Federal Register / Vol. 78, No. 206 / Thursday, October 24, 2013 / Proposed Rules 63429 

5.4.2 Calculate the annual input to the pool 

heater as: 

EIN = EF + EAE

where: 

EF = as defined in 5.2 of this appendix 

EAE = as defined in 5.3 of this appendix 

5.4.3 Calculate the pool heater integrated 

thermal efficiency (TEI) (in percent). 

TEI = 100(EOUT/EIN) 

where: 

EOUT = as defined in 5.4.1 of this appendix 

EIN = as defined in 5.4.2 of this appendix 

100 = conversion factor, from fraction to 

percent 

[FR Doc. 2013–24352 Filed 10–23–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0872; Directorate 

Identifier 2013–SW–012–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 adopt a new 

airworthiness directive (AD) for 

Eurocopter France Model AS332C, 

AS332L, AS332L1, AS332L2, EC225LP, 

and SA330J helicopters with a certain 

tail rotor control turnbuckle 

(turnbuckle) installed. This proposed 

AD would require inspecting the 

turnbuckles for corrosion or a crack, and 

depending on the results, either 

replacing the turnbuckle or treating the 

turnbuckle for corrosion. This proposed 

AD is prompted by a report that a 

turnbuckle had failed because of 

corrosion. The proposed actions are 

intended to detect corrosion or a crack 

on a turnbuckle and prevent the failure 

of a turnbuckle, loss of control of the tail 

rotor and subsequent loss of control of 

the helicopter. 

DATES: We must receive comments on 

this proposed AD by December 23, 

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 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: 

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 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2013– 

0081, dated March 26, 2013, to correct 

an unsafe condition for the Eurocopter 

Model SA330J, AS332C, AS332C1, 

AS332L, AS332L1, AS332L2, EC225LP 

helicopters equipped with tail rotor 

control turnbuckles, part number 

330A27–5031–20. EASA advises that 

one of the two turnbuckles installed on 

the tail rotor’s yaw flight control cables 

failed on a helicopter because of 

corrosion. The subsequent investigation 

revealed a lack of Mastinox sealant 

coating between both sides of the 

turnbuckle’s internal tappings and the 

interface screws of the end-fitting 

components of the yaw flight control 

cables. EASA advises that this likely 

caused the corrosion. This condition, if 

not detected and corrected, could lead 

to failure of a tail rotor control 

turnbuckle, resulting in loss of control 

of the tail rotor and subsequent loss of 

control of the helicopter. 

To address this condition, EASA 

issued AD No. 2013–0081, which 

requires repetitive inspections of each 

turnbuckle and, depending on the 

results, either replacing the turnbuckle 

or treating the turnbuckle for corrosion. 

EASA revised its AD and issued AD No. 

2013–0081R1, dated June 20, 2013, to 

clarify some of the requirements. 

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 products of the same 

type design. 

Related Service Information 

On March 14, 2013, Eurocopter issued 

Alert Service Bulletin (ASB) No. EC225– 

05A031 for Model No. EC225LP 

helicopters; ASB No. AS332–05.00.95 

for Model AS332C, AS332C1, AS332L, 

AS332L1 and AS332L2 and for military 

Model AS332B, AS332B1, AS332F1, 

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63430 Federal Register / Vol. 78, No. 206 / Thursday, October 24, 2013 / Proposed Rules 

AS332M and AS332M1 helicopters; and 

ASB No. SA330–05.98 for Model 

SA330J and military Model SA330Ba, 

SA330Ca, SA330Ea, SA330H, SA330L, 

SA330Jm, SA330S1 and SA330Sm 

helicopters. Eurocopter reports that a 

tail rotor control turnbuckle ruptured 

because of corrosion. The damage was 

discovered during a flight-control check 

after the main gearbox was replaced. An 

investigation revealed that Mastinox 

sealant was missing between the 

turnbuckle tappings and end-fittings 

and led to the formation of galvanic 

corrosion. To prevent a turnbuckle from 

splitting, Eurocopter called for checking 

all tail rotor control turnbuckles for 

cracks and corrosion every 12 months. 

On June 5, 2013, Eurocopter revised all 

of the ASBs with Revision 1 to clarify 

a requirement. 

Proposed AD Requirements 

This proposed AD would require: 

For helicopters delivered before 

March 1, 2013, within 110 hours timein-service (TIS) or 3 months, whichever 

occurs first, and at intervals not to 

exceed 12 months thereafter, inspecting 

the turnbuckles for corrosion or a crack. 

The delivery date is the date the 

helicopter left Eurocopter’s 

manufacturing plant in France and is 

the date on the helicopter’s 

identification plate. 

For helicopters delivered on or after 

March 1, 2013, within 12 months, and 

at intervals not to exceed 12 months 

thereafter, inspecting the turnbuckles 

for corrosion or a crack. 

If there is corrosion or a crack on the 

tappings or middle hole of the internal 

surface of the turnbuckle, or if there is 

corrosion with a depth of more than 0.3 

mm or a crack on the external surface 

of a turnbuckle, removing the 

turnbuckle from service before the next 

flight. 

If corrosion is present at or less than 

a depth of 0.3 mm on the turnbuckle’s 

external surface, before the next flight, 

treating the affected turnbuckle to 

prevent corrosion and then removing 

the treated turnbuckle from service 

within 6 months from the date the part 

is treated for corrosion. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD applies to Eurocopter 

Model AS332C1 helicopters. This 

proposed AD does not because Model 

AS332C1 helicopters are not type 

certificated in the United States. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 46 helicopters of U.S. 

Registry and that labor costs average $85 

a work-hour. Based on these estimates, 

we would expect the following costs: 

• Inspecting the tail rotor control 

turnbuckles for corrosion or a crack 

would require 4 work-hours for a labor 

cost of $340. Parts would cost $148 for 

a total cost of $488 per helicopter, 

$22,448 for the U.S. fleet. 

• Treating the turnbuckle to prevent 

corrosion would require 1 work-hour for 

a labor cost of $85. The cost of parts is 

minimal for a total cost of $85 per 

helicopter. 

• Replacing the turnbuckle would not 

require additional labor costs because it 

can be done as part of the inspection. 

Parts would cost $173 for a total cost of 

$173 per helicopter. 

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 adding 

the following new airworthiness 

directive (AD): 

Eurocopter France: Docket No. FAA–2013– 

0872; Directorate Identifier 2013–SW– 

012–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS332C, AS332L, 

AS332L1, AS332L2, EC225LP, and SA330J 

helicopters with a tail rotor control 

turnbuckle (turnbuckle), part number (P/N) 

330A27–5031–20, installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a turnbuckle. This condition could 

result in loss of the tail rotor control and 

subsequent loss of helicopter control. 

(c) Comments Due Date 

We must receive comments by December 

23, 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 

(1) For helicopters delivered before March 

1, 2013, within 110 hours time-in-service 

(TIS) or 3 months, whichever occurs first, 

and for helicopters delivered on or after 

March 1, 2013, within 12 months, and 

thereafter for all helicopters at intervals not 

to exceed 12 months, using a light source 

visually inspect the tappings, middle hole, 

and external surface of each turnbuckle for 

corrosion or a crack. Indications of corrosion 

include dirt, a bulge, faded paint, a powdery 

deposit, or a pit that is white or red in color. 

(i) If there is corrosion or a crack on the 

tappings or middle hole of the internal 

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Federal Register / Vol. 78, No. 206 / Thursday, October 24, 2013 / Proposed Rules 63431 

surface of a turnbuckle, replace the 

turnbuckle before further flight. 

(ii) If there is a crack on the external 

surface of a turnbuckle, replace the 

turnbuckle before further flight. 

(iii) If there is corrosion on the external 

surface of the turnbuckle, remove the 

corrosion, recondition the surface, and 

measure the corrosion depth in accordance 

with paragraph 3.B.2.b.2 of Eurocopter Alert 

Service Bulletin (ASB) No. EC225–05A031, 

ASB No. AS332–05.00.95, or ASB No. 

SA330–05.98, all Revision 1 and all dated 

June 5, 2013, as applicable to your model 

helicopter, except that you are not required 

to interpret the results per ASB paragraph 

1.E.2. 

(A) If the measured corrosion depth is 

greater than 0.3 mm, replace the turnbuckle 

before further flight. 

(B) If the measured corrosion depth is 0.3 

mm or less, do the following: 

(1) Before further flight, treat the 

turnbuckle for corrosion in accordance with 

paragraph 3.B.2.c of ASB No. EC225–05A031, 

ASB No. AS332–05.00.95, or ASB No. 

SA330–05.98, as applicable to your model 

helicopter. 

(2) Within 6 months from when the 

turnbuckle is treated for corrosion, replace 

the turnbuckle. 

(2) After installation of a turnbuckle, P/N 

330A27–5031–20, with greater than 0 hours 

TIS, before next flight accomplish the actions 

of paragraph (e)(1) of this AD. 

(f) Special Flight Permit 

Special flight permits are prohibited. 

(g) 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– 

5110; 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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0081, dated March 26, 2013. You 

may view the EASA AD in the AD docket on 

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

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

Issued in Fort Worth, Texas on September 

27, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24942 Filed 10–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0866; Directorate 

Identifier 2013–NM–131–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This proposed AD was 

prompted by reports of cracks found in 

the aft support fitting, the rear spar 

upper chord, and the rear spar web. 

This proposed AD would require 

repetitive inspections for cracking of the 

aft support fitting for the main landing 

gear (MLG) beam, and the rear spar 

upper chord and rear spar web in the 

area of rear spar station (RSS) 224.14; 

and repair if necessary. We are 

proposing this AD to detect and correct 

such cracks, which could grow and 

result in a fuel leak and possible fire. 

DATES: We must receive comments on 

this proposed AD by December 9, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0866; Directorate Identifier 2013– 

NM–131–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received five reports of 

cracks found in the aft support fitting 

for the MLG beam, and the rear spar 

upper chord and rear spar web in the 

area of rear spar station (RSS) 224.14. 

One report was of a vertical crack found 

in the rear spar web, along with cracks 

in the aft support fitting and rear spar 

upper chord. A second report indicated 

cracks found in two holes in the rear 

spar upper chord and rear spar web. A 

third report was of a crack in the rear 

spar upper chord that extended 

downward to the edge of the vertical 

flange and upward to the horizontal 

flange. The affected airplanes had 

accumulated between 42,988 and 66,572 

total flight hours, and between 29,015 

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