Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60667 

September 8, 2004), are approved as AMOCs 

for the corresponding provisions of this AD. 

(5) Inspections and corrective actions 

required by paragraph (g) of AD 2009–21–01, 

Amendment 39–16038 (74 FR 52395, October 

13, 2009), are approved as AMOCs for the 

corresponding provisions of paragraph(s) of 

this AD, but only for the areas of the lower 

lobe skin identified in AD 2009–21–01. 

(z) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6447; fax: 425–917– 

6590; email: wayne.lockett@faa.gov. 

(2) Service information that is referenced 

in this AD that is not incorporated by 

reference in this AD may be obtained at the 

addresses identified in paragraphs (aa)(5) and 

(aa)(6) of this AD. 

(aa) 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. 

(3) The following service information was 

approved for IBR on November 6, 2013. 

(i) Boeing Alert Service Bulletin 737– 

53A1210, Revision 3, dated July 16, 2009. 

(ii) Figure 48, General Fuselage Skin 

Repair, of Subject 53–30–3, Skin Repair, of 

Chapter 53, Fuselage, of the Boeing 737–100/ 

–200 SRM D6–15565, Revision 102, dated 

September 10, 2010. The revision level of 

this document is identified in only the 

transmittal letter; no other page of the 

document contains this information. 

(iii) Repair 31, General Fuselage Skin 

Repairs, of Subject 53–00–01, Fuselage 

Skin—General, of Chapter 53, Fuselage, of 

the Boeing 737–300 SRM D6–37635, Revision 

92, dated November 10, 2010. The revision 

level of this document is identified in only 

the transmittal letter; no other page of the 

document contains this information. 

(iv) Repair 31, General Fuselage Skin 

Repairs, of Subject 53–00–01, Fuselage 

Skin—General, of Chapter 53, Fuselage, of 

the Boeing 737–400 SRM D6–38246, Revision 

75, dated November 10, 2010. The revision 

level of this document is identified in only 

the transmittal letter; no other page of the 

document contains this information. 

(v) Repair 31, General Fuselage Skin 

Repairs, of Subject 53–00–01, Fuselage 

Skin—General, of Chapter 53, Fuselage, of 

the Boeing 737–500 SRM D6–38441, Revision 

70, dated November 10, 2010. The revision 

level of this document is identified in only 

the transmittal letter; no other page of the 

document contains this information. 

(4) The following service information was 

approved for IBR on October 13, 2004 (69 FR 

54206, September 8, 2004). 

(i) Boeing Alert Service Bulletin 737– 

53A1210, Revision 1, excluding Appendix A, 

dated October 25, 2001. 

(ii) Reserved. 

(5) 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. 

(6) You may view this 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. 

(7) 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 August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24034 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0360; Directorate 

Identifier 2013–NM–033–AD; Amendment 

39–17591; AD 2013–19–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2012–26– 

51 for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2012–26–51 required revising the 

airplane flight manual (AFM) to advise 

the flightcrew of emergency procedures 

for addressing angle of attack (AoA) 

sensor blockage, and also provided for 

optional terminating action for the AFM 

revision, which involves replacing AoA 

sensor conic plates with AoA sensor flat 

plates. This new AD requires replacing 

AoA sensor conic plates with AoA 

sensor flat plates, and subsequent 

removal of the AFM revision. This AD 

was prompted by a determination that 

replacement of AoA sensor conic plates 

is necessary to address the identified 

unsafe condition. We are issuing this 

AD to prevent reduced control of the 

airplane. 

DATES: This AD becomes effective 

November 6, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 24, 2013 (78 FR 

1723, January 9, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 2, 2013 (78 FR 25666), 

and proposed to supersede AD 2012– 

26–51, Amendment 39–17312 (78 FR 

1723, January 9, 2013). The NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0022, 

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: 

Recently, an Airbus A330 aeroplane 

equipped with Angle of Attack (AoA) sensors 

with conic plates installed, experienced 

blockage of all sensors during climb, leading 

to autopilot disconnection and activation of 

the alpha protection (Alpha Prot) when Mach 

number was increased. 

Based on the results of the subsequent 

analysis, it is suspected that these conic 

plates may have contributed to the event. 

Investigations are on-going to determine what 

caused the blockage of these AoA sensors. 

Blockage of two or three AoA sensors at 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 be unable 


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to counteract with a side stick deflection, 

even in the full backward position. 

This condition, if not corrected, could 

result in reduced control of the aeroplane. 

AoA conic plates of similar design are also 

installed on A320 family aeroplanes, and 

installation of these AoA sensor conic plates 

was required by EASA AD 2012–0236, 

making reference to Airbus Service Bulletin 

(SB) A320–34–1521 for in-service 

modification. 

That requirement was deleted by EASA AD 

2012–0236R1 [http://ad.easa.europa.eu/blob/ 

easa_ad_2012_0236_R1.pdf/AD_2012- 

0236R1_1]. 

To address this potential unsafe condition 

on A320 family aeroplanes, Airbus 

developed an ‘‘AOA Blocked’’ emergency 

procedure, published as a temporary revision 

(TR) of the Airplane Flight Manual (AFM), to 

ensure that flight crews, in case of AoA 

sensors blockage, apply the applicable 

emergency procedure. 

Consequently, EASA issued Emergency AD 

2012–0264–E [http://ad.easa.europa.eu/blob/ 

easa_ad_2012_0264_E_superseded.pdf/ 

EAD_2012-0264-E_2] [which corresponds to 

FAA AD 2012–26–51, Amendment 39–17312 

(78 FR 1723, January 9, 2013)] to require 

amendment of the AFM by incorporating the 

Airbus TR. 

Since that [EASA] AD was issued, Airbus 

published approved instructions to re-install 

AoA sensor flat plates on A320 family 

aeroplanes. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0264–E which is superseded, and 

requires installation of AoA sensor flat 

plates, after which the AFM operational 

procedure can be removed. 

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 

have considered the comments received. 

Support for the NPRM (78 FR 25666, 

May 2, 2013) 

The Air Line Pilots Association 

International (ALPA) stated that it 

supports the installation of the AoA 

sensor flat plates. 

United Airlines (UAL) stated that it 

concurs with the replacement of the 

AoA sensor conic plates with AoA 

sensor flat plats. 

Request To Retain AFM Procedure 

ALPA requested that we retain the 

AFM procedure. ALPA stated that if an 

AoA failure were to occur, the AFM 

procedure would be useful for 

flightcrew reference. 

We disagree with the commenter’s 

request. The AOA conical plates have 

been identified as the root cause of the 

unsafe condition. The AFM procedure 

was an interim corrective action to 

mitigate the immediate risks associated 

with installation of conical plates. Based 

on the service history and our risk 

assessment, we have concluded that the 

AFM procedure associated with 

installation of conical plates is not 

required after the installation of AOA 

sensor flat plates. We have not changed 

this final rule in this regard. 

Request To Clarify Installation Method 

UAL requested clarification on the 

intent and details of the installation 

method specified in paragraph (j)(2) of 

the NPRM (78 FR 25666, May 2, 2013). 

UAL suggested that we revise the NPRM 

installation method from doing the 

installation in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

the EASA (or its delegated agent); to 

using a method stated in an applicable 

section of the airplane maintenance 

manual. 

We agree that clarification is 

necessary. The intent of paragraph (j)(2) 

of this final rule is that operators or 

Airbus use the procedures specified in 

paragraph (o) of this final rule to either 

apply for a method of compliance for 

accomplishing the installation, or for 

Airbus to provide maintenance 

procedures to operators for installation 

of flat conical plates approved by EASA 

or approved under EASA design 

organization approval. We have not 

changed this final rule in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this 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 (78 FR 

25666, May 2, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 25666, 

May 2, 2013). 

Costs of Compliance 

We estimate that this AD affects 100 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. operators 

AFM revision [actions retained from AD 2012–26–51, 

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

1 work-hour × $85 per hour = 

$85.

$0 $85 $8,500 

Flat plate installation and removal of AFM revision [new action].7 work-hours × $85 per hour 

= $595.

0 85 59,500 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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, 


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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60669 

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://

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 AD, the MCAI, 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. 

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 

removing airworthiness directive (AD) 

2012–26–51, Amendment 39–17312 (78 

FR 1723, January 9, 2013), and adding 

the following new AD: 

2013–19–09 Airbus: Amendment 39–17591. 

Docket No. FAA–2013–0360; Directorate 

Identifier 2013–NM–033–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 6, 2013. 

(b) Affected ADs 

This AD supersedes AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013). 

(c) Applicability 

This AD applies to the Airbus airplanes 

listed in paragraphs (c)(1) through (c)(4) of 

this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by a determination 

that replacement of angle of attack (AoA) 

sensor conic plates is necessary to address 

the identified unsafe condition. 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) Retained Airplane Flight Manual (AFM) 

Revision With New Exception 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013), with a new exception. Except as 

specified in paragraph (k) of this AD, for 

airplanes on which an AoA sensor conic 

plate has been installed in production by 

Airbus modification 153213 or 153214, or inservice as specified in Airbus Mandatory 

Service Bulletin A320–34–1521, dated May 

7, 2012; or Revision 01, dated September 12, 

2012: Within 5 days after January 24, 2013 

(the effective date of AD 2012–26–51), revise 

the Emergency Procedures of the Airbus 

A318/A319/A320/A321 AFM by inserting 

Airbus A318/A319/A320/A321 Temporary 

Revision (TR) TR286, Issue 1.0, dated 

December 17, 2012, to advise the flightcrew 

of emergency procedures for addressing AoA 

sensor blockage. When the information in 

Airbus A318/A319/A320/A321 TR TR286, 

Issue 1.0, dated December 17, 2012, is 

included in the general revisions of the AFM, 

the general revisions may be inserted in the 

AFM, and the TR may be removed. 

Accomplishment of the new flat plate 

installation required by paragraph (j) of this 

AD terminates the actions required by this 

paragraph; and after the installation of new 

flat plates has been done, Airbus A318/A319/ 

A320/A321 TR TR286, Issue 1.0, dated 

December 17, 2012, must be removed from 

the AFM before further flight. 

(h) Retained Optional Terminating Action 

With Revised TR Removal Requirement 

This paragraph restates the actions 

specified in paragraph (h) of AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013), with a revised TR removal 

requirement. Modification of an airplane by 

replacing AoA sensor conic plates with AoA 

sensor flat plates, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, constitutes 

terminating action for the AFM revision 

required by paragraph (g) of this AD; and 

after the modification has been done, Airbus 

A318/A319/A320/A321 TR TR286, Issue 1.0, 

dated December 17, 2012, must be removed 

from the AFM before further flight, except for 

airplanes on which the modification has been 

done before the effective date of this AD. For 

airplanes on which the modification has been 

done before the effective date of this AD, 

Airbus A318/A319/A320/A321 TR TR286, 

Issue 1.0, dated December 17, 2012, must be 

removed from the AFM within 5 days after 

the effective date of this AD. 

Accomplishment of the actions required by 

paragraphs (j) and (l) of this AD terminate the 

actions specified in this paragraph. 

(i) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–26–51, Amendment 

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

of January 24, 2013 (the effective date of AD 

2012–26–51), no person may install an AoA 

sensor conic plate in service using Airbus 

Mandatory Service Bulletin A320–34–1521, 

dated May 7, 2012; or Revision 01, dated 

September 12, 2012; on any airplane. 

(j) New Flat Plate Installation 

Within 5 months after the effective date of 

this AD, remove all AoA sensor conic plates 

having part number (P/N) F3411060200000 

or P/N F3411060900000 and install AoA 

sensor flat plates having part numbers 

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

AD, except as specified in paragraph (k) of 

this AD. Install the AoA sensor plates in 

accordance with the applicable method 

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

AD. Accomplishment of the AoA sensor flat 

plate installation terminates the AFM 

revision required by paragraph (g) of this AD; 

and after accomplishing the installation, the 

actions specified in paragraph (l) of this AD 

must be done. 

(1) Install P/N D3411013520200 in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–34–1564, including Appendix 

01, dated January 25, 2013. 

(2) Install P/N D3411007620000 or P/N 

D3411013520000, 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). 

(k) New Exception to Paragraphs (g) and (j) 

of This AD 

An airplane on which Airbus modification 

154863 (installation of AOA sensor flat plate) 

and modification 154864 (coating protection) 

have been embodied in production is not 

affected by the requirements of paragraph (g) 

or (j) of this AD, provided that, since first 

flight, no AoA sensor conic plate having P/ 

N F3411060200000 or P/N F3411060900000 

has been installed on that airplane. 


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(l) New Requirement for Removal of AFM 

Revision 

After modification of an airplane as 

required by paragraph (j) of this AD, Airbus 

A318/A319/A320/A321 TR TR286, Issue 1.0, 

dated December 17, 2012, that was inserted 

into the Airbus A318/A319/A320/A321 

AFM, as required by paragraph (g) of this AD, 

is no longer required and must be removed 

from the AFM of that airplane before further 

flight. 

(m) New Parts Installation Prohibition 

(1) For any airplane that has AoA sensor 

flat plates installed: As of the effective date 

of this AD, do not install any AoA sensor 

conic plate having P/N F3411060200000 or 

P/N F3411060900000, and do not use any 

AoA protection cover having P/N 

98D34203003000. 

(2) For any airplane that has AoA sensor 

conic plates installed: As of the effective date 

of this AD, after modification of the airplane 

as required by paragraph (j) of this AD, do 

not install any AoA sensor conic plate having 

P/N F3411060200000 or P/N 

F3411060900000, and do not use any AoA 

protection cover having P/N 

98D34203003000. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided Airbus A318/A319/A320/A321 TR 

TR286, Issue 1.0, dated December 17, 2012, 

has been inserted into the Emergency 

Procedures of the Airbus A318/A319/A320/ 

A321 AFM. 

(o) 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, WA 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. 

(p) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2013–0022, dated 

February 1, 2013, for related information, 

which can be found in the AD docket on the 

Internet at http://www.regulations.gov. 

(q) 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. 

(3) The following service information was 

approved for IBR on November 6, 2013. 

(i) Airbus Mandatory Service Bulletin 

A320–34–1564, including Appendix 01, 

dated January 25, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on January 24, 2013 (78 FR 

1723, January 9, 2013). 

(i) Airbus A318/A319/A320/A321 

Temporary Revision TR286, Issue 1.0, dated 

December 17, 2012, to the Airbus A318/

A319/A320/A321 Airplane Flight Manual. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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. 

(6) 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. 

(7) 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 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23079 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0211; Directorate 

Identifier 2012–NM–230–AD; Amendment 

39–17597; AD 2013–19–15] 

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 747–100, 

–100B, –100B SUD, –200B, –200C, 

–200F, –300, –400, –400D, –400F, and 

747SR series airplanes. This AD was 

prompted by reports of cracking at the 

aft upper corner of the main entry door 

(MED) 5 cutout. This AD requires 

inspecting for the presence of repairs 

and measuring the edge margin at 

certain fastener locations around the 

upper aft corner of the door cutout, 

inspecting for any cracking of the 

fuselage skin assembly and bear strap in 

the aft upper corner area of the door 

cutout, and repairing or modifying the 

fuselage skin assembly and bear strap if 

necessary. We are issuing this AD to 

detect and correct cracking of the skin 

and bear straps at the aft upper corner 

of the MED 5 cutout, which could result 

in in-flight depressurization. 

DATES: This final rule is effective 

November 6, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2013. 

ADDRESSES: 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. 

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 


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