25902 Federal Register / Vol. 78, No. 86 / Friday, May 3, 2013 / Proposed Rules 

the procedures specified in paragraph (q) of 

this AD. 

(2) Although Boeing Special Attention 

Service Bulletin 747–53–2253, Revision 4, 

dated September 9, 2010, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

(3) As of the effective date of this AD, if 

any cracking is found during any inspection 

required by this AD, and Boeing Special 

Attention Service Bulletin 747–53–2253, 

Revision 2, dated March 29, 1990, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the crack using a 

method approved in accordance with the 

procedures specified in paragraph (q) of this 

AD. 

(p) Credit for Previous Actions 

This paragraph provides credit for the 

repairs and doubler modifications required 

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

actions were performed before the effective 

date of this AD using the service information 

specified in paragraphs (p)(1) through (p)(4) 

of this AD. Post-modification inspections 

must continue, as required by paragraph (n) 

of this AD. 

(1) Boeing Service Bulletin 747–53–2253, 

dated December 14, 1984, which is not 

incorporated by reference in this AD. 

(2) Boeing Service Bulletin 747–53–2253, 

Revision 1, dated January 25, 1990, which is 

not incorporated by reference in this AD. 

(3) Boeing Service Bulletin 747–53–2253, 

Revision 2, dated March 29, 1990. 

(4) Boeing Service Bulletin 747–53–2253, 

Revision 3, dated March 24, 1994, which is 

not incorporated by reference in this AD. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 90–23–14, Amendment 

39–6801 (Docket No. 90–NM–110–AD; 55 FR 

46652, November 6, 1990), are approved as 

AMOCs for the corresponding provisions of 

this AD: 

(5) AMOCs approved previously for the 

ADs specified in paragraphs (q)(5)(i) through 

(q)(5)(vi) of this AD, for repair and doubler 

modification installations in the area affected 

by Boeing Special Attention Service Bulletin 

747–53–2253, Revision 4, dated September 9, 

2010, are approved as AMOCs for the actions 

specified in paragraphs (g), (h), (k), (l), and 

(m) of this AD. The post-modification 

inspections required by paragraph (n) of this 

AD must be accomplished. 

(i) AD 2010–10–05, Amendment 39–16284 

(75 FR 27424, May 17, 2010). 

(ii) AD 2010–09–03, Amendment 39–16268 

(75 FR 22514, April 29, 2010). 

(iii) AD 2009–04–16, Amendment 39– 

15822 (74 FR 8737, February 26, 2009). (iv) 

AD 91–11–01, Amendment 39–6997 (56 FR 

22306, May 15, 1991). 

(v) AD 90–06–06 Amendment 39–6490 (55 

FR 8374, March 7, 1990). 

(vi) AD 2006–24–02 Amendment 39–14831 

(71 FR 67445, November 22, 2006). 

(r) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on April 24, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10481 Filed 5–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0363; Directorate 

Identifier 2013–NM–031–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 A330–200, –300 and –200 

Freighter series airplanes, and Model 

A340–200, –300, –500, and –600 series 

airplanes. This proposed AD would 

require, for certain airplanes, revising 

the airplane flight manual (AFM) to 

advise the flight crew of emergency 

procedures for addressing Angle of 

Attack (AOA) sensor blockage. This 

proposed AD would also mandate 

replacing the AOA sensor conic plates 

with AOA sensor flat plates, which is a 

terminating action for the AFM revision. 

This proposed AD was prompted by a 

report that an airplane equipped with 

AOA sensors installed with conic plates 

recently experienced blockage of all 

sensors during climb, leading to 

autopilot disconnection and activation 

of the alpha protection (Alpha Prot) 

when Mach number was increased. We 

are proposing this AD to prevent 

reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 17, 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 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, 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 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 86 / Friday, May 3, 2013 / Proposed Rules 25903 

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, WA 

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–2013–0363; Directorate Identifier 

2013–NM–031–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 2013–0023, 

dated February 1, 2013 (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: 

An A330 aeroplane experienced a blockage 

of all Angle of Attack (AOA) probes during 

climb leading to Autopilot (AP) 

disconnection and activation of the alpha 

protection (Alpha Prot) when Mach number 

increased. 

Analysis showed that this aeroplane was 

equipped with AOA probes having conic 

plates, and it is suspected that these plates 

might have contributed to the event. 

Investigations are on-going to determine the 

root cause of this AOA probes blockage. The 

AOA conic plates can also be installed on 

A340 aeroplanes. 

These AOA conic plate could have been 

installed in production through Airbus 

modification (mod.) 201609 (associated to 

Thales Avionics AOA probes Part Number 

(P/N) C16291AA and P/N C16291AB) or 

mod. 201610, associated to Goodrich AOA 

probes P/N 0861ED, or in service through 

Airbus Service Bulletin (SB) A340–34–4250 

or SB A340–34–5081. 

The blockage of two or three AOA probes 

of the same angle may cause the Alpha Prot 

of the normal law to activate. 

Under normal flight conditions (in normal 

law), if the Alpha Prot activates and Mach 

number increases, the flight control laws 

order a pitch down of the aeroplane that the 

flight crew may not be able to counteract 

with a sidestick deflection, even in the full 

backward position. 

This condition, if not corrected, could 

result in reduced control of the aeroplane. 

To address this condition, Airbus 

developed a ‘‘Blocked AOA probes’’ 

emergency procedure included in Airbus 

Airplane Flight Manual (AFM) A330 

Temporary Revision (TR) TR293 issue 1 and 

Airbus AFM A340 TR294 issue 1. 

Consequently, EASA issued Emergency AD 

2012–0258–E to require amendment of the 

AFM to ensure that flight crews, in case of 

AOA probe blockage, apply the applicable 

emergency procedure. 

Since that AD was issued, Airbus 

published approved instructions to re-install 

AOA probe flat plates on A330/A340 family 

aeroplanes. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

[Emergency] AD 2012–0258–E which is 

superseded, and requires installation of AOA 

probe flat plates, after which the AFM 

operational procedure must be removed. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Other Related Rulemaking 

On December 27, 2012, the FAA 

issued AD 2012–26–51, Amendment 

39–17312 (78 FR 1723, January 9, 2013), 

applicable to all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

That AD requires revising the AFM to 

advise the flight crew of emergency 

procedures for addressing AOA sensor 

blockage. The actions required by that 

AD are intended to prevent reduced 

control of the airplane. 

Relevant Service Information 

We reviewed Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated 

December 4, 2012, and Airbus A340 

Temporary Revision TR294, Issue 1.0, 

dated December 4, 2012, to the Airbus 

A330 and A340 Airplane Flight 

Manuals. The temporary revisions 

provide information to advise the flight 

crew of emergency procedures for 

addressing AOA sensor blockage. 

We also reviewed the following 

service information: 

• Airbus Mandatory Service Bulletin 

A330–34–3293, including Appendix 01, 

dated January 31, 2013. 

• Airbus Mandatory Service Bulletin 

A340–34–4273, including Appendix 01, 

dated January 30, 2013. 

• Airbus Mandatory Service Bulletin 

A340–34–5093, including Appendix 01, 

dated January 30, 2013. 

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. 

Difference Between the Proposed AD 

and the MCAI or Service Information 

This proposed AD would require 

operators to revise the AFM within 10 

days after the effective date of this AD. 

The MCAI recommends revising the 

AFM ‘‘from the effective date of this 

AD.’’ In developing the compliance time 

for this action, we considered the degree 

of urgency associated with addressing 

the subject unsafe condition and the 

practical aspect of revising the AFM. We 

have determined that 10 days represents 

an appropriate interval of time in which 

to revise the AFM for the affected fleet 

without adversely affecting the safety of 

these airplanes. 

This difference has been coordinated 

with the EASA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 64 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
25904 Federal Register / Vol. 78, No. 86 / Friday, May 3, 2013 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

AFM Revision ......................... 1 work-hour × 85 per hour = 85 ............................................. 0 85 5,440 

Modification ............................ 7 work-hours × 85 per hour = 595 ......................................... 0 595 38,080 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0363; 

Directorate Identifier 2013–NM–031–AD. 

(a) Comments Due Date 

We must receive comments by June 17, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, as identified in 

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

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

223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

all manufacturer serial numbers. 

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

–312, –313, –541 and –642 airplanes, all 

manufacturer serial numbers. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 34: Navigation. 

(e) Reason 

This AD was prompted by a report that an 

airplane equipped with Angle of Attack 

(AOA) sensors installed with conic plates 

recently experienced blockage of all sensors 

during climb, leading to autopilot 

disconnection and activation of the alpha 

protection (Alpha Prot) when Mach number 

was increased. We are issuing this AD to 

prevent 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) Airplane Flight Manual Revision 

For airplanes identified in paragraphs 

(g)(1) and (g)(2) of this AD, except as 

provided by paragraph (i) of this AD: Within 

10 days after the effective date of this AD, 

revise the Emergency Procedures of the 

Airbus A330 and A340 Airplane Flight 

Manuals (AFMs), as applicable, by 

incorporating Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; as 

applicable; to advise the flight crew of 

emergency procedures for addressing AOA 

sensor blockage. This can be done by 

inserting the Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; 

into the applicable AFM. When the 

information in Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; and Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; is 

included in the general revisions of the 

applicable AFM, the general revisions may be 

incorporated into the AFM, and the 

temporary revisions may be removed. 

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

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

all manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A330–34–3255 has 

been embodied in service. 

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

–312, –313, –541, and –642 airplanes, all 

manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A340–34–4250 or 

A340–34–5081, as applicable, has been 

embodied in service. 

(h) Terminating Replacement 

Within 5 months after the effective date of 

this AD: Replace all AOA sensor conic plates 

having part number (P/N) F3411060200000 

or P/N F3411060900000, with an applicable 

AOA sensor flat plate identified in paragraph 

(h)(1) or (h)(2) of this AD. Performing this 

replacement constitutes terminating action 

for the AFM revision required by paragraph 

(g) of this AD; and Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012, and Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012, to 

the Airbus A330 and A340 AFMs, as 

applicable; must be removed from the AFMs 

before further flight after doing the 

replacement. 

(1) Replace with a flat plate having P/N 

F3411007920200 or P/N F3411007920300, as 

applicable, in accordance with the applicable 

service information specified in paragraph 

(h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–34–3293, including Appendix 01, 

dated January 31, 2013. 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 86 / Friday, May 3, 2013 / Proposed Rules 25905 

(ii) Airbus Mandatory Service Bulletin 

A340–34–4273, including Appendix 01, 

dated January 30, 2013. 

(iii) Airbus Mandatory Service Bulletin 

A340–34–5093, including Appendix 01, 

dated January 30, 2013. 

(2) Replace with a flat plate having P/N 

F3411007920000 or P/N F3411007920100, in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) or its delegated agent. 

(i) Exception to Paragraphs (g) and (h) of 

This AD 

For airplanes on which Airbus 

Modification 203285 (improve AOA flat plate 

protection treatment) has been embodied in 

production: The actions specified in 

paragraphs (g) and (h) of this AD are not 

required, provided that, since first flight, no 

AOA probe conic plate having P/N 

F3411060200000 or P/N F3411060900000 

has been installed. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, an AOA 

sensor conic plate having P/N 

F3411060200000 or P/N F3411060900000 or 

an AOA protection cover having P/N 

98D34203003000. 

(k) 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2013–0023, dated 

February 1, 2013, and the service information 

specified in paragraphs (l)(1)(i), (l)(1)(ii), 

(l)(1)(iii), (l)(1)(iv) and (l)(1)(v) of this AD for 

related service information: 

(i) Airbus A330 Temporary Revision 

TR293, Issue 1.0, dated December 4, 2012. 

(ii) Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A330–34–3293, including Appendix 01, 

dated January 31, 2013. 

(iv) Airbus Mandatory Service Bulletin 

A340–34–4273, including Appendix 01, 

dated January 30, 2013. 

(v) Airbus Mandatory Service Bulletin 

A340–34–5093, including Appendix 01, 

dated January 30, 2013. 

(2) 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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on April 23, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10486 Filed 5–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0362; Directorate 

Identifier 2013–NM–030–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 727 

airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the frame-to-floor beam 

attachment is subject to widespread 

fatigue damage (WFD). This proposed 

AD would require repetitive high 

frequency eddy current inspections for 

any crack of the frames at body station 

(STA) 188 through STA 344, and repair 

if necessary. We are proposing this AD 

to detect and correct fatigue cracking at 

the frame-to-floor beam attachment, on 

both the left- and right-sides, which 

could result in reduced structural 

integrity of the airplane, and 

decompression of the cabin. 

DATES: We must receive comments on 

this proposed AD by June 17, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: (562) 627–5239; fax: (562) 627– 

5210; email: 

chandraduth.ramdoss@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


erowe on DSK2VPTVN1PROD with PROPOSALS-1