Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Proposed Rules 48469 

amount specified in § 3.91(b)(3)(ii) of 

this title for all violations occurring 

during a single investigation. FNS shall 

determine the amount of the civil 

money penalty as follows: 

(1) Determine the firm’s average 

monthly redemptions for the 12-month 

period ending with the month 

immediately preceding the month 

during which the firm was charged with 

violations; 

(2) Multiply the average monthly 

redemption figure by 10 percent; 

(3) Multiply the product by 120, in 

accordance with § 278.6(f), to reflect 

double the penalty for a ten year 

disqualification; 

(4) If a second trafficking offense is 

committed by the firm, the firm shall 

not be eligible for a civil money penalty 

in lieu of permanent disqualification. 

* * * * * 

(l) Fines for acceptance of benefits 

without an EBT Card being present. FNS 

may impose a fine against any retail 

food store or wholesale food concern 

that accepts benefits that are not 

accompanied by an EBT card being 

present and with the intent of 

conducting a transaction without a 

recipient’s knowledge or consent. The 

fine to be assessed against a firm found 

to be accepting benefits without an EBT 

card being present shall be $1,000 per 

investigation plus an amount equal to 

double the value of each transaction that 

occurred without an EBT card being 

present, and may be assessed in 

addition to any fiscal claim or civil 

penalty established by FNS under 

§ 278.6(e)(1) through (e)(6), § 278.6(g), or 

§ 278.6(j). The fine shall be paid in full 

within 30 days of receipt of FNS’ 

notification to pay the fine. The 

Attorney General of the United States 

may institute judicial action in any 

court of competent jurisdiction against 

the store or concern to collect the fine. 

FNS may withdraw the authorization of 

the store, as well as other authorized 

locations of a multi-unit firm which are 

under the same ownership, for failure to 

pay such a fine as specified under 

§ 278.6(l). 

7. In § 278.7, remove paragraphs (d) 

through (g); 

8. Remove § 278.8 and redesignate 

§ 278.9 as § 278.8; 

9. In the newly redesignated § 278.8, 

remove paragraph (a) and redesignate 

paragraphs (b) through (m) as (a) 

through (l), respectively; 

10. Remove § 278.10. 

PART 279—ADMINISTRATIVE AND 

JUDICIAL REVIEW—FOOD RETAILERS 

AND FOOD WHOLESALERS 

11. In § 279.1: 

a. Paragraph (a)(2), remove the 

reference to ‘‘§ 278.6(e)(8)’’ and add in 

its place the reference ‘‘§ 278.6(e)(9)’’; 

b. Revise paragraph (a)(4) to read as 

follows: 

§ 279.1 Jurisdiction and authority. 

* * * * * 

(a) * * * 

(4) Denial of all or part of any claim 

asserted by a firm against FNS under 

§ 278.7(c) of this chapter; 

* * * * * 

12. In § 279.2, revise paragraph (a) to 

read as follows: 

§ 279.2 Manner of filing requests for 

review. 

(a) Submitting requests for review. 

Requests for review submitted by firms 

shall be mailed to or filed with the 

Branch Chief, Administrative Review 

Branch, U.S. Department of Agriculture, 

Food and Nutrition Service, 3101 Park 

Center Drive, Alexandria, Virginia 

22302. 

* * * * * 

13. In § 279.6, revise paragraph (a) to 

read as follows: 

§ 279.6 Legal advice and extensions of 

time. 

(a) Advice from the Office of the 

General Counsel. If any request for 

review involves any doubtful questions 

of law, FNS shall obtain the advice of 

the Department’s Office of the General 

Counsel. 

* * * * * 

14. In § 279.7, remove the reference to 

‘‘§ 278.6(e)(8)’’ and add in its place the 

reference ‘‘§ 278.6(e)(9)’’ 

Dated: July 10, 2012. 

Kevin W. Concannon, 

Under Secretary, Food, Nutrition, and 

Consumer Services. 

[FR Doc. 2012–19773 Filed 8–13–12; 8:45 am] 

BILLING CODE 3410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0808; Directorate 

Identifier 2010–NM–170–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Model A330–200 and A330–300 series 

airplanes, and Model A340–200 and 

A340–300 series airplanes. This 

proposed AD was prompted by reports 

of an elevator blocked in the down 

position due to two independent 

failures; first, the inability of a servo 

control to switch to active mode because 

it was not detected by a flight control 

computer, and second, an internal 

hydraulic leak due to the deterioration 

of an O-ring seal on a solenoid. This 

proposed AD would require, depending 

on airplane configuration, modifying 

three flight control primary computers 

(FCPCs); modifying two flight control 

secondary computers (FCSCs); revising 

the airplane flight manual (AFM) to 

include certain information; replacing 

certain O-rings; and checking part 

number, and replacing certain O-ring 

seals if needed. We are proposing this 

AD to detect and correct O-rings with 

incorrect part number whose 

deterioration could lead to improper 

sealing of solenoid valves, and to correct 

FCPC and FCSC software to allow better 

control of elevator positioning; both 

conditions, if not corrected, could lead 

to the loss of elevator control on takeoff, 

and potentially reduce the 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 28, 

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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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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; phone: (425) 

227–1138; fax: (425) 227–1149; email: 

Vladimir.Ulyanov@faa.gov. 

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–2012–0808; Directorate Identifier 

2010–NM–170–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0081, 

dated April 27, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

This [EASA] AD deals with the two 

following points: 

• Case of an elevator blocked in down 

position due to two independent failures one 

of which is hidden: 

Each elevator is controlled by two servo 

controls. In normal operation: 

—One servo control in active mode 

controlled by PRIM 1 (Green servo control), 

—One servo control in damping mode 

(Yellow or Blue servo control) monitored 

by PRIM 2. 

Change from active mode to damped mode 

is obtained by means of a mode selector 

which is controlled by two identical solenoid 

valves housed on the servo control. The 

sealing of each solenoid valve is ensured by 

four O-ring seals. 

During pre-flight control checks, the flight 

crew of an A330–200 aeroplane observed that 

one of the elevators was blocked in down 

position, the ECAM screen displaying ‘‘F/ 

CTL PRIM 1 PITCH FAULT’’. 

This condition was due to two 

independent failures, one of which was 

dormant, which occurred on one of the 

elevators. 

Investigations revealed that the origin of 

the elevator malfunction was due to the 

inability of the Yellow servo control to 

switch to active mode. 

This inability: 

—Was caused by an internal hydraulic leak 

due to the deterioration of an O-ring seal 

on a solenoid valve, 

—Was not detected by the PRIM 2 computer 

nor announced to the flight crew. 

• Incorrect Part Number (P/N) for solenoid 

valve O-ring seals in IPC [illustrated parts 

catalog]: 

An incorrect O-ring seal P/N in IPC 27–34– 

51–1 could have led to the installation of Oring seals incompatible with the hydraulic 

fluid, causing them to deteriorate. 

These conditions if not detected could lead 

to the loss of elevator [control] on takeoff 

and, potentially reduce the controllability of 

the aeroplane. 

The aim of EASA AD 2007–0009 was to: 

—Take over the requirements of AD F–2004– 

158, and 

—Require the terminating action for § (1), (2) 

and (4) of this AD by introducing new 

capped seals on solenoid valves for A330– 

200 only. 

This new [EASA] AD * * * requires the 

embodiment of the latest software standard 

on the three Flight Control Primary 

Computers (FCPC) and on the two Flight 

Control Secondary Computers (FCSC) [by 

modifying the FCPCs and FCSCs] * * *. 

The modification is accomplished 

either by replacing the FCPCs and 

FCSCs with new FCPCs and FCSCs, or 

by replacing or reprogramming the onboard replaceable modules in the FCPCs 

and FCSCs. Required actions also 

include, depending on airplane 

configuration, the following actions: 

revising the airplane flight manual 

(AFM) to include certain information; 

replacing certain O-rings; and checking 

part number, and replacing certain Oring seals if needed. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information: 

• Airbus All Operators Telex (AOT) 

A330–27A3129, Revision 01, dated July 

16, 2004. 

• Airbus Mandatory Service Bulletin 

A330–27–3136, Revision 01, dated July 

19, 2006. 

• Airbus Mandatory Service Bulletin 

A330–27–3146, Revision 01, dated 

September 3, 2008. 

• Airbus Mandatory Service Bulletin 

A330–27–3148, Revision 01, including 

Appendix 1, dated October 9, 2008. 

• Airbus Mandatory Service Bulletin 

A330–27A3131, Revision 01, including 

Appendix 01, dated March 3, 2005. 

• Airbus Mandatory Service Bulletin 

A340–27–4144, including Appendix 1, 

dated October 19, 2009. 

• Airbus Mandatory Service Bulletin 

A340–27–4146, dated June 1, 2007. 

• Airbus Mandatory Service Bulletin 

A340–27–4148, including Appendix 1, 

dated June 13, 2008. 

• Airbus Mandatory Service Bulletin 

A340–27A4130, Revision 01, including 

Appendix 01, dated March 3, 2005. 

• Airbus Service Bulletin A330–27– 

3134, Revision 01, dated May 12, 2006. 

• Airbus Service Bulletin A330–27– 

3144, Revision 01, including Appendix 

1, dated July 16, 2009. 

• Airbus Service Bulletin A330–27– 

3145, dated December 16, 2008. 

• Airbus Service Bulletin A340–27– 

4145, dated December 16, 2008. 

• Airbus Temporary Revision TR4, 

Issue 1.0, ‘‘TR 4.02.00/25 Issue 2— 

Undetected Elevator Control Loss in 

Case of Dual Failure,’’ dated November 

26, 2009, to the Airbus A330/A340 

Airplane Flight Manual. 

• Airbus Temporary Revision TR22, 

Issue 1.0, ‘‘TR 4.02.00/40 Issue 2— 

Undetected Elevator Control Loss in 

Case of Dual Failure,’’ dated November 

26, 2009, to the Airbus A330/A340 

Airplane Flight Manual. 

The actions 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Proposed Rules 48471 

Differences Between This AD and the 

MCAI or Service Information 

EASA AD 2010–0081, dated April 27, 

2010, contains additional requirements 

to modify the four elevator servo 

controls installed on Model A330–200 

series airplanes, as specified in Airbus 

Service Bulletin A330–27–3134. This 

AD does not contain those requirements 

because those actions are already 

mandated by FAA AD 2008–06–07, 

Amendment 39–15419 (73 FR 13103, 

March 12, 2008; as corrected on April 

15, 2008 (73 FR 20367), and must be 

accomplished within 17 months after 

April 16, 2008 (the effective date of AD 

2008–06–07, Amendment 39–15419). 

EASA AD 2010–0081, dated April 27, 

2010, also contains additional 

requirements to amend the airplane 

flight manual to include the operational 

procedure specified in paragraph (n) of 

this proposed AD. This proposed AD 

does not include that requirement, 

because that information is already 

contained in the U.S. operators’ AFMs. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 41 products of U.S. registry. 

We also estimate that it would take 

about 5 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 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 costs. 

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 the proposed AD on U.S. 

operators to be $17,425, or $425 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 that 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 adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0808; 

Directorate Identifier 2010–NM–170–AD. 

(a) Comments Due Date 

We must receive comments by September 

28, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, specified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes, all 

manufacturer serial numbers (MSN). 

(2) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes, all MSN. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by reports of an 

elevator blocked in the down position due to 

two independent failures; first, the inability 

of a servo control to switch to active mode 

because it was not detected by a flight control 

computer, and second, an internal hydraulic 

leak due to the deterioration of an O-ring seal 

on a solenoid. We are issuing this detect and 

correct O-rings with incorrect part number 

whose deterioration could lead to improper 

sealing of solenoid valves, and to correct 

FCPC and FCSC software to allow better 

control of elevator positioning; both 

conditions, if not corrected, could lead to the 

loss of elevator control on takeoff, and 

potentially reduce the 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) Replace O-ring Seals For Elevator Servo 

Controls Installed in Damping Position on 

Model A330–200 Series Airplanes Only 

For all Airbus Model A330–200 series 

airplanes, except those on which Airbus 

modifications 53969 and 54833 have been 

embodied in production: At the later of the 

times specified in paragraphs (g)(1) and (g)(2) 

of this AD, replace the O-ring seals installed 

on the two solenoid valves of each servo 

control using new O-ring seals, in accordance 

with Airbus All Operators Telex (AOT) 

A330–27A3129, Revision 01, dated July 16, 

2004. 

(1) Before the accumulation of 3,000 flight 

cycles by the servo control since first 

installation on an airplane, or 3,000 flight 

cycles since the installation of the solenoid 

valve on the servo control. 

(2) Within 700 flight hours after the 

effective date of this AD. 

(h) Replace O-ring Seals on Spare Elevator 

Servo Controls Whose O-ring Seals Were Not 

Replaced as Required by Paragraph (g) of 

This AD 

For all Airbus Model A330–200 series 

airplanes, except those on which Airbus 

modifications 53969 and 54833 have been 

embodied in production: As of the effective 

date of this AD, before the installation of an 

elevator servo control on an Airbus Model 

A330–200 airplane, replace the O-ring seals 

installed on the two spare servo control 

solenoid valves using new O-ring seals, in 

accordance with Airbus AOT A330– 

27A3129, Revision 01, dated July 16, 2004. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
48472 Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Proposed Rules 

(i) Replace O-ring Seals with Part Number 

(P/N) MS28775–XXX or a Part Number That 

Cannot Be Identified 

For Model A330–200 series airplanes 

which have been modified as specified in 

Airbus AOT A330–27A3129, dated June 24, 

2004, but which have not been modified as 

specified in Airbus AOT A330–27A3129, 

Revision 01, dated July 16, 2004; except 

those airplanes on which Airbus 

modifications 53969 and 54833 have been 

embodied in production: Within 15 days 

after the effective date of this AD, check the 

(P/N) of the seals installed on the solenoid 

valve of the servo control of the elevator in 

the damping position. If the seals installed 

have P/N MS28775–XXX or a part number 

that cannot be identified, before further 

flight, replace the seals with new seals using 

a part number listed in paragraph (i)(1), (i)(2), 

or (i)(3) of this AD, in accordance with 

Airbus AOT A330–27A3129, Revision 01, 

dated July 16, 2004. 

(1) IPC 27–34–51–1 item 130: NAS1611– 

011 or NAS1611–011A; 

(2) IPC 27–34–51–1 item 140: NAS1611– 

012 or NAS1611–012A; or 

(3) IPC 27–34–51–1 item 150: NAS1611– 

013 or NAS1611–013A. 

(j) Replace O-ring Seals on Model A330–200, 

A330–300, A340–200, and A340–300 Series 

Airplanes 

For Model A330–200, A330–300, A340– 

200, and A340–300 series airplanes equipped 

with elevator servo controls P/N SC4800–2/ 

–4/–7/–8 or SC4800–7/–8 modified into P/N 

SC4800–7A/–9, as specified in Airbus 

Service Bulletin A340–27–4083 or Airbus 

Service Bulletin A330–27–3076: Within 

1,400 flight hours after the effective date of 

this AD, replace the O-ring seals installed on 

the two solenoid valves of each elevator 

servo control in damping position (except for 

Model A330–200 series airplanes which have 

to comply with paragraph (g) of this AD), and 

in active position, using a new O-ring seal P/ 

N NAS1611–XXX or P/N NAS1611–XXXA, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27A3131, Revision 01, 

excluding Appendix 01, dated March 3, 2005 

(for Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–27A4130, 

Revision 01, excluding Appendix 01, dated 

March 3, 2005 (for Model A340 series 

airplanes). 

(k) Replace O-ring Seals on Spare Elevator 

Servo Controls on Model A330–200, A330– 

300, A340–200, and A340–300 Series 

Airplanes 

For the spare elevator servo controls P/N 

SC4800–2/–4/–7/–8 or SC4800–7/–8 

modified into P/N SC4800–7A/–9, as 

specified in Airbus Service Bulletin A340– 

27–4083 or Airbus Service Bulletin A330– 

27–3076: Before the installation of a spare 

elevator servo control on an airplane, replace 

the O-ring seals installed on the two spare 

servo control solenoid valves using a new Oring seal P/N NAS1611–XXX or P/N 

NAS1611–XXXA, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27A3131, 

Revision 01, excluding Appendix 01, dated 

March 3, 2005 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–27A4130, Revision 01, 

excluding Appendix 01, dated March 3, 2005 

(for Model A340 series airplanes). 

(l) Modify the Flight Control Primary 

Computers (FCPCs) 

For all Airbus Model A330–200 and A330– 

300 series airplanes, except those on which 

both Airbus modifications 53468 and 55697 

have been embodied in production; and for 

all Airbus Model A340–200 and A340–300 

series airplanes, except those on which both 

modifications 55879 and 55697 have been 

embodied in production: Within 24 months 

after the effective date of this AD, modify the 

three FCPCs in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (l)(1) or (l)(2) of this AD. 

(1) Airbus Service Bulletin A330–27–3144, 

Revision 01, excluding Appendix 1, dated 

July 16, 2009; or Airbus Mandatory Service 

Bulletin A330–27–3148, Revision 01, 

excluding Appendix 1, dated October 9, 2008 

(for Model A330 series airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–27–4144, excluding Appendix 1, dated 

October 19, 2009; or Airbus Mandatory 

Service Bulletin A340–27–4148, excluding 

Appendix 1, dated June 13, 2008 (for Model 

A340 series airplanes). 

(m) Modify the Flight Control Secondary 

Computers (FCSCs) 

For all Airbus Model A330–200 and A330– 

300 series airplanes, except those on which 

both Airbus modifications 53468 and 55697 

have been embodied in production, and for 

all Airbus Model A340–200 and A340–300 

series airplanes, except those on which both 

modifications 55879 and 55697 have been 

embodied in production: Within 24 months 

after the effective date of this AD, modify 

both FCSCs, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (m)(1) or (m)(2) of this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–27–3146, Revision 01, dated 

September 3, 2008; or Airbus Service 

Bulletin A330–27–3145, dated December 16, 

2008 (for Model A330 airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–27–4146, June 1, 2007; or Airbus 

Service Bulletin A340–27–4145, dated 

December 16, 2008 (for Model A340 

airplanes). 

(n) Revise the Airplane Flight Manual 

Before further flight, after doing the 

applicable actions required by both 

paragraphs (l) and (m) of this AD, remove the 

following procedure from the airplane flight 

manual, if inserted, in accordance with the 

instructions contained in Airbus Temporary 

Revision TR4, Issue 1.0, ‘‘TR 4.02.00/25 Issue 

2—Undetected Elevator Control Loss in Case 

of Dual Failure,’’ dated November 26, 2009, 

to the Airbus A330/A340 Airplane Flight 

Manual; and Airbus Temporary Revision 

TR22, Issue 1.0, ‘‘TR 4.02.00/40 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

Undetected Elevator Control Loss in Case of 

Dual Failure 

On ground, before takeoff until takeoff 

power thrust setting, apply the following 

procedure. 

• In the case of a F/CTL PRIM 1 FAULT, 

or F/CTL PRIM 1 PITCH FAULT: Turn off 

PRIM 1, then back on to perform a FCPC 

PRIM 1 reset. 

• If successful: Perform the normal preflight Flight Control check. 

• If unsuccessful: Return to the gate and 

require appropriate maintenance actions. 

• In the case of a F/CTL ELEV SERVO 

FAULT: Return to the gate and require 

appropriate maintenance actions. 

(o) Credit for Previous Actions 

This paragraph provides credit for certain 

actions described in the following 

paragraphs. 

(1) This paragraph provides credit for 

replacements of the O-ring seals, as required 

by paragraphs (j) and (k) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A330–27A3131, dated September 22, 2004 

(for Model A330 airplanes); or Airbus Service 

Bulletin 340–27A4130, dated September 22, 

2004 (for Model A340 airplanes). 

(2) This paragraph provides credit for 

modifications of the FCPC, as required by 

paragraph (l) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A330–27–3144, 

dated April 2, 2009 (for Model A330 

airplanes); or Airbus Service Bulletin A340– 

27–3148, dated July 17, 2008 (for Model 

A340 airplanes). 

(3) This paragraph provides credit for 

modifications of the FCSCs, as required by 

paragraph (m) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Mandatory Service 

Bulletin A330–27–3146, dated June 1, 2007 

(for Model A330 airplanes). 

(p) Terminating Action 

Installation of modified servo-controls at 

all positions on Model A330–200 airplanes in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

27–3134, Revision 01, dated May 12, 2006; 

and Airbus Mandatory Service Bulletin 

A330–27–3136, Revision 01, dated July 19, 

2006; terminates the actions required by 

paragraphs (g), (h), and (i) and of this AD. 

(q) 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– 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Proposed Rules 48473 

3356; telephone (425) 227–1138; fax (425) 

227–1149. 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. 

(r) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0081, dated April 27, 2010, 

and the service information specified in 

paragraphs (r)(1)(i) through (r)(1)(xv) of this 

AD, for related information. 

(i) Airbus AOT A330–27A3129, Revision 

01, dated July 16, 2004. 

(ii) Airbus Mandatory Service Bulletin 

A330–27–3136, Revision 01, dated July 19, 

2006. 

(iii) Airbus Mandatory Service Bulletin 

A330–27–3146, Revision 01, dated 

September 3, 2008. 

(iv) Airbus Mandatory Service Bulletin 

A330–27–3148, Revision 01, excluding 

Appendix 1, dated October 9, 2008. 

(v) Airbus Mandatory Service Bulletin 

A330–27A3131, Revision 01, excluding 

Appendix 01, dated March 3, 2005. 

(vi) Airbus Mandatory Service Bulletin 

A340–27–4144, excluding Appendix 1, dated 

October 19, 2009. 

(vii) Airbus Mandatory Service Bulletin 

A340–27–4146, dated June 1, 2007. 

(viii) Airbus Mandatory Service Bulletin 

A340–27–4148, excluding Appendix 1, dated 

June 13, 2008. 

(ix) Airbus Mandatory Service Bulletin 

A340–27A4130, Revision 01, excluding 

Appendix 01, dated March 3, 2005. 

(x) Airbus Service Bulletin A330–27–3134, 

Revision 01, dated May 12, 2006. 

(xi) Airbus Service Bulletin A330–27– 

3144, Revision 01, excluding Appendix 1, 

dated July 16, 2009. 

(xii) Airbus Service Bulletin A330–27– 

3145, dated December 16, 2008. 

(xiii) Airbus Service Bulletin A340–27– 

4145, dated December 16, 2008. 

(xiv) Airbus Temporary Revision TR4, 

Issue 1.0, ‘‘TR 4.02.00/25 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(xv) Airbus Temporary Revision TR22, 

Issue 1.0, ‘‘TR 4.02.00/40 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(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 August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–19887 Filed 8–13–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0143; Directorate 

Identifier 2011–NM–077–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. 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 all Fokker Services B.V. Model F.28 

Mark 0070 and 0100 airplanes. That 

NPRM proposed to supersede an 

existing AD that requires revising the 

airworthiness limitations section (ALS) 

of the instructions for continued 

airworthiness for certain airplanes, and 

the FAA-approved maintenance 

program for certain other airplanes, to 

incorporate new limitations. That 

NPRM was prompted by Fokker 

Services B.V. issuing a Fokker 70/100 

maintenance review board (MRB) 

document with revised limitations, 

tasks, thresholds, and intervals. This 

action revises that NPRM by revising the 

maintenance program to incorporate the 

limitations, tasks, thresholds, and 

intervals specified in certain revised 

Fokker MRB documents. We are 

proposing this AD to reduce the 

potential of structural failures or of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. Since these actions impose an 

additional burden over that proposed in 

the 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 proposed AD by September 28, 

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 Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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–2012–0143; Directorate Identifier 

2011–NM–077–AD’’ at the beginning of 


tkelley on DSK3SPTVN1PROD with PROPOSALS