Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 49705 

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. 

(3) The following service information was 

approved for IBR on September 21, 2012. 

(i) Embraer Service Bulletin 170–21–0049, 

dated November 29, 2010. 

(ii) Embraer Service Bulletin 190–21–0035, 

dated November 29, 2010. 

(iii) Embraer Service Bulletin 190LIN–21– 

0016, dated February 23, 2011. 

(4) The following service information was 

approved for IBR on September 9, 2010 (75 

FR 52238, August 25, 2010). 

(i) EMBRAER Operational Bulletin 170– 

001/09, Revision 1, dated February 10, 2010. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Embraer S.A., 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. 

(6) You may review copies of the 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. 

(7) 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 July 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–19396 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0659; Directorate 

Identifier 2011–SW–061–AD; Amendment 

39–17101; AD 2012–12–21] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that was 

published in the Federal Register. That 

AD applies to Eurocopter Deutschland 

GmbH Model MBB–BK 117 C–2 

helicopters. A page reference of the 

rotorcraft flight manual in the Required 

Actions section, paragraph (e)(1)(i), is 

incorrect. This document corrects that 

error. In all other respects, the original 

document remains the same. 

DATES: This correction is effective 

August 17, 2012. The effective date for 

AD 2012–12–21 remains July 10, 2012. 

The last date for submitting comments 

to the final rule; request for comments 

remains August 24, 2012. 

ADDRESSES: 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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5110, email: 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2012–12–21, 

Amendment 39–17101 (77 FR 37777, 

June 25, 2012), currently includes the 

following paragraph (e)(1)(i) in the 

Required Actions section: 

‘‘(i) ‘‘Emergency and Malfunction 

Procedures’’: pages 3–3 and 3–4, and’’ 

As published, the reference to page 3– 

4 is incorrect. The correct reference is to 

page 3–3a. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the final rule is being 

published in the Federal Register. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

In the Federal Register of June 25, 

2012, on page 37779 in the second 

column, paragraph (e)(1)(i) of AD 2012– 

12–21 is corrected to read as follows: 

* * * * * 

(i) ‘‘Emergency and Malfunction 

Procedures’’: pages 3–3 and 3–3a, and 

* * * * * 

Issued in Fort Worth, Texas, on August 9, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–20177 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0291; Directorate 

Identifier 2011–NM–168–AD; Amendment 

39–17158; AD 2012–16–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–112 and –121 

airplanes; Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes. This AD was prompted by 

reports that some nuts installed on the 

wing, including on primary structural 

elements, were found cracked. This AD 

requires inspecting to determine if 

certain nuts are installed or cracked, 

and replacing the affected nuts if 

necessary. We are issuing this AD to 

detect and correct missing and cracked 

nuts, which could result in the 

structural integrity of the airplane wings 

being impaired. 

DATES: This AD becomes effective 

September 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 21, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


tkelley on DSK3SPTVN1PROD with RULES
49706 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 21, 2012 (77 FR 

16492). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During structural part assembly in Airbus 

production line, some [wing] nuts Part 

Number (P/N) ASNA2531–4 were found 

cracked. Investigations were performed to 

determine the batches of the affected nuts 

and had revealed that these nuts have been 

installed in production on the fuel tank area 

of aeroplanes listed in the applicability 

section of this [European Aviation Safety 

Agency (EASA)] AD. 

Static, fatigue and corrosion tests were 

performed, which demonstrated that no 

immediate maintenance action is necessary. 

However, a large number of these nuts are 

fitted on primary structural elements, which 

could have long-term consequences. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

For the reasons described above, this 

[EASA] AD requires a detailed inspection of 

the affected nuts [for cracking and to 

determine if nuts are installed], associated 

corrective actions, depending on findings, 

and replacement of the affected P/N 

ASNA2531–4 nuts with new ones, having the 

same P/N [and reporting to Airbus the 

inspection results]. 

This [EASA] AD has been revised to reduce 

the Applicability. Since no spare nuts have 

been delivered to operators for installation on 

Airbus aeroplanes, only the Models and MSN 

[manufacturer’s serial numbers] listed in the 

Airbus SB are affected by this [EASA] AD. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Reference Latest Service 

Information 

Airbus stated that they have issued 

Revision 02, dated April 6, 2012, of 

Mandatory Service Bulletin A320–57– 

1153, including Appendices 01, 02, and 

03. Airbus also requested that we revise 

the NPRM (77 FR 16492, March 21, 

2012) to give credit for Airbus Service 

Bulletin A320–57–1153, Revision 01, 

including Appendices 01, 02, and 03, 

dated June 28, 2010 (referenced as the 

appropriate source of service 

information for the actions in paragraph 

(g) of the NPRM). 

We agree with the commenter. We 

reviewed Airbus Mandatory Service 

Bulletin A320–57–1153, Revision 02, 

including Appendices 01, 02, and 03, 

dated April 6, 2012. Revision 02 

corrects a part number and revises the 

title, certain illustrations, and the test 

job set-up. We also agree, as Revision 02 

of that service bulletin states, that there 

is no additional work required by 

Revision 02 of this service bulletin for 

airplanes modified using previous 

revisions of this bulletin. We have 

changed paragraphs (g) and (h) of this 

AD to refer to Airbus Mandatory Service 

Bulletin A320–57–1153, Revision 02, 

including Appendices 01, 02, and 03, 

dated April 6, 2012, and have changed 

paragraph (i) of this AD (‘‘Credit for 

Previous Actions’’) to include Airbus 

Service Bulletin A320–57–1153, 

Revision 01, including Appendices 01, 

02, and 03, dated June 28, 2010. 

Request To Revise ‘‘Costs of 

Compliance’’ Section 

Airbus requested that we revise the 

‘‘Costs of Compliance’’ section of the 

NPRM (77 FR 16492, March 21, 2012) to 

correctly state the number of U.S.- 

registered airplanes affected by this AD, 

which it noted as 22 airplanes rather 

than 170 airplanes as stated in the 

NPRM. 

We agree that 22 is the correct number 

of U.S.-registered airplanes affected by 

this AD. We have changed the ‘‘Costs of 

Compliance’’ section of this AD 

accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

except for minor editorial changes. We 

have determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

16492, March 21, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 16492, 

March 21, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 22 products of U.S. registry. We 

also estimate that it will take up to 15 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $28,050, or $1,275 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 143 work-hours and require parts 

costing $0, for a cost of $12,155 per 

product. 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 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 above, I 

certify that this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (77 FR 16492, 

March 21, 2012), 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


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 49707 

section. Comments will be available in 

the AD docket shortly after receipt. 

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 AD: 

2012–16–11 Airbus: Amendment 39–17158. 

Docket No. FAA–2012–0291; Directorate 

Identifier 2011–NM–168–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 21, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

112 and –121 airplanes; Model A319–111, 

–112, –115, –132, and –133 airplanes; Model 

A320–214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes; certificated in any category; serial 

numbers 3359, 3361, 3362, 3365, 3366, 3368, 

3370 through 3508 inclusive, 3510 through 

3519 inclusive, 3522, 3523, 3525, 3527, 3529, 

3530, 3533, 3534, 3537, 3539, 3542, 3544, 

3546, 3548, 3552, and 3555. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports that 

some nuts installed on the wing, including 

on primary structural elements, were found 

cracked. We are issuing this AD to detect and 

correct missing and cracked nuts, which 

could result in the structural integrity of the 

airplane wings being impaired. 

(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) Inspection/Replacement of Fuel Tank 

Nuts 

Within the compliance times specified in 

paragraph (g)(1) or (g)(2) of this AD, 

whichever occurs later: Do a detailed 

inspection of the fuel tank areas of the wings 

to determine if nuts with part number (P/N) 

ASNA2531–4 are installed or cracked, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–57–1153, Revision 02, 

including Appendices 01, 02, and 03, dated 

April 6, 2012. Before further flight, replace 

any missing or cracked nut with P/N 

ASNA2531–4 with a new P/N ASNA2531–4 

nut, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–57–1153, Revision 02, 

including Appendices 01, 02, and 03, dated 

April 6, 2012. 

(1) Within 6 years after the first flight of 

the airplane. 

(2) Within 6 years after the most recent 

scheduled fuel tank inspection, or within 6 

months after the effective date of this AD, 

whichever occurs later. 

(h) Inspection Report 

Submit a report of the findings of the 

inspection required by paragraph (h) of this 

AD to Airbus, at the applicable time specified 

in paragraph (h)(1) or (h)(2) of this AD. 

Submit the report using ‘‘Appendix 01— 

Inspection Report,’’ of Airbus Mandatory 

Service Bulletin A320–57–1153, Revision 02, 

dated April 6, 2012. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (i)(1) or 

(i)(2) of this AD. 

(1) Airbus Service Bulletin A320–57–1153, 

including Appendices 01, 02, and 03, dated 

February 9, 2010. 

(2) Airbus Service Bulletin A320–57–1153, 

Revision 01, including Appendices 01, 02, 

and 03, dated June 28, 2010. 

(j) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0121R1, dated July 13, 2011; and 

Airbus Mandatory Service Bulletin A320–57– 

1153, Revision 02, including Appendices 01, 

02, and 03, dated April 6, 2012; for related 

information. 

(l) 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) Airbus Mandatory Service Bulletin 

A320–57–1153, Revision 02, including 

Appendices 01, 02, and 03, dated April 6, 

2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.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– 


tkelley on DSK3SPTVN1PROD with RULES
49708 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

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

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–19815 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0490; Directorate 

Identifier 2012–NM–066–AD; Amendment 

39–17159; AD 2012–16–12] 

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 all The 

Boeing Company Model 707 airplanes, 

and Model 720 and 720B series 

airplanes. This AD was prompted by 

reports of cracking of the midspar 

fittings, and of the engine and nacelle 

strut separating from the airplane. This 

AD requires performing a detailed 

inspection of the midspar fittings of the 

nacelle strut to confirm that the correct 

part number is installed, and installing 

the correct part number if necessary; 

performing repetitive high frequency 

eddy current (HFEC) inspections of the 

midspar fittings of the nacelle strut for 

cracks, and repair if necessary; and 

performing repetitive general visual 

inspections of the nacelle struts to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and 

performing repair if necessary. We are 

issuing this AD to detect and correct 

cracking of the midspar fitting, which 

could result in separation of the nacelle 

strut and engine from the airplane while 

in flight, and consequent loss of 

controllability of the airplane. 

DATES: This AD is effective September 

21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 21, 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; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6577; 

fax: (425) 917–6590; email: 

Berhane.Alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on May 30, 2012 (77 FR 31762). 

That NPRM proposed to require 

performing a detailed inspection of the 

midspar fittings of the nacelle strut to 

confirm that the correct part number is 

installed, and installing the correct part 

number if necessary; performing 

repetitive HFEC inspections of the 

midspar fittings of the nacelle strut for 

cracks, and repair if necessary; and 

performing repetitive general visual 

inspections of the nacelle struts to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and 

performing repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Boeing and the National Transportation 

Safety Board support the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 11 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

operators 

Detailed inspection, repetitive HFEC inspections, and repetitive general visual inspections of the midspar fittings 

of the nacelle strut.

23 work-hours × $85 per hour = $1,955, 

per inspection.

$0 $1,955, per inspection.$21,505, per inspection. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these repairs: 


tkelley on DSK3SPTVN1PROD with RULES