Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations 24833 

time specified in Goodrich Principal 

Instructions for Continued Airworthiness 

Manual for the Analog Transient Suppression 

Device Installation Applicable to Boeing 

737–100 through -500 Airplanes 

Supplemental Type Certificate—ST00146BO, 

Document T3044–0010–0101, Revision D, 

dated September 26, 2011, or within 18 

months after the effective date of this AD, 

whichever occurs later. 

Note 1 to paragraph (g) of this AD: 

Components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the 

maintenance program, as required by 

paragraph (g) of this AD, do not need to be 

reworked in accordance with the CDCCLs. 

However, once the maintenance program has 

been revised, paragraph (g) of this AD 

requires that future maintenance actions on 

these components must follow the CDCCLs. 

(h) No Alternative Actions Intervals, and/or 

Critical Design Configuration Control 

Limitations 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used other than those 

specified in Goodrich Principal Instructions 

for Continued Airworthiness Manual for the 

Analog Transient Suppression Device 

Installation Applicable to Boeing 737–100 

through -500 Airplanes Supplemental Type 

Certificate—ST00146BO, Document 

T3044–0010–0101, Revision D, dated 

September 26, 2011, unless the actions, 

intervals, and/or CDCCLs are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(1) The Manager, Boston Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

For more information about this AD, 

contact Marc Ronell, Aerospace Engineer, 

Engine and Propeller Directorate, ANE–150, 

FAA, New England Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, Massachusetts 01803; phone: 

781–238–7776; fax: 781–238–7170; email: 

marc.ronell@faa.gov. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(i) Goodrich Principal Instructions for 

Continued Airworthiness Manual for the 

Analog Transient Suppression Device 

Installation Applicable to Boeing 737–100 

through -500 Airplanes Supplemental Type 

Certificate—ST00146BO, Document T3044– 

0010–0101, Revision D, dated September 26, 

2011. 

(2) For service information identified in 

this AD, Goodrich Corporation, Sensors and 

Integrated Systems, 100 Panton Road, 

Vergennes, Vermont 05491; phone: 802–877– 

4580; fax: 802–877–4444; email: 

les.blades@goodrich.com; Internet: http:// 

www.goodrich.com/TechPubs. 

(3) 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. 

(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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on April 13, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–9713 Filed 4–25–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0033; Directorate 

Identifier 2011–NM–086–AD; Amendment 

39–17029; AD 2012–08–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310 series airplanes. 

This AD was prompted by a report of an 

electrical arc and hydraulic haze in the 

wheel bay of the left-hand main landing 

gear (MLG) possibly resulting from 

chafing between the hydraulic high 

pressure hose and electrical wiring of 

the green electrical motor pump (EMP). 

This AD requires temporarily 

prohibiting in-flight use of the green 

EMPs; temporarily revising the airplane 

flight manual (AFM) limitations section; 

temporarily installing a placard in the 

cockpit overhead panel; doing a onetime general visual inspection for 

correct condition and installation of 

hydraulic pressure hoses, electrical 

conduits, feeder cables, and associated 

clamping devices; and corrective action 

if necessary. We are issuing this AD to 

detect and correct chafing of hydraulic 

pressure hoses and electrical wiring of 

the green EMPs, which in combination 

with a system failure, could cause an 

uncontrolled and undetected fire in the 

MLG bay. 

DATES: This AD becomes effective May 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 31, 2012. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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 January 20, 2012 (77 FR 

2928). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An operator reported an electrical arc and 

a large hydraulic haze in the left hand Main 

Landing Gear (LH MLG) wheel bay that 

occurred during ground operation. The 

analysis revealed that this occurrence is 

likely the result of chafing between hydraulic 

high pressure hose and electrical wiring of 

the Green Electrical Motor Pump (EMP). 

This condition, if not detected and 

corrected, and in combination with a system 

failure leading to the use of the Green EMPs 

in flight, could lead to an uncontrolled and 

undetected fire in the MLG bay. 

For the reasons explained above, this AD 

temporarily prohibits the in-flight use of 

green EMPs, by mandating an update of the 

Aeroplane Flight Manual (AFM) limitations 

section and installation of a placard in the 

cockpit overhead panel. This [EASA] AD 

requires also a one-time [general] visual 

inspection of hydraulic pressure hoses and 

electrical wiring of Green EMPs and 

corrective action(s), depending on findings. 

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24834 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations 

Corrective actions include repairing or 

replacing the hydraulic pressure hoses 

and electrical wiring. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Request To Add Word to Summary 

Paragraph 

Airbus requested the word 

‘‘temporarily’’ be added before the 

phrases in the Summary section of the 

NPRM (77 FR 2928, January 20, 2012): 

‘‘prohibiting in-flight use of the green 

EMPs,’’ ‘‘revising the airplane flight 

manual (AFM) limitations section,’’ and 

‘‘installing a placard in the cockpit 

overhead panel.’’ Airbus explained that 

after the one-time visual inspection of 

the hydraulic pressure hoses and 

electrical wiring of the green EMPs and 

accomplishing the corrective actions, if 

needed, these limitations must be 

removed. 

We concur. We have added the word 

‘‘temporarily’’ before those phrases in 

the Summary section of this AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 2928, 

January 20, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 2928, 

January 20, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

58 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $200 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $21,460, or 

$370 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 

We 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 the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (77 FR 2928, 

January 20, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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: 

2012–08–12 Airbus: Amendment 39–17029. 

Docket No. FAA–2012–0033; Directorate 

Identifier 2011–NM–086–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 31, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29: Hydraulic Power. 

(e) Reason 

This AD was prompted by a report of an 

electrical arc and hydraulic haze in the wheel 

bay of the left-hand main landing gear (MLG) 

possibly resulting from chafing between the 

hydraulic high pressure hose and electrical 

wiring of the green electrical motor pump 

(EMP). We are issuing this AD to detect and 

correct chafing of hydraulic pressure hoses 

and electrical wiring of the green EMP, 

which in combination with a system failure, 

could cause an uncontrolled and undetected 

fire in the MLG bay. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Installing Placard and Revising Airplane 

Flight Manual (AFM) 

For all airplanes, as of the effective date of 

this AD, the in-flight use of green EMPs is 

prohibited. Before the next flight, do the 

actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) Install in the cockpit on the hydraulic 

power overhead panel 427VU, a locally 

manufactured self-adhesive placard 

temporarily prohibiting the in-flight use of 

the green EMPs, in accordance with the 

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Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations 24835 

instructions in Airbus All Operators Telex 

A310–29A2101, Revision 01, dated April 12, 

2011 (for airplanes equipped with EATON 

(formerly VICKERS) hydraulic EMPs); or 

Airbus All Operators Telex A310–29A2102, 

dated April 12, 2011 (for airplanes equipped 

with PARKER (formerly ABEX) hydraulic 

EMPs). 

(2) Revise the Limitations section of the 

applicable AFM to prohibit the in-flight use 

of the green EMPs. This may be 

accomplished by inserting a copy of this AD 

into the Limitations section of the AFM. 

(h) Inspecting for Damage and Chafing 

Within 500 flight hours or 4 months after 

the effective date of this AD, whichever 

occurs first, do a one-time general visual 

inspection for correct condition (i.e., no 

damage and no chafing) and correct 

installation of the hydraulic pressure hoses, 

electrical conduits, feeder cables, and 

associated clamping devices at frame 54, as 

well as the electrical conduits and feeder 

cables underneath the clamps (including 

removal of the concerned clamps), in 

accordance with the instructions in Airbus 

All Operators Telex A310–29A2101, Revision 

01, dated April 12, 2011 (for airplanes 

equipped with EATON (formerly VICKERS) 

hydraulic EMPs); or Airbus All Operators 

Telex A310–29A2102, dated April 12, 2011 

(for airplanes equipped with PARKER 

(formerly ABEX) hydraulic EMPs). If any 

incorrect installation is found, before further 

flight, install the affected parts correctly, in 

accordance with Airbus All Operators Telex 

A310–29A2101, Revision 01, dated April 12, 

2011 (for airplanes equipped with EATON 

(formerly VICKERS) hydraulic EMPs); or 

Airbus All Operators Telex A310–29A2102, 

dated April 12, 2011 (for airplanes equipped 

with PARKER (formerly ABEX) hydraulic 

EMPs). 

(1) If any damage or chafing marks are 

found during the inspection required by 

paragraph (h) of this AD, before further flight, 

replace or repair the affected parts (hydraulic 

pressure hoses, electrical conduits, feeder 

cables, clamps, and spacer, if installed), in 

accordance with the instructions in Airbus 

All Operators Telex A310–29A2101, Revision 

01, dated April 12, 2011 (for airplanes 

equipped with EATON (formerly VICKERS) 

hydraulic EMPs); or Airbus All Operators 

Telex A310–29A2102, dated April 12, 2011 

(for airplanes equipped with PARKER 

(formerly ABEX) hydraulic EMPs). 

(2) Before further flight after compliance 

with the requirements of paragraph (h) of this 

AD, as applicable, remove the placard 

required by paragraph (g)(1) of this AD; and 

remove the revision of the Limitations 

section of the AFM, as required by paragraph 

(g)(2) of this AD; from the airplane and the 

AFM, respectively. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(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 FAA-approved 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. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0071, dated April 18, 2011; 

Airbus All Operators Telex A310–29A2101, 

Revision 01, dated April 12, 2011; and 

Airbus All Operators Telex A310–29A2102, 

dated April 12, 2011; for related information. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus All Operators Telex A310– 

29A2101, Revision 01, dated April 12, 2011. 

The document number, revision level, and 

issue date of this document is specified only 

on the first page of the document. 

(ii) Airbus All Operators Telex A310– 

29A2102, dated April 12, 2011. The 

document number, revision level, and issue 

date of this document is specified only on the 

first page of the document. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email: account.airwortheas@airbus.com; Internet http:// 

www.airbus.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 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 April 12, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–9475 Filed 4–25–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0277; Directorate 

Identifier 2009–NM–217–AD; Amendment 

39–17031; AD 2012–08–14] 

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 767 

airplanes. This AD was prompted by 

reports of cracking in the upper wing 

skin at the fastener holes common to the 

pitch load fittings of the inboard and 

outboard front spar, which could result 

in the loss of the strut-to-wing upper 

link load path and possible separation 

of a strut and engine from the airplane 

during flight. This AD requires 

repetitive inspections to detect fatigue 

cracking in the wing skin, and 

corrective actions if necessary. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective May 31, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 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; email 

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:// 

mstockstill on DSK4VPTVN1PROD with RULES