Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 64701 

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): 

2012–21–07—AGUSTA S.p.A. (Agusta): 

Amendment 39–17223; Docket No. 

FAA–2012–0448; Directorate Identifier 

2010–SW–016–AD. 

(a) Applicability 

This AD applies to Agusta Model A109S 

helicopters, serial numbers up to and 

including 22151, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of the 35 ampere (amp) ‘‘BATT BUS,’’ 

which could result in an electrical failure 

and fire, loss of electrical power to 

instruments powered by the ‘‘BATT BUS’’ 

system, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective November 27, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 50 hours time-in-service, modify 

the electrical power distribution system by 

installing the ‘‘BATT BUS’’ Circuit Breaker 

Modification Kit, part number 109–0824–73– 

107, as depicted in Figures 1 through 3 and 

by following the Compliance Instructions, 

paragraphs 4. through 7., of Agusta Bollettino 

Tecnico No. 109S–35, dated December 11, 

2009 (ASB). Thereafter, operationally test the 

electrical system by following paragraphs 

19.1 through 19.7 of the ASB. 

(f) Special Flight Permits 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the requirements of this AD can be 

accomplished provided that you do not 

simultaneously operate the landing light and 

the search light. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Mark F. Wiley, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

mark.wiley@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2009–0264, dated December 15, 2009. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2460, DC Power/Distribution System. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Agusta Bollettino Tecnico No. 109S–35, 

dated December 11, 2009. 

(ii) Reserved. 

(3) For Agusta service information 

identified in this AD, contact Agusta, S.p.A., 

Via Giovanni Agusta 520, 21017 Cascina 

Costa di Samarate (VA), Italy, ATTN: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39–0331–711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this 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/ibrlocations.html. 

Issued in Fort Worth, Texas, on October 12, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–25896 Filed 10–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0144; Directorate 

Identifier 2011–NM–152–AD; Amendment 

39–17220; AD 2012–21–04] 

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 A300 series airplanes; 

Model A310 series airplanes; and Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). This AD was prompted by 

reports of cracked fuel pump canister 

hoods located in fuel tanks. This AD 

requires replacing any cracked hood 

halves of fuel pump canisters. We are 

issuing this AD to prevent any detached 

canister hood fragments/debris from 

being ingested into the fuel feed system, 

and becoming a potential source of 

ignition with consequent fire or 

explosion. 

DATES: This AD becomes effective 

November 27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 27, 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 February 22, 2012 (77 FR 

10409). That NPRM proposed to correct 


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64702 Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 

an unsafe condition for the specified 

products. The MCAI states: 

This [European Aviation Safety Agency 

(EASA)] AD results from findings of cracked 

fuel pump canister hoods located in fuel 

tanks. 

From the analyses, laboratory testing and 

examinations made so far, it is presently 

thought that vibration-induced fatigue can be 

identified as the root cause for the cracks 

found on in-service aeroplanes. However, 

current data does not yet permit to exclude 

some other potential contributing factors. 

This condition, if not detected and 

corrected, could lead to detached canister 

hood fragments/debris to be ingested into the 

fuel feed system. Also, the metallic debris 

inside the fuel tank could result in a 

potential source of ignition and consequent 

fire or explosion. 

For the reasons described above, this 

[EASA] AD requires repetitive [detailed] 

inspections of all fuel pump canister hood 

halves and their replacement if any 

[cracking] damage is found. This [EASA] AD 

also requires the inspection results to be 

reported. 

This [EASA] AD is considered to be an 

interim action. The reports that are required 

by this [EASA] AD will enable the 

manufacturer to obtain better insight into the 

nature, cause, and extent of the fuel pump 

canister hood cracking, and eventually to 

develop final action to address the unsafe 

condition. Once final action has been 

identified, further AD actions could be 

considered. 

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 comments received. 

Request To Extend Reporting Time 

FedEx requested that the time for 

submitting reports, proposed in the 

NPRM (77 FR 10409, February 22, 2012) 

as 30 days, be extended to 90 days, 

because it might not have immediate 

access to maintenance vendors’ records 

of the completed tasks, and system-wide 

reporting can sometimes require longer 

times. 

Although EASA AD 2011–0124, dated 

June 30, 2011, specifies a 30-day 

compliance time for submitting reports, 

we agree with the commenter’s request 

to extend the compliance time for 

reporting because a delay will not 

compromise safety. We have changed 

paragraphs (j)(1) and (j)(2) of this final 

rule accordingly. This difference has 

been coordinated with EASA. 

Request for Specific Contact 

Information for Reporting 

FedEx requested that we provide 

specific information for submitting the 

reports proposed in the NPRM (77 FR 

10409, February 22, 2012), including an 

email address, to facilitate reporting. 

We agree with the commenter’s 

request for the reason given, and have 

added that information in paragraph (j) 

of this final rule. 

Request To Delay the Final Rule 

Effective Date and Extend the 

Compliance Time 

UPS requested that the AD be 

effective after Airbus completes 

certifying the improved design for the 

fuel pump half hood, projected to be 

completed in late 2012. UPS also 

requested an initial compliance time of 

36 months (versus the 30 months 

proposed in the NPRM (77 FR 10409, 

February 22, 2012)) to allow for 

purchasing and part lead time. UPS 

stated that these changes to the NPRM 

would enable a one-time through-thefleet solution without the need for 

repetitive inspections. 

We do not agree with the commenter’s 

request for extending the compliance 

time. In developing an appropriate 

compliance time for this action, we 

considered not only the degree of 

urgency associated with addressing the 

subject unsafe condition, but the 

manufacturer’s and EASA’s 

recommendations for an appropriate 

compliance time, and the availability of 

required parts. We have not changed the 

AD in this regard. 

Further, we do not agree with the 

request for delaying the AD. For 

continued operational safety, operators 

need to begin the inspections, and not 

delay the inspections until the part is 

certified. We will consider an 

alternative method of compliance 

(AMOC) when parts are available. 

Operators may request approval of an 

AMOC in accordance with paragraph 

(k)(1) of this final rule, if sufficient data 

are submitted to substantiate that the 

method would provide an acceptable 

level of safety. We have not changed the 

AD in this regard. 

Airplane Models Added to This AD 

We have determined that Model A300 

B2–1A and A300 B4–601 airplanes were 

inadvertently omitted from the 

Applicability of the NPRM (77 FR 

10409, February 22, 2012). We have 

added those models to the Applicability 

of this AD in paragraphs (c)(1) and (c)(3) 

respectively. However, none of the 

airplanes added to the Applicability of 

this AD are on the U.S. Register. 

Therefore, additional notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Explanation of Updated Credit 

Language 

We have revised the heading and 

wording for paragraph (i) of this AD to 

provide appropriate credit for previous 

accomplishment of certain actions. This 

change does not affect the intent of that 

paragraph. 

Conclusion 

We reviewed the available data, 

including the comments received, 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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

10409, February 22, 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 10409, 

February 22, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 221 products of U.S. registry. We 

also estimate that it will take up to 12 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $225,420, or $1,020 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour. We have no way of 

determining the number of products 

that may need these actions. 

We have received no definitive data 

that would enable us to provide cost 

estimates for certain parts required for 

the on-condition actions (replacing fuel 

pump canister hood halves) specified in 

this AD. 

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 


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Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 64703 

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 10409, 

February 22, 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: 

2012–21–04 Airbus: Amendment 39–17220. 

Docket No. FAA–2012–0144; Directorate 

Identifier 2011–NM–152–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

certificated models, all serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes. 

(3) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes, Model A300 

B4–605R and B4–622R airplanes, Model 

A300 F4–605R and F4–622R airplanes, and 

Model A300 C4–605R Variant F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by reports of 

cracked fuel pump canister hoods located in 

fuel tanks. We are issuing this AD to prevent 

any detached canister hood fragments/debris 

from being ingested into the fuel feed system, 

and becoming a potential source of ignition 

with consequent fire or explosion. 

(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) Initial Inspection and Replacement 

Within 30 months after the effective date 

of this AD, do a detailed inspection for 

cracking of the fuel pump canister hood 

halves installed on all fuel pump canisters 

having part numbers (P/N) 2052C11, 

2052C12, and C93R51–601, in accordance 

with the Accomplishment Instructions of the 

service bulletin specified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD, as applicable. If 

any crack is found on any fuel pump canister 

hood half during any inspection, before 

further flight, replace the fuel pump canister 

hood half, in accordance with the 

Accomplishment Instructions of the service 

bulletin specified in paragraph (g)(1), (g)(2), 

or (g)(3) of this AD, as applicable. 

(1) For Model A300 series airplanes: 

Airbus Mandatory Service Bulletin A300–28– 

0089, Revision 01, including Inspection 

Findings—Reporting Sheet, dated April 15, 

2011. 

(2) For Model A300–600 series airplanes: 

Airbus Mandatory Service Bulletin A300–28– 

6106, Revision 01, including Inspection 

Findings—Reporting Sheet, dated April 15, 

2011. 

(3) For Model A310 series airplanes: 

Airbus Mandatory Service Bulletin A310–28– 

2173, Revision 01, including Inspection 

Findings—Reporting Sheet, dated April 15, 

2011. 

(h) Repetitive Inspections 

Within 30 months after accomplishing the 

actions specified in paragraph (g) of this AD, 

and thereafter at intervals not to exceed 30 

months, repeat the detailed inspection 

specified in paragraph (g) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this 

AD, if those actions were performed 

before the effective date of this AD using 

the Airbus Mandatory Service Bulletins 

specified in paragraph (i)(1), (i)(2), or 

(i)(3) of this AD, which are not 

incorporated by reference in this AD. 

(1) Airbus Mandatory Service Bulletin 

A300–28–0089, dated January 13, 2011. 

(2) Airbus Mandatory Service Bulletin 

A300–28–6106, dated January 13, 2011. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2173, dated January 13, 2011. 

(j) Reporting to Airbus 

Submit reports of the findings (both 

positive and negative) of the inspections 

required by paragraphs (g) and (h) of 

this AD to Airbus at the applicable time 

specified in paragraph (j)(1) or (j)(2) of 

this AD, using the form ‘‘Inspection 

Findings—Reporting Sheet’’ provided in 

the service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this 

AD, as applicable. Submit information 

to Airbus, SDC32 Technical Data and 

Documentation Services, fax (+33) 5 61 

93 28 06, email 

sb.reporting@airbus.com, or via the 

operator’s Resident Customer Support 

Office. 

(1) If the inspection was done on or 

after the effective date of this AD: 

Submit the report within 90 days after 

the inspection. 

(2) If the inspection was done before 

the effective date of this AD: Submit the 

report within 90 days after the effective 

date of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply 

to this AD: 

(1) Alternative Methods of 

Compliance (AMOCs): The Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, 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; 


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64704 Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 

telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed 

to: 9-ANM-116-AMOCREQUESTS@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. 

(3) Reporting Requirements: 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. 

(l) Related Information 

Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 

2011–0124, dated June 30, 2011; and the 

Airbus mandatory service bulletins 

identified in paragraphs (l)(1), (l)(2), and 

(l)(3) of this AD; for related information. 

(1) Airbus Mandatory Service Bulletin 

A300–28–0089, Revision 01, including 

Inspection Findings—Reporting Sheet, 

dated April 15, 2011. 

(2) Airbus Mandatory Service Bulletin 

A300–28–6106, Revision 01, including 

Inspection Findings—Reporting Sheet, 

dated April 15, 2011. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2173, Revision 01, including 

Inspection Findings—Reporting Sheet, 

dated April 15, 2011. 

(m) Material Incorporated by Reference 

(1) 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. 

(2) You must use the following service 

information to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(i) Airbus Mandatory Service Bulletin 

A300–28–0089, Revision 01, including 

Inspection Findings—Reporting Sheet, 

dated April 15, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A300–28–6106, Revision 01, including 

Inspection Findings—Reporting Sheet, 

dated April 15, 2011. 

(iii) Airbus Mandatory Service 

Bulletin A310–28–2173, Revision 01, 

including Inspection Findings— 

Reporting Sheet, dated April 15, 2011. 

(3) For Airbus 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.airworth-eas@airbus.com; 

Internet http://www.airbus.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/cfr/ 

ibr-locations.html. 

Issued in Renton, Washington, on October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25675 Filed 10–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0619; Directorate 

Identifier 2007–NM–356–AD; Amendment 

39–17219; AD 2012–21–03] 

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 all The 

Boeing Company Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–200F, 747–300, 747SR, and 

747SP series airplanes. This AD was 

prompted by reports of two in-service 

occurrences on Model 737–400 

airplanes of total loss of boost pump 

pressure of the fuel feed system, 

followed by loss of fuel system suction 

feed capability on one engine, and inflight shutdown of the engine. This AD 

requires repetitive operational tests, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

loss of the engine fuel suction feed 

capability of the fuel system, which, in 

the event of total loss of the fuel boost 

pumps, could result in dual engine 

flameout, inability to restart the engines, 

and consequent forced landing of the 

airplane. 

DATES: This AD is effective November 

27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 27, 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, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; 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 


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