10226 Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 

European regulatory process upon issuance 

by the type certificate holder. The FAA must 

mandate any such changes through 

rulemaking, specifically in this case an 

airworthiness directive. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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 FAAapproved 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to Piaggio Aero Industries S.p.A. 

Service Bulletin (Mandatory) 

N.: SB 80–0275, Rev. N. 0, dated June 15, 

2009; Piaggio Aero P.180 AVANTI 

Temporary Change No. 7 to the Pilot’s 

Operating Handbook and EASA Approved 

Airplane Flight Manual Rep. 6591, issued: 

February 24, 2009; and Piaggio Aero P.180 

AVANTI II Temporary Change No. 11 to the 

EASA Approved Airplane Flight Manual 

Rep. 180–MAN–0010–01100, issued: 

February 24, 2009, for related information. 

For service information related to this AD, 

contact Piaggio Aero Industries S.p.A., Via 

Cibrario, 4–16154 Genoa, Italy; phone: +39 

010 6481 353; fax: +39 010 6481 881; e-mail: 

airworthiness@piaggioaero.it; Internet: http:// 

www.piaggioaero.com. You may review 

copies of the referenced service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

Material Incorporated by Reference 

(i) You must use Piaggio Aero Industries 

S.p.A. Service Bulletin (Mandatory) N.: SB 

80–0275, Rev. N. 0, dated June 15, 2009; 

Piaggio Aero P.180 AVANTI Temporary 

Change No. 7 to the Pilot’s Operating 

Handbook and EASA Approved Airplane 

Flight Manual Rep. 6591, issued: February 

24, 2009; and Piaggio Aero P.180 AVANTI II 

Temporary Change No. 11 to the EASA 

Approved Airplane Flight Manual Rep. 180– 

MAN–0010–01100, issued: February 24, 

2009, 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 Piaggio Aero Industries 

S.p.A., Via Cibrario, 4–16154 Genoa, Italy; 

phone: +39 010 6481 353; fax: +39 010 6481 

881; e-mail: airworthiness@piaggioaero.it; 

Internet: http://www.piaggioaero.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on 

February 14, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–3923 Filed 2–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0698; Directorate 

Identifier 2009–NM–264–AD; Amendment 

39–16613; AD 2011–05–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires sealing the fasteners 

on the front and rear spars inside the 

left and right main fuel tanks and on the 

rear spar and lower panel of the center 

fuel tank. That AD also requires 

inspections of the wire bundle support 

installations to verify if certain clamps 

are installed and if Teflon sleeving 

covers the wire bundles inside the left 

and right equipment cooling system 

bays, on the left and right rear spars, 

and on the left and right front spars; and 

corrective actions if necessary. This new 

AD also requires sealing the additional 

fasteners on the rear spar inside the left 

and right main fuel tanks. This AD was 

prompted by a fuel system review 

conducted by the manufacturer. We 

have received reports from the 

manufacturer that additional fasteners 

in the main fuel tanks must be sealed for 

lightning strike protection. We are 

issuing this AD to detect and correct 

improper wire bundle support 

installation and sleeving and to prevent 

improperly sealed fasteners in the main 

and center fuel tanks from becoming an 

ignition source, in the event of a fault 

current or lightning strike, which could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD is effective March 31, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 31, 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. 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 


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Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tak 

Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590.; 

e-mail: Takahisa.Kobayashi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

directive (AD) 2008–23–19, Amendment 

39–15740 (73 FR 71534, November 25, 

2008). That AD applies to the specified 

products. The NPRM published in the 

Federal Register on July 23, 2010 (75 FR 

43097). That NPRM proposed to 

continue to require sealing the fasteners 

on the front and rear spars inside the 

left and right main fuel tanks and on the 

rear spar and lower panel of the center 

fuel tank. That NPRM also proposed to 

require inspections of the wire bundle 

support installations to verify if certain 

clamps are installed and if Teflon 

sleeving covers the wire bundles inside 

the left and right equipment cooling 

system bays, on the left and right rear 

spars, and on the left and right front 

spars; corrective actions if necessary; 

and sealing of additional fasteners on 

the rear spar inside the left and right 

main fuel tanks. 

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. 

Concurrence With the NPRM 

Boeing concurs with the contents of 

the proposed rule. 

Request To Revise the Compliance 

Time 

FedEx, US Airways, Delta, European 

Air Transport Leipzig GmbH (European 

Air)/DHL Air requested a change in the 

compliance time. FedEx, Delta, and US 

Airways requested that we change the 

compliance time from ‘‘60 months after 

December 30, 2008,’’ to ‘‘60 months after 

the effective date of the final rule’’ in 

paragraph (h) of the NPRM. European 

Air/DHL Air requested an extension of 

the compliance time from 60 months to 

a minimum of 72 months for airplanes 

that have already been modified in 

accordance with Boeing Alert Service 

Bulletin 757–57A0064, dated July 16, 

2007. FedEx and Delta stated that fuel 

tank access occurs at 72-month 

intervals. European Air/DHL Air stated 

that they purge the fuel tanks during a 

4C-check corresponding to 72 months, 

12,000 flight cycles, or 24,000 flight 

hours, whichever occurs first. European 

Air/DHL Air stated that the proposed 

compliance time does not allow a 

suitable maintenance opportunity to 

accomplish the additional work without 

disturbing the scheduled maintenance 

activities. Delta stated that the proposed 

compliance time allows approximately 

3 years from the effective date of the 

final rule. Delta considered this 

requirement an undue burden that is not 

justified. Delta stated that the SFAR88 

initiative and the Aging Aircraft 

initiatives generally have a timeline of 

60 months to upgrade the airplanes 

based on the FAA harmonization policy 

of the aging airplane programs per ‘‘Fuel 

Tank Safety Compliance Extension 

(Final Rule) and Aging Airplane 

Program Update (Request for 

Comments)’’ (69 FR 45936, July 30, 

2004). 

We agree that the compliance time in 

paragraph (h) of this AD should be 

changed to ‘‘within 60 months after the 

effective date of this AD’’ to avoid 

causing an undue burden on operators 

who have already accomplished the 

modification in accordance with Boeing 

Alert Service Bulletin 757–57A0064, 

dated July 16, 2007. In addition, we 

consider the following condition may 

warrant this change in the compliance 

time. The additional work specified in 

Boeing Alert Service Bulletin 757– 

57A0064, Revision 1, dated October 5, 

2009, is intended to provide an 

additional layer of protection to the 

main fuel tanks to prevent ignition 

sources from occurring inside those 

tanks under a lightning strike event. The 

existing fastener installation is able to 

tolerate lightning current without 

introducing ignition sources inside the 

main fuel tanks if no failure conditions 

exist. The additional work of sealing the 

affected fasteners will add a fail-safe 

design feature to the existing fastener 

installation so that no ignition sources 

are introduced under the presence of 

single failures. Because of this, we 

consider that an acceptable level of 

safety would still be provided with this 

change in the compliance time. We have 

also limited the airplanes affected by 

paragraph (h) of this AD to airplanes on 

which Boeing Alert Service Bulletin 

757–57A0064, dated July 16, 2007, was 

done before the effective date of this 

AD. 

We have also revised paragraph (g) of 

this AD to add the following sentence: 

‘‘As of the effective date of this AD, only 

Boeing Alert Service Bulletin 757– 

57A0064, Revision 1, dated October 5, 

2009, may be used.’’ 

We do not agree with extending the 

compliance time to 72 months. In 

developing an appropriate compliance 

time, we considered the safety 

implications, parts availability, and 

normal maintenance schedules for 

timely replacement of the fasteners. In 

consideration of all of these factors, we 

determined that the 60-month 

compliance time represents an 

acceptable interval in which the 

fasteners can be sealed in a timely 

manner, while still maintaining an 

acceptable level of safety. According to 

the provisions of paragraph (j) of this 

AD, operators may request an 

alternative method of compliance 

(AMOC) to request a longer compliance 

time, if the request is submitted with 

substantiating data that proves that the 

longer compliance time will provide an 

acceptable level of safety. We have not 

changed the AD further in this regard. 

Request To Allow Modification in 

Accordance With Original Issue of 

Service Bulletin 

European Air/DHL Air requested that 

we allow the modification, in 

accordance with Boeing Alert Service 

Bulletin 757–57A0064, dated July 16, 

2007, and Boeing Multi Operator 

Message (MOM) 

1–1046487761, dated November 6, 2008, 

as an accepted means of compliance. 

European Air stated that they started 

incorporating the modifications 

specified in Boeing Alert Service 

Bulletin 757–57A0064, dated July 16, 

2007, and Boeing MOM 1–1046487761, 

dated November 6, 2008, before AD 

2008–23–19 was issued. 

We infer that European Air/DHL Air 

are requesting that we allow the 

modification done in accordance with 

Boeing Alert Service Bulletin 757– 

57A0064, dated July 16, 2007, and 

Boeing MOM 1–1046487761, dated 

November 6, 2008, as a means of 

compliance with paragraphs (g) and (h) 

of this AD. We do not agree. Boeing 

Alert Service Bulletin 757–57A0064, 

dated July 16, 2007, is not sufficient to 

address the unsafe condition, and 

Boeing MOM 1–1046487761, dated 

November 6, 2008, merely informs 

operators of a forthcoming revision to 

Boeing Alert Service Bulletin 757– 

57A0064, dated July 16, 2007, which 

will include additional work of sealing 

40 fasteners that are not identified in 

Boeing Alert Service Bulletin 757– 

57A0064, dated July 16, 2007. Boeing 

MOM 1–1046487761, dated November 

6, 2008, refers to two sketches that 

provide the locations of additional 


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fasteners that must be sealed. Those 

sketches can help operators to 

accomplish the additional work, but 

they only provide figures that are 

applicable to certain airplane groups 

identified in Boeing Alert Service 

Bulletin 757–57A0064, dated July 16, 

2007. In addition, those sketches are not 

a published document and cannot be 

incorporated by reference in the AD. We 

have determined that it is inappropriate 

to include Boeing MOM 1–1046487761, 

dated November 6, 2008, as an accepted 

means to comply with the actions 

required by this AD. However, operators 

who have used those data can still 

request approval of an AMOC, in 

accordance with paragraph (j) of this 

AD. No change has been made to the AD 

in this regard. 

Request To Clarify Instructions for 

Continued Airworthiness (ICA) 

Continental stated that proper ICA 

must be provided in order to prevent 

inadvertent reversal of implemented 

changes that can lead to violation of 

requirements of the SFAR88 program as 

well as the final rule. Continental 

Airlines requested that we coordinate 

with Boeing to ensure proper 

instructions are provided. 

We acknowledge the commenter’s 

concern. Operators and owners are 

responsible for ensuring that the 

configuration mandated by this AD is 

maintained in accordance with section 

39.7 of the Federal Aviation Regulations 

(14 CFR 39.7). If any new airworthiness 

limitations (AWLs) related to any of the 

design features mandated by this AD are 

developed, we may consider additional 

rulemaking to mandate incorporation of 

those AWLs into operators’ maintenance 

programs. The FAA is working with 

industry to evaluate potential changes to 

the AD process that are intended to 

more clearly identify how to maintain 

configurations that are required for AD 

compliance. We have not changed the 

AD regarding this issue. 

Request To Allow Alternative Color of 

Lacing Tape 

Continental raised a question 

regarding the color of lacing tape 

specified in Boeing Alert Service 

Bulletins 757–57A0064, dated July 16, 

2007; and Revision 1, dated October 5, 

2009. Continental stated that those 

service bulletins require use of a lacing 

tape identified as BMS 13–54, Type III, 

Class 1, Finish C, Black. Continental 

stated that a specific color of the lacing 

tape should not be mandated. 

Continental stated that Boeing Standard 

Wiring Process Manual 20–10–11 makes 

no distinction regarding the color of the 

lacing tape for sleeve installation. 

We infer that Continental is 

requesting that we allow any color as 

long as the lacing tape is BMS 13–54, 

Type III, Class 1, Finish C. We agree to 

allow the use of white lacing tape 

because white is a neutral color that is 

not associated with any specific color 

code requirement. However, we disagree 

with allowing the use of lacing tape 

with colors other than black or white 

because use of colors other than black 

or white may be inconsistent with colorcoding used by the manufacturer or 

operator, and could create confusion in 

wiring identification. We have granted a 

global AMOC to allow the use of lacing 

tape BMS 13–54, Type III, Class 1, 

Finish C, with white color in place of 

black color when accomplishing the 

actions specified in Boeing Alert Service 

Bulletin 757–57A0064, dated July 16, 

2007, as required by paragraph (f) of AD 

2008–23–19, Amendment 39–15740. 

Paragraph (i) has been added to this AD 

to reflect these changes. 

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 have determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

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 667 

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 

Fastener Sealing and Inspections (required by AD 2008–23–19).Up to 545 work-hours × $85 per hour 

= Up to $46,325 per airplane depending on configuration.

$325 Up to $46,650 .......... Up to $31,115,550. 

Main Tank Fastener Sealing (new proposed action).Up to 30 work-hours × $85 per hour = 

Up to $2,550.

$0 Up to $2,550 ............ Up to $1,700,850. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Clamp Replacement ................................................ Up to 6 work-hours × $85 per hour = $510 ............ $0 Up to $510. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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, 


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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 

We have determined that 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 

removing airworthiness directive (AD) 

2008–23–19, Amendment 39–15740 

(73 FR 71534, November 25, 2008), and 

adding the following new AD: 

2011–05–04 The Boeing Company: 

Amendment 39–16613; Docket No. 

FAA–2010–0698; Directorate Identifier 

2009–NM–264–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective March 31, 2011. 

Affected ADs 

(b) This AD supersedes AD 2008–23–19, 

Amendment 39–15740. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 757–200, –200CB, –200PF, 

and –300 series airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from a fuel system 

review conducted by the manufacturer. We 

have received reports from the manufacturer 

that additional fasteners in the main fuel 

tanks must be sealed for lightning strike 

protection. The Federal Aviation 

Administration is issuing this AD to detect 

and correct improper wire bundle support 

installation and sleeving and to prevent 

improperly sealed fasteners in the main and 

center fuel tanks from becoming an ignition 

source, in the event of a fault current or 

lightning strike, which could result in a fuel 

tank explosion and consequent loss 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. 

Restatement of Requirements of AD 2008– 

23–19, With Revised Service Information 

Fastener Sealing and Inspections 

(g) Within 60 months after December 30, 

2008 (the effective date of AD 2008–23–19), 

seal the applicable fasteners and do the 

general visual inspections of the wire bundle 

support installations, and do all the 

applicable corrective actions before further 

flight, by accomplishing all of the applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–57A0064, dated July 16, 2007; or Part 1 

through Part 10 of the Work Instructions of 

Boeing Alert Service Bulletin 757–57A0064, 

Revision 1, dated October 5, 2009. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 757–57A0064, Revision 1, 

dated October 5, 2009, may be used. 

New Requirements of This AD 

Fastener Sealing on the Rear Spar 

(h) For airplanes on which the actions in 

Boeing Alert Service Bulletin 757–57A0064, 

dated July 16, 2007, were accomplished 

before the effective date of this AD: Within 

60 months after the effective date of this AD, 

seal the fasteners on the rear spar inside the 

left and right main fuel tanks, in accordance 

with Part 11 of the Work Instructions of 

Boeing Alert Service Bulletin 757–57A0064, 

Revision 1, dated October 5, 2009. 

Acceptable Lacing Tape for Repair Actions 

(i) Where Boeing Alert Service Bulletin 

757–57A0064, Revision 1, dated October 5, 

2009, describes the use of lacing tape BMS 

13–54, Type III, Class 1, Finish C, Black, this 

AD also allows the use of lacing tape BMS 

13–54, Type III, Class 1, Finish C, White, as 

an alternative. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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: Tak 

Kobayashi, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-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, 

notify your 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. 

(3) AMOCs approved previously in 

accordance with AD 2008–23–19, 

Amendment 39–15740, are approved as 

AMOCs for the corresponding provisions of 

paragraph (g) of this AD. 

Related Information 

(k) For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6499; fax (425) 

917–6590; e-mail: 

Takahisa.Kobayashi@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 757–57A0064, Revision 1, dated 

October 5, 2009, 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, 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 


jlentini on DSKJ8SOYB1PROD with RULES
10230 Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 

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 February 

14, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–4013 Filed 2–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0859; Directorate 

Identifier 2010–NM–113–AD; Amendment 

39–16614; AD 2011–05–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes 

and Model A340–200, –300, –500, and 

–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

* * * * * 

* * * [T]here is a possible path for fluid 

ingress, resulting in connector internal arcing 

and hydraulic system malfunction. In 

addition, as the connectors are located in 

areas adjacent to fuel tanks, such arcing 

associated with the presence of a fuel leakage 

could lead to an uncontrolled fire. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 31, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 31, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

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 was published in the Federal 

Register on September 29, 2010 (75 FR 

60010). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several A330 and A340 operators have 

reported in service occurrences of hydraulic 

pump electrical motor connector internal 

arcing, resulting in: 

—Either false hydraulic system overheat 

Electronic Centralized Aircraft Monitoring 

(ECAM) warnings 

—and/or hydraulic pump electrical motor 

malfunction. 

Investigations have shown that, due to the 

manufacturing tolerances of the cables and 

the connectors rear grommet, there is a 

possible path for fluid ingress, resulting in 

connector internal arcing and hydraulic 

system malfunction. In addition, as the 

connectors are located in areas adjacent to 

fuel tanks, such arcing associated with the 

presence of a fuel leakage could lead to an 

uncontrolled fire. 

In order to protect the hydraulic pump 

electrical motor connectors against fluid 

ingress from the rear of the connector 

grommet and prevent false hydraulic system 

overheat ECAM warnings and/or hydraulic 

pump electrical motor malfunction, this AD 

requires modification of the three hydraulic 

pump electrical motor connectors associated 

to the Blue, Yellow and Green hydraulic 

systems. 

This Revision 1 is issued to delete Airbus 

modifications 55923S18878 and 

55924S19452 from the applicability of this 

AD. 

The modification adds heat shrink 

sleeves to certain cable contacts and a 

sealing plug to the connector free cavity. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

The NPRM referred to the service 

information in the following table as the 

applicable sources of service 

information. 

TABLE—SERVICE INFORMATION CITED IN THE NPRM 

Airplane 

model— Airbus Mandatory Service Bulletin— Revision— Dated— 

A330 ................. A330–92–3088, including Appendix 01 ........................................................................ 01 February 22, 2010. 

A340 ................. A340–92–4081, including Appendix 01 ........................................................................ 01 February 22, 2010. 

A340 ................. A340–92–5053, including Appendix 01 ........................................................................ 01 February 22, 2010. 

Airbus has released the service 

information in the following table. No 

additional work is necessary for 

airplanes on which earlier revisions of 

the service information are done. We 

have updated Tables 1 and 3 of the final 

rule to refer to these sources of service 

information. We have also updated 

Table 2 of the final rule to give credit 

for using Revision 01 of the service 

information. 

TABLE—REVISED SERVICE INFORMATION

Airplane 

model— Airbus Mandatory Service Bulletin— Revision— Dated— 

A330 ................. A330–92–3088, including Appendix 01 ........................................................................ 02 September 1, 2010. 

A340 ................. A340–92–4081, including Appendix 01 ........................................................................ 02 September 1, 2010. 

A340 ................. A340–92–5053, including Appendix 01 ........................................................................ 02 September 1, 2010. 


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