Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations 24831 

modification 44385 has been embodied either 

in production or in service by Airbus Service 

Bulletin A330–27–3159 or Airbus Service 

Bulletin A340–27–4158; and Airbus 

modification 44431 has been embodied either 

in production or in service by Airbus Service 

Bulletin A330–24–3011 or Airbus Service 

Bulletin A340–24–4019: Within 30 days after 

the effective date of this AD, revise the 

Limitations section of the applicable AFM to 

include the following statement. This may be 

done by inserting a copy of this AD into the 

AFM. 

Dispatch with the FCPC ‘‘PRIM 1’’ 

inoperative is allowed provided that the 

operational test of the FCPC3 second 

electrical power supply is successfully 

performed, in accordance with the 

instructions of Airbus AOT A330–27A3158, 

or AOT A340–27A4157, as applicable, before 

the first flight of the MMEL interval. 

If the test is not successful, repair in 

accordance with the instructions of Airbus 

AOT A330–27A3158 or AOT A340–27A4157, 

as applicable, before dispatch with FCPC 

‘‘PRIM 1’’ inoperative. 

Note 2 to paragraph (h)(1) of this AD: 

When a statement identical to that in 

paragraph (h)(1) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

(2) Model A330–223F and –243F airplanes 

are not affected by paragraph (h) of this AD. 

(i) AFM Revision for Model A330–223F and 

A330–243F Airplanes 

For Model A330–223F and A330–243F 

airplanes: Within 30 days after the effective 

date of this AD, revise the Limitations section 

of the AFM to include the following 

statement. This may be done by inserting a 

copy of this AD into the AFM. 

Dispatch with the FCPC ‘‘PRIM 1’’ 

inoperative is allowed provided that the 

operational test of the FCPC3 second 

electrical power supply is successfully 

performed, in accordance with the 

instructions of Airbus AOT A330–27A3158, 

before the first flight of the MMEL interval. 

If the test is not successful, repair in 

accordance with the instructions of Airbus 

AOT A330–27A3158, before dispatch with 

FCPC ‘‘PRIM 1’’ inoperative. 

Note 3 to paragraph (i) of this AD: When 

a statement identical to that in paragraph (i) 

of this AD has been included in the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, and the copy 

of this AD may be removed from the AFM. 

(j) 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: 

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. 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0109, 

dated June 28, 2010, for related information. 

(l) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on April 5, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–10029 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–2012–0110; Directorate 

Identifier 2011–NM–148–AD; Amendment 

39–17034; AD 2012–08–17] 

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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes equipped with analog 

transient suppression devices (ATSDs) 

installed in accordance with 

Supplemental Type Certificate 

ST00146BO. This AD was prompted by 

multiple reports of corrosion on ATSDs. 

This AD requires revising the 

maintenance program to incorporate 

certain limitations. We are issuing this 

AD to detect and correct corrosion on 

ATSDs, which could result in the loss 

of high voltage transient protection (e.g., 

lightning protection) in the fuel tanks 

and consequent fuel tank explosion and 

loss of the airplane. 

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 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. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Marc Ronell, Aerospace Engineer, 

Engine and Propeller Directorate, ANE– 

150, FAA, New England Aircraft 

Certification Office (ACO), 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; phone: 781–238– 

7776; fax: 781–238–7170; email: 

marc.ronell@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 9, 2012 (77 FR 

6692). That NPRM proposed to require 

revising the maintenance program to 

incorporate certain limitations. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

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24832 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations 

FR 6692, February 9, 2012) or on the 

determination of the cost to the public. 

Changes Made to This AD 

We have redesignated Note 1 of the 

NPRM (77 FR 6692, February 9, 2012) 

as paragraph (c)(2) of this AD and 

redesignated subsequent notes 

accordingly, and redesignated paragraph 

(c) of the NPRM as paragraph (c)(1) of 

this AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 6692, 

February 9, 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 6692, 

February 9, 2012). 

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 384 

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 

Revise maintenance program ......................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $32,640 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–08–17 The Boeing Company: 

Amendment 39–17034; Docket No. 

FAA–2012–0110; Directorate Identifier 

2011–NM–148–AD. 

(a) Effective Date 

This AD is effective May 31, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category, with an original 

airworthiness certificate or original export 

certificate of airworthiness issued before 

September 26, 2011, equipped with analog 

transient suppression devices (ATSDs) 

installed in accordance with Supplemental 

Type Certificate ST00146BO. http:// 

rgl.faa.gov/Regulatory

_and_Guidance_Library/rgstc.nsf/0/2399C

433BB10CF1085256CCB00601A12?Open

Document&Highlight=st00146bo 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections and/or Critical 

Design Configuration Control Limitations 

(CDCCLs). Compliance with these actions is 

required by 14 CFR 91.403(c). For airplanes 

that have been previously modified, altered, 

or repaired in the areas addressed by these 

inspections, the operator may not be able to 

accomplish the inspections described in the 

revisions. In this situation, to comply with 14 

CFR 91.403(c), the operator must request 

approval for an alternative method of 

compliance (AMOC) according to paragraph 

(i) of this AD. The request should include a 

description of changes to the required actions 

that will ensure the continued operational 

safety of the airplane. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2841, Fuel Quantity Indicator. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of corrosion on ATSDs. We are issuing this 

AD to detect and correct corrosion on ATSDs, 

which could result in the loss of high voltage 

transient protection (e.g., lightning 

protection) in the fuel tanks and consequent 

fuel tank explosion and loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision 

Within 3 months after the effective date of 

this AD, revise the maintenance program to 

incorporate the limitations 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. The initial compliance time for 

accomplishing each task is at the applicable 

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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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