15874 Federal Register / Vol. 78, No. 49 / Wednesday, March 13, 2013 / Rules and Regulations 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

7, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–04634 Filed 3–12–13; 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; Amendment 

39–17372; AD 2013–04–14] 

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 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 AD was 

prompted by a report of an 

uncommanded slide back of the co-pilot 

seat to the end stop position. This AD 

requires a one-time inspection for a part 

number, a tensile test of the affected 

seats, and corrective actions if 

necessary. We are issuing 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: This AD becomes effective April 

17, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 17, 2013. 

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 December 10, 2012 (77 FR 

73343). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (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 [European Aviation Safety 

Agency] 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 73343, December 10, 2012), or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

73343, December 10, 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 73343, 

December 10, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

161 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $4,523 

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 parts. 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 

this AD to the U.S. operators to be 

$741,888, or $4,608 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 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: 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 49 / Wednesday, March 13, 2013 / Rules and Regulations 15875 

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 73343, 

December 10, 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: 

2013–04–14 Airbus: Amendment 39–17372. 

Docket No. FAA–2012–1224; Directorate 

Identifier 2012–NM–112–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 17, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes; and Model A310–203, 

–204, –221, –222, –304, –322, –324, and –325 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by a report of an 

uncommanded slide back of the co-pilot seat 

to the end stop position. We are issuing 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 possibly resulting in loss of 

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) Part Number (P/N) Inspection 

Within 6 months after the effective date of 

this AD, except as provided by paragraph (h) 

of this AD: Do an inspection to determine the 

part number of each SOGERMA pilot and copilot seat installed on the airplane. As an 

alternative, a review of the maintenance or 

delivery records may be used to determine 

the part number of the pilot and co-pilot seat 

if the part number can be positively 

determined from that review. 

(h) Seats That Have Been Previously Tested 

or Modified 

SOGERMA pilot and co-pilot seats having 

P/N 2510112 series (all suffixes) or P/N 

2510113 series (all suffixes) that, before the 

effective date of this AD, have already passed 

the tensile test specified in paragraph (i) of 

this AD, or have been modified as specified 

in the Operating Instructions of EADS 

SOGERMA Inspection Service Bulletin 

2510112–25–898, dated April 25, 2012, are 

not required to be tested, and are considered 

to be compliant with the requirements of this 

AD. 

(i) Tensile Test 

If, during the inspection required by 

paragraph (g) of this AD, the part number of 

a seat is identified as P/N 2510112 series (all 

suffixes), or P/N 2510113 series (all suffixes): 

Within 6 months after the effective date of 

this AD, do a tensile test on that seat, in 

accordance with Airbus Alert Operators 

Transmission (AOT) A25W001–12, dated 

June 6, 2012. 

(j) Replacement or Modification 

If the tensile test sample does not break off 

while performing the test required by 

paragraph (i) of this AD, before further flight, 

do one of the actions specified in paragraph 

(j)(1) or (j)(2) of this AD. 

(1) Replace the affected seat with a new or 

serviceable seat that has passed the tensile 

test specified in paragraph (i) of this AD. Do 

the replacement in accordance with Airbus 

AOT A25W001–12, dated June 6, 2012. 

(2) Modify the seat by replacing actuator P/ 

N RT19H4FX of the affected seat, in 

accordance with the Operating Instructions 

of EADS SOGERMA Inspection Service 

Bulletin 2510112–25–898, dated April 25, 

2012; or Airbus AOT A25W001–12, dated 

June 6, 2012. 

(k) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install a SOGERMA pilot or copilot seat having P/N 2510112 series, or P/ 

N 2510113 series, on any airplane unless it 

has passed the tensile test required by 

paragraph (i) of this AD, or has been replaced 

or modified as required by paragraph (j) of 

this AD. 

(l) 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; telephone (425) 227–2125; 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. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0102, dated June 8, 2012, and 

the service information specified in 

paragraphs (m)(1) and (m)(2) of this AD, for 

related information. 

(1) Airbus Alert Operators Transmission 

A25W001–12, dated June 6, 2012. 

(2) EADS SOGERMA Inspection Service 

Bulletin 2510112–25–898, dated April 25, 

2012. 

(n) 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) Airbus Alert Operators Transmission 

A25W001–12, dated June 6, 2012. 


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15876 Federal Register / Vol. 78, No. 49 / Wednesday, March 13, 2013 / Rules and Regulations 

(ii) EADS SOGERMA Inspection Service 

Bulletin 2510112–25–898, dated April 25, 

2012. 

(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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) 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. 

(5) You may review copies of the 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. 

(6) 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/ibr-l

ocations.html. 

Issued in Renton, Washington, on February 

21, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–04628 Filed 3–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 121 

[Docket No. FAA–2009–0675; Amendment 

No. 121–363] 

RIN 2120–AJ43 

Activation of Ice Protection 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: The FAA is correcting a final 

rule published on August 22, 2011 (76 

FR 52241). In that rule, the FAA 

amended its regulations to create new 

operating rules for flight in icing 

conditions. This document corrects an 

error in the amendatory language of the 

final rule which inadvertently led to the 

omission of the new section from the 

Code of Federal Regulations. 

DATES: Effective March 13, 2013. 

FOR FURTHER INFORMATION CONTACT: For 

operational questions, contact Charles J. 

Enders, Air Carrier Operations Branch, 

AFS–220, Flight Standards Service, 

Federal Aviation Administration, 800 

Independence Ave. SW., Washington, 

DC 20591; telephone (202) 493–1422; 

facsimile (202) 267–5229; email 

Charles.J.Enders@faa.gov. 

For aircraft certification questions, 

contact Robert Jones, Propulsion/ 

Mechanical Systems Branch, ANM–112, 

Federal Aviation Administration, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; telephone (425) 227–1234; 

facsimile (425) 227–1007; email 

Robert.C.Jones@faa.gov. 

For legal questions concerning this 

action, contact Doug Anderson, Office of 

Regional Counsel, Federal Aviation 

Administration, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 

(425) 227–2166; facsimile (425) 227– 

1007; email Douglas.Anderson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On August 22, 2011, the FAA 

published a final rule entitled, 

‘‘Activation of Ice Protection,’’ (76 FR 

52241). 

In that final rule the FAA added 

operating rules for flight in icing 

conditions. For certain airplanes 

certificated for flight in icing, the new 

standards require either installation of 

ice detection equipment or changes to 

the airplane flight manual to ensure 

timely activation of the airframe icing 

protection system. The FAA 

inadvertently wrote the amendatory 

language incorrectly to say that we were 

revising § 121.321 when, in fact, we 

were creating that section and adding it 

to the CFR. 

The Technical Amendment 

This technical amendment corrects 

the amendatory language of the final 

rule to indicate that § 121.321 is being 

added, not revised. 

Because the change in this technical 

amendment results in no substantive 

change, we find good cause exists under 

5 U.S.C. 553(d)(3) to make the 

amendment effective in less than 30 

days. 

List of Subjects in 14 CFR Part 121 

Air carriers, Aircraft, Aviation safety, 

Reporting and recordkeeping 

requirements. 

The Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends Chapter I of Title 14, Code of 

Federal Regulations, as follows: 

PART 121—OPERATING 

REQUIREMENTS: DOMESTIC, FLAG, 

AND SUPPLEMENTAL OPERATIONS 

■ 1. The authority citation for part 121 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 40119, 

41706, 44101, 44701–44702, 44705, 44709– 

44711, 44713, 44716–44717, 44722, 44901, 

44903–44904, 44912, 45101–45105, 46105, 

46301. 

■ 2. Add new § 121.321 to read as 

follows: 

§ 121.321 Operations in icing. 

After October 21, 2013, no person 

may operate an airplane with a 

certificated maximum takeoff weight 

less than 60,000 pounds in conditions 

conducive to airframe icing unless it 

complies with this section. As used in 

this section, the phrase ‘‘conditions 

conducive to airframe icing’’ means 

visible moisture at or below a static air 

temperature of 5 °C or a total air 

temperature of 10 °C, unless the 

approved Airplane Flight Manual 

provides another definition. 

(a) When operating in conditions 

conducive to airframe icing, compliance 

must be shown with paragraph (a)(1), or 

(2), or (3) of this section. 

(1) The airplane must be equipped 

with a certificated primary airframe ice 

detection system. 

(i) The airframe ice protection system 

must be activated automatically, or 

manually by the flightcrew, when the 

primary ice detection system indicates 

activation is necessary. 

(ii) When the airframe ice protection 

system is activated, any other 

procedures in the Airplane Flight 

Manual for operating in icing conditions 

must be initiated. 

(2) Visual cues of the first sign of ice 

formation anywhere on the airplane and 

a certificated advisory airframe ice 

detection system must be provided. 

(i) The airframe ice protection system 

must be activated when any of the 

visual cues are observed or when the 

advisory airframe ice detection system 

indicates activation is necessary, 

whichever occurs first. 

(ii) When the airframe ice protection 

system is activated, any other 

procedures in the Airplane Flight 

Manual for operating in icing conditions 

must be initiated. 

(3) If the airplane is not equipped to 

comply with the provisions of 

paragraph (a)(1) or (2) of this section, 

then the following apply: 

(i) When operating in conditions 

conducive to airframe icing, the 

airframe ice protection system must be 

activated prior to, and operated during, 

the following phases of flight: 


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