76228 Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0995; Directorate 

Identifier 2012–NM–056–AD; Amendment 

39–17291; AD 2012–25–10] 

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 A330–300 series airplanes 

and Model A340–200 and –300 series 

airplanes. This AD was prompted by 

reports that, during a flight test, several 

spoiler servo-controls (SSCs) did not 

remain locked in the retracted position 

(hydraulic locking function) after 

manual depressurization of the 

corresponding hydraulic circuit. Loss of 

that locking function—which is ensured 

by a blocking valve—was caused by an 

internal leak from a sheared seal on the 

blocking valve. This AD requires 

inspecting to determine if certain SSCs 

are installed, performing an operational 

test of any affected SSC, and replacing 

if necessary. We are issuing this AD to 

prevent loss of the hydraulic locking 

function during take-off and go-around 

phases, which, in combination with 

malfunction of one engine, could result 

in reduced controllability of the 

airplane. 

DATES: This AD becomes effective 

January 31, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 31, 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: 

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: 

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 September 20, 2012 (77 FR 

58327). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

Two operators have reported that several 

spoilers did not remain locked in the 

retracted position (lifted up without order) 

after manual depressurization of the 

corresponding hydraulic circuit during flight 

test. 

Subsequent checks on ground confirmed 

that, for each affected spoiler surface, the 

spoiler was fitted with one MZ-type Spoiler 

Servo Control (SSC) (Part Number (P/N) 

MZ4339390–12 or P/N MZ4306000–12). 

The results of the investigations on the 

affected SSCs, done by the supplier, revealed 

that the loss of the hydraulic locking 

function—which is ensured by a blocking 

valve—was due to an internal leakage caused 

by a sheared seal. This seal is installed at the 

left end of the blocking valve. 

During the on-wing modification of the 

maintenance cover, blocking valve movement 

may have damaged the seal on the outer 

diameter of the blocking valve assembly, 

causing the loss of the hydraulic locking 

function. 

This condition, if not detected and 

corrected, if occurring during take-off and goaround phases in combination with one 

engine inoperative, could jeopardize the 

aeroplane safe flight. 

For the reasons described above, this 

[EASA] AD requires the identification of the 

installed SSCs, to perform an operational test 

of the hydraulic locking function of the 

affected SSCs and to accomplish the 

applicable corrective actions if any 

discrepancy is detected during the 

operational test. This [EASA] AD also 

requires reporting operational test results to 

Airbus. 

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 58327, September 20, 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. 

Costs of Compliance 

We estimate that this AD will affect 

61 products of U.S. registry. We also 

estimate that it will take up to 7 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$36,295, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 36 work-hours and require parts 

costing $34,928, for a cost of $37,988 

per affected SSC. 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


pmangrum on DSK3VPTVN1PROD with 
Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 76229 

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 58327, 

September 20, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–25–10 Airbus: Amendment 39–17291. 

Docket No. FAA–2012–0995; Directorate 

Identifier 2012–NM–056–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 31, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by reports that, 

during flight test, several spoiler servocontrols (SSCs) did not remain locked in the 

retracted position (hydraulic locking 

function) after manual depressurization of 

the corresponding hydraulic circuit. Loss of 

that locking function—which is ensured by a 

blocking valve—was caused by an internal 

leak from a sheared seal on the blocking 

valve. We are issuing this AD to prevent loss 

of the hydraulic locking function during takeoff and go-around phases, which, in 

combination with malfunction of one engine, 

could result in 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) Actions 

Within 90 days after the effective date of 

this AD: Inspect to determine the part 

number (P/N) of all SSCs installed, in 

accordance with Airbus All Operators Telex 

(AOT) A330–27A3185 (for Model A330–300 

series airplanes) or A340–27A4181 (for 

Model A340–200 and –300 series airplanes), 

both dated January 4, 2012. A review of 

airplane maintenance records is acceptable in 

lieu of the inspection to identify the part 

number of the SSC installed, provided that 

part number can be conclusively determined 

from that review. 

(1) For any SSC having P/N MZ4339390– 

12 or P/N MZ4306000–12 (MZ-type): Within 

90 days after identification of the part, 

perform an operational test of the hydraulic 

locking function at each position fitted with 

an MZ-type SSC, in accordance with Airbus 

AOT A330–27A3185 (for Model A330–300 

series airplanes) or A340–27A4181 (for 

Model A340–200 and –300 series airplanes), 

both dated January 4, 2012. 

(2) If any discrepancy is detected during 

the operational test specified in paragraph 

(g)(1) of this AD, or if the test fails, before 

further flight, replace the affected SSC with 

a new or serviceable SSC, in accordance with 

Airbus AOT A330–27A3185 (for Model 

A330–300 series airplanes) or A340–27A4181 

(for Model A340–200 and –300 series 

airplanes), both dated January 4, 2012. 

(h) Reporting to Airbus 

Submit a report of the findings of the 

operational test required by paragraph (g)(1) 

of this AD (both positive and negative) to 

Airbus, Customer Services, Engineering and 

Technical Support, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France, Attn: 

Daniel Lopez-Fernandez, SEEL6; fax: (+33) 5 

61 93 04 52; email: daniel.lopezfernandez@airbus.com; at the applicable time 

specified in paragraph (h)(1) or (h)(2) of this 

AD. 

(1) If the test was done on or after the 

effective date of this AD: Submit the report 

within 30 days after the test. 

(2) If the test was done before the effective 

date of this AD: Submit the report within 30 

days after the effective date of this AD. 

(i) 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2012–0009, 

dated January 13, 2012, and the service 

information specified in paragraph (j)(1) or 

(j)(2) of this AD, for related information. 

(1) Airbus All Operators Telex (AOT) 

A330–27A3185, dated January 4, 2012. 

(2) Airbus AOT A340–27A4181, dated 

January 4, 2012. 

(k) 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 All Operators Telex A330– 

27A3185, dated January 4, 2012. The 

document number and issue date are 

identified on only the first page of this 

document. 

(ii) Airbus All Operators Telex A340– 

27A4181, dated January 4, 2012. The 

document number and issue date are 

identified on only the first page of this 

document. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 


pmangrum on DSK3VPTVN1PROD with 
76230 Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 

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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on 

December 7, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30369 Filed 12–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1222; Directorate 

Identifier 2010–NM–268–AD; Amendment 

39–17286; AD 2012–25–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This AD was prompted 

by reports of escape slides failing to 

deploy from the forward and aft righthand doors during scheduled 

maintenance slide deployments. This 

AD requires modifying the escape slide. 

Also, for certain airplanes, this AD 

requires modifying or replacing the 

Vespel piston. For certain other 

airplanes, this AD requires an additional 

modification of the escape slide. We are 

issuing this AD to prevent failure of an 

escape slide to deploy, which could 

result in the slide being unusable during 

an emergency evacuation and increased 

likelihood of injury to passengers or 

crewmembers due to the difficulty in 

evacuating the airplane. 

DATES: This AD is effective January 31, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 31, 2013. 

ADDRESSES: For service information 

identified in this AD, Goodrich 

Corporation, Aircraft Interior Products 

ATTN: Technical Publications, 3414 

South Fifth Street, Phoenix, Arizona 

85040; phone: 602–243–2270; Internet: 

http://www.goodrich.com/TechPubs. 

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 Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sarah Piccola, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, Seattle Aircraft 

Certification Office (ACO), FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6483; fax: 425– 

917–6590; email: sarah.piccola@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on August 31, 2012 (77 FR 

53155). The original NPRM (76 FR 

69159, November 8, 2011) proposed to 

require checking the escape slide girt for 

serviceability, and replacement if 

necessary; modifying the cable routing 

provision; replacing the regulator 

padding; modifying the aspirator 

orientation; and modifying the valise. 

The original NPRM also proposed to 

require, for certain airplanes, modifying 

or replacing the Vespel piston, 

modifying the pilot valve regulator, 

installing a new firing cable and safety 

pin, and modifying the slide valise. The 

SNPRM proposed to add airplanes to 

the applicability of the original NPRM, 

and specify revised service information. 

For certain other airplanes, this AD 

requires an additional modification of 

the escape slide. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Support for the SNPRM (77 FR 53155, 

August 31, 2012) 

Boeing stated that it concurs with the 

contents of the SNPRM (77 FR 53155, 

August 31, 2012), and therefore, no 

additional comments will be 

forthcoming. 

Goodrich Corporation stated that the 

comments it submitted to the original 

NPRM (76 FR 69159, November 8, 2011) 

have been satisfactorily addressed, and 

therefore, it has no additional comments 

or changes to offer. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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 SNPRM (77 FR 

53155, August 31, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 53155, 

August 31, 2012). 

Additional Change Made to This Final 

Rule 

We have removed the girt 

replacement on-condition cost specified 

in the SNPRM (77 FR 53155, August 31, 

2012) from this AD, because the 

proposed girt check for continued 

serviceability was removed from the 

SNPRM and is not included in this AD. 

Costs of Compliance 

We estimate that this AD affects 557 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


pmangrum on DSK3VPTVN1PROD with