Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules 58327 

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– 

2012–0987; Directorate Identifier 2012– 

NM–130–AD. 

(a) Comments Due Date 

We must receive comments by November 

5, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes, certificated in any category, as 

identified in Boeing Special Attention 

Service Bulletin 737–23–1302, dated August 

24, 2009; and Model 757–200 series 

airplanes, certificated in any category, as 

identified in Boeing Special Attention 

Service Bulletin 757–23–0107, Revision 1, 

dated May 16, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 23, Communications. 

(e) Unsafe Condition 

This AD was prompted by a report of 

damage caused by electrical arcing to the 

wires that connect seat electronics boxes. We 

are issuing this AD to prevent power from 

being supplied to passenger seats when the 

entertainment control switch is in the OFF 

position, which could cause an electrical 

shock hazard resulting in serious or fatal 

injury to maintenance personnel. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of New Relay and Wiring 

Bundle Change 

Within 24 months after the effective date 

of this AD: Change the wire bundle route, 

and install a new relay and applicable wiring 

of the entertainment control switch, in 

accordance with the Accomplishment 

Instructions of the service information 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable. 

(1) For Model 737–300, –400, and –500 

series airplanes: Use Boeing Special 

Attention Service Bulletin 737–23–1302, 

dated August 24, 2009. 

(2) For Model 757–200 series airplanes: 

Use Boeing Special Attention Service 

Bulletin 757–23–0107, Revision 1, dated May 

16, 2012. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Binh Tran, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6485; fax: 425–917– 

6590; email: binh.tran@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 

September 7, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23150 Filed 9–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0995; Directorate 

Identifier 2012–NM–056–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 A330–300 series airplanes 

and Model A340–200 and –300 series 

airplanes. This proposed AD was 

prompted by reports that, during a flight 

test, several spoiler servo-controls 

(SSCs) did not remain locked in the 

retracted position (hydraulic locking 

function) after manual depressurization 

of the corresponding hydraulic circuit. 

Loss of that locking function—which is 

ensured by a blocking valve—was 

caused by an internal leak from a 

sheared seal on the blocking valve. This 

proposed AD would require inspecting 

to determine if certain SSCs are 

installed, performing an operational test 

of any affected SSC, and replacing if 

necessary. We are proposing this AD to 

prevent loss of the hydraulic locking 

function during take-off and go-around 

phases, which, in combination with 

malfunction of one engine, could result 

in reduced controllability of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 5, 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 Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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: 

Vladimir Ulyanov, Aerospace Engineer, 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
58328 Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 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–2012–0995; Directorate Identifier 

2012–NM–056–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 2012–0009, 

dated January 13, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Two operators have reported that several 

spoilers did not remain locked in the 

retracted position (lifted up without order) 

after manual depressurization of the 

corresponding hydraulic circuit during flight 

test. 

Subsequent checks on ground confirmed 

that, for each affected spoiler surface, the 

spoiler was fitted with one MZ-type Spoiler 

Servo Control (SSC) (Part Number (P/N) 

MZ4339390–12 or P/N MZ4306000–12). 

The results of the investigations on the 

affected SSCs, done by the supplier, revealed 

that the loss of the hydraulic locking 

function—which is ensured by a blocking 

valve—was due to an internal leakage caused 

by a sheared seal. This seal is installed at the 

left end of the blocking valve. 

During the on-wing modification of the 

maintenance cover, blocking valve movement 

may have damaged the seal on the outer 

diameter of the blocking valve assembly, 

causing the loss of the hydraulic locking 

function. 

This condition, if not detected and 

corrected, if occurring during take-off and goaround phases in combination with one 

engine inoperative, could jeopardize the 

aeroplane safe flight. 

For the reasons described above, this 

[EASA] AD requires the identification of the 

installed SSCs, to perform an operational test 

of the hydraulic locking function of the 

affected SSCs and to accomplish the 

applicable corrective actions if any 

discrepancy is detected during the 

operational test. This [EASA] AD also 

requires reporting operational test results to 

Airbus. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Other Related Rulemaking 

On August 26, 2009, the FAA issued 

AD 2009–18–20, Amendment 39–16017 

(74 FR 46313, September 9, 2009), 

applicable to certain Airbus Model 

A330–300, A340–200, and A340–300 

series airplanes. That AD requires 

identifying the part number of spoiler 

servo-controls installed on the airplane 

at all positions to determine the number 

of affected hydraulic circuits, and 

modifying affected spoiler servocontrols. The actions required by that 

AD are intended to prevent loss of the 

three hydraulic systems, which could 

result in reduced controllability of the 

airplane. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) A330–27A3185 and AOT A340– 

27A4181, both dated January 4, 2012. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

Unlike the procedures recommended 

in Airbus AOTs A330–27A3185 and 

A340–27A4181, both dated January 4, 

2012, this proposed AD would not 

permit further flight after a faulty SSC 

is detected on the green or yellow 

hydraulic line. Instead, this proposed 

AD would require replacing the SSC 

with a new or serviceable SSC before 

further flight. We find that, to achieve 

an adequate level of safety for the 

affected fleet, damaged SSCs must be 

replaced before further flight. 

Although the MCAI mandates 

performing the operational test within 

90 days after the effective date of the 

AD, we have determined that the 

operational test should be performed 

within 90 days after identification of the 

part. 

These differences have been 

coordinated with EASA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 61 products of U.S. registry. 

We also estimate that it would take up 

to 7 work-hours per product to comply 

with the basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$36,295, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 36 work-hours and require parts 

costing $34,928, for a cost of $37,988 

per affected SSC. We have no way of 

determining the number of products 

that may need these actions. 

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 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: 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules 58329 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0995; 

Directorate Identifier 2012–NM–056–AD. 

(a) Comments Due Date 

We must receive comments by November 

5, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by reports that, 

during flight test, several spoiler servocontrols (SSCs) did not remain locked in the 

retracted position (hydraulic locking 

function) after manual depressurization of 

the corresponding hydraulic circuit. Loss of 

that locking function—which is ensured by a 

blocking valve—was caused by an internal 

leak from a sheared seal on the blocking 

valve. We are issuing this AD to prevent loss 

of the hydraulic locking function during takeoff and go-around phases, which, in 

combination with malfunction of one engine, 

could result in reduced controllability of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 90 days after the effective date of 

this AD: Inspect to determine the part 

number (P/N) of all SSCs installed, in 

accordance with Airbus All Operators Telex 

(AOT) A330–27A3185 (for Model A330–300 

series airplanes) or A340–27A4181 (for 

Model A340–200 and –300 series airplanes), 

both dated January 4, 2012. A review of 

airplane maintenance records is acceptable in 

lieu of the inspection to identify the part 

number of the SSC installed, provided that 

part number can be conclusively determined 

from that review. 

(1) For any SSC having P/N MZ4339390– 

12 or P/N MZ4306000–12 (MZ-type): Within 

90 days after identification of the part, 

perform an operational test of the hydraulic 

locking function at each position fitted with 

an MZ-type SSC, in accordance with the 

Accomplishment Instructions of Airbus AOT 

A330–27A3185 (for Model A330–300 series 

airplanes) or A340–27A4181 (for Model 

A340–200 and –300 series airplanes), both 

dated January 4, 2012. 

(2) If any discrepancy is detected during 

the operational test specified in paragraph 

(g)(1) of this AD, or if the test fails, before 

further flight, replace the affected SSC with 

a new or serviceable SSC, in accordance with 

Airbus AOT A330–27A3185 (for Model 

A330–300 series airplanes) or A340–27A4181 

(for Model A340–200 and –300 series 

airplanes), both dated January 4, 2012. 

(h) Reporting to Airbus 

Submit a report of the findings of the 

operational test required by paragraph (g)(1) 

of this AD (both positive and negative) to 

Airbus, Customer Services, Engineering and 

Technical Support, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France, Attn: 

Daniel Lopez-Fernandez, SEEL6; fax: (+33) 5 

61 93 04 52; email: daniel.lopezfernandez@airbus.com; at the applicable time 

specified in paragraph (h)(1) or (h)(2) of this 

AD. 

(1) If the test was done on or after the 

effective date of this AD: Submit the report 

within 30 days after the test. 

(2) If the test was done before the effective 

date of this AD: Submit the report within 30 

days after the effective date of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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. 

(j) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2012–0009, dated January 13, 2012, 

and the service information specified in 

paragraph (j)(1)(i) or (j)(1)(ii) of this AD, for 

related information. 

(i) Airbus AOT A330–27A3185, dated 

January 4, 2012. 

(ii) Airbus AOT A340–27A4181, dated 

January 4, 2012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
58330 Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules 

Issued in Renton, Washington, on 

September 11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23217 Filed 9–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0994; Directorate 

Identifier 2012–NM–119–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 supersede an 

existing airworthiness directive (AD) 

that applies to all The Boeing Company 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes. The 

existing AD currently requires repetitive 

inspections of the aft attach lugs of the 

elevator tab control mechanisms, and 

replacement of any discrepant elevator 

tab control mechanism. Since we issued 

that AD, Boeing has developed a 

modification of the aft attach lugs of the 

elevator tab control mechanisms, which 

will adequately address the unsafe 

condition. This proposed AD would 

require replacing the left and right 

elevator tab control mechanisms with 

elevator tab control mechanisms that 

have the modified attach lugs, which 

would terminate the existing 

requirements. We are proposing this AD 

to prevent discrepancies in the aft attach 

lugs of the elevator tab control 

mechanism, which could result in 

severe elevator and tab vibration. 

Consequent structural failure of the 

elevator or horizontal stabilizer could 

result in loss of structural integrity and 

aircraft control. 

DATES: We must receive comments on 

this proposed AD by November 5, 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 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: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; 

phone: 425–917–6490; fax: 425–917– 

6590; email: kelly.mcguckin@faa.gov. 

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–2012–0994; Directorate Identifier 

2012–NM–119–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 

On August 11, 2010, we issued AD 

2010–17–19, Amendment 39–16413 (75 

FR 52242, August 25, 2010), for all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. That AD requires repetitive 

inspections of the aft attach lugs of the 

elevator tab control mechanisms, and 

replacement of any discrepant elevator 

tab control mechanism. That AD was 

prompted by reports of failure of the aft 

attach lugs on the elevator tab control 

mechanisms, which resulted in severe 

elevator vibration. That AD also was 

prompted by reports of gaps in elevator 

tab control mechanisms and analysis 

that additional elevator tab control 

mechanisms might have bearings that 

will come loose. We issued that AD to 

detect and correct discrepancies in the 

aft attach lugs of the elevator tab control 

mechanism, which could result in 

elevator and tab vibration. Consequent 

structural failure of the elevator or 

horizontal stabilizer could result in loss 

of structural integrity and aircraft 

control. 

Actions Since Existing AD (AD 2010– 

17–19, Amendment 39–16413 (75 FR 

52242, August 25, 2010)) Was Issued 

The preamble to AD 2010–17–19, 

Amendment 39–16413 (75 FR 52242, 

August 25, 2010), specifies that we 

consider the requirements ‘‘interim 

action’’ and that the manufacturer is 

developing a modification to address 

the unsafe condition. That AD explains 

that we might consider further 

rulemaking if a modification is 

developed, approved, and available. The 

manufacturer now has developed such a 

modification, and we have determined 

that further rulemaking is indeed 

necessary; this proposed AD follows 

from that determination. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

737–27–1300, dated April 16, 2012, 

which describes procedures for 

replacing elevator tab control 

mechanisms that have sheet metal aft 

attach lugs with elevator tab control 

mechanisms that have new machined 

aft attach lugs. 

Boeing Service Bulletin 737–27–1300, 

dated April 16, 2012, has been approved 

as an alternative method of compliance 

with the requirements of paragraphs (g) 

through (t) of AD 2010–17–19, 

Amendment 39–16413 (75 FR 52242, 

August 25, 2010). 

Clarification of Part Name 

The elevator tab control mechanism is 

incorrectly identified as the ‘‘elevator 

control tab mechanism’’ in certain 


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