78594 Federal Register / Vol. 75, No. 241 / Thursday, December 16, 2010 / Rules and Regulations 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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– 

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

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

November 18, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–30612 Filed 12–15–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0430; Directorate 

Identifier 2008–NM–148–AD; Amendment 

39–16540; AD 2010–26–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 777–200 series airplanes. This 

AD requires installing a new insulation 

blanket on the latch beam firewall of 

each thrust reverser (T/R) half. This AD 

results from an in-flight shutdown due 

to an engine fire indication; an undercowl engine fire was extinguished after 

landing. The cause of the fire was 

uncontained failure of the starter in the 

engine core compartment; the fire 

progressed into the latch beam cavity 

and was fueled by oil from a damaged 

integrated drive generator oil line. We 

are issuing this AD to prevent a fire 

from entering the cowl or strut area, 

which could weaken T/R parts and 

result in reduced structural integrity of 

the T/R, possible separation of T/R parts 

during flight, and consequent damage to 

the airplane and injury to people or 

damage to property on the ground. 

DATES: This AD is effective January 20, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 20, 2011. 

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: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6500; 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 

certain Boeing Model 777–200 series 

airplanes. That NPRM was published in 

the Federal Register on May 7, 2009 (74 

FR 21284). That NPRM proposed to 

require installing a new insulation 

blanket on the latch beam firewall of 

each thrust reverser (T/R) half. 

Relevant Service Information 

Since we issued the NPRM, we have 

reviewed Boeing Alert Service Bulletin 

777–78A0066, Revision 2, dated April 8, 

2010. Boeing Service Bulletin 777– 

78A0066, Revision 1, dated March 12, 

2009, was referred to in the original 

NPRM as the appropriate source of 

service information for accomplishing 

the proposed actions. No more work is 

necessary for airplanes on which 

Revision 1 of this service bulletin was 

used for doing the actions. Boeing Alert 

Service Bulletin 777–78A0066, Revision 

2, dated April 8, 2010, moves certain 

airplanes to Group 1, and contains 

minor editorial changes. 

We have revised paragraphs (c) and 

(g) of this AD to refer to Revision 2 of 

Boeing Alert Service Bulletin 777– 

78A0066, Revision 2, dated April 8, 

2010, and paragraph (h) to add credit for 

accomplishing the specified actions in 

accordance with Boeing Service Bulletin 

777–78A0066, Revision 1, dated March 

12, 2009. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Clarify Description of 

Unsafe Condition 

Boeing asked that we clarify the 

description of the unsafe condition by 

removing the words ‘‘or strut’’ from the 

identified description. Boeing stated 

that the unsafe condition, as currently 

written, is not correct. Boeing did not 

provide the reason that the description 

is not correct. 

We disagree that the description of 

the unsafe condition should be clarified 

by removing ‘‘or strut’’ from the 

description. A fire in the lower latch 

beam area that burns through an 

inadequate firewall may propagate into 

the strut. We have made no change to 

the AD in this regard. 

Request To Clarify Applicability 

Japan Airlines International (JALI) 

asked for clarification of the 

applicability specified in the NPRM. 

JALI stated that the applicability 

specifies Model 777–200 series 

airplanes identified in Boeing Service 

Bulletin 777–78A0066, Revision 1, 

dated March 12, 2009. JALI noted that 

the service bulletin specifies its 

effectivity as delivered condition, and 

the proposed rule is considered to be 

applicable to each T/R half that has 

been installed on airplanes with the 

applicable serial numbers. JALI added 

that the T/R half is a replaceable line 

unit and the installed airplane and/or 

engine position will be changed from 

the delivered condition in the future; 

the T/R half that is not necessary for 

doing the requirements in the NPRM 

may be installed on an airplane 

identified in the applicability. 

JALI stated that, in light of these 

factors, it is not clear whether 

compliance with the specified actions 

has been met. JALI asked that we clarify 

the applicability either to note that the 

NPRM does not apply to airplanes on 

which a T/R is installed with a design 

change known as ‘‘Commonality T/R,’’ 

which is common to Model 777–300 

series airplanes, or to change the 


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Federal Register / Vol. 75, No. 241 / Thursday, December 16, 2010 / Rules and Regulations 78595 

airplane serial numbers to T/R part 

numbers or serial numbers. 

We do not agree that the effectivity 

specified in Boeing Service Bulletin 

777–78A0066, Revision 1, dated March 

12, 2009, could apply to an airplane that 

has an incorrect T/R configuration 

because the T/R is a line replaceable 

unit and is not identified in the 

effectivity. The manufacturer has 

informed us that for airplanes not 

identified in Revision 1 or Revision 2 of 

this service bulletin, the specified T/R 

configuration is not an approved 

configuration. We have determined that 

it is not possible to install the T/R with 

the unsafe condition on airplanes that 

were manufactured after line number 

413; therefore, the AD does not apply to 

those airplanes. We have made no 

change to the AD in this regard. 

Request To Include Part Number and 

Compliance Status for T/R Halves 

JALI asked that we include the 

applicable part numbers of each T/R 

half and add a procedure in the NPRM 

to reidentify the parts as the part 

numbers change. JALI added that this 

change to the NPRM would include 

indicating the service bulletin number 

or adding a suffix to the serial number 

on the ID plate for each T/R so operators 

can easily track the applicable part 

number and compliance status for each 

T/R half. JALI noted that there is 

nothing identified in the service 

bulletin, and the only way for operators 

to identify the applicable part number 

and compliance status of each T/R half 

is by reviewing the maintenance record. 

JALI added that this would be 

burdensome for operators. 

We agree that the part numbers of 

each T/R half should be included in the 

service information and a procedure 

should be added to reidentify the parts 

as the part numbers change. Boeing 

Alert Service Bulletin 777–78A0066, 

Revision 2, dated April 8, 2010, 

includes the part marking provision. As 

stated previously, we have revised 

paragraph (c) of this AD (i.e., the AD 

applicability) to refer to Revision 2 of 

this service bulletin. Therefore, we have 

made no further change to the AD in 

this regard. 

Explanation of Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the relevant data, 

considered the comments 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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the original NPRM, 

we have increased the labor rate used in 

the Costs of Compliance from $80 per 

work-hour to $85 per work-hour. The 

Costs of Compliance information, 

below, reflects this increase in the 

specified hourly labor rate. 

Costs of Compliance 

We estimate that this AD affects 25 

airplanes of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

between $3,546 and $5,253 per product. 

Based on these figures, we estimate the 

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

be between $103,525 and $146,200, or 

between $4,141 and $5,848 per product. 

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: 

2010–26–01 The Boeing Company: 

Amendment 39–16540. Docket No. 

FAA–2009–0430; Directorate Identifier 

2008–NM–148–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective January 20, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 777–200 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 777–78A0066, 

Revision 2, dated April 8, 2010. 

Unsafe Condition 

(d) This AD results from an in-flight 

shutdown due to an engine fire indication; an 

under-cowl engine fire was extinguished 

after landing. The cause of the fire was 

uncontained failure of the starter in the 

engine core compartment; the fire progressed 

into the latch beam cavity and was fueled by 

oil from a damaged integrated drive generator 

oil line. We are issuing this AD to prevent 

a fire from entering the cowl or strut area, 

which could weaken thrust reverser (T/R) 

parts and result in reduced structural 

integrity of the T/R, possible separation of T/ 

R parts during flight, and consequent damage 

to the airplane and injury to people or 

damage to property on the ground. 


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78596 Federal Register / Vol. 75, No. 241 / Thursday, December 16, 2010 / Rules and Regulations 

Subject 

(e) Air Transport Association (ATA) of 

America Code 78: Exhaust. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Installation of Insulation Blanket 

(g) Within 60 months or 4,500 flight cycles 

after the effective date of this AD, whichever 

is first: Install a new insulation blanket on 

the latch beam firewall of each T/R half by 

doing all the applicable actions specified in 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–78A0066, 

Revision 2, dated April 8, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 777–78A0066, dated June 5, 

2008; or Boeing Service Bulletin 777– 

78A0066, Revision 1, dated March 12, 2009; 

are acceptable for compliance with the 

corresponding requirements of paragraph (g) 

of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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. Send information to Attn: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6500; 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. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 777–78A0066, Revision 2, dated 

April 8, 2010, 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. 

(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 

December 3, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–31384 Filed 12–15–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1242; Directorate 

Identifier 2010–CE–062–AD; Amendment 

39–16542; AD 2010–26–03] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Models B200, 

B200GT, B300, and B300C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires fabricating and 

installing a placard incorporating 

information that limits operation when 

there is known or forecast icing and 

requires replacing a section of the 

pneumatic supply tube for the tail deice 

system with a new tube of a different 

material. This AD requires fabricating 

and installing a placard incorporating 

information that limits operation when 

there is known or forecast icing and 

requires replacing the entire length of 

the pneumatic supply tube for the tail 

deice system with a new tube of a 

different material. This AD was 

prompted by reports of two failures of 

the pneumatic supply tube for the tail 

deice system outside the area covered 

by AD 2008–07–10. We are issuing this 

AD to prevent collapsed pneumatic 

supply tubes, which could result in 

failure of the tail deice boots to operate. 

This failure could lead to loss of control 

in icing conditions. 

DATES: This AD is effective December 

20, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 20, 2010. 

We must receive any comments on 

this AD by January 31, 2011. 

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 Hawker Beechcraft 

Corporation, P.O. Box 85, Wichita, 

Kansas 67201–0085; telephone: (800) 

429–5372 or (316) 676–3140; Internet: 

www.hawkerbeechcraft.com. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust St., Kansas City, 

MO 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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: Don 

Ristow, Aerospace Engineer, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4120; fax: (316) 946–4107; e-mail: 

donald.ristow@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 27, 2008, we issued AD 

2008–07–10, Amendment 39–15451 (73 

FR 18706, April 7, 2008), for certain 

Hawker Beechcraft Corporation Models 

B200, B200GT, B300, and B300C 

airplanes. That AD requires fabricating 

and installing a placard incorporating 


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