60670 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 

(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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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60671 

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: 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. 

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 published in the Federal 

Register on March 28, 2013 (78 FR 

18917). The NPRM proposed to require 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 18917, 

March 28, 2013) and the FAA’s response 

to each comment. 

Request To Provide Clarification or 

Revision of Corrective Actions Phrase 

in Paragraph (g)(2) of the NPRM (78 FR 

18917, March 28, 2013) 

UPS requested that the phrase 

‘‘applicable corrective or additional 

actions’’ be used in place of ‘‘applicable 

corrective actions’’ in paragraph (g)(2) of 

the NPRM (78 FR 18917, March 28, 

2013). UPS found the use of ‘‘applicable 

corrective actions’’ to be confusing in 

the case when no cracks are found 

during the inspection and stated the 

phrase could lead to problems with 

interpretation. UPS stated that for 

airplanes on which no cracks are found, 

Boeing Alert Service Bulletin 747– 

53A2839, dated November 6, 2012, 

specifies the installation of a 

preventative modification, with the 

option of doing the repetitive 

inspections until installation of the 

preventative modification. UPS added 

that it is not intuitively clear that 

corrective action is required for the case 

where no cracks are found. 

We agree that clarification is 

necessary. We have revised the phrasing 

and paragraph structure of paragraph 

(g)(2) of this final rule to clarify what is 

required or acceptable in the case of no 

crack findings. However, we have not 

used the phrase ‘‘applicable corrective 

or additional actions’’ as suggested by 

UPS. 

Request To Add Option To Do Certain 

Actions by Using Service Information 

Boeing requested that paragraph (g)(1) 

of the NPRM (78 FR 18917, March 28, 

2013) be revised to refer to Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, for instructions 

instead of referencing the alternative 

method of compliance (AMOC) process. 

Boeing referred to similar language in 

the last sentence of paragraph (g)(2) of 

the NPRM and suggested adding that 

language to paragraph (g)(1) of the 

NPRM would clarify the required 

actions. 

We disagree. For the condition 

addressed by paragraph (g)(1) of this 

final rule, Boeing Alert Service Bulletin 

747–53A2839, dated November 6, 2012, 

states to ‘‘Do inspections or change the 

repair, as described by Boeing.’’ To 

require operators to contact Boeing for 

these actions would be delegating our 

rulemaking authority to the 

manufacturer. Paragraph (h)(2) of this 

final rule also requires using the AMOC 

process instead where Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, specifies to contact 

Boeing. We have not changed this final 

rule in this regard. 

Request To Approve an Alternate 

Generic Repair Scheme as an AMOC 

British Airways requested that an 

alternate generic repair scheme be 

approved as an AMOC to this final rule. 

British Airways stated that it is in favor 

of doing the detailed inspections for the 

presence of repairs and measuring the 

edge margin, as it has had several 

findings during the accomplishment of 

Boeing Alert Service Bulletin 747– 

53A2839, dated November 6, 2012. 

However, due to insufficient availability 

of the modification kit (due to the 

service bulletin validation process), 

Boeing had provided an alternate 

generic repair scheme to British 

Airways which allowed British Airways 

to manufacture certain repair parts. 

British Airways stated it has requested 

that Boeing include the alternate generic 

repair scheme in the next revision of 

Boeing Alert Service Bulletin 747– 

53A2839, dated November 6, 2012. 

We disagree. An AMOC is issued only 

after an AD has been issued and only 

after data are provided to show that the 

proposed solution is complete and 

addresses the unsafe condition. The 

alternate generic repair scheme that 

British Airways attached to its comment 

states that the ‘‘repair is generic, and 

may need to be modified to account for 

the existing configuration and reported 

conditions.’’ Therefore, each repair will 

need to be evaluated on a case-by-case 

basis. Once we issue this final rule, 

anyone may submit an AMOC request to 

use an alternate generic repair scheme 

under the provisions of paragraph (j) of 

this final rule. Sufficient data must be 

submitted to substantiate the generic 

repair and show that it would provide 

an acceptable level of safety. We have 

not changed this final rule in this 

regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

18917, March 28, 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 18917, 

March 28, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 246 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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60672 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspect for repair and measure edge margin.1 work-hour × $85 per hour = $85 per 

door (up to 2 doors per airplane).

None ................. Up to $170 ....... Up to $41,820. 

We estimate the following costs to do 

any necessary repetitive inspections, 

repairs or modifications that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these inspections, repairs or 

modification: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repetitive inspections of un-repaired area.6 work-hours × $85 per hour = 

$510 per door, per inspection 

cycle.

None ............................................. $510 per door, per inspection 

cycle. 

Repair or modification .................... 10 work-hours × $85 per hour = 

$850 per door.

Between $7,654 and $17,426 per 

door.

Between $8,504 and $18,276 per 

door. 

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 

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 

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. 

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 airworthiness 

directive (AD): 

2013–19–15 The Boeing Company: 

Amendment 39–17597; Docket No. 

FAA–2013–0211; Directorate Identifier 

2012–NM–230–AD. 

(a) Effective Date 

This AD is effective November 6, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, –100B, –100B SUD, –200B, 

–200C, –200F, –300, –400, –400D, –400F, and 

747SR series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking at the aft upper corner of the main 

entry door (MED) 5 cutout. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Measurement 

Except as specified in paragraph (h)(1) of 

this AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2839, dated 

November 6, 2012: Do a detailed inspection 

for the presence of repairs at the aft upper 

corner of the MED 5 cutout, and measure the 

edge margin at certain fastener locations 

around the corner of the door cutout, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2839, dated November 6, 2012. 

(1) If a repair is found: Before further flight, 

inspect or change the repair, using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(2) If no repair is found, except as specified 

in paragraph (h)(1) of this AD, at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2839, dated November 6, 

2012: Do detailed and high frequency eddy 

current (HFEC) inspections for any cracking 

of the fuselage skin assembly and bear strap 

in the aft upper corner area of the door 

cutout, as applicable, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, except as required by 

paragraph (h)(2) of this AD. Do all applicable 


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corrective actions before further flight. If no 

cracking is found: Before further flight, 

install a preventative modification, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2839, dated November 6, 2012, 

except as required by paragraph (h)(2) of this 

AD. 

(i) Options provided in Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, for accomplishing the 

applicable corrective action are acceptable 

for the corresponding requirements of 

paragraph (g)(2) of this AD, provided that the 

inspections and preventative modification 

are done at the applicable times in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2839, dated November 6, 

2012. 

(ii) Options provided in Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, for accomplishing the 

preventative modification when no cracking 

is found are acceptable for the corresponding 

requirements of paragraph (g)(2) of this AD, 

provided that the inspections and 

preventative modification are done at the 

applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2839, dated November 6, 

2012. 

(h) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2839, dated November 6, 2012, 

specifies compliance times ‘‘after the original 

issue date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance times ‘‘after the effective date of 

this AD.’’ 

(2) Where Boeing Alert Service Bulletin 

747–53A2839, dated November 6, 2012, 

specifies to contact Boeing for appropriate 

action: Before further flight, do the action 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(i) Post-Repair/Post-Modification Inspections 

The post-repair or post-modification 

inspections specified in table 3 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2839, dated November 6, 

2012, are not required by this AD. 

Note 1 to paragraph (i) of this AD: The 

post-repair or post-modification inspection 

specified in table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2839, dated November 6, 

2012, may be used in support of compliance 

with section 121.1109(c)(2) or 129.109(b)(2) 

of the Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(b)(2)). The 

corresponding actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2839, dated 

November 6, 2012, are not required by this 

AD. 

(j) 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 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

(k) Related Information 

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. 

(l) 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) Boeing Alert Service Bulletin 747– 

53A2839, dated November 6, 2012. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at 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 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24029 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–2012–1041; Directorate 

Identifier 2011–NM–272–AD; Amendment 

39–17590; AD 2013–19–08] 

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 727 

airplanes; Model 737–100, –200, and 

–200C series airplanes; and Model 747– 

100, –100B, –100B SUD, –200B, –200C, 

–200F, –300, –400, –400D, –400F, 

747SR, and 747SP series airplanes. This 

AD was prompted by a report of an 

activation of the control column shaker 

during takeoff. This AD requires 

performing a general visual inspection 

to determine if a certain angle of attack 

(AOA) sensor with a paddle type vane 

is installed, and, for affected sensors, 

performing an operational test of the 

stall warning system, and replacing the 

AOA sensor with a new sensor if 

necessary. We are issuing this AD to 

prevent erroneous activation of the 

control column shaker during takeoff, 

which could result in runway overrun, 

failure to clear terrain or obstacles after 

takeoff, or reduced controllability of the 

airplane. 

DATES: This AD is effective November 6, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 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, Washington 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. 

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 


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