This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

73340 

Vol. 77, No. 237 

Monday, December 10, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0150; Directorate 

Identifier 2011–NM–234–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 Airbus Model A318, A319, A320, 

and A321 series airplanes. That 

supplemental notice of proposed 

rulemaking (SNPRM) proposed an 

inspection to determine if certain angle 

of attack (AOA) probes are installed, 

and replacement of any affected AOA 

probe. That SNPRM was prompted by 

reports of oil residue between the stator 

and the rotor parts of the position 

resolvers of the AOA vane, which was 

a result of incorrect removal of the 

machining oil during the manufacturing 

process of the AOA resolvers. This 

action revises that SNPRM by clarifying 

the affected parts. We are proposing this 

AD to prevent erroneous AOA 

information and consequent delayed or 

non-activation of the AOA protection 

systems which, during flight at a high 

angle of attack, could result in reduced 

control of the airplane. Since these 

actions impose an additional burden 

over that proposed in the SNPRM, 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 January 4, 2013. 

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, 

Airworthiness Office—EAS, 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. For 

Thales Avionics service information 

identified in this proposed AD, contact 

Thales Avionics, Retrofit Manager, 105, 

Avenue du Ge ́ne ́ral Eisenhower, BP 

63647, 31036 Toulouse Cedex 1, France; 

telephone +33 5 61 19 76 95; fax +33 5 

61 19 68 20; email 

retrofit.ata@fr.thalesgroup.com; Internet 

http://www.thalesgroup.com/aerospace. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; 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–2012–0150; Directorate Identifier 

2011–NM–234–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 

We proposed to amend 14 CFR part 

39 with an earlier SNPRM for the 

specified products, which was 

published in the Federal Register on 

July 11, 2012 (77 FR 40823). That earlier 

SNPRM proposed to require actions 

intended to address the unsafe 

condition for all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

Since that SNPRM (77 FR 40823, July 

11, 2012) was issued, we received 

further information from Airbus 

clarifying the affected parts subject to 

the unsafe condition. 

Comments 

We gave the public the opportunity to 

comment on the previous SNPRM (77 

FR 40823, July 11, 2012). The following 

presents the comments received on the 

previous SNPRM and the FAA’s 

response to each comment. 

Request To Include Other Service 

Information 

Airbus requested that we revise 

paragraph (g)(2) of the previous SNPRM 

(77 FR 40823, dated July 11, 2012) to 

include other service information that 

clarifies the affected parts. Airbus stated 

that paragraph (g)(2) of the previous 

SNPRM should read, ‘‘If any probe is 

found having P/N C16291AB, on which 

* * * or AIRBUS Service Bulletin 34– 

1444 [sic] Revision 00 dated October 07, 

2009, has been incorporated * * * ’’ 

We agree with Airbus’s request. We 

have revised paragraph (g)(2) of this 

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Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Proposed Rules 73341 

SNPRM to include replacement of an 

AOA probe, P/N C16291AB, on which 

Thales Avionics Service Bulletin 

C16291A–34–009, dated September 10, 

2009; or Airbus Service Bulletin A320– 

34–1444, dated October 7, 2009; has 

been accomplished. We have removed 

the reference to Thales Avionics Service 

Bulletin C16291A–34–007, Revision 01, 

dated December 3, 2009, from paragraph 

(g)(2) and (i)(2) of this SNPRM. 

We have also revised paragraphs (g)(1) 

and (i)(2) of this SNPRM to prevent 

replacement with an AOA probe on 

which Thales Avionics Service Bulletin 

C16291A–34–009, dated September 10, 

2009; or Airbus Service Bulletin A320– 

34–1444, dated October 7, 2009; has 

been incorporated. 

Request To Use Additional Service 

Information 

Airbus requested that we revise 

paragraph (i)(1) of the previous SNPRM 

(77 FR 40823, dated July 11, 2012) to 

include Thales Avionics Service 

Bulletin C16291A–34–007, Revision 01, 

dated December 3, 2009; and Thales 

Avionics Service Bulletin C16291A–34– 

007, Revision 02, dated December 16, 

2011. 

We agree with Airbus’s request. We 

have added the service information to 

paragraph (i) of this AD. 

Request To Use the Airplane 

Maintenance Manual for Replacing the 

AOA Probes 

UAL requested that, in paragraph 

(g)(2) of the previous SNPRM (77 FR 

40823, dated July 11, 2012), the AOA 

probes be replaced using Airplane 

Maintenance Manual (AMM) 34–11–19 

PB 401, for the corrective action. 

We partially agree with UAL’s 

request. Although we do not agree to 

mandate the use of Task 34–11–19–000– 

001–A, Removal of the Angle of Attack 

Sensor, of the Airbus A318/A319/A320/ 

A321 AMM, we do agree that this AMM 

task includes procedures for replacing 

the AOA probes. Therefore, we have 

added Note 1 to paragraph (g)(2) of this 

SNPRM, to specify that additional 

guidance for replacing the AOA probes 

may be found in Task 34–11–19–000– 

001–A, Removal of the Angle of Attack 

Sensor, of the Airbus A318/A319/A320/ 

A321 AMM. 

Request To Revise the Labor Rate 

United Airlines (UAL) requested that 

the ‘‘Costs of Compliance’’ section in 

the previous SNPRM (77 FR 40823, July 

11, 2012) be updated to a new labor rate. 

UAL stated that the FAA’s costs of 

compliance were estimated to take 

about 2 work-hours per product to 

comply with the basic requirements of 

the previous SNPRM, and that the 

average labor rate is $85 per work-hour. 

UAL stated that it agrees with the 

estimated work-hours, but it would like 

to provide an updated labor rate of $97 

per work-hour. 

We disagree with UAL’s request to 

change the labor rate in this SNPRM. 

Our estimate of $85 per work-hour is the 

current burdened labor rate established 

for use by the FAA Office of Aviation 

Policy, Plans, and Management 

Analysis. The burdened labor rate 

includes the labor cost, overhead, 

administrative expenses, etc. Because 

the labor rate used in our calculations 

accounts for the variations in costs 

among those in the airline industry, we 

consider that $85 per work-hour is 

appropriate. No change to this SNPRM 

is necessary in this regard. 

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. 

Certain changes described above 

expand the scope of the earlier SNPRM 

(77 FR 40823, dated July 11, 2012). As 

a result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this proposed 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 755 products of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with the 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 

$128,350, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $0, for a cost of $255 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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: 

mstockstill on DSK4VPTVN1PROD with 

73342 Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Proposed Rules 

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–2012–0150; 

Directorate Identifier 2011–NM–234–AD. 

(a) Comments Due Date 

We must receive comments by January 4, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34: Navigation. 

(e) Reason 

This AD was prompted by reports of oil 

residue between the stator and the rotor parts 

of the position resolvers of the angle of attack 

(AOA) vane, which was a result of incorrect 

removal of the machining oil during the 

manufacturing process of the AOA resolvers. 

We are issuing this AD to prevent erroneous 

AOA information and consequent delayed or 

non-activation of the AOA protection 

systems which, during flight at a high angle 

of attack, could result in reduced control 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) Inspection 

Within 12 months after the effective date 

of this AD, except as provided by paragraph 

(h) of this AD: Do the inspections specified 

in paragraphs (g)(1) and (g)(2) of this AD. 

(1) Inspect to determine the part number 

(P/N) and serial number of each Thales 

Avionics AOA probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, excluding 

Appendix 01, dated January 29, 2010. If any 

probe is found having P/N C16291AA and 

having a serial number listed in Thales 

Avionics Service Bulletin C16291A–34–007, 

Revision 03, dated April 10, 2012: Within 12 

months after the effective date of this AD, 

replace the AOA probe, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, excluding 

Appendix 01, dated January 29, 2010, 

provided that Thales Avionics Service 

Bulletin C16291A–34–009, dated September 

10, 2009; or Airbus Service Bulletin A320– 

34–1444, dated October 7, 2009; have not 

been accomplished. Thales Avionics Service 

Bulletin C16291A–34–009, dated September 

10, 2009; and Airbus Service Bulletin A320– 

34–1444, dated October 7, 2009 (which are 

not incorporated by reference in this AD); 

cannot be used for the installation of AOA 

probes having P/N C16291AB. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the installed AOA probes 

can be conclusively determined from that 

review. 

(2) Inspect to determine the part number 

and serial number of each Thales Avionics 

AOA probe, in accordance with paragraph 

3.C.(1)a of the Accomplishment Instructions 

of Airbus Service Bulletin A320–34–1452, 

excluding Appendix 01, dated January 29, 

2010. If any probe is found having P/N 

C16291AB, on which Thales Avionics 

Service Bulletin C16291A–34–009, dated 

September 10, 2009; or Airbus Service 

Bulletin A320–34–1444, dated October 7, 

2009 (which are not incorporated by 

reference in this AD); has been 

accomplished: Within 12 months after the 

effective date of this AD, replace the AOA 

probe, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, FAA, or European 

Aviation Safety Agency (EASA) (or its 

delegated agent). A review of airplane 

maintenance records is acceptable in lieu of 

the inspection specified in this paragraph if 

the part number of the installed AOA probes 

can be conclusively determined from that 

review. 

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

Additional guidance for replacing the AOA 

probes may be found in Task 34–11–19–000– 

001–A, Removal of the Angle of Attack 

Sensor, of the Airbus A318/A319/A320/A321 

Aircraft Maintenance Manual, which is not 

incorporated by reference in this AD. 

(h) Exception 

For any airplane on which Airbus 

modification 150006 (installation of Thales 

Avionics AOA probes P/N C16291AB) or 

modification 26934 (installation of Goodrich 

AOA probes P/N 0861ED) has been embodied 

in production, and on which no AOA probe 

replacement has been made since first flight: 

The actions specified in paragraph (g) of this 

AD are not required. 

(i) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AA, having a serial 

number listed in Thales Avionics Service 

Bulletin C16291A–34–007, Revision 03, 

dated April 10, 2012, on any airplane, unless 

that Thales Avionics probe has been 

inspected, re-identified, and tested, in 

accordance with the Accomplishment 

Instructions of the service information 

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

(i)(1)(iii) of this AD. 

(i) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. 

(ii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 02, dated 

December 16, 2011. 

(iii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 01, dated 

December 3, 2009. 

(2) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AB, on which Thales 

Avionics Service Bulletin C16291A–34–009, 

dated September 10, 2009; or Airbus Service 

Bulletin A320–34–1444, dated October 7, 

2009 (which is not incorporated by reference 

in this AD); has been incorporated. 

(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, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0203, dated October 13, 2011, and the service 

information specified in paragraphs (k)(1)(i) 

and (k)(1)(ii) of this AD, for related 

information. 

(i) Airbus Service Bulletin A320–34–1452, 

excluding Appendix 01, dated January 29, 

2010. 

(ii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For Thales Avionics service 

information identified in this AD, contact 

Thales Avionics, Retrofit Manager, 105, 

mstockstill on DSK4VPTVN1PROD with 

Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Proposed Rules 73343 

Avenue du Ge ́ne ́ral Eisenhower, BP 63647, 

31036 Toulouse Cedex 1, France; telephone 

+33 5 61 19 76 95; fax +33 5 61 19 68 20; 

email retrofit.ata@fr.thalesgroup.com; 

Internet http://www.thalesgroup.com/ 

aerospace. 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 

November 30, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–29713 Filed 12–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1224; Directorate 

Identifier 2012–NM–112–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 all 

Airbus 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); and Model 

A310 series airplanes. This proposed 

AD was prompted by a report of an 

uncommanded slide back of the co-pilot 

seat to the end stop position. This 

proposed AD would require a one-time 

inspection for a part number, a tensile 

test of the affected seats, and corrective 

actions if necessary. We are proposing 

this AD to detect and prevent unwanted 

movement of a pilot or co-pilot seat in 

the horizontal direction, which could 

lead to inadvertent input on the flight 

control commands and possibly result 

in loss of controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 24, 2013. 

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 Airbus service information 

identified in this proposed AD, contact 

Airbus SAS–EAW (Airworthiness 

Office), 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

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

www.airbus.com. For EADS SOGERMA 

service information identified in this 

AD, contact EADS SOGERMA, Zone 

Industrielle de l’Arsenal, CS. 60109, 

17303 Rochefort, Cedex France; phone: 

33 5 46 82 84 84; fax: 33 5 46 82 88 13; 

email: SCOD1@sogerma.eads.net; 

Internet: http://www.sogerma.eads.net. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

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: 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: 

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–2012–1224; Directorate Identifier 

2012–NM–112–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 aviation authority 

for Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0102, 

dated June 8, 2012 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During a steep climb manoeuvre that was 

flown with a high pitch (25°) for training of 

ground threat avoidance, an Airbus A310 

aeroplane experienced an uncommanded 

slide back of the co-pilot seat to the end stop 

position. 

Investigation revealed that on the affected 

seat, the disc key inside the clutch was 

broken. SOGERMA Service Bulletin (SB) No 

2510112–25–813, which addresses the 

previous end stop switch issue and which is 

covered by EASA AD 2010–0070 [which 

corresponds to FAA AD 2011–06–09, 

Amendment 39–16634 (76 FR 15805, March 

22, 2011)] had been accomplished on this 

seat, but due to seizure, the key failure was 

not detected at time. This broken disc key 

caused a jamming between the gear and the 

shaft of the clutch. Despite this failure, the 

torque transmission between the gear and the 

shaft was sufficient for normal operation, but 

not to keep the seat in locked position during 

climbing, due to the high longitudinal loads 

generated by the high aeroplane incidence. 

This condition, if not detected and 

corrected, could cause the pilot to lose 

contact with the controls, leading to an 

inadvertent input on the flight control 

commands during take-off or climb, possibly 

resulting in loss of control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection 

[part number (P/N) inspection of the seats 

and tensile test] of the affected seats and, 

depending on findings, accomplishment of 

applicable corrective action(s) [replacing the 

seat or modifying the seat by replacing 

actuator P/N RT19H4FX with a new 

actuator]. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Alert Operators 

Transmission A25W001–12, dated June 

6, 2012; and EADS SOGERMA has 

issued Inspection Service Bulletin 

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