This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

65611 

Vol. 77, No. 210 

Tuesday, October 30, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0727; Directorate 

Identifier 2012–NM–012–AD; Amendment 

39–17229; AD 2012–21–13] 

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 DC–9–81 

(MD–81), DC–9–82 (MD–82), DC–9–83 

(MD–83), DC–9–87 (MD–87), and MD– 

88 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 structural integrity of the wing. 

DATES: This AD is effective December 4, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 4, 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, 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 

45518). 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 

45518, 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 

45518, 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 45518, 

August 1, 2012). 

Costs of Compliance 

We estimate that this AD affects 502 

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 

Inspection ............... 13 work-hours × $85 per hour = $1,105 

per inspection cycle.

None ....................... $1,105 per inspection cycle.$554,710 per inspection cycle. 

Post-repair inspection.13 work-hours × $85 per hour = $1,105 None ....................... $1,105 .................... $554,710. 

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 this repair: 


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65612 Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Splice repair per wing ........................ 93 work-hours × $85 per hour = $7,905 ........................................................ $17,759 $25,664 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

for 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): 

2012–21–13 The Boeing Company: 

Amendment 39–17229; Docket No. 

FAA–2012–0727; Directorate Identifier 

2012–NM–012–AD. 

(a) Effective Date 

This AD is effective December 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model DC–9–81 (MD–81), DC–9–82 (MD–82), 

DC–9–83 (MD–83), DC–9–87 (MD–87), and 

MD–88 airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin MD80–57A243, dated 

December 20, 2011. 

(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 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 19,000 total 

flight cycles, or within 8,710 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, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–57A243, dated December 20, 2011. If 

no cracking is found, repeat the inspection 

thereafter at intervals not to exceed 29,000 

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 

MD80–57A243, dated December 20, 2011. 

(i) Post-Repair Inspection 

Within 60,000 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 

MD80–57A243, dated December 20, 2011. 

Repeat the inspection thereafter at intervals 

not to exceed 29,000 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 45, 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– 


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Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 65613 

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 MD80– 

57A243, dated December 20, 2011. 

(ii) Reserved. 

(3) For The Boeing Company 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/ibrlocations.html. 

Issued in Renton, Washington, on October 

12, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26073 Filed 10–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1104; Directorate 

Identifier 2012–NM–073–AD; Amendment 

39–17226; AD 2012–21–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200LR 

and –300ER series airplanes. This AD 

requires reviewing the airplane’s 

maintenance records for each rudder 

power control unit (PCU) to identify the 

condition of its related reaction link 

assembly, and replacing the rudder PCU 

and its related reaction link assembly if 

necessary. This AD was prompted by a 

report of an abnormal airframe vibration 

in the aft fuselage during flight. We are 

issuing this AD to prevent excessive 

freeplay in the rudder control surface, 

which could cause rudder vibration, 

and result in structural damage severe 

enough to prevent continued safe flight 

and landing. 

DATES: This AD is effective November 

14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 14, 2012. 

We must receive comments on this 

AD by December 14, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, 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, 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 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: 

Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: (425) 917– 

6468; fax: (425) 917–6590; email: 

Kenneth.frey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report of an 

abnormal airframe vibration in the aft 

fuselage during flight. A subsequent 

inspection of the rudder PCU 

installations found that the bushing 

liners were missing from all six end cap 

assemblies on the three rudder PCUs. 

An investigation revealed that the cause 

of the problem was failure of the bond 

between the liner and the bushing 

substrate because of the use of liquid 

nitrogen during installation of the 

bushing into the reaction link end cap 

housing. This condition, if not 

corrected, could result in excessive 

freeplay in the rudder control surface, 

which could cause rudder vibration, 

and result in structural damage severe 

enough to prevent continued safe flight 

and landing. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–27A0109, dated December 

1, 2011. The service information 

describes procedures, for airplanes 

having certain line numbers, for 

reviewing the airplane’s maintenance 

records for each rudder PCU to identify 

the condition of its related reaction link 

assembly, and replacing the rudder PCU 

and its related reaction link assembly if 

necessary. 

FAA’s Determination 

We are issuing 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 this same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously. 

FAA’s Justification and Determination 

of the Effective Date 

No U.S. airplanes are affected by this 

AD. Therefore, we find that notice and 

opportunity for prior public comment 

are unnecessary and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 


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