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contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

70355 

Vol. 77, No. 227 

Monday, November 26, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0595; Directorate 

Identifier 2012–NM–055–AD; Amendment 

39–17262; AD 2012–23–06] 

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 777 

airplanes. This AD was prompted by 

reports of failure of wire support clamps 

in the forward section of the aft pressure 

bulkhead. This AD requires a detailed 

inspection of the clamps on the power 

feeder cable of the auxiliary power unit 

(APU) to determine if certain clamps are 

installed, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to prevent failure of the 

clamp, which could result in wire 

chafing and potential arcing and 

consequent fire in section 48 (a 

flammable fluid leakage zone) or heat 

damage to the APU power feeder cable, 

insulation blankets, or pressure 

bulkhead. 

DATES: This AD is effective December 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 31, 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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: (425) 917– 

6482; fax: (425) 917–6590; email: 

georgios.roussos@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 June 12, 2012 (77 FR 34876). 

That NPRM proposed to require a 

detailed inspection of the clamps on the 

power feeder cable of the APU to 

determine if certain clamps are 

installed, and related investigative and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. American 

Airlines and United Airlines stated they 

will incorporate the requirements of the 

NPRM (77 FR 34876, June 12, 2012). 

Request To Remove Paragraph (h) of 

the NPRM (77 FR 34876, June 12, 2012) 

Boeing requested that paragraph (h) of 

the NPRM (77 FR 34876, June 12, 2012), 

‘‘Exception to the Service Bulletin,’’ be 

removed from the NPRM. Boeing stated 

that paragraph (h) of the NPRM requires 

repair of the APU power feeder, 

insulation blankets, and clamps, if no 

primer discoloration or structural 

damage is found. Boeing stated that 

paragraph (h) of the NPRM is redundant 

to steps 3.B.6.f.(2) of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–24A0119, 

dated November 11, 2011, which 

accomplishes the replacement and 

repair of all damaged components found 

during the progressive detailed 

inspection outlined in that service 

bulletin. 

We disagree with Boeing’s request to 

remove paragraph (h) of this AD. Step 

3.B.6.f.(2) of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 777–24A0119, dated November 

11, 2011, is part of the requirements of 

step 3.B.6.b. of that service bulletin, 

which states, ‘‘If visual indications of 

heat damage are found, do steps 6.c 

through 6.f.’’ However, if no primer 

discoloration or structural deterioration 

is detected after doing the inspection 

specified in 3.B.6.a. of that service 

bulletin, the service information does 

not specify which step to accomplish 

next, which is repairing the APU power 

feeder cable and insulation blanket, and 

replacing the existing clamps. We have 

not changed this final rule in this 

regard. 

Request To Clarify the ‘‘Differences 

Between the Proposed AD and the 

Service Information’’ Section of the 

NPRM (77 FR 34876, June 12, 2012) 

FedEx requested clarification 

regarding the statement in the 

‘‘Differences Between the Proposed AD 

and the Service Information’’ section of 

the NPRM (77 FR 34876, June 12, 2012), 

and the statement in Boeing Alert 

Service Bulletin 777–24A0119, dated 

November 11, 2011, to contact Boeing 

for repair instructions. FedEx stated 

that, in the ‘‘Differences Between the 

Proposed AD and the Service 

Information’’ section, the repairs will be 

addressed in one of the following ways: 

In accordance with a method approved 

by the FAA, or using data that meets the 

certification basis of the airplane, and 

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70356 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 

has been approved by Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA). 

FedEx stated that it would like to know 

if any repair design by the airline will 

require an alternative method of 

compliance (AMOC), and whether 

Boeing will provide repair methods in a 

revised service bulletin, or if the airline 

will have to provide Boeing with 

information on the damage and request 

a repair. FedEx stated that standard 

repair methods, if listed in the service 

information, would expedite the repair, 

especially if the repair would need to be 

‘‘bought off’’ by an airline certified 

structures inspector. 

We agree to clarify the intent of the 

‘‘Differences Between the Proposed AD 

and the Service Information’’ section in 

the NPRM (77 FR 34876, June 12, 2012). 

Any deviation from the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–24A0119, 

dated November 11, 2011, requires an 

AMOC approval. Also, as stated in 

paragraph (i) of this AD, where that 

service bulletin specifies to contact 

Boeing for the repair, the repair must be 

done in accordance with the procedures 

specified in paragraph (j) of this AD, 

which is the ‘‘Alternative Methods of 

Compliance (AMOCs)’’ paragraph of this 

AD. The AMOC requests, whether the 

structural repair design is developed by 

the airline or by Boeing engineering, 

could either be approved by the 

Manager of the Seattle Aircraft 

Certification Office, or by the Boeing 

ODA that has been authorized by the 

Manager, Seattle ACO, to approve 

AMOC requests specifically for this AD. 

We understand FedEx’s concern on the 

potential delays due to the absence of 

standard structural repair methods in 

Boeing Alert Service Bulletin 777– 

24A0119, dated November 11, 2011; 

however, we have not received any 

information from the manufacturer on 

whether that service bulletin will be 

revised. We have not changed this final 

rule in this regard. 

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 164 

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 and Clamp Replacement ............... 8 work-hours × $85 per hour = $680 ............. $500 $1,180 $193,520 

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: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspection and Repair of the Pressure Bulkhead ........ 48 work-hours × $85 per hour = $4,080 ...................... $0 $4,080 

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): 

2012–23–06 The Boeing Company: 

Amendment 39–17262; Docket No. 

FAA–2012–0595; Directorate Identifier 

2012–NM–055–AD. 

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Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 70357 

(a) Effective Date 

This AD is effective December 31, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–24A0119, dated 

November 11, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2421; AC Generator-Alternator. 

(e) Unsafe Condition 

This AD was prompted by reports of failure 

of wire support clamps in the forward section 

of the aft pressure bulkhead. We are issuing 

this AD to prevent failure of the clamp, 

which could result in wire chafing and 

potential arcing and consequent fire in 

section 48 (a flammable fluid leakage zone) 

or heat damage to the auxiliary power unit 

(APU) power feeder cable, insulation 

blankets, or pressure bulkhead. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection of the Clamps 

Within 48 months after the effective date 

of this AD: Do a detailed inspection of the 

clamps on the APU power feeder cable to 

determine if TA027063 clamps are installed, 

and all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–24A0119, dated 

November 11, 2011, except as required by 

paragraphs (h) and (i) of this AD. Do all 

related investigative and corrective actions 

before further flight. 

(h) Exception to the Service Information 

If during any inspection of the fuselage 

structure required by paragraph (g) of this 

AD, no primer discoloration or structural 

deterioration is found, before further flight, 

repair the APU power feeder cable and 

insulation blanket and replace the existing 

clamps, in accordance with steps 3.B.7, 3.B.8, 

and 3.B.9 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–24A0119, dated November 11, 2011. 

(i) Repair Approval 

Where Boeing Alert Service Bulletin 777– 

24A0119, dated November 11, 2011, specifies 

to do the repair in accordance with the 

instruction from Boeing, before further flight, 

repair 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, 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any structural 

repair required by this AD if it is approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO, to make those 

findings. For a structural repair method to be 

approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: (425) 917– 

6482; fax: (425) 917–6590; email: 

georgios.roussos@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 777– 

24A0119, dated November 11, 2011. 

(ii) Reserved. 

(3) For Boeing 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. 

(4) You may view this 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 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 

November 8, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27908 Filed 11–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0591; Directorate 

Identifier 2012–NM–015–AD; Amendment 

39–17264; AD 2012–23–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

737–600, –700, –700C, –800, and –900 

series airplanes. That AD currently 

requires replacing the drain tube 

assemblies and support clamps on the 

aft fairing of the engine struts. This new 

AD requires replacing the drain tube 

assembly of the left and right engine 

strut aft fairings with a new one, which 

includes an integral support clamp 

made of nickel alloy 625. This AD also 

adds airplanes to the applicability. This 

AD was prompted by a report of a 

broken drain tube assembly on the left 

engine strut at the clamp support 

location under the aft fairing 

compartment, inside the heat shield 

cavity of the aft fairing. There have also 

been reports of tube wear at this clamp 

location on additional airplanes. We are 

issuing this AD to prevent failure of the 

drain tube assemblies and clamps on the 

aft fairings of the engine struts. Such 

failure could allow leaked flammable 

fluids in the drain systems to discharge 

onto the heat shields of the aft fairings 

of the engine struts, which could result 

in an undetected and uncontrollable 

fire. 

DATES: This AD is effective December 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 31, 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, 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. 

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