Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 65803 

to the International Branch, send it to ATTN: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1175; 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. 

(j) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0220, dated November 11, 2011; and BAE 

SYSTEMS (OPERATIONS) LIMITED 

Modification Service Bulletin SB.29–048– 

30676A, Revision 2, dated December 23, 

2010; for related information. 

(2) For service information identified in 

this AD, contact BAE SYSTEMS 

(OPERATIONS) LIMITED, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) BAE SYSTEMS (OPERATIONS) 

LIMITED Modification Service Bulletin 

SB.29–048–30676A, Revision 2, dated 

December 23, 2010. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact BAE SYSTEMS 

(OPERATIONS) LIMITED, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

14, 2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26185 Filed 10–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0728; Directorate 

Identifier 2012–NM–050–AD; Amendment 

39–17234; AD 2012–21–18] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model MD–90–30 

airplanes. This AD was prompted by 

reports of fatigue cracks found in 

Stringer 11 at the outboard flap, inboard 

drive hinge at Station Xrs=164.000. This 

AD requires repetitive inspections for 

cracks in Stringer 11, and a splice repair 

if necessary; and repetitive post-repair 

inspections, and repair if necessary. We 

are issuing this AD to detect and correct 

such cracking, which could result in the 

wing structure not supporting the limit 

load condition, which could lead to loss 

of the structural integrity of the wing. 

DATES: This AD is effective December 5, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 5, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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: 

Roger Durbin, Airframe Branch, ANM– 

120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5233; fax: (562) 627–5210; email: 

roger.durbin@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 August 1, 2012 (77 FR 

45515). That NPRM proposed to require 

repetitive inspections for cracks in 

Stringer 11, and a splice repair if 

necessary; and repetitive post-repair 

inspections, and repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supports the NPRM (77 FR 

45515, August 1, 2012). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

45515, August 1, 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 45515, 

August 1, 2012). 

Costs of Compliance 

We estimate that this AD affects 52 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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65804 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 

ESTIMATED COSTS

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

Inspection ................................ 13 work-hours × $85 per hour 

= $1,105 per inspection 

cycle.

None ........... $1,105 per inspection cycle ... $57,460 per inspection cycle 

Post-repair inspection ............. 13 work-hours × $85 per hour 

= $1,105.

None ........... $1,105 ..................................... $57,460. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Splice repair per wing ............................................... 93 work-hours × $85 per hour = $7,905 .................. $28,126 $36,031 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions of 

the post-repair inspection specified in 

this AD. 

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 

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 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–21–18 The Boeing Company: 

Amendment 39–17234; Docket No. 

FAA–2012–0728; Directorate Identifier 

2012–NM–050–AD. 

(a) Effective Date 

This AD is effective December 5, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model MD–90–30 airplanes, certificated in 

any category, as identified in Boeing Alert 

Service Bulletin MD90–57A030, dated 

February 14, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracks found in Stringer 11 at the 

outboard flap, inboard drive hinge at Station 

Xrs=164.000. We are issuing this AD to 

detect and correct such cracking, which 

could result in the wing structure not 

supporting the limit load condition, which 

could lead to loss of the structural integrity 

of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before the accumulation of 14,000 total 

flight cycles, or within 9,470 flight cycles 

after the effective date of this AD: Whichever 

occurs later, do an in-tank eddy current high 

frequency (ETHF) inspection for cracks in 

Stringer 11 at the outboard flap, inboard 

drive hinge at Station Xrs=164.000 of the left 

and right wings, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–57A030, dated 

February 14, 2012. If no cracking is found, 

repeat the inspection thereafter at intervals 

not to exceed 31,000 flight cycles. 

(h) Splice Repair 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, do a splice repair, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–57A030, dated February 14, 2012. 

(i) Post-Repair Inspection 

Within 42,000 flight cycles after doing the 

splice repair specified in paragraph (h) of this 

AD: Do an ETHF inspection for cracks in 

Stringer 11 at the outboard flap, inboard 

drive hinge at Station Xrs=164.000, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–57A030, dated February 14, 2012. 

Repeat the inspection thereafter at intervals 

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Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 65805 

not to exceed 31,000 flight cycles. If any 

crack is found: Before further flight, repair 

the crack using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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. 

(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, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and 14 

CFR 25.571, Amendment 54, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Roger Durbin, Airframe Branch, 

ANM–120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; phone: (562) 627–5233; fax: (562) 627– 

5210; email: roger.durbin@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin MD90– 

57A030, dated February 14, 2012. 

(ii) Reserved. 

(3) For The Boeing Company Airplanes 

service information identified in this AD, 

contact Boeing Commercial Airplanes, 

Attention: Data & Services Management, 3855 

Lakewood Boulevard, MC D800–0019, Long 

Beach, CA 90846–0001; telephone 206–544– 

5000, extension 2; fax 206–766–5683; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

12, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26187 Filed 10–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0652; Directorate 

Identifier 2010–NM–045–AD; Amendment 

39–17240; AD 2012–22–04] 

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 MD–90–30 

airplanes. This AD was prompted by 

reports of cracks of the wing rear spar 

lower cap at the outboard flap, inboard 

drive hinge at station Xrs=164.000. This 

AD requires repetitive eddy current high 

frequency (ETHF) inspections for 

cracking on the aft side of the left and 

right wing rear spar lower caps at 

station Xrs=164.000, further ETHF 

inspections if cracks are found, and 

repair if necessary; and repetitive postrepair inspections, and repair if 

necessary. We are issuing this AD to 

detect and correct cracking of the left 

and right rear spar lower caps, which 

could result in fuel leaks and damage to 

the wing skin or other structure, and 

consequent loss of the structural 

integrity of the wing. 

DATES: This AD is effective December 5, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 5, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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: 

Roger Durbin, Airframe Branch, ANM– 

120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5233; Fax: (562) 627–5210; email: 

roger.durbin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on July 24, 2012 (77 FR 43178). 

The original NPRM (76 FR 40288, July 

8, 2011) proposed to require repetitive 

eddy current high frequency (ETHF) 

inspections for cracking on the aft side 

of the left and right wing rear spar lower 

caps at station Xrs=164.000, further 

ETHF inspections if cracks are found, 

and repair if necessary. The original 

NPRM also proposed to require 

repetitive post-repair inspections and 

repair if necessary. The SNPRM 

proposed to continue to have the same 

requirements as the original NPRM, but 

also added new repetitive post-repair 

inspections, and corrective action if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(77 FR 43178, July 24, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

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