for a 

separation, a crack, or an extrusion. This 

inspection is not a daily inspection. If there 

is a separation, crack, or extrusion, before 

further flight, replace the four bearings with 

airworthy bearings. 

(viii) Within 130 hours TIS: 

(A) Modify the chin weight support as 

described in the Accomplishment 

Instructions, paragraphs 3.B.2.a through 

3.B.2.h, of Eurocopter Service Bulletin (SB) 

No. AS350–64.00.11, Revision 0, dated 

December 19, 2012. 

(B) Remove the additional chin weights, 

install blanks on the chin weights, replace 

bearings with more than 5 hours TIS, and reidentify the blade assembly as described in 

the Accomplishment Instructions, paragraph 

3.B.2.a., of Eurocopter SB No. AS350– 

01.00.66, Revision 1, dated February 15, 2013 

(SB AS350–01.00.66). 

(C) Modify and re-identify the rotating 

pitch-change spider assembly as described in 

the Accomplishment Instructions, paragraph 

3.B.2.b., of SB AS350–01.00.66. 

(D) Install a load compensator as described 

in the Accomplishment Instructions, 

paragraph 3.B.3.b., of SB AS350–01.00.66. 

(E) Modify the electrical installation as 

described in the Accomplishment 

Instructions, section 3.B.4., of SB AS350– 

01.00.66. 

Note 4 to paragraph (f): The manufacturer 

refers to the actions in paragraphs 

(f)(1)(viii)(B) through (f)(1)(viii)(E) as MOD 07 

5606. 

(ix) After modification of a helicopter as 

required by paragraphs (f)(1)(viii)(A) through 

(f)(1)(viii)(E) of this AD, the actions of 

paragraph (f)(1)(iii) through (f)(1)(vii) of this 

AD are no longer required and the operating 

limitation placards and RFM procedures 

required by paragraphs (f)(1)(i) through 

(f)(1)(ii)(C) of this AD may be removed. 

(2) For Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, AS355NP helicopters, 

and Model AS350B3 helicopters that do not 

have MOD 07 5601 installed: 

(i) No later than after the last flight of the 

day, and thereafter during each last flight of 

the day check, without exceeding 10 hours 

TIS between two checks, visually check each 

bearing as described in paragraphs 

(f)(1)(iii)(A) through (f)(1)(vi) of this AD. 

(ii) If there is an extrusion on any bearing, 

before further flight, replace the bearing with 

an airworthy bearing. 

(iii) If there is a separation or a crack on 

the bearing, measure the separation or the 

crack. If the separation or crack is greater 

than 5 mm (.196 inches) as indicated by 

dimension ‘‘L’’ and greater than 2 mm (.078 

inches) as indicated by dimension ‘‘P’’ in 

Figure 3 of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 05.00.71 or No. 

05.00.63, both Revision 2 and both dated 

December 19, 2012, as required for your 

model helicopter, before further flight, 

replace the bearing. 

(g) Credit for Actions Previously Completed 

Actions accomplished before the effective 

date of this AD in accordance with 

Emergency AD No. 2012–21–51 or AD No. 

2012–25–04, Amendment 39–17285 (78 FR 

24041, April 24, 2013) are considered 

acceptable for compliance with the 

corresponding actions of this AD. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5328; email robert.grant@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. 

(j) Additional Information 

(1) Eurocopter EASB No. 01.00.65 and No. 

01.00.24, both Revision 3 and both dated 

February 4, 2013, which are co-published as 

one document and which are not 

incorporated by reference, contain additional 

information about the subject of this AD. You 

may review this service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency Emergency 

AD No. 2013–0029, dated February 8, 2013, 

which can be found in the AD Docket on the 

Internet at http://www.regulations.gov. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400: Tail Rotor. 


emcdonald on DSK67QTVN1PROD with PROPOSALSer23se13.004</GPH>
58264 Federal Register / Vol. 78, No. 184 / Monday, September 23, 2013 / Proposed Rules 

Issued in Fort Worth, Texas, on September 

13, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23102 Filed 9–20–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Mine Safety and Health Administration 

30 CFR Parts 7 and 75 

RIN 1219–AB79 

Refuge Alternatives for Underground 

Coal Mines 

AGENCY: Mine Safety and Health 

Administration, Labor. 

ACTION: Request for information; 

extension of comment period. 

SUMMARY: In response to requests from 

interested parties, the Mine Safety and 

Health Administration (MSHA) is 

extending the comment period on the 

Agency’s Request for Information (RFI) 

on Refuge Alternatives for Underground 

Coal Mines. This extension gives 

interested parties additional time to 

review new information on refuge 

alternatives. 

DATES: Comments must be received by 

midnight Eastern Standard Time on 

December 6, 2013. 

ADDRESSES: Submit comments and 

supporting documentation by any of the 

following methods: 

• Federal E-Rulemaking Portal: 

http://www.regulations.gov. Follow the 

on-line instructions for submitting 

comments for Docket Number MSHA– 

2013–0033. 

• Electronic mail: zzMSHAcomments@dol.gov. Include ‘‘RIN 1219– 

AB79’’ in the subject line of the 

message. 

• Mail: Send comments to MSHA, 

Office of Standards, Regulations, and 

Variances, 1100 Wilson Boulevard, 

Room 2350, Arlington, Virginia 22209– 

3939. 

• Hand Delivery or Courier: MSHA, 

Office of Standards, Regulations, and 

Variances, 1100 Wilson Boulevard, 

Room 2350, Arlington, Virginia, 

between 9:00 a.m. and 5:00 p.m. 

Monday through Friday, except Federal 

holidays. Sign in at the receptionist’s 

desk on the 21st floor. 

Instructions: Clearly identify all 

submissions with ‘‘RIN 1219–AB79’’. 

Because comments will not be edited to 

remove any identifying or contact 

information, MSHA cautions the 

commenter against including 

information in the submission that 

should not be publicly disclosed. 

FOR FURTHER INFORMATION CONTACT: 

George F. Triebsch, Director, Office of 

Standards, Regulations, and Variances, 

MSHA, at triebsch.george@dol.gov 

(email); 202–693–9440 (voice); or 202– 

693–9441 (facsimile). These are not tollfree numbers. 

SUPPLEMENTARY INFORMATION: On August 

8, 2013 (78 FR 48593), MSHA published 

a Request for Information on Refuge 

Alternatives for Underground Coal 

Mines. The RFI comment period had 

been scheduled to close on October 7, 

2013. In response to requests, MSHA is 

extending the comment period to 

December 6, 2013 to allow interested 

parties additional time to review 

National Institute for Occupational 

Safety and Health information. 

Dated: September 18, 2013. 

Joseph A. Main, 

Assistant Secretary of Labor for Mine Safety 

and Health. 

[FR Doc. 2013–23031 Filed 9–20–13; 8:45 am] 

BILLING CODE 4510–43–P 

DEPARTMENT OF VETERANS 

AFFAIRS 

38 CFR Part 9 

RIN 2900–AO42 

Servicemembers’ Group Life Insurance 

and Veterans’ Group Life Insurance 

Information Access 

AGENCY: Department of Veterans Affairs. 

ACTION: Proposed rule. 

SUMMARY: The Department of Veterans 

Affairs (VA) proposes to amend its 

regulations governing Servicemembers’ 

Group Life Insurance (SGLI), Family 

SGLI, SGLI Traumatic Injury Protection, 

and Veterans’ Group Life Insurance (all 

hereafter referred to as SGLI). The 

purpose is to acknowledge and clarify 

what is implicit in the law: That VA, 

which has the responsibility under the 

law to oversee the SGLI program and 

ensure its proper operation, also has the 

right to full access to records held by the 

insurer or on behalf of the insurer from 

whom VA has purchased a policy. 

These records include all of the 

insurer’s records related to the operation 

and administration of the SGLI 

programs necessary to protect the legal 

and financial rights of the Government 

and of the persons affected by the 

activities of the agency and its agents. 

DATES: Comments must be received by 

VA on or before November 22, 2013. 

ADDRESSES: Written comments may be 

submitted through http://

www.Regulations.gov; by mail or hand 

delivery to Director, Regulation Policy 

and Management (02REG), Department 

of Veterans Affairs, 810 Vermont Ave. 

NW., Room 1068, Washington, DC 

20420; or by fax to (202) 273–9026. 

Comments should indicate that they are 

submitted in response to ‘‘RIN 2900– 

AO42 Servicemembers’ Group Life 

Insurance and Veterans’ Group Life 

Insurance Information Access.’’ Copies 

of comments received will be available 

for public inspection in the Office of 

Regulation Policy and Management, 

Room 1068, between the hours of 8:00 

a.m. and 4:30 p.m., Monday through 

Friday (except holidays). Please call 

(202) 461–4902 for an appointment. 

(This is not a toll-free number.) In 

addition, during the comment period, 

comments may be viewed online 

through the Federal Docket Management 

System at http://www.Regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Monica Keitt, Attorney/Advisor, 

Department of Veterans Affairs Regional 

Office and Insurance Center (310/290B), 

5000 Wissahickon Avenue, P.O. Box 

8079, Philadelphia, PA 19101, (215) 

842–2000, ext. 2905. This is not a tollfree number. 

SUPPLEMENTARY INFORMATION: Section 

1966(a) of title 38, United States Code, 

authorizes the Secretary of Veterans 

Affairs (Secretary) to purchase one or 

more group life insurance policies from 

one or more life insurance companies 

for the purposes of providing the 

benefits specified in 38 U.S.C. 1965– 

1980A, namely the Servicemembers’ 

Group Life Insurance (SGLI), Family 

SGLI, SGLI Traumatic Injury Protection, 

and Veterans’ Group Life Insurance 

programs (all hereafter referred to as 

SGLI). Under 38 U.S.C. 1966 and the 

terms of the policy purchased by VA 

pursuant to section 1966(a), the insurer 

has the responsibility of administering 

the SGLI programs on a day-to-day basis 

with VA retaining oversight 

responsibility to ensure that the SGLI 

programs are managed in an effective 

and efficient manner that allows the 

Secretary to fulfill his responsibilities 

under the law. 

Section 3101 of title 44, United States 

Code, requires the head of each Federal 

agency to make and preserve records 

containing adequate and proper 

documentation of the organization, 

functions, policies, decisions, 

procedures, and essential transactions of 

the agency and designed to furnish the 

information necessary to ‘‘protect the 

legal and financial rights of the 

Government and of persons directly 

affected by the agency’s activities.’’ The 

records that are created and maintained 


emcdonald on DSK67QTVN1PROD with PROPOSALS