Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 37829 

Issued in Renton, Washington, on June 18, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15451 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0671; Directorate 

Identifier 2011–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A330–243, –341, –342 and –343 

airplanes. The existing AD currently 

requires modifying certain cowl 

assemblies of the left- and right-hand 

thrust reversers. Since we issued that 

AD, the manufacturer has issued new 

life limits on certain thrust reverser Cduct assemblies. This proposed AD 

would require removing certain C-duct 

assemblies of the left- and right-hand 

thrust reversers from service at certain 

designated life limits, and would also 

add airplanes to the applicability. We 

are proposing this AD to prevent fatigue 

cracking of the hinges integrated into 

the 12 o’clock beam of the thrust 

reversers, which could result in 

separation of a thrust reverser from the 

airplane, and consequent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 9, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, 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. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0671; Directorate Identifier 

2011–NM–096–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 2, 2005, we issued AD 

2005–25–21, Amendment 39–14414 (70 

FR 73919, December 14, 2005). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A330–243, –341, –342, and –343 

airplanes equipped with Rolls-Royce 

RB211 TRENT 700 engines. 

Since we issued AD 2005–25–21, 

Amendment 39–14414 (70 FR 73919, 

December 14, 2005), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2011–0018, dated February 3, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI has 

added Model A330–243F airplanes to 

the applicability. The MCAI states: 

The life limits of the thrust reversers Cducts are not addressed by the definition of 

the structural life limits of Safe Life items as 

defined in the A330 Airworthiness 

Limitations Section—ALS Part 1. As a result, 

these life limits are covered by an 

Airworthiness Directive (AD). 

These life limits are due to unexpected 

high fatigue loads (measured during 

certification tests) on the hinges integrated 

into the 12 o’clock beam, which forms the 

upper extreme edge of the thrust reverser CDuct of Rolls Royce Trent 700 engines. 

The aim of the [Direction Ge ́ne ́rale de 

l’Aviation Civile] (DGAC) France AD F– 

2001–528 was to mandate the life limits, 

depending of the modifications applied to 

the C-duct. 

Revision 1 of the DGAC France AD F– 

2001–528 deferred the accomplishment 

threshold of the modification to be applied 

in-service from 6,000 flight cycles (FC) to 

6,500 FC. 

Revision 2 of DGAC France AD F–2001– 

528 [which corresponds to FAA AD 2005– 

25–21, Amendment 39–14414 (70 FR 73919, 

December 14, 2005)] was issued to update 

again the accomplishment threshold from 

6,500 FC to 7,200 FC. 

This [EASA] AD retains the requirements 

of DGAC France AD F–2001–528 R2, which 

is superseded, and adds [certain] life limits. 

The action required in this proposed AD 

is removing certain C-duct assemblies of 

the left- and right-hand thrust reversers 

from service at certain designated life 

limits. This proposed AD also adds 

Model A330–243F airplanes to the 

applicability and revises the 

applicability to include all airplanes of 

the affected models. The unsafe 

condition is fatigue cracking of the 

hinges integrated into the 12 o’clock 

beam of the thrust reversers, which 

could result in separation of a thrust 

reverser from the airplane, and 

consequent reduced controllability of 

the airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–78–3010, Revision 03, 

dated April 28, 2004. The actions 


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37830 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 17 products of U.S. registry. 

We estimate that it would take up to 48 

work-hours per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$69,360, or $4,080 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2005–25–21, Amendment 39–14414 (70 

FR 73919, December 14, 2005), and 

adding the following new AD: 

Airbus: Docket No. FAA–2012–0671; 

Directorate Identifier 2011–NM–096–AD. 

(a) Comments Due Date 

We must receive comments by August 9, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2005–25–21, 

Amendment 39–14414 (70 FR 73919, 

December 14, 2005). 

(c) Applicability 

This AD applies to all Airbus Model A330– 

243, –243F, –341, –342 and –343 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Reason 

This AD was prompted by new life limits 

on certain thrust reverser C-duct assemblies. 

We are issuing this AD to prevent fatigue 

cracking of the hinges integrated into the 12 

o’clock beam of the thrust reversers, which 

could result in separation of a thrust reverser 

from the airplane, and consequent reduced 

controllability of the airplane. 

(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) C-Duct Assembly Removal 

At the applicable compliance time 

specified in table 1 of this AD: Remove the 

applicable C-duct assemblies of the left- and 

right-hand thrust reversers, in accordance 

with a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). Thereafter, for any Cduct assembly of the left- and right-hand 

thrust reversers installed after the effective 

date of this AD, before the accumulation of 

the applicable total flight cycles specified in 

table 1 of this AD: Remove the C-duct 

assembly, in accordance with a method 

approved by either the Manager, 

International Branch, ANM 116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent). 

TABLE 1—PART REMOVAL THRESHOLDS

Part No.— Compliance times at the later of the times specified— 

HDTR3410L, HDTR3410R, HDTR3411L, HDTR3411R, 

HDTR3412R, HDTR3413R.

Before the accumulation of 10,000 total flight cycles 

since the first installation of C-duct on the airplane.

Within 3 months after the 

effective date of this AD. 

HDTR3414L, HDTR3416R, HDTR3417R that have been 

modified in service as specified in Airbus Mandatory 

Service Bulletin A330-78-3010, or Rolls-Royce Service 

Bulletin RB.211–78–C899, at 7,200 total flight cycles 

or more since first installation on an airplane.

Before the accumulation of 10,000 total flight cycles 

since the first installation of C-duct on the airplane.

Within 3 months after the 

effective date of this AD. 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 37831 

TABLE 1—PART REMOVAL THRESHOLDS—Continued 

HDTR3414L, HDTR3416R, HDTR3417R that have been 

modified in production by Airbus Modification 47316; 

or modified in service as specified in Airbus Mandatory Service Bulletin A330-78-3010, or Rolls-Royce 

Service Bulletin RB.211–78–C899, before the accumulation of 7,200 total flight cycles since first installation on an airplane.

Before the accumulation of 25,000 total flight cycles 

since the first installation of C-duct on the airplane.

Within 3 months after the 

effective date of this AD. 

HDTR3412L, HDTR3416L, HDTR3417L, HDTR3414R, 

HDTR3419R, HDTR3420R.

Before the accumulation of 25,000 total flight cycles 

since the first installation of C-duct on the airplane.

Within 3 months after the 

effective date of this AD. 

HDTR3413L, HDTR3415R, HDTR3415L, HDTR3418R .. Before the accumulation of 40,000 total flight cycles 

since the C-duct was new.

Within 3 months after the 

effective date of this AD. 

(h) 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: 

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. 

(i) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0018, dated February 3, 2011; 

and Airbus Mandatory Service Bulletin 

A330–78–3010, Revision 03, dated April 28, 

2004; for related information. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.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. 

Issued in Renton, Washington, on June 14, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15461 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0617; Directorate 

Identifier 2007–NM–354–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. That NPRM 

proposed to require repetitive 

operational tests of the engine fuel 

suction feed of the fuel system, and 

other related testing if necessary. That 

NPRM was prompted by a report of an 

in-service occurrence 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 in-flight shutdown of the engine. 

This action revises that NPRM by 

proposing to require repetitive 

operational tests, and other related 

testing and corrective action if 

necessary. We are proposing this 

supplemental NPRM 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. 

Since these actions impose an 

additional burden over that proposed in 

the previous NPRM, we are reopening 

the comment period to allow the public 

the chance to comment on these 

proposed changes. 

DATES: We must receive comments on 

this supplemental NPRM by August 9, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this proposed 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 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 


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