40954 Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / Rules and Regulations 

By the National Credit Union 

Administration Board, on July 2, 2013. 

Mary F. Rupp, 

Secretary of the Board. 

[FR Doc. 2013–16399 Filed 7–8–13; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0553; Directorate 

Identifier 2011–SW–041–AD; Amendment 

39–17502; AD 2013–13–14] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for various 

restricted category Model HH–1K, TH– 

1F, TH–1L, UH–1A, UH–1B, UH–1E, 

UH–1F, UH–1H, UH–1L, and UH–1P 

helicopters with certain main rotor hub 

inboard strap fittings (fittings) installed. 

This AD requires a magnetic particle 

inspection (MPI) of the fittings for a 

crack, and if there is a crack, replacing 

the fitting with an airworthy fitting. 

This AD is prompted by reports of 

cracked fittings on Bell model 

helicopters and the determination that 

these same part-numbered fittings may 

be installed on various restricted 

category helicopters. These actions are 

intended to detect a crack in a fitting, 

which may lead to failure of a fitting, 

loss of a main rotor blade, and 

subsequent loss of helicopter control. 

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 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 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 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: 

Michael Kohner, Aerospace Engineer, 

FAA, Rotorcraft Directorate, Rotorcraft 

Certification Office, 2601 Meacham 

Blvd., Fort Worth, Texas, 76137, phone: 

(817) 222–5170; fax: (817) 222–5783; 

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, 

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 

On January 28, 2013, we issued AD 

2013–03–16, Amendment 39–17339 (78 

FR 9793, February 12, 2013), for Bell 

Model 204B, 205A, 205A–1, 205B, 210, 

and 212 helicopters with certain partnumbered fittings installed. AD 2013– 

03–16 requires a one-time MPI of the 

fittings for a crack, replacing the fittings 

with airworthy fittings if there is a 

crack, and re-identifying the fitting by 

adding ‘‘FM’’ to the end of its partnumber (P/N) if there is no crack. The 

AD was prompted by reports of cracks 

in the fittings. The cracking was 

determined to have been caused by the 

manufacturer’s failure to follow 

approved manufacturing processes and 

controls during the quenching operation 

from the heat treating of the fittings. 

After AD 2013–03–16 was issued, we 

determined that the same partnumbered Bell fittings may be installed 

on various restricted category Model 

HH–1K, TH–1F, TH–1L, UH–1A, UH– 

1B, UH–1E, UH–1F, UH–1H, UH–1L, 

and UH–1P helicopters and are 

susceptible to the same type of cracking. 

Therefore, we are mandating the 

inspection requirements for the 

applicable restricted category 

helicopters. While Bell is the 

manufacturer of these helicopters, the 

type certificates are held by other 

entities. The type certificate holders for 

the Model HH–1K, TH–1F, TH–1L, UH– 

1A, UH–1B, UH–1E, UH–1F, UH–1H, 

UH–1L, and UH–1P helicopters are: 

Arrow Falcon Exporters Inc.; AST, Inc.; 

Bell Helicopter Textron, Inc..; Global 

Helicopter Technology, Inc.; Hagglund 

Helicopters, LLC; JJASPP Engineering 

Services, LLC; Northwest Rotorcraft, 

LLC; Overseas Aircraft Support, Inc.; 

Richards Heavylift Helo, Inc.; Robinson 

Air Crane, Inc.; Rotorcraft Development 

Corporation; San Joaquin Helicopters; 

Southern Helicopter, Inc.; and Tamarack 

Helicopters, Inc. Southwest Florida 

Aviation International, Inc. is the type 

certificate holder for the UH–1B (SW204 

and SW204HP) and UH–1H (SW205) 

helicopters. 

The actions specified in this AD are 

intended to detect a crack in a fitting, 

leading to a failure of the fitting, loss of 

a main rotor blade, and subsequent loss 

of helicopter control. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Related Service Information 

We have reviewed Bell Alert Service 

Bulletin (ASB) No. UH–1H–11–07 for 

Model UH–1H helicopters, dated May 

31, 2011. The procedures provided in 

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Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / Rules and Regulations 40955 

this ASB concern all applicable 

helicopters. This ASB specifies: 

• For fittings with less than 400 hours 

time-in-service (TIS), performing an MPI 

within 100 flight hours but before the 

fitting reaches 425 flight hours or before 

November 26, 2011, whichever occurs 

first. 

• For fittings with more than 400 

hours, performing an MPI within 25 

flight hours or before November 26, 

2011, whichever occurs first. 

• If cracks are found, replacing the 

fitting. 

• If no cracks are found, visually 

inspecting all edges for raised material. 

If raised material is found, removing the 

material by hand using an India stone, 

repeating the MPI inspection, and reidentifying the fitting as described 

below. If the raised material cannot be 

removed within specified limits, 

replacing the fitting. 

• If no cracks and no raised material 

are found, re-identifying the fitting and 

historical service records by adding an 

‘‘FM’’ at the end of the part number and 

marking a record entry. 

AD Requirements 

This AD requires: 

• Within 25 hours TIS or 15 days, 

whichever comes first, performing an 

MPI of each fitting for a crack. 

• If a fitting has a crack, before further 

flight, replacing the fitting with an 

airworthy fitting. 

• If a fitting has no crack, reidentifying the fitting and its component 

history card or equivalent record by 

adding ‘‘FM’’ at the end of the P/N. 

Differences Between This AD and the 

Service Information 

This AD differs from the ASBs in that 

we require an MPI within 25 hours TIS 

or 15 days, whichever comes first, of 

any fitting with an applicable P/N and 

S/N. Bell requires different compliance 

times based on the hours TIS of the 

fitting. We also do not require returning 

parts to Bell. Finally, we do not require 

visually inspecting all edges for raised 

material (shot peen rollover) on fittings 

with a certain P/N. 

Interim Action 

We consider this AD to be an interim 

action. Bell is investigating the safety 

risks regarding the raised material at the 

fittings’ edges. Depending on the 

outcome of the investigation, we might 

consider additional rulemaking. 

Costs of Compliance 

We estimate that this AD affects 300 

helicopters of U.S. registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs to comply with this AD: 

• MPI of each set of fittings (two per 

helicopter) requires 40 work-hours for a 

labor cost of $3,400 per helicopter, 

$1,020,000 for the fleet. No parts are 

needed. 

• If a fitting is cracked, replacement 

parts will cost $2,367 per fitting. Labor 

costs will not be an additional expense 

as they can be absorbed as part of the 

inspection. 

FAA’s Justification and Determination 

of the Effective Date 

We find that the risk to the flying 

public justifies waiving notice and 

comment prior to the adoption of this 

rule because of the short compliance 

time of 25 hours TIS or 15 days, 

whichever comes first, to magnetic 

particle inspect for a crack in the fitting. 

As these helicopters are often used in 

the timber industry and for firefighting, 

they may accrue 25 hours TIS within a 

week. Failure of these fittings could 

result in a catastrophic accident. 

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: 

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): 

2013–13–14 Various Restricted Category 

Helicopters: Amendment 39–17502; 

Docket No. FAA–2013–0553; Directorate 

Identifier 2011–SW–041–AD. 

(a) Applicability 

This AD applies to Arrow Falcon Exporters 

Inc.; AST, Inc.; Bell Helicopter Textron, Inc.; 

Global Helicopter Technology, Inc.; 

Hagglund Helicopters, LLC; JJASPP 

Engineering Services, LLC; Northwest 

Rotorcraft, LLC; Overseas Aircraft Support, 

Inc.; Richards Heavylift Helo, Inc.; Robinson 

Air Crane, Inc.; Rotorcraft Development 

Corporation; San Joaquin Helicopters; 

Southern Helicopter, Inc.; and Tamarack 

Helicopters, Inc. Model HH–1K, TH–1F, TH– 

1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, 

UH–1L, and UH–1P helicopters, and 

Southwest Florida Aviation International, 

Inc., Model UH–1B (SW204 and SW204HP) 

and UH–1H (SW205) helicopters, certificated 

in any category, with a main rotor hub 

inboard strap fitting (fitting) with a part 

number (P/N) and serial number (S/N) listed 

in Table 1 to paragraph (a) of this AD. 

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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, 

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