37790 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1137; fax (425) 227– 

1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0115, 

dated June 17, 2011; and Fokker Service 

Bulletin SBF100–53–115, dated June 16, 

2011; for related information. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Fokker Service Bulletin SBF100–53– 

115, dated June 16, 2011. 

(3) For Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com 

(4) You may review copies of the service 

information 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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 7, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14546 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0566; Directorate 

Identifier 2011–SW–008–AD; Amendment 

39–17065; AD 2012–11–02] 

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) that 

supersedes an existing Emergency 

Airworthiness Directive (EAD) for 

certain Eurocopter Deutschland GmbH 

(ECD) Model EC135 helicopters. The 

existing EAD, which was previously 

sent to all known U.S. owners and 

operators of ECD Model EC135 

helicopters and not made generally 

effective by publication in the Federal 

Register, currently requires inspecting 

the ring frame between the rear 

structure tube (tailboom) and the tail 

rotor fenestron housing (fenestron 

housing) for a crack before the first 

flight of each day and replacing any 

cracked ring frame with an airworthy 

ring frame. Since we issued that EAD, 

we have determined that a pre-flight 

pilot check in conjunction with a 

recurring 25-hour inspection is 

sufficient for determining the 

airworthiness of the ring frame. 

Additionally, ECD has developed a 

modification that is terminating action 

for the requirements of that EAD. This 

superseding AD revises the inspection 

requirements of the EAD to allow an 

owner/operator to perform the pre-flight 

pilot check, adds a recurring inspection 

of the ring frame, and allows for 

installation of a ring frame 

reinforcement as an optional 

terminating action for the AD 

requirements. The actions are intended 

to detect a crack in the ring frame which 

could result in loss of the fenestron 

structure and subsequent loss of control 

of the helicopter. 

DATES: This AD becomes effective July 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 10, 2012. 

We must receive comments on this 

AD by August 24, 2012. 

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, 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 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: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; phone (817) 

222–5110; email: sharon.y.miles@faa.

gov. 


erowe on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37791 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA EAD No.: 

2008–0190–E, dated October 13, 2008 

(EAD 2008–0190–E), to correct an 

unsafe condition for EC135 and EC635 

model helicopters. EASA advises that, 

during a recent pre-flight check on an 

EC 135 helicopter, a crack was detected 

on the ring frame that connects the tail 

rotor fenestron housing to the rear 

structure tube (tailboom). EASA states 

that this condition, if not corrected, 

could lead to crack propagation 

remaining undetected, possibly 

resulting in loss of the fenestron 

structure and loss of control of the 

helicopter. EAD 2008–0190–E requires 

accomplishing a pilot pre-flight check of 

the rear structure tube for cracks before 

each first flight of the day; amending the 

flight manual to reflect the pilot preflight check; within 25 flight hours, 

having the rear structure tube inspected 

for cracks by a mechanic; and, if any 

cracks are detected contacting ECD for 

approved corrective actions. 

On October 16, 2008, we issued EAD 

No. 2008–22–51 (EAD 2008–22–51) for 

the ECD Model EC135 helicopter. That 

EAD requires, before further flight and 

thereafter before the first flight of each 

day, visually inspecting the ring frame 

between the tailboom and fenestron 

housing for a crack, and replacing the 

ring frame with an airworthy ring frame 

if there is a crack. That EAD resulted 

from two reports of cracks on the ring 

frame connecting the tail rotor fenestron 

housing to the tailboom. The first crack 

was discovered in Germany and is 

discussed in EAD 2008–0190–E. The 

second crack, which was 9 inches long, 

was discovered in the U.S. and was in 

the same area as the first reported crack. 

We issued EAD 2008–22–51 to detect a 

crack in the ring frame, which could 

result in loss of the fenestron structure 

and subsequent loss of control of the 

helicopter. 

Actions Since Existing EAD Was Issued 

Since we issued EAD 2008–22–51, 

EASA issued AD No.: 2009–0065, dated 

March 13, 2009 (AD 2009–0065), which 

supersedes EAD 2008–0190–E. AD 

2009–0065 retains the requirements of 

EAD 2008–0190–E, expands the 

applicability to EC 135 helicopters 

manufactured in Spain, and adds a 

repetitive 100-hour inspection of the 

rear fuselage structure area for cracks. 

EASA next issued AD No.: 2009– 

0065R1, dated September 8, 2009 (AD 

2009–0065R1), which revises AD 2009– 

0065. EASA advises that ECD has 

developed a modification 

(reinforcement) of the aft ring frame, 

including a part number (P/N) change, 

for both production and in-service 

application. Consequently, AD 2009– 

0065R1 retains the inspection 

requirements of AD 2009–0065 but 

limits its applicability to helicopters 

without the reinforced aft ring frame 

installed, and allows installation of the 

reinforced aft ring frame as an optional 

terminating action for the repetitive 

checks and inspections. 

EASA then issued AD No.: 2010– 

0254, dated December 20, 2010 (AD 

2010–0254), which supersedes AD 

2009–0065R1. AD 2010–0254 retains the 

repetitive inspection requirements of 

AD 2009–0065R1, but reduces the 

interval of the visual inspection from 

100 hours to 25 hours and requires 

installation of the reinforced aft ring 

frame within 12 months as terminating 

action for the repetitive checks and 

inspections. 

Since we issued EAD 2008–22–51, we 

have determined that a pre-flight pilot 

check in conjunction with a recurring 

25-hour inspection is sufficient for 

determining the airworthiness of the 

ring frame. Therefore, we are issuing 

this AD to revise the inspection 

requirements, as well as allow for the 

optional terminating action developed 

by ECD. 

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, their 

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 is likely to exist or 

develop on other helicopters of these 

same type designs. 

Related Service Information 

We reviewed ECD Emergency Alert 

Service Bulletin (ASB) EC135–53A–022, 

Revision 02, dated November 30, 2010 

(ASB EC135–53A–022). ASB EC135– 

53A–022 describes procedures for a 

pilot check of the ring frame during the 

preflight check. ASB EC135–53A–022 

additionally prescribes a recurring 

inspection of the ring frame every 25 

flight hours and accomplishment of ECD 

Service Bulletin EC135–53–023, as 

corrected November 13, 2009 (SB 

EC135–53–023), which describes 

procedures to attach a frame 

reinforcement to the ring frame. The 

correction coversheet attached to SB 

EC135–53–023 is dated November 13, 

2009; it describes the correction on page 

6 of the service bulletin. All pages of the 

corrected service bulletin show the 

original issue date of August 19, 2009; 

the date has been underlined on page 6 

of the corrected service bulletin. 

Accomplishment of SB EC135–53–023 

constitutes terminating action for the 

visual inspection requirements of ASB 

EC135–53A–022. 

AD Requirements 

This AD supersedes EAD 2008–22–51 

and requires the following: 

• Before further flight, and thereafter 

at each preflight check, performing a 

visual check of the ring frame which 

connects the tail rotor Fenestron 

housing to the tailboom for a crack. An 

owner/operator (pilot) may perform this 

check because it involves only a visual 

check for a crack in the ring frame and 

can be performed equally well by a pilot 

or a mechanic. 

• Within 25 hours time-in-service 

(TIS), and every 25 hours TIS thereafter, 

removing the tail rotor drive shaft 

paneling and inspecting the ring frame 

for a crack. 

• As an optional terminating action 

for the requirements of this AD, 

installing a frame reinforcement to the 

ring frame and re-identifying the ring 

frame by following specified portions of 

the manufacturer’s service bulletin. 


erowe on DSK2VPTVN1PROD with RULES
37792 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

Differences Between This AD and the 

EASA AD 

This AD differs from the EASA AD as 

follows: 

• The EASA AD requires amendment 

of the Flight Manual with a page from 

ASB EC135–53A–022. Following 

issuance of the EASA AD, a revision has 

been published for the Flight Manuals 

and the amended pages are no longer 

issued with ASB EC135–53A–022. 

Therefore, this AD does not require this. 

• The EASA AD requires 

modification of the aft ring frame within 

12 months as terminating action; this 

AD provides it as an optional 

terminating action. 

• The EASA AD applies to the Model 

EC 635 helicopter, and this AD does not 

include this model because it does not 

have an FAA-issued type certificate. 

• The EASA AD includes a 

‘‘tolerance’’ range for accomplishment 

of the pilot check and visual 

inspections. This AD does not allow 

this. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

the installation of the ECD-developed 

ring frame modification as terminating 

action for the repetitive inspection 

requirements of this AD. However, the 

planned compliance time for the 

installation of the modification would 

allow enough time to provide notice and 

opportunity for prior public comment 

on the merits of the modification. 

Costs of Compliance 

We estimate that this AD will affect 

226 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Inspecting the ring frame 

requires .5 work-hour at an average 

labor rate of $85 per hour, for a cost per 

inspection cycle of $42.50 per 

helicopter, and a cost to the fleet of 

$9,605. Replacing a cracked ring frame 

will require about 8 work hours at an 

average labor rate of $85 per hour, and 

a parts cost of $7,425, for a total cost per 

helicopter of $8,105. Modifying and reidentifying the ring frame requires 17 

work-hours and a parts cost of $1,320, 

for a total cost per helicopter of $2,765 

and the cost to the fleet is $624,890. 

According to the manufacturer, they 

will cover all parts costs for a cracked 

ring frame, thereby reducing the cost 

impact on affected persons. However, as 

we do not control such coverage by the 

manufacturer, we have included all 

costs in our cost estimate. 

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 some of the required 

checks and inspections 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: 

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): 

2012–11–02 Eurocopter Deutschland 

GmbH: Amendment 39–17065; Docket 

No. FAA–2012–0566; Directorate 

Identifier 2011–SW–008–AD. 

(a) Applicability 

This AD applies to Model EC135 

helicopters with a ring frame, part number 

(P/N) L535A3501230, installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the ring frame connecting the rear 

structure tube (tailboom) and the tail rotor 

fenestron housing. This condition could 

result in loss of the fenestron structure and 

subsequent loss of control of the helicopter. 

(c) Other Affected ADs 

This AD supersedes Emergency AD 2008– 

22–51, dated October 16, 2008. 

(d) Effective Date 

This AD becomes effective July 10, 2012. 

(e) 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. 

(f) Required Actions 

(1) Before further flight, and thereafter at 

before the first flight of the day, visually 

check the ring frame that connects the tail 

rotor fenestron housing to the tailboom for a 

crack. This action 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 91.173, 121.380, or 135.439. 


erowe on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37793 

(2) Within 25 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 25 

hours TIS, remove the tail rotor driveshaft 

paneling and visually inspect the ring frame 

for a crack. 

(3) While performing a check or an 

inspection as required in paragraph (f)(1) or 

(f)(2) of this AD, paint cracks around the rivet 

heads and in the transition area between the 

tailboom and ring frame or between the ring 

frame and fenestron housing may be present 

and do not create an unsafe condition. If you 

are unable to determine whether a crack is 

on the paint or on the ring frame, you must 

remove the paint to do an accurate 

inspection. 

(4) If there is a crack in the ring frame, 

before further flight, replace it with an 

airworthy ring frame. 

(5) As an optional terminating action for 

the requirements of this AD, you may install 

a frame reinforcement to the ring frame and 

re-identify the ring frame in accordance with 

the Accomplishment Instructions, paragraph 

3.B. of Eurocopter EC135 Service Bulletin 

EC135–53–023, as corrected on November 13, 

2009, except you are not required to contact 

ECD as noted under paragraphs 3.B.(3) 

Caution and 3.B.(8). 

(g) Special Flight Permits 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; phone (817) 222–5110; email: 

sharon.y.miles@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. 

(i) Additional Information 

(1) Eurocopter Emergency Alert Service 

Bulletin (ASB) EC135–53A–022, Revision 02, 

dated November 30, 2010, 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, 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2010–0254, dated December 20, 2010. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302: Rotorcraft Tailboom. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter EC135 Service Bulletin 

EC135–53–023, as corrected on November 13, 

2009. The correction coversheet attached to 

this document is dated November 13, 2009; 

it describes the correction on page 6 of the 

service bulletin. All pages of the corrected 

service bulletin show the original issue date 

of August 19, 2009. On page 6 of the 

corrected service bulletin the date has been 

underlined. 

(ii) Reserved. 

(3) For Eurocopter 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. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(5) You may also view this service 

information at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on May 22, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–15290 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1257; Directorate 

Identifier 2011–NM–124–AD; Amendment 

39–17099; AD 2012–12–19] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

the Boeing Company Model 777–200, 

–200LR, and –300ER series airplanes. 

This AD was prompted by a report from 

the manufacturer indicating that the 

lowered ceiling support structure of 

Section 41, in airplanes incorporating 

the overhead space utilization (OSU) 

option, was found to be under-strength 

when subjected to a 9.0 g forward load. 

This AD requires installing new 

structural members, tie rod(s), and 

attach fittings on the left and right sides 

of the lowered ceiling support structure. 

We are issuing this AD to prevent the 

forward lowered ceiling panels and 

support structure from becoming 

dislodged during a 9.0 g forward load 

and consequent injury to personnel or 

interference with an emergency 

evacuation. 

DATES: This AD is effective July 30, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 30, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone (206) 544–5000, 

extension 1; fax (206) 766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ana 

Martinez Hueto, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: (425) 917– 

6592; fax: (425) 917–6591; email: 

ana.m.hueto@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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