This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

56170 

Vol. 77, No. 177 

Wednesday, September 12, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0933; Directorate 

Identifier 2012–NM–107–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 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. This proposed AD was 

prompted by reports of an incorrect 

procedure used to apply the wear and 

corrosion protective surface coating to 

attach pins of the horizontal stabilizer 

rear spar. This proposed AD would 

require inspecting to determine the part 

number of the attach pins of the 

horizontal stabilizer rear spar, and 

replacing certain attach pins with new, 

improved attach pins. We are proposing 

this AD to prevent premature failure of 

the attach pins, which could cause 

reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 29, 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, 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, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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, WA 

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– 

2012–0933; Directorate Identifier 2012– 

NM–107–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 reports of pins with an 

unapproved surface coating installed at 

the horizontal stabilizer rear spar attach 

locations. An incorrect procedure to 

apply the wear and corrosion protective 

surface coating was used by a supplier. 

The pins were installed on new 

airplanes and were also distributed by 

Boeing Spares. 

A large number of the part number (P/ 

N) 180A1612–3 and 180A1612–4 pins 

that were supplied to Boeing between 

June 30, 2006, and January 31, 2008, 

have an unapproved surface coating. 

These pins were distributed by Boeing 

Spares and were installed on most new 

airplanes delivered between August 

2006 and July 2008. These pins could 

also have been installed as terminating 

action for Boeing Service Bulletin 737– 

55–1086 (specified in AD 2004–05–19, 

Amendment 39–13514 (69 FR 10921, 

March 9, 2004; corrected April 13, 2004 

(69 FR 19313)), or during maintenance 

as specified in Section 9 of the Boeing 

737–600/700/700C/800/900/900ER 

Maintenance Planning Document. No 

practical non-destructive inspection 

procedures exist to determine whether 

the pins have an approved or 

unapproved surface coating. This 

condition, if not corrected, could result 

in premature failure of the attach pins, 

which could cause reduced structural 

integrity of the horizontal stabilizer to 

fuselage attachment, resulting in loss of 

control of the airplane. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 737–55– 

1093, dated April 9, 2012. The service 

information describes procedures for 

replacing certain attach pins of the 

horizontal stabilizer rear spar with new, 

improved attach pins. 

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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 177 / Wednesday, September 12, 2012 / Proposed Rules 56171 

Proposed AD Requirements 

This proposed AD would require 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins with new, improved 

attach pins. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,050 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 and attach pin replacement.39 work-hours × $85 per hour = 

$3,315.

Up to $6,312 ................................. $9,627 Up to $10,108,350. 

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– 

2012–0933; Directorate Identifier 2012– 

NM–107–AD. 

(a) Comments Due Date 

We must receive comments by October 29, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes; 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of an 

incorrect procedure used to apply the wear 

and corrosion protective surface coating to 

attach pins of the horizontal stabilizer rear 

spar. We are issuing this AD to prevent 

premature failure of the attach pins, which 

could cause reduced structural integrity of 

the horizontal stabilizer to fuselage 

attachment, resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number (P/N) Inspection 

For airplanes having line numbers 1 

through 3534 inclusive: Before the 

accumulation of 56,000 total flight cycles, or 

within 3,000 flight cycles after the effective 

date of this AD, whichever occurs later, 

inspect to determine the part number of the 

attach pins of the horizontal stabilizer rear 

spar. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the attach 

pin can be conclusively determined from that 

review. 

(h) Replacement 

If, during the inspection required by 

paragraph (g) of this AD, any attach pin of 

the horizontal stabilizer rear spar has P/N 

180A1612–3 or 180A1612–4, before further 

flight, replace with a new attach pin having 

P/N 180A1612–7 or 180A1612–8, 

respectively, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–55– 

1093, dated April 9, 2012. 

(i) Parts Installation Prohibition 

For all airplanes: As of the effective date 

of this AD, no person may install an attach 

pin of the horizontal stabilizer rear spar 

having P/N 180A1612–3 or 180A1612–4, on 

any airplane. 

(j) 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
56172 Federal Register / Vol. 77, No. 177 / Wednesday, September 12, 2012 / Proposed Rules 

(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. 

(k) 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, WA 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, 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, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22392 Filed 9–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0934; Directorate 

Identifier 2011–NM–260–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A330–200 and –300 series 

airplanes. This proposed AD was 

prompted by a report of a prematurely 

fractured main landing gear (MLG) bogie 

beam. This proposed AD would require 

replacing certain MLG bogie beams 

before reaching new reduced life limits. 

We are proposing this AD to prevent 

fracture of the MLG bogie beam, which, 

under high speed, could ultimately 

result in the airplane departing the 

runway, the bogie beam detaching from 

the airplane, or collapse of the MLG; 

and consequent structural damage to the 

airplane and injury to the occupants. 

DATES: We must receive comments on 

this proposed AD by October 29, 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 MessierDowty: Messier Services Americas, 

Customer Support Center, 45360 Severn 

Way, Sterling, VA 20166–8910; 

telephone 703–450–8233; fax 703–404– 

1621; Internet https://techpubs.services/ 

messier-dowty.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0934; Directorate Identifier 

2011–NM–260–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 based on 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0212, 

dated October 31, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During ground load test cycles on an 

A340–600 aeroplane, the MLG bogie beam 

has prematurely fractured. 

The results of the investigation identified 

that this premature fracture was due to high 

tensile standing stress, resulting from dry fit 

axle assembly method. Improvement has 

been introduced subsequently with a grease 

fit axle assembly method. 

Fatigue and damage tolerance analyses 

were performed, whose results demonstrated 

that the current life limit of certain MLG 

bogie beams with dry fit axles installed on 

A330 aeroplanes only must be reduced 

compared to the life limit stated in the A330 

Airworthiness Limitations Section (ALS) Part 

1—Safe Life Airworthiness Limitation Items 

revision 05 approved by EASA on 29 July 

2010. 

Failure to comply with the reduced life 

limit of the MLG bogie beam with dry fit axle 

might jeopardize the MLG structural 

integrity. 

For the reasons described above, this 

[EASA] AD requires the replacement of the 

affected MLG bogie beams before reaching 

the new reduced life limit. 

The unsafe condition is a possible 

fracture of the MLG bogie beam, which, 

under high speed, could ultimately 

result in the airplane departing the 

runway, the bogie beam detaching from 

the airplane, or collapse of the MLG; 

and consequent structural damage to the 

airplane and injury to the occupants. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Messier-Dowty has issued Service 

Letter A33–34 A20, Revision 5, 


tkelley on DSK3SPTVN1PROD with PROPOSALS