36222 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules 

(ii) If there is no corrosion, apply touch up 

protective treatment, if required, and renew 

the bead of any damaged sealing compound 

in the upper part of the anchor fitting. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–4389; email: 

rao.edupaganti@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. 

(f) Additional Information 

(1) Eurocopter Repair Sheet 365–63–36–08, 

dated April 4, 2008 and Standard Practices 

Manual (MTC) Work Cards 20.04.04, 

20.04.05, and 20.05.01, which are not 

incorporated by reference, contain additional 

information regarding the subject of this 

proposed AD and in particular regarding the 

procedures for corrosion repair, protective 

treatment touch-up, and renewing the 

damaged sealing bead. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. You may review a 

copy of the service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(3) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0127, dated July 1, 2011. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320: Main Rotor Gearbox. 

Issued in Fort Worth, Texas, on June 7, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–14805 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0637; Directorate 

Identifier 2012–NM–006–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 certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This proposed AD was 

prompted by a report of an inboard 

main landing gear (MLG) door assembly 

departure due to premature fatigue 

cracking in the inboard MLG door hinge 

fittings. This proposed AD would 

require repetitive inspections for 

cracking of the inboard MLG door hinge 

fittings; and modification of cracked 

fittings, which would terminate the 

repetitive inspections. We are proposing 

this AD to detect and correct fatigue 

cracking in the inboard MLG door hinge 

fittings which could result in loss of the 

MLG door assembly from the airplane; 

loss of the MLG door assembly could 

impact the flight control surfaces and 

result in reduced controllability of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 2, 2012. 

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, Washington 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, 

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, 

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– 

2012–0637; Directorate Identifier 2012– 

NM–006–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 received a report of an inboard 

MLG door assembly departure due to 

premature fatigue cracking in the 

inboard MLG door hinge fittings. 

Fatigue cracking in the inboard MLG 

door hinge fittings could result in loss 

of the MLG door assembly from the 

airplane; such loss could impact the 

flight control surfaces and result in 

reduced controllability of the airplane. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules 36223 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–52A1167, dated December 

1, 2011. The service information 

describes procedures for doing 

repetitive detailed or surface high 

frequency eddy current (HFEC) 

inspections for cracking of the inboard 

MLG door hinge fittings; and 

modification of fittings, which would 

eliminate the need for the repetitive 

inspections. The modification consists 

of replacing the hinge fitting assembly. 

The initial compliance time is before 

10,000 total flight cycles, within 10,000 

flight cycles since replacement, or 

within 600 flight cycles after the 

effective date of this AD, whichever 

occurs latest. The repetitive interval is 

600 flight cycles or 5,500 flight cycles 

depending on inspection type. 

FAA’s Determination 

We are proposing 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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,175 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ......... 3 work-hours × $85 per hour = 

$255 per inspection cycle.

$0 $255 per inspection cycle ............. $299,625 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Optional Terminating Modification ............................ 9 work-hours × $85 per hour = $765 ....................... $6,550 $7,315 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 above, 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, 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. 

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): 

The Boeing Company: Docket No. FAA– 

2012–0637; Directorate Identifier 2012– 

NM–006–AD. 

(a) Comments Due Date 

We must receive comments by August 2, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800, –900, 

and –900ER series airplanes; certificated in 

any category; as identified in Boeing Alert 

Service Bulletin 737–52A1167, dated 

December 1, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 52, Doors. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
36224 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules 

(e) Unsafe Condition 

This AD was prompted by a report of an 

inboard main landing gear (MLG) door 

assembly departure due to premature fatigue 

cracking in the inboard MLG door hinge 

fittings. We are issuing this AD to detect and 

correct fatigue cracking in the inboard MLG 

door hinge fittings, which could result in loss 

of the MLG door assembly from the airplane; 

loss of the MLG door assembly could impact 

the flight control surfaces and result in 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial and Repetitive Inspections 

Except as provided by paragraph (h) of this 

AD, at the applicable time in paragraph 1.E. 

of Boeing Alert Service Bulletin 737– 

52A1167, dated December 1, 2011, do either 

a detailed or surface high frequency eddy 

current (HFEC) inspection for cracking of the 

left- and right-side inboard MLG door hinge 

fittings, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1167, dated 

December 1, 2011. If any cracking is found, 

before further flight, modify the inboard MLG 

door hinge fittings on both left- and right-side 

inboard MLG doors, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1167, dated 

December 1, 2011. Repeat either inspection at 

the applicable time in paragraph 1.E. of 

Boeing Alert Service Bulletin 737–52A1167, 

dated December 1, 2011. Doing the 

modification terminates the inspection 

requirements of this AD. 

(h) Exception 

Where Boeing Alert Service Bulletin 737– 

52A1167, dated December 1, 2011, specifies 

a compliance time ‘‘after the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: nancy.marsh@faa.gov. 

(2) 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; 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. 

Issued in Renton, Washington, on June 8, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14806 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0638; Directorate 

Identifier 2011–NM–266–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) 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 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 airplanes, 

and Model EMB–145, –145ER, –145MR, 

–145LR, –145MP, and –145EP airplanes. 

This proposed AD was prompted by a 

report of a lightning strike hitting an 

airplane tail boom causing certain rear 

bulkhead parts to jam an elevator 

control rod. This proposed AD would 

require installing or reworking, as 

applicable, metallic diverters and 

aluminum sheets; modifying the lights 

assembly on the tail boom rear movable 

fairing; and replacing the hood assembly 

with a new hood assembly and 

rerouting its electrical harness. We are 

proposing this AD to prevent lightning 

strikes from causing certain parts to 

contact the airplane pitch control 

system, which could reduce airplane 

controllability. 

DATES: We must receive comments on 

this proposed AD by August 2, 2012. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER), Technical Publications 

Section (PC 060), Av. Brigadeiro Faria 

Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; 

telephone +55 12 3927–5852 or +55 12 

3309–0732; fax +55 12 3927–7546; 

email distrib@embraer.com.br; Internet: 

http://www.flyembraer.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 Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS