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(2) Do not install a GCU P/N 51530–021– 

EI with no MOD, MOD A, or MOD B on any 

helicopter. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5114; email 

george.schwab@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 

(1) Eurocopter Deutschland GmbH Alert 

Service Bulletin MBB–BK117 C–2–24A–010 

Revision 2, dated September 14, 2011, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. 

(2) For service information identified in 

this 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 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. 

(3) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0149R1, dated September 30, 2011. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2436: DC Generator Control Unit. 

Issued in Fort Worth, Texas, on October 30, 

2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28039 Filed 11–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1188; Directorate 

Identifier 2012–SW–049–AD; Amendment 

39–17254; AD 2012–10–53] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH 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 Deutschland GmbH (ECD) 

Model EC135 P1, EC135 P2, EC135 P2+, 

EC135 T1, EC135 T2, and EC135 T2+ 

helicopters. This is the Federal Register 

publication of an Emergency AD (EAD) 

that was previously sent to all known 

owners and operators of these 

helicopters. That EAD superseded an 

earlier related EAD. This AD requires, 

before further flight and at specified 

intervals, checking and inspecting the 

upper and lower main rotor hub (MRH) 

shaft flanges for a crack, and inspecting 

the lower hub-shaft flange bolt 

attachment areas for a crack. This AD is 

prompted by three reported incidents of 

cracking on the lower hub-shaft flanges 

of EC135 model helicopters. These 

actions are intended to detect a crack on 

the hub-shaft flange, which if not 

corrected could result in failure of the 

MRH and subsequent loss of control of 

the helicopter. 

DATES: This AD becomes effective 

December 5, 2012 to all persons except 

those persons to whom it was made 

immediately effective by Emergency AD 

No. 2012–10–53, issued on May 18, 

2012, which contained the requirements 

of this AD. 

We must receive comments on this 

AD by January 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 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 American Eurocopter 

Corporation, 2701 N. Forum Drive, 

Grand Prairie, Texas 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 May 15, 2012, we issued 

Emergency AD 2012–10–51 for the ECD 

Model EC135 series helicopters to detect 

a crack on the MRH shaft flange. 

Emergency AD 2012–10–51 required a 

pilot check of the lower MRH shaft 

flange for a crack or deformed blade 

attachment bolt safety pins before the 

first flight of each day, inspecting the 

upper and lower MRH shaft flanges for 

a crack within 5 hours time-in-service 

(TIS), and replacing the MRH shaft if 

there is a crack. 

After we issued Emergency AD 2012– 

10–51, the European Aviation Safety 


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Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, issued EASA AD No. 

2012–0085–E, dated May 17, 2012 

(2012–0085–E), which superseded 

EASA AD No. 2012–0041R1, dated 

March 15, 2012 (2012–0041R1), to 

correct an unsafe condition for the ECD 

Model EC 135 series helicopters. EASA 

advises that since issuing 2012–0041R1, 

further cracks have been detected on 

two other helicopters during the preflight checks. These are the same two 

cracks that prompted our Emergency 

AD. However, EASA also states that 

identification of deformed safety pins 

may not be sufficient to detect a crack 

on the MRH shaft flange. ECD is 

investigating the cause of the cracks and 

has developed new inspection 

procedures with further corrective 

actions. Therefore, we issued 

superseding Emergency AD 2012–10–53 

on May 18, 2012, to detect a crack on 

the MRH shaft flange, which if not 

corrected could result in failure of the 

MRH and subsequent loss of control of 

the helicopter. 

When we issued superseding 

Emergency AD 2012–10–53, we 

included additional part-numbered 

MRH shafts that should have been 

included in EAD 2012–10–51, changed 

the daily checks to recurring checks at 

intervals not to exceed 6 hours TIS, 

added a 10 hour-TIS recurring 

inspection on MRH shafts with 400 or 

more hours TIS, and removed the check 

of the blade attachment bolt safety pins 

for deformation. 

This is the Federal Register 

publication of Emergency AD 2012–10– 

53 as Amendment 39–17254; AD 2012– 

10–53. There are no differences in the 

regulatory language or requirements 

between this AD and that Emergency 

AD as it was previously sent to all 

known owners and operators of these 

helicopters. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin EC135–62A–029, 

Revision 2, dated May 17, 2012 (EC135– 

62A–029), which describes procedures 

for conducting a repetitive check of the 

visible area of the upper and lower MRH 

shaft flanges and a repetitive inspection 

of the area of the blade bolts lower MRH 

shaft flange. 

AD Requirements 

This AD supersedes Emergency AD 

2012–10–51 and requires the following: 

• Before further flight, and thereafter 

at intervals not to exceed 6 hours TIS, 

checking the lower MRH shaft flange 

and the visible area of the upper MRH 

shaft flange for a crack. An owner/ 

operator (pilot) may perform this 

required visual check and must enter 

compliance with the applicable 

paragraph of this AD into the helicopter 

maintenance records in accordance with 

14 CFR 43.9(a)(1)–(4) and 

91.417(a)(2)(v). A pilot may perform this 

check because it involves only looking 

at the visible area of the MRH shaft 

flanges and can be performed equally 

well by a pilot or a mechanic. This 

check is an exception to our standard 

maintenance regulations. 

• For an MRH shaft with 400 or more 

hours TIS, within 10 hours TIS, and 

thereafter at intervals not to exceed 10 

hours TIS, removing the rotor-hub cap; 

inspecting the upper and lower hubshaft flanges for a crack; removing the 

blade attachment bolt safety pins, nut, 

and washer; and inspecting the lower 

hub-shaft flange bolt attachment areas 

for a crack. 

• If there is a crack, replacing the 

MRH shaft. 

Differences Between This AD and the 

EASA AD 

The EASA AD identifies ECD Alert 

Service Bulletin EC135–62A–029, 

Revision 1, dated May 16, 2012. This 

AD references Revision 2. The EASA 

AD requires you to report the findings 

and sending any cracked MRH to ECD, 

and this AD does not. The EASA AD 

requires the initial check within 3 days, 

while this AD requires the check before 

further flight. 

Interim Action 

We consider this AD to be an interim 

action. Eurocopter 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 

244 helicopters of U.S. Registry. We 

estimate inspecting the MRH shaft 

flanges will require 2.5 hours at an 

average labor rate of $85 per work-hour, 

for a total cost per helicopter of $212 

and a total cost to U.S. operators of 

$51,850 per inspection cycle. Replacing 

an MRH shaft will require about 8 hours 

at an average labor rate of $85 per workhour, and required parts will cost 

$55,715, for a total cost per helicopter 

of $56,395. 

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 before 

further flight. 

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: 


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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): 

2012–10–53 Eurocopter Deutschland 

GMBH (ECD): Amendment 39–17254; 

Docket No. FAA–2012–1188; Directorate 

Identifier 2012–SW-049–AD. 

(a) Applicability 

This AD applies to Model EC135 P1, EC135 

P2, EC135 P2+, EC135 T1, EC135 T2, and 

EC135 T2+ helicopters, with a main rotor 

hub (MRH) shaft, part number (P/N) 

L623M1006101, L623M1206101, 

L623M1006102, L623M1206102, 

L623M1006103, or L623M1206103 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the MRH shaft flange, which could 

result in failure of the MRH shaft and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective December 5, 

2012 to all persons except those persons to 

whom it was made immediately effective by 

Emergency AD No. 2012–10–53, issued on 

May 18, 2012, which contained the 

requirements of this AD. 

(d) Other Affected ADs 

This AD supersedes Emergency AD No. 

2012–10–51, dated May 15, 2012. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time. 

(f) Required Actions 

(1) Before further flight, and thereafter at 

intervals not to exceed 6 hours time-inservice (TIS), check the MRH shaft lower 

flange and the visible area of the MRH shaft 

upper flange for a crack. Figures 1 and 2 to 

Paragraph (f)(1) of this AD are examples of 

cracks that have been discovered in the MRH 

shaft lower flange. The actions required by 

this paragraph 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. 

(2) For MRH shafts with 400 or more hours 

TIS, within 10 hours TIS, and thereafter at 

intervals not to exceed 10 hours TIS: 

(i) Remove rotor-hub cap. 

(ii) Clean the upper and lower MRH shaft 

flange as depicted in Figure 3 to Paragraph 

(f)(2)(ii) of this AD and visually inspect for 

a crack. 


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(iii) Remove the safety pins and nut from 

each blade bolt and the washers from the 

lower MRH shaft flange. 

(iv) Clean the blade bolt attachment area. 

(v) Using a 10X or higher power 

magnification, inspect all lower MRH shaft 

flange blade bolt attachment areas for a crack 

as shown in Figure 4 to Paragraph (f)(2)(v) of 

this AD. 


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(3) If there is a crack in the upper or lower 

MRH shaft flange, before further flight, 

replace the MRH shaft. Replacing the MRH 

shaft with an MRH shaft having a part 

number listed in the applicability of this AD 

does not constitute terminating action for the 

requirements of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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) Eurocopter Emergency Alert Service 

Bulletin EC135–62A–029, Revision 2, dated 

May 17, 2012, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

American Eurocopter Corporation, 2701 N. 

Forum Drive, Grand Prairie, Texas 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. 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 AD No. 

2012–0085–E, dated May 17, 2012. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

Issued in Fort Worth, Texas, on October 30, 

2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28100 Filed 11–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2012–0994] 

Drawbridge Operation Regulation; 

Barataria Bayou, Lafitte, LA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of temporary deviation 

from regulations. 

SUMMARY: The Coast Guard has issued a 

temporary deviation from the operating 

schedule that governs the LA 302 

(Kerner) swing span bridge across the 

Barataria Bayou, mile 35.7, at Lafitte, 

Louisiana. The deviation is necessary to 

allow a movie production crew to safely 

film at the bridge site. This deviation 

allows the bridge to remain closed to 

navigation for 12 hours on two separate 

nights. 

DATES: This deviation is effective from 

6 p.m. on November 28 through 6 a.m. 

November 30, 2012. 

ADDRESSES: Documents mentioned in 

this preamble as being available in the 

docket are part of docket USCG–2012– 

0994 and are available online by going 

to http://www.regulations.gov, inserting 

USCG–2012–0994 in the ‘‘Keyword’’ 

box and then clicking ‘‘Search’’. They 

are also available for inspection or 

copying at the Docket Management 

Facility (M–30), U.S. Department of 

Transportation, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this rule, call or 

email Kay Wade, Bridge Branch, Coast 

Guard; telephone 504–671–2128, email 

Kay.B.Wade@uscg.mil. If you have 

questions on viewing the docket, call 

Renee V. Wright, Program Manager, 

Docket Operations, telephone 202–366– 

9826. 

SUPPLEMENTARY INFORMATION: The 

Louisiana Department of Transportation 

and Development has requested a 

temporary deviation from the operating 

schedule of the swing span bridge 

across the Barataria Bayou at mile 35.7 

in Lafitte, Jefferson Parish, Louisiana. 

The vertical clearance of the bridge in 

the closed-to-navigation position is 7.2 

feet above Mean High Water, elevation 

0.8 feet and unlimited in the open-tonavigation position. Vessels will not be 

allowed to pass under the bridge during 

the closure. 

In accordance with 33 CFR 117.5, the 

bridge opens on signal for the passage 

of vessels. This deviation allows the 

swing span of the bridge to remain 

closed to navigation from 6 p.m. to 6 

a.m. on the evenings of Wednesday, 

November 28, 2012 and Thursday, 

November 29, 2012. 

The closure is necessary in order to 

safely allow movie production crews to 

film at the bridge site. Notices will be 

published in the Eighth Coast Guard 

District Local Notice to Mariners and 

will be broadcast via the Coast Guard 

Broadcast Notice to Mariners System. 

Navigation on the waterway consists 

of commercial and recreational fishing 

vessels, oil industry supply boats, crew 

boats, tug boats and standard barges. No 

alternate routes are available for the 

passage of vessels; however, the closure 

was coordinated with waterway 

interests who have indicated that they 

will be able to adjust their operations 

around the proposed schedule. 

The bridge will be able to open in the 

event of an emergency. 

Due to prior experience and 

coordination with waterway users, it 

has been determined that this closure 

will not have a significant effect on 

vessels that use the waterway. 

In accordance with 33 CFR 117.35(e), 

the drawbridge must return to its regular 

operating schedule immediately at the 

end of the designated time period. This 

deviation from the operating regulations 

is authorized under 33 CFR 117.35. 

Dated: November 2, 2012. 

David M. Frank, 

Bridge Administrator. 

[FR Doc. 2012–28126 Filed 11–19–12; 8:45 am] 

BILLING CODE 9110–04–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2012–0911] 

Drawbridge Operation Regulation; 

Thea Foss Waterway Previously 

Known as City Waterway, Tacoma, WA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of temporary deviation 

from regulations; request for comments. 

SUMMARY: The Coast Guard has issued a 

temporary deviation from the operating 

schedule that governs the Murray 

Morgan Bridge, also known as the South 

11th Street Bridge, across the Thea Foss 

Waterway, mile 0.6, previously known 

as City Waterway, at Tacoma, WA. This 

deviation will test a change to the 

drawbridge operating schedule to 

determine whether a permanent change 

to the schedule is needed. This test 

deviation will modify the existing 

regulation and add an advance 

notification requirement for obtaining 

bridge openings during designated 

times. The Coast Guard has also 

published a notice of proposed 

rulemaking (NPRM) under docket 

number USCG–2012–0911 to which 

comments may be posted 


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