Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 62217 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

(f) At the next engine shop visit after the 

effective date of this AD, but no later than 

June 30, 2010, rework the forward fan stator 

case and install the fan module secondary 

containment shield. 

(1) For engines on Airbus 300 series 

airplanes, use paragraph 3, Accomplishment 

Instructions, of GE Service Bulletin (SB) No. 

CF6–50 S/B 72–0985, Revision 3, dated 

August 22, 2007, to do the rework and 

installation. 

(2) Deleted. 

(g) The rework and installation specified in 

paragraph (f)(1) of this AD can also be done 

on-wing. 

Previous Credit 

(h) Previous credit is allowed for fan stator 

cases reworked and containment shields 

installed using GE SB No. CF6–50 S/B 72– 

0985, dated December 2, 1991, Revision 1, 

dated September 15, 1998, or Revision 2, 

dated March 21, 2007, before the effective 

date of this AD. Credit is also allowed for fan 

stator cases reworked and containment 

shields installed using GE SB No. CF6–50 S/ 

B 72–0986, dated December 2, 1991, Revision 

1, dated September 15, 1998, or Revision 2, 

dated march 21, 2007. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) Deleted. 

(k) Contact James Rosa, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.rosa@faa.gov; telephone 

(781) 238–7152; fax (781) 238–7199, for more 

information about this AD. 

(l) Contact General Electric Company, GE– 

Aviation, Room 285, 1 Newmann Way, 

Cincinnati, OH 45215, telephone (513) 552- 

3272; fax (513) 552–3329; e-mail: 

geae.aoc@ge.com, for a copy of the service 

information referenced in this AD. 

Material Incorporated by Reference 

(m) You must use GE Service Bulletin No. 

CF6–50 S/B 72–0985, Revision 3, dated 

August 22, 2007, to do the rework and 

installation required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact General Electric 

Company, GE–Aviation, Room 285, 1 

Newmann Way, Cincinnati, OH 45215, 

telephone (513) 552- 3272; fax (513) 552– 

3329; e-mail: geae.aoc@ge.com, for a copy of 

this service information. You may review 

copies at the FAA, New England Region, 12 

New England Executive Park, Burlington, 

MA; or 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 Burlington, Massachusetts, on 

November 16, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–28167 Filed 11–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0571; Directorate 

Identifier 2009–NM–004–AD; Amendment 

39–16096; AD 2009–24–08] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777–200, –200LR, –300, and 

–300ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 777–200, –200LR, –300, 

and –300ER series airplanes. This AD 

requires inspections for scribe lines in 

the skin along lap joints, butt joints, 

certain external doublers, and the large 

cargo door hinges; and related 

investigative and corrective actions if 

necessary. This AD results from reports 

of scribe lines found at lap joints and 

butt joints, around external doublers, 

and at locations where external decals 

had been removed. We are issuing this 

AD to detect and correct scribe lines, 

which can develop into fatigue cracks in 

the skin. Undetected fatigue cracks can 

grow and cause sudden decompression 

of the airplane. 

DATES: This AD is effective January 4, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 4, 2010. 

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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 (telephone 

800–647–5527) is the 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, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 777 series airplanes. That 

NPRM was published in the Federal 

Register on June 25, 2009 (74 FR 30245). 

That NPRM proposed to require 

inspections for scribe lines in the skin 

along lap joints, butt joints, certain 

external doublers, and the large cargo 

door hinges; and related investigative 

and corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received from 

the one commenter. 

Request To Eliminate Reporting 

Requirement for Negative Findings 

Boeing requests that we revise 

paragraph (k) of the NPRM to eliminate 

the requirement to report negative 

findings. Boeing states that this 

requirement deviates from Boeing Alert 

Service Bulletin 777–53A0054, dated 

August 7, 2008, in that the service 

bulletin specified that operators report 

findings of cracking. Boeing states that 

since the Model 777 fleet is young 

relative to the inspection thresholds, 

this reporting requirement may last for 

decades and it would involve hundreds 

of airplanes. Boeing states that after a 

period of time, the requirement would 

become redundant and is therefore an 

unnecessary burden. 

We agree with the commenter for the 

reasons provided. We revised paragraph 

(k) of the final rule to eliminate the 

requirement to report negative findings. 


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62218 Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 

Explanation of Change To Applicability 

We have revised the applicability of 

this AD to identify model designations 

as published in the type certificate data 

sheet for the affected models listed in 

Boeing Alert Service Bulletin 777– 

53A0054, dated August 7, 2008. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 129 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 

A work-hour estimate is not available 

for the inspection for an external repair 

doubler since the inspection required 

can be different depending on the inservice repair history of the airplane. 

This inspection affects up to 129 U.S.- 

registered airplanes. 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Exploratory Inspection 9 to 34 ........................ $80 None ............ $720 to $2,720 ........... 129 $92,880 to 

$350,880 

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), and 

(3) 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2009–24–08 Boeing: Amendment 39–16096. 

Docket No. FAA–2009–0571; Directorate 

Identifier 2009–NM–004–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective January 4, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 777– 

200, –200LR, –300, and –300ER series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

777–53A0054, dated August 7, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of scribe 

lines found at lap joints and butt joints, 

around external doublers, and at locations 

where external decals had been cut. We are 

issuing this AD to detect and correct scribe 

lines, which can develop into fatigue cracks 

in the skin. Undetected fatigue cracks can 

grow and cause sudden decompression of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0054, dated 

August 7, 2008, except as provided in 

paragraphs (h) and (j) of this AD, do detailed 

exploratory inspections for scribe lines in the 

skin along lap joints, butt joints, certain 

external doublers, and the large cargo door 

hinges. Do all applicable related investigative 

and corrective actions at the times specified 

in the service bulletin, by accomplishing all 

actions specified in the Accomplishment 

Instructions of the service bulletin, except as 

provided by paragraph (i) of this AD. 

Note 1: The inspection exemptions 

described in NOTES 1.–5. in paragraph 1.E. 

of Boeing Alert Service Bulletin 777– 

53A0054, dated August 7, 2008, apply to this 

AD. 

Exceptions to Service Bulletin Specifications 

(h) Where Boeing Alert Service Bulletin 

777–53A0054, dated August 7, 2008, 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) Where Boeing Alert Service Bulletin 

777–53A0054, dated August 7, 2008, 

specifies to contact Boeing for appropriate 

action, accomplish applicable actions using a 

method approved in accordance with the 


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Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 62219 

procedures specified in paragraph (l) of this 

AD. 

(j) Where paragraph 1.E. of Boeing Alert 

Service Bulletin 777–53A0054, dated August 

7, 2008, specifies to ‘‘contact Boeing for 

inspection requirements for operation 

beyond 60,000 total flight-cycles after first 

repaint,’’ for those airplanes, this AD requires 

contacting the Manager, Seattle Aircraft 

Certification Office (ACO), for all inspection 

requirements of this AD and doing the 

requirements. 

Report 

(k) At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD: Submit 

a report of positive findings of cracks found 

during the inspection required by paragraph 

(g) of this AD to the Boeing Commercial 

Airplane Group, P.O. Box 3707, Seattle, 

Washington 98124–2207. Alternatively, 

operators may submit reports to their Boeing 

field service representatives. The report must 

contain, at a minimum, the inspection 

results, a description of any discrepancies 

found, the airplane serial number, and the 

number of flight cycles and flight hours on 

the airplane. Under the provisions of the 

Paperwork Reduction Act (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6577; fax (425) 

917–6590. Or, e-mail information to 9–ANM– 

Seattle-ACO–AMOC–Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin 777–53A0054, dated August 7, 2008, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(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; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) 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 or 425–227–1152. 

(4) 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 NARA, 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 

November 12, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–28169 Filed 11–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1073; Directorate 

Identifier 2009–NM–174–AD; Amendment 

39–16097; AD 2007–15–06 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–111 and –112 Series Airplanes, 

and Model A319, A320, and A321 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to all Airbus Model 

A318–111 and –112 series airplanes, 

and all Model A319, A320, and A321 

series airplanes. That AD currently 

requires revising the Airworthiness 

Limitations section of the Instructions 

for Continued Airworthiness to 

incorporate new limitations for fuel tank 

systems. This AD clarifies the intended 

effect of the AD on spare and onairplane fuel tank system components. 

This AD results from fuel system 

reviews conducted by the manufacturer. 

We are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: This AD is effective December 

14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 14, 2009. 

On August 28, 2007 (72 FR 40222, 

July 24, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in the AD. 

We must receive any comments on 

this AD by January 11, 2010. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

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 (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 


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