40956 Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (a) 

Fitting P/Ns Fitting S/Ns 

204–012–102–001 ..... All. 

204–012–102–005 ..... All. 

204–012–102–009 ..... All, except 7500 or 

larger with a prefix 

of ‘‘A’’ or ‘‘A–FS.’’ 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the fitting and the determination that 

the applicable fittings may not have been 

manufactured in accordance with approved 

manufacturing processes and controls. This 

condition could result in failure of a fitting, 

loss of a main rotor blade, and loss of 

helicopter control. 

(c) Effective Date 

This AD becomes effective July 24, 2013. 

(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 25 hours time-in-service or 15 days, 

whichever occurs first: 

(1) Perform a magnetic particle inspection 

(MPI) of each fitting for a crack. If an MPI 

was already performed on a fitting resulting 

in re-identifying the fitting with ‘‘FM’’ at the 

end of the P/N or at the end of the P/N on 

the fitting’s component history card or 

equivalent record, then the requirements of 

this AD have been met. 

(2) If a fitting is cracked, before further 

flight, replace it with an airworthy fitting. 

(3) If a fitting is not cracked, before further 

flight, re-identify the fitting by adding ‘‘FM’’ 

at the end of the P/N using a vibrating stylus. 

The depth of the ‘‘FM’’ must not exceed 

0.005 inches or extend within 0.10 inch of 

the part’s edge. Also, add ‘‘FM’’ at the end 

of the P/N on the fitting’s component history 

card or equivalent record. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

2601 Meacham Blvd., Fort Worth, Texas, 

76137, phone: (817) 222–5710; fax: (817) 

222–5783; 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. 

(g) Additional Information 

Bell Alert Service Bulletin (ASB) No. UH– 

1H–11–07, dated May 31, 2011, which is not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

this service information, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, Fort 

Worth, TX 76101, telephone (817) 280–3391, 

fax (817) 280–6466, or at 

www.bellcustomer.com. 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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

Issued in Fort Worth, Texas, on June 18, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15946 Filed 7–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0520; Directorate 

Identifier 2013–SW–027–AD; Amendment 

39–17484; AD 2013–12–06] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model MBB–BK117 A–3, 

MBB–BK117 A–4, MBB–BK117 B–1, 

and MBB–BK117 C–2 helicopters with a 

Metro Aviation (Metro) vapor-cycle air 

conditioning kit installed in accordance 

with Supplemental Type Certificate 

(STC) No. SH3880SW. This AD requires 

repetitively inspecting the air 

conditioning drive pulley (pulley) for 

looseness and properly installed 

lockwire, and also requires reinstalling 

the pulley. This AD is prompted by two 

reports of the pulley detaching from the 

rotor brake disc on the tail rotor (T/R) 

driveshaft. These actions are intended to 

prevent separation of the pulley, 

damage to the T/R driveshaft, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

24, 2013. 

We must receive comments on this 

AD by September 9, 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 AD, the STC, 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 AD, contact Metro Aviation, Inc., 

1214 Hawn Ave, Shreveport, LA 71107; 

phone: (318) 222–5529; Web site: 

metroproductsupport.com. You may 

review the referenced 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: 

Martin Crane, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5056; email 

7-AVS-ASW-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / Rules and Regulations 40957 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

STC No. SH3880SW approves the 

installation of the Metro vapor-cycle air 

conditioning kit on Eurocopter Model 

MBB–BK117 A–3, MBB–BK117 A–4, 

MBB–BK117 B–1, and MBB–BK117 C– 

2 helicopters. The air conditioning 

compressor is driven by a pulley 

attached to the rotor brake disc. We 

received a report of a recent incident 

where the fasteners attaching the air 

conditioning compressor pulley to the 

rotor brake disc lost torque and allowed 

the pulley to separate. After the 

helicopter landed without incident, the 

pulley was discovered loose, rotating 

freely on, and causing damage to the T/ 

R driveshaft. A prior incident in 2008 

occurred where the pulley mount bolts 

sheared, resulting in the pulley 

detaching from the rotor brake disc. 

Separation of the pulley from the rotor 

brake disc could damage the T/R 

driveshaft, resulting in subsequent loss 

of control of the helicopter. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all information provided by 

Metro and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of these 

same type designs. 

Related Service Information 

We reviewed Metro Alert Service 

Bulletin No. MA145–21A–003, Revision 

A, dated April 26, 2013 (ASB MA145– 

21A–003), which describes procedures 

to inspect the pulley for properly 

installed lockwire, and for removing, 

inspecting, and re-installing the pulley. 

AD Requirements 

This AD requires, before further flight, 

and thereafter at intervals not exceeding 

10 hours time-in-service (TIS), 

inspecting the pulley for looseness and 

proper installation of the lockwire on 

the pulley mount bolts. 

Additionally, within 25 hours TIS, 

this AD requires removing the pulley, 

inspecting the bolts and mounting holes 

with a 10X or higher magnifying glass 

for damage or distortion, and reinstalling the pulley. If there is any 

damage or distortion, this AD requires 

replacing the damaged pulley. 

Differences Between This AD and the 

Manufacturer’s Service Information 

This AD requires repetitively 

inspecting the pulley bolts every 10 

hours TIS; the ASB does not require the 

repetitive inspections after re-installing 

the pulley. 

This AD also applies to Model MBB– 

BK117 A–3, MBB–BK117 A–4, MBB– 

BK117 B–1, and MBB–BK117 C–2 

helicopters; the ASB only applies to 

Model MBB–BK C–2 helicopters. 

Interim Action 

We consider this AD to be an interim 

action. The design approval holder is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Costs of Compliance 

We estimate that this AD will affect 

75 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 hour, inspecting the pulley will 

require about .5 work-hour, for a cost 

per helicopter of $43, and a total cost of 

$3,225 for the fleet per inspection cycle. 

Inspecting and re-installing the pulley 

will require about 2 work-hours, for a 

cost per helicopter of $170, and a total 

cost of $12,750 for the fleet. 

If necessary, replacing a damaged 

pulley would require about 2 workhours, and required parts would cost 

$525, for a total cost per helicopter of 

$695. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the required corrective 

actions must be accomplished within 25 

hours TIS or 30 calendar days, a very 

short time period based on the average 

flight hour utilization rate of these 

helicopters in the air ambulance and 

offshore operations industries. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

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 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

mstockstill on DSK4VPTVN1PROD with RULES

40958 Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / Rules and Regulations 

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): 

2013–12–06 Eurocopter Deutschland 

(Eurocopter): Amendment 39–17484; 

Docket No. FAA–2013–0520; Directorate 

Identifier 2013–SW–027–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

MBB–BK 117 A–3, MBB–BK 117 A–4, MBB– 

BK 117 B–1, and MBB–BK 117 C–2 

helicopters with a Metro Aviation, Inc. 

(Metro) vapor-cycle air conditioning kit 

installed in accordance with Supplemental 

Type Certificate (STC) No. SH3880SW, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loosening of an air conditioning drive pulley 

(pulley) mount bolt, which could result in 

separation of the pulley from the rotor brake 

disc on the tail rotor (T/R) driveshaft, damage 

to the T/R driveshaft, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective July 24, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time. 

(e) Required Actions 

(1) Before further flight, and thereafter at 

intervals not exceeding 10 hours time-inservice (TIS), inspect the lockwire securing 

the pulley mount bolts for proper installation 

and the pulley for looseness. If the lockwire 

is damaged or broken, or is not installed in 

a tightening direction, or if the pulley is 

loose, remove and inspect the pulley as 

described in paragraphs (e)(2)(i) and (e)(2)(ii) 

of this AD. 

(2) Within 25 hours TIS: 

(i) Remove the pulley from the rotor brake 

disc and, using a 10X or higher power 

magnifying glass, inspect the bolts and 

mounting holes glass for damage or 

distortion. If there is any damage or 

distortion, replace the pulley. 

(ii) Install the pulley and torque each 

mount bolt to 90 inch-pounds. After 

torqueing, determine whether a gap exists 

among each bolt head, washer, and the 

mating surface of the rotor brake disc. If there 

is a gap, replace the pulley. 

(iii) Lock wire each pulley mount bolt to 

its adjacent rotor brake mounting bolt with 

0.6 millimeter lockwire. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5056; 

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. 

(h) Additional Information 

(1) Metro Alert Service Bulletin No. 

MA145–21A–003, Revision A, dated April 

26, 2013, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Metro Aviation, Inc., 1214 Hawn Ave, 

Shreveport, LA 71107; phone: (318) 222– 

5529; Web site: metroproductsupport.com. 

You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) STC No. SH3880SW, amended April 16, 

2004, may be found on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2013–0520. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6500: Tail Rotor Drive. 

Issued in Fort Worth, Texas, on June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–16388 Filed 7–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2013–0515; Airspace 

Docket No. 13–AWP–8] 

RIN 2120–AA66 

Amendment of Restricted Areas R– 

2504A & R–2504B; Camp Roberts, CA, 

and Restricted Area R–2530; Sierra 

Army Depot, CA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends the 

descriptions of restricted areas R–2504A 

and R–2504B, Camp Roberts, CA, and 

restricted area R–2530, Sierra Army 

Depot, CA, by removing the 

abbreviation ‘‘PST’’ from the time of 

designation. This amendment does not 

change the dimensions of, or activities 

conducted within, R–2504A, R–2504B, 

and R–2530. 

DATES: Effective Date: 0901 UTC, 

October 17, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Colby Abbott, Airspace Policy and ATC 

Procedures Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

Background 

The time of designation for R–2504A 

and R–2504B currently reads ‘‘0600 to 

2400 PST, daily’’ and the time of 

designation for R–2530 currently reads 

‘‘0800 to 1800 PST, Monday–Friday; 

other times by NOTAM.’’ Since the 

restricted areas lie completely within 

the pacific time zone, it is unnecessary 

to specify ‘‘PST’’ in the descriptions. 

The use of ‘‘PST’’ has led to confusion 

about the time of designation during 

that part of the year when daylight 

saving time is in effect. The intended 

time of designation for restricted areas 

R–2504A and R–2504B is 0600–2400 

local time, daily, during both standard 

time and daylight saving time periods 

and for R–2530 is 0800–1800 local time, 

Monday–Friday; other times by 

NOTAM, during both standard time and 

daylight saving time periods. 

The Rule 

This action amends Title 14, Code of 

Federal Regulations (14 CFR) part 73 by 

removing ‘‘PST’’ from the time of 

designation for restricted areas R–2504A 

and R–2504B, Camp Roberts, CA, and 

R–2530, Sierra Army Depot, CA, and 

inserting the words ‘‘local time’’ in its 

place. The time of designation is 

amended to read ‘‘0600 to 2400 local 

time, daily’’ for R–2504A and R–2504B 

and ‘‘0800–1800 local time, Monday– 

Friday; other times by NOTAM’’ for R– 

2530. These changes do not alter the 

current dimensions or usage of the 

restricted areas. 

Because this action is a minor 

editorial change that does not alter the 

physical location or utilization of the 

restricted areas, I find that notice and 

public procedures under 5 U.S.C. 553(b) 

are unnecessary. 

Section 73.25 of Title 14 CFR part 73 

was republished in FAA Order JO 

7400.8V, effective February 16, 2013. 

The FAA has determined that this 

regulation only involves an established 

mstockstill on DSK4VPTVN1PROD with RULES